=LDR  03775nam  2200793 i 4500
=001  CTR10016J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10016J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10016J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aU22.3
=082  04$a355/.001/9$223
=100  1\$aMinnetyan, L., $eauthor.
=245  10$aProgressive Fracture of Composite Cylindrical Shells Subjected to External Pressure / $cL Minnetyan, CC Chamis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aProgressive fractures of laminated graphite/epoxy composite cylindrical shells are investigated under external hydrostatic pressure. An integrated computer code is used for the simulation of composite structural degradation under loading. Damage initiation, growth, accumulation, and propagation to structural fracture are included in the simulations. Results indicate that local defects do not have a significant effect on structural survivability under hydrostatic loading for thick composite shells. Influence of constituent material properties and the effects of residual stresses on damage initiation and progression under external pressure are evaluated. Structural safety and damage tolerance characteristics of a prototype composite cylindrical shell are examined.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite structures.
=650  \0$aComposites.
=650  \0$aCompression.
=650  \0$aDamage.
=650  \0$aDegradation.
=650  \0$aDurability.
=650  \0$aExternal pressure.
=650  \0$aFracture.
=650  \0$aLaminates.
=650  \0$aSimulation.
=650  \0$aStructural degradation.
=650  \0$aDecision making.
=650  \7$aTECHNOLOGY & ENGINEERING $xScience.
=653  10$aComposites.
=653  20$aComposite structures.
=653  20$aCompression.
=653  20$aDamage.
=653  20$aDegradation.
=653  20$aDurability.
=653  20$aExternal pressure.
=653  20$aFracture.
=653  20$aLaminates.
=653  20$aSimulation.
=653  20$aStructural degradation.
=700  1\$aChamis, CC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10016J.htm

=LDR  03470nam  2200661 i 4500
=001  CTR10017J
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=024  7\$a10.1520/CTR10017J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10017J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTJ1185
=082  04$a671.5/3$223
=100  1\$aKarri, V., $eauthor.
=245  10$aMachining of Filled Polymers Using Single-Edge Tools / $cV Karri.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 2 (April 1997)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe importance and industrial applications of filled polymers is reported. In recent years cast nylon with various fillers has been extensively used in industry, where machining is carried out as a secondary process to achieve necessary surface finish and shape. There is a pressing need to develop various cutting techniques to enhance the machining performance features for these polymers. An understanding of the effect of major process variables on forces, power, and surface finish help practicing engineers in selection of cutting tools and machine tools for efficient manufacturing. In this paper, the qualitative and quantitative effects of major process variables such as tool, cut geometry, and cutting speeds are studied for cast nylon with two different fillers, namely MoS2 and vulcanized vegetable oil (VVO). The data processing is carried out by a suite of statistical routines.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCast nylon.
=650  \0$aCutting techniques.
=650  \0$aFillers.
=650  \0$aMachining.
=650  \0$aPolymers.
=650  \0$aSurface finish.
=650  \0$aCutting.
=650  \0$aManufacturing processes.
=653  10$aPolymers.
=653  20$aCast nylon.
=653  20$aFillers.
=653  20$aMachining.
=653  20$aSurface finish.
=653  20$aCutting techniques.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10017J.htm

=LDR  03384nam  2200649 i 4500
=001  CTR10018J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10018J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10018J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aGanesh, VK., $eauthor.
=245  10$a(±45) Degree Off-Axis Tension Test for Shear Characterization of Plain Weave Fabric Composites / $cVK Ganesh, NK Naik.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b22.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDifferent test techniques for shear characterization are reassessed for their suitability for woven fabric composites. Considering the accuracy of results, ease of specimen fabrication, and simplicity of test technique, (±45) degree off-axis tension test is recommended for shear characterization of woven fabric composites. Calculations show that for typical E-glass/epoxy LY556 and T-300 carbon/epoxy LY556 two-dimensional orthogonal plain weave fabric laminates, the percentage shear contribution at failure is about 99 and 97-98, respectively. Hence, this test technique leads to a near pure shear condition in the test section for WF laminates.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aIn-plane shear modulus.
=650  \0$aIn-plane shear strength.
=650  \0$aShear contribution.
=650  \0$aTension test.
=650  \0$aWoven fabric laminate.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aWoven fabric laminate.
=653  20$aShear contribution.
=653  20$a(±45) degree off-axis tension test.
=653  20$aIn-plane shear strength.
=653  20$aIn-plane shear modulus.
=700  1\$aNaik, NK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10018J.htm

=LDR  03322nam  2200781 i 4500
=001  CTR10019J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10019J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10019J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aTaheri, F., $eauthor.
=245  10$aImprovement of Strength and Ductility of Adhesively Bonded Joints by Inclusion of SiC Whiskers / $cF Taheri.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn real-life applications, adhesively bonded joints that are subjected to in-plane loads will, in turn, experience out-of-plane normal and shear stresses. The resulting stresses, in addition to the brittle nature of most epoxy-based adhesives, often create brittle fracture and failure.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive bonding.
=650  \0$aComposite materials.
=650  \0$aDuctility.
=650  \0$aEnergy-absorbing capacity.
=650  \0$aInterply.
=650  \0$aRepair.
=650  \0$aSiC whiskers.
=650  \0$aStacking sequence.
=650  \0$aSurface preparation.
=650  \0$aToughened adhesive.
=650  \0$aWhisker reinforcement.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aAdhesive bonding.
=653  20$aComposite materials.
=653  20$aWhisker reinforcement.
=653  20$aSiC whiskers.
=653  20$aDuctility.
=653  20$aRepair.
=653  20$aEnergy-absorbing capacity.
=653  20$aToughened adhesive.
=653  20$aSurface preparation.
=653  20$aInterply.
=653  20$aStacking sequence.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10019J.htm

=LDR  02236nam  2200505 i 4500
=001  CTR10020J
=003  IN-ChSCO
=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10020J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10020J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aJohnson, WS., $eauthor.
=245  10$aDamage Tolerance in Advanced Composites / $cWS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (1 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 2 (April 1997)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10020J.htm

=LDR  04006nam  2200601 i 4500
=001  CTR10023J
=003  IN-ChSCO
=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10023J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10023J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aAdams, DF., $eauthor.
=245  14$aThe Wyoming Combined Loading Compression (CLC) Test Method / $cDF Adams, JS Welsh.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 3 (July 1997)
=504  \\$aIncludes bibliographical references$b28.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aBased upon extensive experimental testing and analytical modeling of compression test methods at the University of Wyoming and elsewhere during the past several years, a specific procedure is recommended for obtaining representative axial compressive strength design values for continuous fiber composite materials. A specimen in the form of an untabbed, straight-sided strip of a [90/0]ns cross-ply composite laminate is tested in a newly developed Wyoming combined loading compression (CLC) test fixture. The standard specimen is 140-mm (5.50-in.) long, 12.7-mm (0.50-in.) wide, and of uniform but arbitrary thickness. This length produces a 12.7-mm (0.50-in.) gage section in the fixture. By increasing the torque applied to the fixture clamping bolts, the ratio of shear-loading to end-loading is readily increased as required to avoid end crushing of the untabbed cross-ply specimen. Typically, the required torque is low, in the range of 2.26 to 2.83 N-m (20 to 25 in.-lb). Classical (linear) lamination theory is adequate to calculate a "back-out factor," which is used to determine the unidirectional ply axial strength. Using a Hercules AS4/3501-6 carbon/epoxy composite material, it is demonstrated that the axial compressive strength obtained is fully comparable to the stress at failure in the 0° plies of laminates of any general lay-up configuration, and also to that measured for unidirectional composites tested using special mini-sandwich and thickness-tapered test specimens.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aCompression.
=650  \0$aCross-ply laminates.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCross-ply laminates.
=653  20$aComposites.
=653  20$aCompression.
=700  1\$aWelsh, JS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10023J.htm

=LDR  03763nam  2200661 i 4500
=001  CTR10024J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10024J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10024J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aAnanth, CR., $eauthor.
=245  10$aEffect of Time-Dependent Matrix Behavior on the Evolution of Processing-Induced Residual Stresses in Metal Matrix Composites / $cCR Ananth, S Mukherjee, N Chandra.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe usefulness of load-relaxation experiments in investigating the need for rate-dependent matrix material models for predicting the processing-induced residual stresses in metal matrix composites (MMCs) is examined in this study. The experimental data is used in the selection of the appropriate constitutive equations for modeling the cooling process after composite consolidation. Boron/Al-2024 MMC is chosen as the model material system. Bodner-Partom unified model and a classical creep-plasticity model based on the relaxation experiments are used to represent the rate-dependent behavior of Al-2024. The results show that conventional B-P model based on purely monotonic strain-rate tests is not able to capture the inelastic strain variations under practical cooling conditions. The classical creep-plasticity model has been shown to be an effective alternative for this purpose as it considers load-relaxation data while deriving the material constants for the constitutive equations.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCreep.
=650  \0$aFinite element method.
=650  \0$aResidual stresses.
=650  \0$aStress-relaxation.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMMC.
=653  20$aResidual stresses.
=653  20$aStress-relaxation.
=653  20$aCreep.
=653  20$aFinite element method.
=700  1\$aMukherjee, S., $eauthor.
=700  1\$aChandra, N., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10024J.htm

=LDR  04253nam  2200697 i 4500
=001  CTR10025J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10025J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10025J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aHuang, X., $eauthor.
=245  10$aMatrix Cracking of High-Performance Composite Laminates with Variation of Laminate Stacking Sequence and Testing Temperature / $cX Huang, JW Gillespie, RF Eduljee.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 3 (July 1997)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aExtensive investigation has been done on composite cross-ply laminates; however, in practical use, the laminate layers are in multiple angles. The quasi-laminate is one example of a multi-angle laminate. Matrix fracture mechanisms of quasi-laminates are significant in composites design and application. This paper describes the experimental details in laminate parameter selection, microcracking tests, observation of matrix cracking mechanisms, and documentation of test results. The first material failure mode, matrix crack initiation, and matrix cracking propagation in the width and length of the specimen were determined. Results are presented for high-performance X5250/IM7 cross-ply and quasi-laminates in thin and thick prepregs. Ultrasonic C-scanning and optical microscopy were used as the primary means to detect and track matrix cracking. The specimens have a variety of lay-up sequences and thicknesses. The effects of stacking sequence and ply thickness on the matrix cracking behavior were determined. Based on test results, a finite element modeling approach was performed for quasi-laminates, which includes three-dimensional stress distribution analysis for the free edge and middle plane of the specimen. Both test results and theoretical analyses provide a deeper understanding of the matrix cracking mechanisms that operate at the microstructure level.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCrack evolution.
=650  \0$aLaminate.
=650  \0$aMatrix cracking.
=650  \0$aResidual stress.
=650  \0$aStacking sequence.
=650  \0$aTemperature effect.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMatrix cracking.
=653  20$aLaminate.
=653  20$aStacking sequence.
=653  20$aCrack evolution.
=653  20$aResidual stress.
=653  20$aTemperature effect.
=700  1\$aGillespie, JW., $eauthor.
=700  1\$aEduljee, RF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10025J.htm

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=024  7\$a10.1520/CTR10026J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA413.5
=082  04$a620.1/123/028$223
=100  1\$aMasters, JE., $eauthor.
=245  10$aStrain Gage Selection Criteria for Textile Composite Materials / $cJE Masters, PG Ifju.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (16 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aComposite materials reinforced with braided, woven, knit, and stitched fibrous preforms are emerging as potential alternatives to unidirectional prepreg tape. A variety of these material forms are currently being evaluated by major airframe manufacturers.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBraids.
=650  \0$aCoefficient of variation.
=650  \0$aGage length.
=650  \0$aModulus.
=650  \0$aStrain gage.
=650  \0$aTextile composites.
=650  \0$aUnit cell.
=650  \0$aWeaves.
=650  \0$aExtensometer.
=650  \0$aGages.
=653  10$aTextile composites.
=653  20$aBraids.
=653  20$aWeaves.
=653  20$aStrain gage.
=653  20$aGage length.
=653  20$aModulus.
=653  20$aCoefficient of variation.
=653  20$aUnit cell.
=700  1\$aIfju, PG., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10026J.htm

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=024  7\$a10.1520/CTR10027J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aGowayed, YA., $eauthor.
=245  14$aThe Effect of Voids on the Elastic Properties of Textile Reinforced Composites / $cYA Gowayed.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 3 (July 1997)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this paper, the effect of voids on the elastic properties of textile composites is investigated. The investigation is carried out in two steps. First, the volume fraction and spatial distribution of voids are characterized using stereological analysis and image enhancement techniques. Then, an analytical model, that takes into consideration the effect of voids' location and volume fraction, is constructed. It uses the theory of reinforcing by slip and Eshelby's and Mori-Tanaka theories of composites with voids/inclusions in the micro-mechanics solution. The micro-level analysis is integrated with the graphical integrated numerical analysis (GINA)
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCeramic composites.
=650  \0$aComposites.
=650  \0$aElastic properties.
=650  \0$aFabrics.
=650  \0$aFinite element.
=650  \0$aMechanics.
=650  \0$aTextiles.
=650  \0$aVoids.
=650  \0$aFinite element method.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aComposites.
=653  20$aTextiles.
=653  20$aFabrics.
=653  20$aVoids.
=653  20$aMechanics.
=653  20$aElastic properties.
=653  20$aCeramic composites.
=653  20$aFinite element.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10027J.htm

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=001  CTR10028J
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=024  7\$a10.1520/CTR10028J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aLi, J., $eauthor.
=245  10$aEvaluation of the Edge Crack Torsion (ECT) Test for Mode III Interlaminar Fracture Toughness of Laminated Composites / $cJ Li, SM Lee, EW Lee, TK O'Brien.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 3 (July 1997)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn analytical and experimental investigation was carried out on G40-800/R6376 graphite/epoxy laminates to evaluate the edge crack torsion (ECT) test as a candidate for a standard Mode III interlaminar fracture toughness test for laminated composites. The ECT test consists of a [90?(±45)3?(?45)3?90]s laminate with a delamination introduced by a non-adhesive film at the mid-plane along one edge and loaded in a special fixture to create torsion along the length of the laminate. Dye penetrant enhanced X-radiograph of failed specimens revealed that the delamination initiated at the middle of the specimen length and propagated in a self-similar manner along the laminate midplane. A three-dimensional finite element analysis was performed that indicated that a pure Mode III delamination exists at the middle of specimen length away from both ends. At the ends near the loading point a small Mode II component exists. However, the magnitude of this Mode II strain energy release rate at the loading point is small compared to the magnitude of Mode III component in the mid-section of the specimen. Hence, the ECT test yielded the desired Mode III delamination. The Mode III fracture toughness was obtained from a compliance calibration method that was in good agreement with the finite element results. Mode II end-notched flexure (ENF) tests and Mode I double cantilever beam (DCB) tests were also performed for the same composite material. The Mode I fracture toughness is much smaller than both the Mode II and Mode III fracture toughness. The Mode II fracture toughness is found to be 75% of the Mode III fracture toughness.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompliance calibration.
=650  \0$aComposite materials.
=650  \0$aDelamination.
=650  \0$aFracture toughness.
=650  \0$aStrain energy release rate.
=650  \0$aThree-dimensional finite element analysis.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aFracture toughness.
=653  20$aDelamination.
=653  20$aCompliance calibration.
=653  20$aThree-dimensional finite element analysis.
=653  20$aStrain energy release rate.
=700  1\$aLee, SM., $eauthor.
=700  1\$aLee, EW., $eauthor.
=700  1\$aO'Brien, TK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10028J.htm

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=001  CTR10029J
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10029J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10029J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.C43
=082  04$a620.1/404292$223
=100  1\$aChuck, L., $eauthor.
=245  10$aHoop Tensile Strength and Fracture Behavior of Continuous Fiber Ceramic Composite (CFCC) Tubes from Ambient to Elevated Temperatures / $cL Chuck, GA Graves.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aPresently, continuous-fiber ceramic composites (CFCCs) are considered leading candidate materials for many high-temperature applications, such as high-pressure heat exchangers, radiant burner tubes, and engine combustors. To adequately evaluate these materials in their cylindrical configurations, a hoop tension test is needed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCeramic.
=650  \0$aContinuous-fiber ceramic composite (CFCC).
=650  \0$aDiametral strain.
=650  \0$aFracture behavior.
=650  \0$aHigh temperature.
=650  \0$aHoop tensile strength.
=650  \0$aMechanical properties.
=650  \0$aPressurized cylindrical specimen.
=650  \0$aCeramic-matrix composites $xMechanical properties.
=650  \0$aCeramic.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aHoop tensile strength.
=653  20$aPressurized cylindrical specimen.
=653  20$aCeramic.
=653  20$aContinuous-fiber ceramic composite (CFCC).
=653  20$aHigh temperature.
=653  20$aMechanical properties.
=653  20$aFracture behavior.
=653  20$aDiametral strain.
=700  1\$aGraves, GA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10029J.htm

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=001  CTR10048J
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10048J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10048J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aNicholas, T., $eauthor.
=245  10$aMicromechanics Analysis and Life Prediction of Titanium Matrix Composites / $cT Nicholas, JL Kroupa.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 2 (April 1998)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe response of a unidirectional SCS-6/Ti-6Al-4V composite is evaluated under a range of isothermal fatigue (IF) and thermomechanical fatigue (TMF) conditions. Both processing and thermomechanical test conditions are simulated using a cylinder in cylinder code, FIDEP, which treats the fiber as thermoelastic while the matrix is characterized using a recent version of the Bodner-Partom constitutive law. Computed stresses and strains in the constituents are obtained after 10 cycles of loading and are used as input into a new and simpler version of a life fraction model. Applied stress at temperature and computed matrix strains are used for the time-dependent and matrix fatigue terms in the model, respectively. Cyclic stress-strain behavior of the matrix material is also computed and used, together with fatigue life data, to identify the governing mechanisms and to explain the observed trends in fatigue life as a function of frequency and applied stress level. Comparisons of fatigue behavior with that of SCS-6/Timetal 21S illustrate differences when tested under nominally similar conditions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aConstitutive model.
=650  \0$aLife prediction.
=650  \0$aMetal matrix composite.
=650  \0$aMicromechanics.
=650  \0$aThermomechanical fatigue.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMetal matrix composites (MMCs).
=653  20$aMicromechanics.
=653  20$aLife prediction.
=653  20$aThermomechanical fatigue.
=653  20$aConstitutive model.
=700  1\$aKroupa, JL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10048J.htm

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=001  CTR10049J
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10049J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10049J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHansen, U., $eauthor.
=245  10$aDependence of Intralaminar Fracture Toughness on Direction of Crack Propagation in Unidirectional Composites / $cU Hansen, JW Gillespie.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 2 (April 1998)
=504  \\$aIncludes bibliographical references$b29.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aMode I intralaminar fracture toughness GIC of graphite fiber-reinforced bismaleimide (X5260/G40-800) has been studied experimentally using double edge notch (DEN) specimens and three-point-bend specimens. The intralaminar fracture toughness was found to depend significantly on the direction of fracture propagation. Examination of the fracture surface showed the fracture surface to be relatively smooth or ragged depending on the direction of the fracture propagation, thus substantiating the measured differences in of graphite fiber-reinforced bismaleimide (X5260/G40-800) has been studied experimentally using double edge notch (DEN) specimens and three-point-bend specimens. The intralaminar fracture toughness was found to depend significantly on the direction of fracture propagation. Examination of the fracture surface showed the fracture surface to be relatively smooth or ragged depending on the direction of the fracture propagation, thus substantiating the measured differences in GIC. Furthermore the material exhibited a substantial. Furthermore the material exhibited a substantial R-curve behavior, which appeared related to fiber pull-out.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aCrack-tip geometry.
=650  \0$aFracture toughness.
=650  \0$aOrthotropy.
=650  \0$aR-curve.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aFracture toughness.
=653  20$aOrthotropy.
=653  20$aR-curve.
=653  20$aCrack-tip geometry.
=700  1\$aGillespie, JW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10049J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10050J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10050J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aNeumeister, JM., $eauthor.
=245  10$aInclined Double Notch Shear Test for Improved Interlaminar Shear Strength Measurements / $cJM Neumeister, AC Pålsson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA novel method to measure interlaminar shear strengths of composites is presented. This method uses the double notch shear (DNS) specimen and modifies the load introduction by use of a fixture. The main concept is to eliminate the compressive stress intensity at the notch roots, arising from the external load, by imposing a counteracting tensile load field there. This field is caused by a bending moment acting over the notched region. Proportional loading is achieved by holding the specimen in an inclined position with supports near its ends and behind the notches. The inclination angle determines the ratio between the compressive normal field and the tensile bending field. The required inclination angle depends on the notch distance, specimen thickness ratio, and to a lesser degree on any material anisotropy. Two test series, with four different notch distances, were carried out to compare the standard DNS test to the new method. The new method produced consistently higher strengths at all notch distances. For the shortest notch distance, which incidentally gives the highest strength values, the measured average interlaminar shear strength was almost doubled with the new method. As with the standard method, the new method still gives lower strength values with increasing notch distances and notable experimental scatter. Causes for this are discussed and some possibilities for improvements are outlined.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComparison.
=650  \0$aExperiments.
=650  \0$aInclined double notch shear.
=650  \0$aInterlaminar shear strength.
=650  \0$aShear stress distribution.
=650  \0$aTest method.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aInterlaminar shear strength.
=653  20$aTest method.
=653  20$aShear stress distribution.
=653  20$aInclined double notch shear.
=653  20$aExperiments.
=653  20$aComparison.
=700  1\$aPålsson, AC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10050J.htm

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=030  \\$aJCTRER
=037  \\$aCTR10051J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.A3
=082  04$a668/.3$223
=100  1\$aValentin, RV., $eauthor.
=245  12$aA Finite Element and Experimental Evaluation of Boron-Epoxy Doublers Bonded to an Aluminum Substrate / $cRV Valentin, LM Butkus, WS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 2 (April 1998)
=504  \\$aIncludes bibliographical references$b29.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA multi-faceted study was performed to investigate the durability of a boron-epoxy doubler (patch) adhesively bonded to an aluminum substrate. Double cantilever beam (DCB) specimens were tested to determine the fracture toughness and fatigue characteristics of the adhesive bond line. A finite element analysis using ABAQUS was performed to determine the levels of Mode I and Mode II strain energy release rate present at a crack tip within the adhesive. These tests and analyses were used to determine the fatigue threshold in terms of the total strain energy release rate. To evaluate the utility of these results for the analysis of a more realistic geometry, independent fatigue tests of a boron-epoxy doubler bonded to a cracked aluminum sheet were also examined. No debonding of the doubler occurred during 300 000 cycles. A finite element analysis of the independent study revealed that strain energy release rate levels were below the experimentally determined threshold. Thus, the lack of debonding was consistent with previous results. This study demonstrates the utility of using fracture mechanics to evaluate the fatigue and durability characteristics of adhesively bonded joints.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive bonding.
=650  \0$aBoron-epoxy doubler.
=650  \0$aDebonding.
=650  \0$aDouble cantilever beam.
=650  \0$aDurability.
=650  \0$aFatigue threshold.
=650  \0$aFinite element analysis.
=650  \0$aFracture toughness.
=650  \0$aThermal mismatch.
=650  \0$aAdhesive joints.
=650  \0$aGlued joints.
=653  10$aAdhesive bonding.
=653  20$aBoron-epoxy doubler.
=653  20$aFinite element analysis.
=653  20$aDebonding.
=653  20$aFracture toughness.
=653  20$aFatigue threshold.
=653  20$aDurability.
=653  20$aDouble cantilever beam.
=653  20$aThermal mismatch.
=700  1\$aButkus, LM., $eauthor.
=700  1\$aJohnson, WS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10051J.htm

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=037  \\$aCTR10052J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aRobertson, DD., $eauthor.
=245  10$aStrength Reduction and Damage Characterization of SCS6/Ti-6Al-4V Composite Exposed to Fatigue at Elevated Temperature / $cDD Robertson, S Mall, S-M Lee.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aEffect of fatigue loading on the residual strength of a unidirectional titanium matrix composite, SCS6/Ti-6-4, was investigated. The composite was fatigued isothermally at 427°C under load-controlled mode with an applied maximum stress of 900 MPa up to a certain fraction of the fatigue life, and then loaded monotonically to failure to obtain the residual strength. Two frequencies, 1 Hz and 0.01 Hz, were used to examine the time-dependent characteristics of the fatigue loading. Substantially different failure mechanisms and fatigue lives were observed, but the reduction in strength as a percentage of fatigue life was similar for the two cases. Practically no reduction in strength occurred until 75% of the expected fatigue life.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDamage mechanisms.
=650  \0$aFatigue life.
=650  \0$aFatigue.
=650  \0$aMetal matrix composites.
=650  \0$aResidual strength.
=650  \0$aTensile loading.
=650  \0$aTitanium matrix composites.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aTitanium matrix composites.
=653  20$aMetal matrix composites.
=653  20$aFatigue.
=653  20$aResidual strength.
=653  20$aFatigue life.
=653  20$aTensile loading.
=653  20$aDamage mechanisms.
=700  1\$aMall, S., $eauthor.
=700  1\$aLee, S-M, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10052J.htm

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=001  CTR10053J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10053J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10053J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.A3
=082  04$a668/.3$223
=100  1\$aVintilescu, I., $eauthor.
=245  10$aMixed Mode I, II, and III Fracture Characterization of Adhesive Joints / $cI Vintilescu, J Spelt.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 2 (April 1998)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper examines mixed-Mode I-II-III fracture of adhesive joints using a new experimental method. The expressions used for the average energy release rate in Mode I, Mode II, and Mode III along the idealized straight crack front of a cracked, generalized adhesive sandwich are based on beam theory, the J-integral and a beam-on-elastic foundation model. Fracture experiments were performed with adhesively bonded, obliquely-loaded, equal-adherend, split-cantilever-beam (SCB) specimens of different widths and loading angles, using two different adhesives. It was seen that the fracture surface had an arrowhead shape for small loading angles (similar to that of SCB-type specimens), and a thumbnail shape for larger loading angles (similar to that of double-cantilever-beam (DCB)-type specimens). Moreover, a sharp step was observed in the thickness of the residual adhesive half-way across the specimen width. When no Mode I was present, the effect of a Mode II loading component on the critical energy release rate GC was different from the effect of Mode III for one epoxy, but was the same for the other. The addition of Mode I caused the effect on was different from the effect of Mode III for one epoxy, but was the same for the other. The addition of Mode I caused the effect on GC of Mode II to be similar to that of Mode III for both adhesives.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive joints.
=650  \0$aEnergy release rate.
=650  \0$aFracture.
=650  \0$aMixed-mode.
=650  \0$aSplit cantilever beam.
=650  \0$aAdhesive bonding.
=650  \0$aAdhesive joints.
=650  \0$aGlued joints.
=653  10$aFracture.
=653  20$aAdhesive joints.
=653  20$aMixed-mode.
=653  20$aMode I.
=653  20$aMode II.
=653  20$aMode III.
=653  20$aEnergy release rate.
=653  20$aSplit cantilever beam.
=700  1\$aSpelt, J., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10053J.htm

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=024  7\$a10.1520/CTR10068J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10068J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aNimmer, RP., $eauthor.
=245  10$aMicromechanical Modeling of Fiber/Matrix Interface Effects in Transversely Loaded SiC/Ti-6-4 Metal Matrix Composites / $cRP Nimmer, RJ Bankert, ES Russell, GA Smith, P Kennard Wright.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 1 (March 1991)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe transverse tensile behavior of a composite composed of unidirectional silicon-carbide fiber (Textron SCS-6) in a Ti-6AL-4V matrix is examined with emphasis on the effects of fiber-matrix interface strength. The residual stresses as a result of a mismatch in the coefficients of thermal expansion of silicon carbide and titanium are estimated analytically and compared with measurements made using X-ray diffraction techniques. Idealizing the composite as a regular rectangular array of fibers in an elasto-plastic matrix, the transverse tensile stress-strain behavior is predicted under the assumptions of an infinitely strong interface as well as an interface without tensile strength. These results are compared with experiments conducted at three different temperatures. The agreement between experiment and predictions based on an interface without tensile strength is extremely close. The modeled stress-strain curves predict a well-defined knee in the transverse tensile stress-strain curve associated with the separation of fiber and matrix at their interface. The same stress-strain behavior is observed experimentally. Results of edge replica experiments and mechanical unloading from stress levels above the knee are also presented as additional evidence of the association of fiber-matrix separation with the knee in the transverse tensile stress-strain curve.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aInterface strength.
=650  \0$aMetal matrix.
=650  \0$aResidual stress.
=650  \0$aTitanium silicon carbide.
=650  \0$aTransverse tension tests.
=650  \0$aUnit-cell composite idealization.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMetal matrix.
=653  20$aTitanium silicon carbide.
=653  20$aResidual stress.
=653  20$aInterface strength.
=653  20$aTransverse tension tests.
=653  20$aUnit-cell composite idealization.
=653  20$aFEM analysis.
=700  1\$aBankert, RJ., $eauthor.
=700  1\$aRussell, ES., $eauthor.
=700  1\$aSmith, GA., $eauthor.
=700  1\$aKennard Wright, P., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10068J.htm

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=024  7\$a10.1520/CTR10069J$2doi
=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aU22.3
=082  04$a355/.001/9$223
=100  1\$aMital, SK., $eauthor.
=245  10$aFiber Pushout Test : $bA Three-Dimensional Finite Element Computational Simulation / $cSK Mital, CC Chamis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 1 (March 1991)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA fiber pushthrough process has been computationally simulated using a three-dimensional (3-D) finite element method. The interphase material is replaced by an anisotropic material with greatly reduced shear modulus, such that the simulation becomes linear up to the fiber pushthrough load. Such a procedure is easily implemented and is computationally very effective. It can be used to predict fiber pushthrough load for a composite system at any temperature. The average interface shear strength obtained from pushthrough load can easily be separated into its two components: one that comes from frictional stresses and the other that comes from chemical adhesion between fiber and the matrix and mechanical interlocking that develops as a result of shrinkage of the composite because of phase change during the processing. Step-by-step procedures are described to perform the computational simulation, to establish bounds on interfacial bond, and to interpret interfacial bond quality.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBonding.
=650  \0$aFibers.
=650  \0$aInterface.
=650  \0$aInterphase.
=650  \0$aPushout.
=650  \0$aPushthrough.
=650  \0$aResidual stress.
=650  \0$aShear strength.
=650  \0$aSimulation.
=650  \0$aThermal stress.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFibers.
=653  20$aInterface.
=653  20$aInterphase.
=653  20$aPushthrough.
=653  20$aPushout.
=653  20$aShear strength.
=653  20$aBonding.
=653  20$aSimulation.
=653  20$aResidual stress.
=653  20$aThermal stress.
=700  1\$aChamis, CC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10069J.htm

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=030  \\$aJCTRER
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=041  \\$aeng
=050  \4$aTK5103.15
=082  04$a621.36/92$223
=100  1\$aWaterbury, MC., $eauthor.
=245  10$aOn the Determination of Fiber Strengths by In-Situ Fiber Strength Testing / $cMC Waterbury, LT Drzal.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 1 (March 1991)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA method is described and experimental results given which demonstrate the feasibility of determining fiber strengths at short gage lengths by monitoring the fiber failure process during the embedded single-fiber fragmentation test. A computerized weakest link fiber model was used to perform data analysis, without making assumptions about the statistical nature of the flaw distributions. Fiber strength data at short gage lengths can be directly obtained by this technique without the necessity for extrapolation from longer specimens. A dependence on specimen fabrication technique was found, which demonstrates the necessity of careful control of fiber prestrain. Specially fabricated strain-free specimens tested by this method, the in-situ fiber strength test (ISFS), generated length-strength data that were in close agreement with conventional tension test results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFibers.
=650  \0$aInterfacial strength.
=650  \0$aLength-strength.
=650  \0$aStrength.
=650  \0$aTesting.
=650  \0$aFiber.
=650  \7$aTECHNOLOGY & ENGINEERING $xFiber Optics.
=653  10$aFibers.
=653  20$aTesting.
=653  20$aStrength.
=653  20$aIn situ.
=653  20$aLength-strength.
=653  20$aInterfacial strength.
=700  1\$aDrzal, LT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10070J.htm

=LDR  03543nam  2200721 i 4500
=001  CTR10071J
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=008  161219c19919999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10071J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10071J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMurphy, KA., $eauthor.
=245  10$aElliptical-Core, Dual-Mode, Optical Fiber Strain and Vibration Sensors for Composite Material Laminates / $cKA Murphy, MS Miller, AM Vengsarkar, RO Claus.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 1 (March 1991)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWe present a novel class of rugged, lead-insensitive, fiber optic sensors for the measurement of strain and vibration in composite material laminates. The sensors are embedded within the material as well as attached to the surface in a retrofit fashion. Static strain measurement is demonstrated by attaching the fiber sensor to a metallic beam. Modal components of a vibrating cantilever beam have been resolved using such sensors. Sensors with variable sensitivity have been demonstrated by placing the sensing fiber at varying distances from the neutral axis of the beam.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aDual-mode fiber sensors.
=650  \0$aElliptical core fibers.
=650  \0$aFiber optic sensors.
=650  \0$aLaminates.
=650  \0$aSmart structures.
=650  \0$aVibration sensors.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aLaminates.
=653  20$aFiber optic sensors.
=653  20$aElliptical core fibers.
=653  20$aDual-mode fiber sensors.
=653  20$aSmart structures.
=653  20$aVibration sensors.
=653  20$aComposite materials.
=700  1\$aMiller, MS., $eauthor.
=700  1\$aVengsarkar, AM., $eauthor.
=700  1\$aClaus, RO., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10071J.htm

=LDR  03255nam  2200625 i 4500
=001  CTR10072J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10072J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10072J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/93$223
=100  1\$aAdams, DF., $eauthor.
=245  10$aInfluence of Test Fixture Configuration on the Measured Compressive Strength of a Composite Material / $cDF Adams, EM Odom.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 1 (March 1991)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThree compression test fixtures, the IITRI (Illinois Institute of Technology Research Institute), Wyoming-Modified Celanese, and Wyoming-Modified IITRI fixtures, are directly compared by testing Hercules AS4/3501-6 carbon/epoxy unidirectional composites in axial compression. The principal characteristics of each fixture are described, and the relative advantages and disadvantages of each are discussed. It is demonstrated that, if proper fixtures and test procedures are used, all three test fixture configurations produce equivalent results for both axial compressive strength and modulus.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon/epoxy composites.
=650  \0$aCompression testing.
=650  \0$aTest methods.
=650  \0$aUnidirectional composites.
=650  \0$aCarbon composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCompression testing.
=653  20$aTest methods.
=653  20$aUnidirectional composites.
=653  20$aCarbon/epoxy composites.
=700  1\$aOdom, EM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10072J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10073J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10073J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.7
=082  04$a620.1/126$223
=100  1\$aDonaldson, SL., $eauthor.
=245  14$aThe Split Cantilever Beam Test for Characterizing Mode III Interlaminar Fracture Toughness / $cSL Donaldson, S Mall, C Lingg.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 1 (March 1991)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe paper extends the development of the split cantilever beam test specimen. The specimen is intended to measure the Mode III out-of-plane tearing interlaminar fracture toughness of composite materials. To help identify the effects of Mode I and Mode II in the specimen, the specimen end rotation, end opening, and adherend thickness are quantified experimentally. In addition, the crack-tip profile is determined using X-ray techniques, and the fracture morphology is identified as a function of location on the fracture surface.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDelamination.
=650  \0$aFractography.
=650  \0$aInterlaminar fracture.
=650  \0$aToughness.
=650  \0$aMicrofractography.
=650  \0$aElectron microscopy.
=653  10$aComposites.
=653  20$aInterlaminar fracture.
=653  20$aDelamination.
=653  20$aMode III.
=653  20$aFractography.
=653  20$aToughness.
=700  1\$aMall, S., $eauthor.
=700  1\$aLingg, C., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10073J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10077J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10077J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQD171
=082  04$a620.1/6$223
=100  1\$aRobertson, DD., $eauthor.
=245  10$aFiber-Matrix Interphase Effects upon Transverse Behavior in Metal-Matrix Composites / $cDD Robertson, S Mall.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 1 (March 1992)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aTo develop reasonable analytical models and to understand better how the integrity of the fiber-matrix interface in high temperature titanium-based metal-matrix composites affects the overall transverse normal characteristics, a parametric study of various fiber-matrix interface conditions was performed. Analysis methods included both a simplified one-dimensional mathematical model and a finite element analysis using MSC/NASTRAN. First, both strong (perfectly bonded) and vanishingly weak (unbonded) interfaces were examined. Subsequently, to provide for partial bonding, a model that used an elastic-plastic interphase zone between the fiber and matrix was examined. It was found that the variation in the plastic properties (that is, yield stress and strain hardening) of this interphase zone provided the flexibility to model any level of interfacial bonding.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite micromechanics.
=650  \0$aInterfacial effects.
=650  \0$aInterphase.
=650  \0$aMetal-matrix composites.
=650  \0$aMicrostresses.
=650  \0$aPartial bonding.
=650  \0$aResidual thermal stresses.
=650  \0$aTransverse modulus.
=650  \0$aMicromechanics.
=650  \0$aComposite micromechanics.
=653  10$aComposite micromechanics.
=653  20$aMetal-matrix composites.
=653  20$aResidual thermal stresses.
=653  20$aTransverse modulus.
=653  20$aInterphase.
=653  20$aInterfacial effects.
=653  20$aPartial bonding.
=653  20$aMicrostresses.
=700  1\$aMall, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10077J.htm

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=024  7\$a10.1520/CTR10078J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10078J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aReeder, JR., $eauthor.
=245  10$aRedesign of the Mixed-Mode Bending Delamination Test to Reduce Nonlinear Effects / $cJR Reeder, JH Crews.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 1 (March 1992)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe mixed-mode bending (MMB) test uses a lever to apply simultaneously Mode I and Mode II loading to a split-beam specimen. An iterative analysis that accounts for the geometric non-linearity of the MMB test was developed. The analysis accurately predicted the measured load-displacement response and the strain energy release rate, G, of an MMB test specimen made of APC22 (AS4/PEEK). The errors in G when calculated using linear theory were found to be as large as 30% in some cases. Because it would be inconvenient to use a nonlinear analysis to analyze MMB data, the MMB apparatus was redesigned to minimize the nonlinearity. The nonlinear analysis was used as a guide in redesigning the MMB apparatus. With the improved apparatus, loads are applied just above the midplane of the test specimen through a roller attached to the lever. This apparatus was demonstrated by measuring the mixed-mode delamination fracture toughness of APC2. The nonlinearity errors associated with testing this tough composite material were less than ±3%. The data from the improved MMB apparatus analyzed with a linear analysis were similar to those found with the original apparatus and the nonlinear analysis.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDelamination.
=650  \0$aMixed-mode.
=650  \0$aNonlinear analysis.
=650  \0$aTest apparatus.
=650  \0$aToughness.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aDelamination.
=653  20$aMixed-mode.
=653  20$aNonlinear analysis.
=653  20$aTest apparatus.
=653  20$aToughness.
=653  20$aPEEK.
=700  1\$aCrews, JH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10078J.htm

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=001  CTR10079J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10079J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10079J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aHong, S-J., $eauthor.
=245  10$aConsistent Shear Constitutive Relations for a Laminated Plate / $cS-J Hong, RS Sandhu, HS Chohan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 1 (March 1992)
=504  \\$aIncludes bibliographical references$b25.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aStarting from a mixed variational formulation of linear elastostatics, it is shown that, for a laminated composite, the shearing force in any lamina would in general depend upon the shear deformation of that lamina as well as of the others. The coupling depends upon the material properties, the stacking sequence, and the applied surface tractions. Existing theories of homogeneous as well as laminated plates are seen to arise as specializations/approximations of the general theory. The theory is illustrated by studying the transverse shear coupling in a twelve-layer laminate. Examples illustrating the influence of the coupling on the accuracy of modelling laminate behavior are given.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aLaminates.
=650  \0$aMaterial properties.
=650  \0$aShear deformation.
=650  \0$aTransverse shear.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aLaminates.
=653  20$aTransverse shear.
=653  20$aMaterial properties.
=653  20$aShear deformation.
=700  1\$aSandhu, RS., $eauthor.
=700  1\$aChohan, HS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10079J.htm

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=001  CTR10080J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19929999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10080J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10080J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aAbu-Farsakh, G., $eauthor.
=245  12$aA Bimodular Material Model for Orthotropic Composite Thin Plates / $cG Abu-Farsakh.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 1 (March 1992)
=504  \\$aIncludes bibliographical references$b31.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new bimodular material model has been developed for the determination of reference-surface positions. The model is applicable to linear elastic isotropic and orthotropic composite rectangular thin plates of different aspect ratios. The basic concept of the model is to convert the actual material section to an equivalent one. The upper part of the cross section above the reference surface is assumed to be in compression, while the part below is assumed to be in tension. The reference-surface positions are determined independently of the plate boundary conditions and the loading. In the examples discussed here, the results of the reference-surface positions using the present model are found to be very close to neutral-surface positions determined by other methods, such as closed form and finite element methods. Moreover, the new material model does not require any iterations unlike the other models. Hence, it can be incorporated easily into linear and geometrically nonlinear structural analysis computer programs.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBimodular material.
=650  \0$aComposites.
=650  \0$aIsotropic.
=650  \0$aLinear elastic.
=650  \0$aModelling.
=650  \0$aOrthotropic.
=650  \0$aPlates.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aModelling.
=653  20$aBimodular material.
=653  20$aComposites.
=653  20$aLinear elastic.
=653  20$aPlates.
=653  20$aIsotropic.
=653  20$aOrthotropic.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10080J.htm

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=001  CTR10081J
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=024  7\$a10.1520/CTR10081J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10081J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA409
=082  04$a620.1/26$223
=100  1\$aCairns, DS., $eauthor.
=245  10$aStatic and Dynamic Mode II Strain Energy Release Rates in Toughened Thermosetting Composite Laminates / $cDS Cairns.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 1 (March 1992)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this work, the static and dynamic Mode II fracture properties of several thermosetting resin-based composite laminates are presented. Two classes of materials are explored. These are homogeneous thermosetting resins and toughened, multiphase, thermosetting resin systems. A new dynamic Mode II test is presented for composite laminates based on an end-notched flexure (ENF) specimen geometry. The specimen is impacted in three-point bending with an instrumented impact tower. Fracture initiation and propagation energies under static and dynamic conditions are determined analytically and experimentally. The test results show that the toughened systems provide superior fracture initiation and higher resistance to propagation under dynamic conditions. The results indicate that static fracture testing is inadequate for determining the fracture performance of composite laminates subjected to conditions such as low velocity impact. A good correlation between the basic Mode II dynamic fracture properties and the performance in a combined material/structural compression after impact (CAI) test is found. The results underscore the importance of examining rate-dependent behavior for determining the longevity of structures manufactured from composite materials.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdvanced composites.
=650  \0$aDynamic fracture.
=650  \0$aInterlaminar fracture.
=650  \0$aStrain energy release rate.
=650  \0$aToughened composites.
=650  \0$aFracture mechanics.
=650  \0$aFracture of materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aAdvanced composites.
=653  20$aInterlaminar fracture.
=653  20$aStrain energy release rate.
=653  20$aMode II fracture.
=653  20$aDynamic fracture.
=653  20$aToughened composites.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10081J.htm

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=001  CTR10084J
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=024  7\$a10.1520/CTR10084J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10084J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA347.F5
=082  04$a620.00151825$223
=100  1\$aWisnom, MR., $eauthor.
=245  10$aMicromechanical Modelling of the Transverse Tensile Ductility of Unidirectional Silicon Carbide/6061 Aluminum / $cMR Wisnom.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 2 (June 1992)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFinite element micromechanical modelling of unidirectional silicon carbide/6061 aluminum has been conducted to investigate ways to improve the transverse tensile strain to failure. The analysis included the effects of nonlinear matrix behavior, interface debonding, residual stresses as a result of manufacturing, and subsequent stress relaxation. The influence of heat treatment, fiberpacking geometry, and volume fraction have been analyzed. The most important factor affecting transverse tensile ductility is the relationship between the stress at which the matrix yields and the interface strength. Residual stresses are beneficial because they are compressive in the radial direction at the interface, effectively increasing the interface strength. Highest ductility is obtained when significant plasticity occurs before interface debonding. The model suggests that this can be achieved by annealing the composite and arranging the fibers to be in thin plies, spaced apart as far as possible to reduce the stress concentration factor at the interface. Reducing the volume fraction is also beneficial provided it is done by increasing the fiber spacing rather than increasing the ply thickness.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDuctility.
=650  \0$aFiber spacing.
=650  \0$aFiber-packing geometry.
=650  \0$aFinite element analysis.
=650  \0$aMatrix heat treatment.
=650  \0$aMetal-matrix composites.
=650  \0$aMicromechanical modelling.
=650  \0$aSilicon carbide/aluminum.
=650  \0$aTransverse tension.
=650  \0$aVolume fraction.
=650  \0$aFinite element method.
=650  \7$aTECHNOLOGY & ENGINEERING $xEngineering (General.
=653  10$aMetal-matrix composites.
=653  20$aSilicon carbide/aluminum.
=653  20$aMicromechanical modelling.
=653  20$aFinite element analysis.
=653  20$aTransverse tension.
=653  20$aDuctility.
=653  20$aMatrix heat treatment.
=653  20$aFiber-packing geometry.
=653  20$aVolume fraction.
=653  20$aFiber spacing.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10084J.htm

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=001  CTR10085J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10085J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10085J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aCrane, RM., $eauthor.
=245  12$aA Robust Testing Method for Determination of the Damping Loss Factor of Composites / $cRM Crane, JW Gillespie.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 2 (June 1992)
=504  \\$aIncludes bibliographical references$b22.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper describes a robust testing method for the experimental determination of the vibration damping loss factor of composites. This procedure is being proposed as a result of a detailed experimental program that was undertaken to characterize the damping loss factor of glass and graphite-epoxy composite materials. During the experimental testing to determine the damping loss factor of the composites, it became evident that the amplitude of vibration of the test beam had a pronounced effect on the calculated loss factor determined using the half-power bandwidth method. Calculated loss factors were significantly reduced if the tip displacement amplitude versus time were lower than 0.001 in. (0.0025 cm) for more than 25% of the data set. To alleviate this problem, a robust testing method was developed. In this procedure, a set of 2048 displacement versus time data points are recorded. This displacement versus time data is then partitioned into 512 data point intervals. A Fourier transform is performed on each of these data sets and loss factor determined using the half-power bandwidth method. The loss factor as a function of the maximum tip displacement within each data set is plotted. A linear least squares fit is performed on the data, with an extrapolation being made to zero displacement. The extrapolation to zero displacement effectively reduces the extraneous losses, providing a more robust testing protocol for material characterization. This testing method should provide increased accuracy and precision for the determination of the damping loss factor of materials.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDamping loss factor.
=650  \0$aExperimental testing.
=650  \0$aGlass/epoxy.
=650  \0$aGraphite/epoxy.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=653  10$aGlass/epoxy.
=653  20$aGraphite/epoxy.
=653  20$aDamping loss factor.
=653  20$aExperimental testing.
=700  1\$aGillespie, JW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10085J.htm

=LDR  04033nam  2200649 i 4500
=001  CTR10086J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19929999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10086J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10086J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNaik, RA., $eauthor.
=245  10$aFracture Mechanics Analysis for Various Fiber/Matrix Interface Loadings / $cRA Naik, JH Crews.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 2 (June 1992)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFiber/matrix (F/M) cracking was analyzed to provide better understanding and guidance in developing F/M interface fracture toughness tests. Two configurations, corresponding to F/M cracking at a broken fiber and at the free edge, were investigated. The effects of mechanical loading, thermal cooldown, and friction were investigated. Each configuration was analyzed for two loadings: longitudinal and normal to the fiber. A nonlinear finite element analysis was performed to model friction and slip at the F/M interface. A procedure for fitting a square-root singularity to calculated stresses was used to determine stress intensity factors (KI and KII) for a bimaterial interface crack. For the case of F/M cracking at a broken fiber with longitudinal loading, crack tip conditions were strongly influenced by interface friction. As a result, a F/M interface toughness test based on this case was not recommended because nonlinear data analysis methods would be required to calculate frictional energy. For the free edge crack configuration, both mechanical and thermal loading caused crack opening, thereby avoiding frictional effects. A F/M interface toughness test based on this configuration would provide data for KI/KII ratios of about 0.7 and 1.6 for fiber and radial normal loading, respectively. However, thermal effects must be accounted for in the data analysis.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aFinite element analysis.
=650  \0$aFracture.
=650  \0$aInterface.
=650  \0$aStress intensity factors.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aInterface.
=653  20$aStress intensity factors.
=653  20$aFracture.
=653  20$aFinite element analysis.
=700  1\$aCrews, JH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10086J.htm

=LDR  03503nam  2200661 i 4500
=001  CTR10087J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19929999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10087J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10087J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aO'Brien, TK., $eauthor.
=245  10$aResidual Thermal and Moisture Influences on the Analysis of Local Delaminations / $cTK O'Brien.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 2 (June 1992)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn analysis using laminated plate theory is developed to calculate the strain energy release rate associated with local delaminations originating at off-axis, angle-ply, matrix cracks in laminates subjected to uniaxial loads. The analysis includes the contribution of residual thermal and moisture stresses to the strain energy released. Examples are calculated for the strain energy release rate associated with local delaminations originating at 90° and angle-ply (non 90°) matrix-ply cracks in glass-epoxy and graphite-epoxy laminates. The solution developed may be used to assess the relative contribution of mechanical, residual thermal, and moisture stresses on the strain energy release rate for local delamination for a variety of layups and materials.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDelamination.
=650  \0$aHygroscopic stress.
=650  \0$aMatrix crack.
=650  \0$aMoisture.
=650  \0$aResidual thermal stress.
=650  \0$aStrain energy release rate.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aResidual thermal stress.
=653  20$aHygroscopic stress.
=653  20$aMoisture.
=653  20$aStrain energy release rate.
=653  20$aDelamination.
=653  20$aMatrix crack.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10087J.htm

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=001  CTR10088J
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=008  161219c19929999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10088J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10088J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTK7870.25
=082  04$a621.381548$223
=100  1\$aZenkert, D., $eauthor.
=245  10$aShear Cracks in Foam Core Sandwich Panels : $bNondestructive Testing and Damage Assessment / $cD Zenkert, M Vikström.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 2 (June 1992)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aShear cracks in the core of foam core sandwich panels may be found as a result of overloading, impact, or fatigue. These are subsurface flaws and are therefore hard to find nondestructively and may act as initiation points for final failure. Hence, it is of vital interest to detect these flaws and compute their influence on the load-bearing capacity of the panel. In the present paper, different types of shear cracks are simulated in foam core sandwich panels. They are inspected with a thermal nondestructive testing (NDT) method based on an infrared (IR) detector. It is found that all types of simulated cracks can be satisfactorily detected.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCellular foam.
=650  \0$aFinite element method.
=650  \0$aFracture analysis.
=650  \0$aFracture toughness.
=650  \0$aNondestructive testing.
=650  \0$aSandwich construction.
=650  \0$aShear crack.
=650  \0$aThermography.
=650  \0$aInfrared photography.
=650  \0$aHeat.
=653  10$aSandwich construction.
=653  20$aCellular foam.
=653  20$aThermography.
=653  20$aNondestructive testing.
=653  20$aShear crack.
=653  20$aFracture analysis.
=653  20$aFracture toughness.
=653  20$aFinite element method.
=700  1\$aVikström, M., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10088J.htm

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=001  CTR10091J
=003  IN-ChSCO
=005  20161219163000.0
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=008  161219c19929999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10091J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10091J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aMcCartney, LN., $eauthor.
=245  10$aMechanics for the Growth of Bridged Cracks in Composite Materials : $bPart I. Basic Principles / $cLN McCartney.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (14 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 3 (September 1992)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe fracture mechanics are established for a large plate containing an embedded crack of finite length taking account of: (1) the anisotropy of the material, (2) the effect of residual stresses arising from isothermal temperature changes, and (3) the effect of tractions applied to the crack surfaces resulting from the mechanical effect of crack-bridging ligaments. An expression for the crack-opening displacement distribution in terms of the crack-bridging traction distribution is derived together with the corresponding fracture criterion based on energy considerations.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnisotropy.
=650  \0$aCross-ply laminates.
=650  \0$aElasticity.
=650  \0$aFracture mechanics.
=650  \0$aIntegral equations.
=650  \0$aMatrix cracking.
=650  \0$aResidual stress.
=650  \0$aTransverse cracking.
=650  \0$aUnidirectional composites.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aElasticity.
=653  20$aAnisotropy.
=653  20$aFracture mechanics.
=653  20$aUnidirectional composites.
=653  20$aCross-ply laminates.
=653  20$aResidual stress.
=653  20$aMatrix cracking.
=653  20$aTransverse cracking.
=653  20$aIntegral equations.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10091J.htm

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=024  7\$a10.1520/CTR10092J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10092J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA409
=082  04$a620.1/26$223
=100  1\$aLN, McCartney, $eauthor.
=245  10$aMechanics for the Growth of Bridged Cracks in Composite Materials : $bPart II. Applications / $cMcCartney LN.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 3 (September 1992)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA fracture mechanics analysis valid for long cracks is applied to three crack-bridging problems that arise in the composites area, namely, (1) matrix cracking in perfectly bonded unidirectional composites, (2) transverse cracking in perfectly bonded cross-ply laminates, and (3) matrix cracking in unidirectional composites in which frictional slip occurs at fiber matrix interfaces governed by the constant shear-stress shear-lag model of stress transfer.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnisotropy.
=650  \0$aCross-ply laminates.
=650  \0$aElasticity.
=650  \0$aFiber fracture.
=650  \0$aFracture mechanics.
=650  \0$aInterfacial friction.
=650  \0$aMatrix cracking.
=650  \0$aPerfect interfacial bonding.
=650  \0$aResidual stress.
=650  \0$aTransverse cracking.
=650  \0$aUnidirectional composites.
=650  \0$aFracture of materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aElasticity.
=653  20$aAnisotropy.
=653  20$aFracture mechanics.
=653  20$aUnidirectional composites.
=653  20$aCross-ply laminates.
=653  20$aResidual stress.
=653  20$aMatrix cracking.
=653  20$aTransverse cracking.
=653  20$aPerfect interfacial bonding.
=653  20$aInterfacial friction.
=653  20$aFiber fracture.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10092J.htm

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=024  7\$a10.1520/CTR10093J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10093J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTJ825
=082  04$a333.9/2$223
=100  1\$aIshai, O., $eauthor.
=245  10$aDamage Tolerance of a Composite Sandwich with Interleaved Foam Core / $cO Ishai, C Hiel.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (14 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 3 (September 1992)
=504  \\$aIncludes bibliographical references$b45.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA composite sandwich panel consisting of carbon fiber-reinforced plastic (CFRP) skins and a syntactic foam core was selected as an appropriate structural concept for the design of wind tunnel compressor blades. Interleaving of the core with tough interlayers was doen to prevent core cracking and improve damage tolerance of the sandwich. Simply supported sandwich beam specimens were subjected to low-velocity, drop-weight impacts as well as high-velocity, ballistic impacts. The performance of the interleaved core sandwich panels was characterized by localized skin damage and minor cracking of the core. Residual compressive strength (RCS) of the skin, which was derived from flexural test, shows the expected trend of decreasing with increasing size of the damage, impact energy, and velocity. In the case of skin damage, RCS values of around 50% of the virgin interleaved reference were obtained at the upper impact energy range. Based on the similarity between low velocity and ballistic impact effects, it was concluded that impact energy is the main variable controlling damage and residual strength, where as velocity plays a minor role. The superiority (in damage tolerance) of the composite sandwich with interleaved foam core, as compared with its plain version, is well established. This is attributable to the toughening effect of the interlayers which serve the dual role of crack arrestor and energy absorber of the impact loading.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBallistic impact.
=650  \0$aCarbon fiber-reinforced foam.
=650  \0$aDamage tolerance.
=650  \0$aDamage.
=650  \0$aImpact energy.
=650  \0$aImpact velocity.
=650  \0$aImpact.
=650  \0$aInterleaving.
=650  \0$aResidual strength.
=650  \0$aSandwich beam.
=650  \0$aSyntactic foam.
=650  \0$aVelocity.
=653  10$aDamage.
=653  20$aDamage tolerance.
=653  20$aImpact.
=653  20$aBallistic impact.
=653  20$aImpact velocity.
=653  20$aImpact energy.
=653  20$aSandwich beam.
=653  20$aInterleaving.
=653  20$aSyntactic foam.
=653  20$aResidual strength.
=653  20$aCarbon fiber-reinforced foam.
=700  1\$aHiel, C., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10093J.htm

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=001  CTR10094J
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=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19929999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10094J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10094J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC367.3.I58
=082  04$a522/.6$223
=100  1\$aHowell, BF., $eauthor.
=245  10$aEffect of Expanding Monomer on Carbon Fiber-Reinforced Epoxy Composites / $cBF Howell.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 3 (September 1992)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this investigation, it was confirmed that copolymerization of dinorbornene spiroorthocarbonate (DNSOC) with epoxy can reduce sample shrinkage without degrading mechanical properties. To maximize control of shrinkage, it is important to bring epoxy to the gel stage before the DNSOC begins to copolymerize.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDinorbornene spiroorthocarbonate.
=650  \0$aEpoxy.
=650  \0$aExpanding monomer.
=650  \0$aInterferometry.
=650  \0$aMicroindentation test.
=650  \0$aPolymer.
=650  \0$aResidual strain.
=650  \0$aInterferometry.
=650  \0$aOptical measurements.
=653  10$aDinorbornene spiroorthocarbonate.
=653  20$aEpoxy.
=653  20$aExpanding monomer.
=653  20$aInterferometry.
=653  20$aMicroindentation test.
=653  20$aPolymer.
=653  20$aResidual strain.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10094J.htm

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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c19929999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10095J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10095J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aLiao, K., $eauthor.
=245  10$aDetection of Stress Fields and Delaminations in Vibrating Composite Beams by a Thermoelastic Technique / $cK Liao, LH Tenek, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 3 (September 1992)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA thermoelastic technique (SPATE-stress pattern analysis by thermal emission) was used to determine the qualitative stress distributions and detect imbedded delaminations in thin composite beam specimens during vibrational excitation. The capability of the SPATE system to record qualitative stress distribution patterns in a vibrating beam was verified by scanning the beam at its resonance frequencies where the recorded stress patterns matched their corresponding mode shapes. It was found from the SPATE images that self-resonance of the imbedded delaminations occurred when the vibrating frequency of the beam specimen reached a certain value. Results from a finite element model exhibited good agreement with the experimental findings.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aDelamination.
=650  \0$aThermoelastic technique.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aThermoelastic technique.
=653  20$aSPATE (stress pattern analysis by thermal emission).
=653  20$aComposite materials.
=653  20$aDelamination.
=700  1\$aTenek, LH., $eauthor.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10095J.htm

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=001  CTR10096J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19929999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10096J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10096J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.118$223
=100  1\$aNaik, RA., $eauthor.
=245  10$aSimplified Micromechanical Equations for Thermal Residual Stress Analysis of Coated Fiber Composites / $cRA Naik.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 3 (September 1992)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe fabrication of metal matrix composites poses unique problems to the materials engineer. The large thermal expansion coefficient (CTE) mismatch between the fiber and matrix leads to high tensile residual stresses at the fiber/matrix (F/M) interface which could lead to premature matrix cracking during cooldown. Fiber coatings could be used to reduce thermal residual stresses. A simple closed-form analysis, based on a three-phase composite cylinder model, was developed to calculate thermal residual stresses in a fiber/interphase/matrix system. Guidelines, in the form of simple equations, for the selection of appropriate material properties of the fiber coating were also derived to minimize thermal residual stresses in the matrix during fabrication.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aClosed form.
=650  \0$aComposite cylinder.
=650  \0$aInterphase.
=650  \0$aMetal matrix composites.
=650  \0$aMicromechanics.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \0$aSolid state physics.
=653  10$aComposite cylinder.
=653  20$aClosed form.
=653  20$aMicromechanics.
=653  20$aInterphase.
=653  20$aMetal matrix composites.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10096J.htm

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=008  161219c19929999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10099J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10099J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQA273.6
=082  04$a519/.1$223
=100  1\$aGao, Z., $eauthor.
=245  10$aTensile Failure of Composites : $bInfluence of Interface and Matrix Yielding / $cZ Gao, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 4 (December 1992)
=504  \\$aIncludes bibliographical references$b43.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aYielding stress of matrix and interface is chosen to represent the influence of the chemical, mechanical, and thermodynamical nature of the bonding process between matrix and fiber materials. The shear stress-strain behavior of interface and matrix material is modeled as elastic-perfectly plastic. A local stress analysis model is used to represent the influence of interface and matrix yielding on stress distribution resulting from fiber fractures. The model is combined with the concept of multiple fiber fractures in the development of a mechanistic representation of tensile strength. In this strength formulation, fibers are assumed to be a statistical quantity, and as the material is loaded, fibers fracture randomly throughout the body causing localized stress concentration. The accumulation of these breaks results in overall failure. The resulting analysis is applied to numerical studies of the influence of interface/matrix yielding on stress and damage characteristics of unidirectional composites under quasistatic uniaxial loading. A discussion of optimal design parameters for composites is also presented.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aFiber.
=650  \0$aInterface.
=650  \0$aMatrix.
=650  \0$aMicromechanics.
=650  \0$aOptimal.
=650  \0$aShear lag.
=650  \0$aSurface treatment.
=650  \0$aTensile failure.
=650  \0$aWeibull distribution.
=650  \0$aYielding.
=650  \0$aWeibull distribution.
=650  \0$aWeibull method.
=653  10$aComposites.
=653  20$aInterface.
=653  20$aMatrix.
=653  20$aYielding.
=653  20$aFiber.
=653  20$aTensile failure.
=653  20$aWeibull distribution.
=653  20$aSurface treatment.
=653  20$aOptimal.
=653  20$aMicromechanics.
=653  20$aShear lag.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10099J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10100J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10100J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aBigelow, CA., $eauthor.
=245  14$aThe Effects of Uneven Fiber Spacing on Thermal Residual Stresses in a Unidirectional SCS-6/Ti-15-3 Laminate / $cCA Bigelow.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 4 (December 1992)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aHigh residual stresses develop in SCS-6/Ti-15-3 composites during cooldown from the fabrication temperature; these residual stresses can affect the behavior of the composite. Discrete fibermatrix finite element models were used to study the residual stresses caused by the temperature change during the fabrication process, including the effects of uneven fiber spacing, the free surface, and increased fiber volume fractions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aFiber volume fraction.
=650  \0$aFree surface.
=650  \0$aMatrix cracks.
=650  \0$aMicromechanics.
=650  \0$aThree-dimensional finite elements.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aFree surface.
=653  20$aFiber volume fraction.
=653  20$aMicromechanics.
=653  20$aMatrix cracks.
=653  20$aThree-dimensional finite elements.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10100J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10101J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10101J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA417.6
=082  04$a624.1/76$223
=100  1\$aHillberry, BM., $eauthor.
=245  10$aPrediction of Matrix Fatigue Crack Initiation in Notched SCS-6/Ti-15-3 Metal Matrix Composites / $cBM Hillberry, W Steven Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 4 (December 1992)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSeveral lay-ups of SCS-6/Ti-15-3 metal matrix composites were tested in either a center hole or a double-edge-notched geometry. At different cyclic stress levels, the number of cycles required to initiate a matrix fatigue crack at the notch was recorded. A strain-life fatigue curve was developed for the Ti-15-3 matrix material. A strain-life fatigue analysis method was developed that incorporates a modified Smith, Watson, and Topper effective strain parameter to account for local stress concentration at the notch tip and thermal residual stresses in the matrix material. This analysis method was used to predict the number of cycles required for matrix crack initiation at the notches. The predictions were in good agreement with the experimental data.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEffective strain.
=650  \0$aMetal matrix composites.
=650  \0$aResidual thermal stress.
=650  \0$aStress concentration.
=650  \0$aStress distribution.
=650  \0$aStructural analysis (Engineering)
=653  10$aMetal matrix composites.
=653  20$aEffective strain.
=653  20$aResidual thermal stress.
=653  20$aStress concentration.
=700  1\$aSteven Johnson, W., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10101J.htm

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=001  CTR10102J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10102J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10102J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRomeo, G., $eauthor.
=245  12$aA New Test Facility for Measuring the Coefficient of Moisture Expansion of Advanced Composite Materials / $cG Romeo, E Miraldi, G Ruscica, F Bertoglio, G Frulla, G Ruvinetti.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 4 (December 1992)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new test facility is here described; it has been designed to measure carefully the coefficient of moisture expansion (CME) in specimens made of advanced composite materials. The facility is basically composed of a thermostat, contained in a vacuum chamber, in which five carbon fiber-reinforced plastic (CFRP) samples, one Invar sample, and six displacement transducers are enclosed. The CFRP specimens are first subjected to an accelerated absorption cycle and, later on, placed into the vacuum environment (10−3 Pa) of the thermostat at a temperature of 330K, controlled within ±0.1K. The measurement of dimensional variations are carried out using very accurate inductive displacement transducers mounted on Invar frames (5 × 10−8 m is the typical accuracy). One of the specimens tested is made by Invar, with a zero CME, to have a stable length reference during the simultaneous measurement of the five CFRP samples. About 100 h are usually necessary for the test. A coefficient of moisture expansion of 3.85 × 10−5 and 3.1 × 10−3 (ΔM/M)%−1 was obtained along the fiber direction and normal to the fiber direction, respectively. A maximum standard deviation of 5 × 10−6 (ΔM/M)%−1 in the CME along the fiber direction has been confirmed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCoefficient of moisture expansion (CME).
=650  \0$aComposite materials.
=650  \0$aDimensional stability.
=650  \0$aTest facilities.
=650  \0$aVacuum moisture desorption.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aCoefficient of moisture expansion (CME).
=653  20$aTest facilities.
=653  20$aVacuum moisture desorption.
=653  20$aDimensional stability.
=700  1\$aMiraldi, E., $eauthor.
=700  1\$aRuscica, G., $eauthor.
=700  1\$aBertoglio, F., $eauthor.
=700  1\$aFrulla, G., $eauthor.
=700  1\$aRuvinetti, G., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10102J.htm

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=001  CTR10103J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10103J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10103J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSrinivasan, K., $eauthor.
=245  10$aShear Failure and Impact Resistance in Graphite Fiber Laminates / $cK Srinivasan, TW Coats, JA Hinkley.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 4 (December 1992)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe multispan beam (MSB) test was evaluated as a predictor of damage resistance and damage tolerance in quasi-isotropic graphite laminates. Materials studied were five commercial prepreg systems using high-strain and intermediate-modulus carbon fibers, as well as an amorphous thermoplastic system prepared in-house. Failure loads and displacements in the MSB tests showed little rate dependence. Values of compressive strength after a standard low-velocity impact (compression after impact [CAI]) correlated fairly well with the MSB results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBending tests.
=650  \0$aComposite materials.
=650  \0$aCompressive strength.
=650  \0$aDamage tolerance.
=650  \0$aEpoxy resins.
=650  \0$aGraphite composites.
=650  \0$aImpact damage.
=650  \0$aThermoplastic resins.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aGraphite composites.
=653  20$aEpoxy resins.
=653  20$aThermoplastic resins.
=653  20$aImpact damage.
=653  20$aCompressive strength.
=653  20$aDamage tolerance.
=653  20$aBending tests.
=700  1\$aCoats, TW., $eauthor.
=700  1\$aHinkley, JA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10103J.htm

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=001  CTR10104J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10104J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10104J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aHe, MY., $eauthor.
=245  10$aFinite Element Analysis of Beam Specimens Used to Measure the Delamination Resistance of Composites / $cMY He, AG Evans.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1992.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 14, Issue 4 (December 1992)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe energy release rates G applicable to various beam specimens used to measure the delamination resistance of composites have been calculated using finite element methods. The results have been compared with beam theory solutions, GBT. While appreciable discrepancies exist, it has been found that the differences are expressible through a nondimensional parameter, ρ, identified from orthotropy rescaling. Consequently, accurate solutions for G are presented in terms of GBT, qualified by analytical series functions containing ρ.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1992. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCracks.
=650  \0$aDelamination.
=650  \0$aEnd-notched flexure specimens (ENF).
=650  \0$aFinite element analysis.
=650  \0$aInterlaminar fracture toughness.
=650  \0$aFinite element method.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aFinite element analysis.
=653  20$aDelamination.
=653  20$aEnd-notched flexure specimens (ENF).
=653  20$aInterlaminar fracture toughness.
=653  20$aCracks.
=700  1\$aEvans, AG., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10104J.htm

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=001  CTR10109J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10109J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10109J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aWelsh, JS., $eauthor.
=245  10$aUnidirectional Composite Compression Strengths Obtained by Testing Cross-Ply Laminates / $cJS Welsh, DF Adams.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 4 (October 1996)
=504  \\$aIncludes bibliographical references$b30.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe strength and stiffness of a unidirectional AS4/3501-6 carbon/epoxy composite material system was experimentally determined using tabbed and untabbed cross-ply specimens tested in established shear- and end-loaded compression test fixtures. Four different analysis techniques were used to predict the unidirectional lamina strength from the measured cross-ply specimen strength. The compressive strength and failure mode of the cross-ply laminates showed a desirable immunity to fabrication techniques, testing conditions, and fixture type. Several special aspects of using cross-ply laminates, including isolating the 0° laminae, free-edge effects, and stress concentrations induced by end tabs, are discussed. The effects of these topics on the cross-ply laminates used in the present study are compared to conventional unidirectional specimens.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBack-out factor.
=650  \0$aCarbon/epoxy composites.
=650  \0$aCompression testing.
=650  \0$aCross-ply laminates.
=650  \0$aUnidirectional composites.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aCompression testing.
=653  20$aUnidirectional composites.
=653  20$aCross-ply laminates.
=653  20$aCarbon/epoxy composites.
=653  20$aBack-out factor.
=700  1\$aAdams, DF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10109J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10110J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10110J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aShaker, M., $eauthor.
=245  10$aImprovement of the Interfacial Adhesion Between Kevlar Fiber and Resin by Using R-F Plasma / $cM Shaker, I Kamel, F Ko, JW Song.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe interfacial adhesion between fiber and matrix has a significant effect on the overall performance of a composite. The necessity of binding the fibers together in a structural composite creates the need for an enhanced interfacial bond between fibers and matrix. One possibility to change the fiber/matrix bond in composite materials is to modify the surface of the reinforcing fiber. One technology useful for this purpose is plasma treatment. This paper discusses optimizing R-F plasma polymerization of allylamine onto Kevlar 29 and KM2 fibers. The treatment was carried out in two steps. First, the fiber was treated with Argon; second, the fiber was treated by allylamine. A method was found such that, under such optimum treatment conditions, the plasma treatment does not adversely affect the mechanical properties of the fibers. This allows flexibility in the tailoring of interfacial properties to optimize the energy absorption capability of the composities. A method was also found that increases interfacial adhesion between PPTA fiber (Kevlar) filament and the matrix as the thickness of the plasma allylamine coating increases.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy.
=650  \0$aInterfacial adhesion.
=650  \0$aPlasma treatment.
=650  \0$aPlasma.
=650  \0$aKevlar fiber.
=653  10$aKevlar fiber.
=653  20$aEpoxy.
=653  20$aPlasma treatment.
=653  20$aInterfacial adhesion.
=653  20$aMonomer.
=700  1\$aKamel, I., $eauthor.
=700  1\$aKo, F., $eauthor.
=700  1\$aSong, JW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10110J.htm

=LDR  03136nam  2200649 i 4500
=001  CTR10111J
=003  IN-ChSCO
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10111J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10111J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSingh, SP., $eauthor.
=245  10$aRotordynamic Experiments on Composite Shafts / $cSP Singh, K Gupta.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 4 (October 1996)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aRotordynamic experiments are performed on two hollow tubular Carbon/Epoxy filament wound composite shafts. The experiments comprise of determination of critical speed and unbalance response as well as orbital and spectrum analysis. Step-wise progressive balancing near the critical speed was needed to operate the shaft in the super-critical region. Critical speeds determined from experiments match extremely well with theoretical values obtained from the equivalent modulus beam theory.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite shafts.
=650  \0$aCritical speeds.
=650  \0$aRotordynamic experiments.
=650  \0$aUnbalance response.
=650  \0$aWhirl orbits.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCritical speeds.
=653  20$aComposite shafts.
=653  20$aRotordynamic experiments.
=653  20$aUnbalance response.
=653  20$aWhirl orbits.
=700  1\$aGupta, K., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10111J.htm

=LDR  03631nam  2200649 i 4500
=001  CTR10112J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10112J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10112J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRobertson, DD., $eauthor.
=245  10$aIncorporating Fiber Damage in a Micromechanical Analysis of Metal Matrix Composite Laminates / $cDD Robertson, S Mall.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b26.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA micromechanics based formulation involving the method of cells is developed to analyze metal matrix composite behavior in the presence of fiber fragmentation. The effects of fiber fracture are accounted for by determining an instantaneous effective fiber modulus from a modified chain-of-bundles approach. The analysis assumes a uniform density of fiber breakage throughout the composite. This crack density is determined from Weibull statistics whose parameters may be obtained from single-fiber tests or estimated. The ultimate strength of titanium-based metal matrix composite (MMC) laminates as well as their inelastic stress-strain response in the presence of fiber fragmentation are predicted from the present analysis which are in good agreement with the experimental counterparts. Also, the applicability of the present analysis to predict the low cycle/high stress fatigue lives of MMC laminates is demonstrated.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite damage.
=650  \0$aFiber failure.
=650  \0$aMetal matrix composites.
=650  \0$aTitanium composites.
=650  \0$aUltimate strength.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMetal matrix composites.
=653  20$aComposite damage.
=653  20$aFiber failure.
=653  20$aUltimate strength.
=653  20$aTitanium composites.
=700  1\$aMall, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10112J.htm

=LDR  03334nam  2200637 i 4500
=001  CTR10113J
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=024  7\$a10.1520/CTR10113J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10113J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKassapoglou, C., $eauthor.
=245  10$aCompression Strength of Composite Sandwich Structures After Barely Visible Impact Damage / $cC Kassapoglou.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 4 (October 1996)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA simple approach to determine the compressive strength of composite sandwich structures after barely visible impact damage is presented. The damaged region of the facesheet is modeled as an inclusion area of reduced stiffness. The stress concentration caused by the damage is calculated using a classical elasticity approach. Test specimens were fabricated and tested at three environmental conditions to complement tests already available in the literature. The predictions of the present approach were compared to test results from the literature and the present study and found to be in very good agreement over a wide variety of materials and environmental conditions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBarely visible impact.
=650  \0$aComposites.
=650  \0$aCompression strength.
=650  \0$aImpact damage.
=650  \0$aSandwich structures.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCompression strength.
=653  20$aImpact damage.
=653  20$aBarely visible impact.
=653  20$aSandwich structures.
=653  20$aComposites.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10113J.htm

=LDR  04198nam  2200649 i 4500
=001  CTR10118J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10118J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10118J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHighsmith, AL., $eauthor.
=245  10$aUsing Measured Damage Parameters to Predict the Residual Strength of Impacted Composites : $bA Neural Network Approach / $cAL Highsmith, S Keshav.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 4 (October 1997)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe poor performance of composite materials under transverse quasi-static and impact loading is of major concern in their application as primary load carrying components in advanced structural applications. These materials sustain substantial internal damage in the form of matrix cracking, delaminations and fiber fracture. The present paper reports the results of a modeling exercise which used neural networks as a tool to predict the loss in residual strength resulting from localized damage in impacted laminates. Several measured fiber fracture parameters, as well as matrix damage areas, obtained from damaged laminates were used as inputs. Neural networks were used to identify those damage parameters that were essential for effective residual strength prediction. Development of the neural network models was performed using experimental data from specimens fabricated from the Fiberite IM7/977-2 material system which were first damaged via quasi-static contact loading, and then loaded in tension to failure. Data obtained from specimens tested for residual strength after impact were used to test the model's generalization capability. A pruning study was also conducted to determine an optimally connected, robust neural network model that generalized better than conventional fully connected feedforward networks. The predicted strength values were found to be in very good agreement with those obtained from experiments indicating the suitability of neural networks in this application.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFiber fracture.
=650  \0$aLaminate.
=650  \0$aNeural networks.
=650  \0$aRobustness.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aNeural networks.
=653  20$aFiber fracture.
=653  20$aLaminate.
=653  20$aRobustness.
=700  1\$aKeshav, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10118J.htm

=LDR  02266nam  2200505 i 4500
=001  CTR10119J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10119J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10119J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMartin, R., $eauthor.
=245  10$aIntroduction to Symposium on Non-Aerospace Applications for Composite Materials / $cR Martin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 4 (October 1997)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10119J.htm

=LDR  03555nam  2200769 i 4500
=001  CTR10120J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10120J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10120J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aChin, JW., $eauthor.
=245  10$aEffects of Environmental Exposure on Fiber-Reinforced Plastic (FRP) Materials Used in Construction / $cJW Chin, T Nguyen, K Aouadi.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 4 (October 1997)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA major hindrance to the acceptance of polymer composites in civil engineering applications is the susceptibility of the polymeric matrix to weathering. The polymer matrix is prone to degradation initiated by ultraviolet (UV) radiation, moisture, temperature, and high pH environments. The objective of this study was to characterize chemical and physical changes in polymeric matrix resins following exposure to these environments. The ultimate goal is to identify factors that contribute to matrix resin degradation under environmental and mechanical stresses.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAlkaline conditions.
=650  \0$aBuilding technology.
=650  \0$aComposites.
=650  \0$aDurability.
=650  \0$aMoisture.
=650  \0$aPolyester.
=650  \0$aSaline conditions.
=650  \0$aUltraviolet radiation.
=650  \0$aVinyl ester.
=650  \0$aComposite material.
=650  \0$aAlkaline conditions.
=650  \0$aBuilding technology.
=653  10$aAlkaline conditions.
=653  20$aBuilding technology.
=653  20$aComposites.
=653  20$aDurability.
=653  20$aPolyester.
=653  20$aMoisture.
=653  20$aSaline conditions.
=653  20$aVinyl ester.
=653  20$aUltraviolet radiation.
=700  1\$aNguyen, T., $eauthor.
=700  1\$aAouadi, K., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10120J.htm

=LDR  04139nam  2200673 i 4500
=001  CTR10121J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10121J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10121J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.84
=082  04$a620.1/127$223
=100  1\$aChiou, P-L, $eauthor.
=245  10$aSeawater Effects on Strength and Durability of Glass/Epoxy Filament-Wound Tubes as Revealed by Acoustic Emission Analysis / $cP-L Chiou, WL Bradley.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effect of seawater on the strength and durability of glass/epoxy [903/±25/903] filament-wound composite tubes was investigated by testing tubes in the closed-ended test mode with internal hydraulic pressure. Acoustic emission was used to monitor the damage progression and to interpret seawater effect. Two types of tests were performed. In the burst test, the tube was pressurized monotonically at a constant rate to failure. In the second type of test, tubes were subjected to 14 mechanical conditioning cycles of load and unload prior to performing a stress rupture test. Both types of tests were performed with as-fabricated and seawater-saturated tubes to establish seawater effects on damage progression and failure strength. Static moisture absorption did not have a large effect on the tube strength. In the burst test, seawater saturated tubes only suffered a 6% decrease in their strength. Acoustic emission analysis showed a minor difference between the damage progression of as-fabricated and seawater saturated tubes. The combination of stress and moisture had a much larger effect on the tubes studied. During the mechanical conditioning cycles, seawater saturated tubes exhibited much greater damage accumulation than that exhibited by as-fabricated tubes. As a result, the times to rupture for seawater saturated tubes were much shorter than for as-fabricated tubes in subsequent stress rupture tests.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAcoustic emission.
=650  \0$aComposite tube.
=650  \0$aDamage.
=650  \0$aDegradation.
=650  \0$aGlass/epoxy.
=650  \0$aSeawater.
=650  \0$aAcoustic emission.
=650  \0$aAcoustical engineering.
=653  10$aGlass/epoxy.
=653  20$aComposite tube.
=653  20$aSeawater.
=653  20$aDamage.
=653  20$aDegradation.
=653  20$aAcoustic emission.
=700  1\$aBradley, WL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10121J.htm

=LDR  03518nam  2200769 i 4500
=001  CTR10122J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10122J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10122J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aStumpf, H., $eauthor.
=245  10$aQUIKTEMP-A New Short-Cycle-Time Manufacturing Method for Thermoplastic Composites Made from Low-Cost Textile Preforms / $cH Stumpf, K Schulte.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 4 (October 1997)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWeft-inserted warp-knitting can be applied to produce textile composite preforms comprising both reinforcement fibers and thermoplastic matrix ribbons at comparatively low cost. A newly developed technique (denoted QUIKTEMP) for fast processing of molded parts is presented. As a special feature, the concept allows for the material staying with one mold throughout the process, while the cycle time is still short. Hence, pressure can be applied continuously and without additional cost due to prolonged cycle times.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDrapability.
=650  \0$aFast processing.
=650  \0$aGlass fibers.
=650  \0$aHeat transfer.
=650  \0$aPolylpropylene matrix.
=650  \0$aSplit film.
=650  \0$aThermoplastic manufacturing.
=650  \0$aWarp-knitting.
=650  \0$aComposite material.
=650  \0$aSplit film.
=650  \0$aDrapability.
=653  10$aComposites.
=653  20$aWarp-knitting.
=653  20$aDrapability.
=653  20$aPolylpropylene matrix.
=653  20$aGlass fibers.
=653  20$aSplit film.
=653  20$aThermoplastic manufacturing.
=653  20$aFast processing.
=653  20$aHeat transfer.
=653  20$aFEM calculation.
=700  1\$aSchulte, K., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10122J.htm

=LDR  04138nam  2200733 i 4500
=001  CTR10123J
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10123J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10123J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA462
=082  04$a620.1/1223$223
=100  1\$aKoko, TS., $eauthor.
=245  10$aComposite Repair of a Stainless Steel-GRP Sonar Dome / $cTS Koko, MJ Connor, GV Corbett.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper describes the application of composite materials for the repair of corrosion damage on stainless-steel components of hull-mounted sonar domes on typical warships. The domes have an aerofoil shape in plan, approximately 4.08 m nose to tail, 1.27 m maximum width, and 1.83 m high. The sides (acoustic window) of the domes are made of stainless steel and the canoe-shaped bottom is made of glass-reinforced plastic (GRP) composite. A bottom-mounted stainless-steel insert and drain plug unit is used for flooding and draining the dome. Due to the severe marine environment, the stainless steel drain plug suffers extensive corrosion damage and has to be replaced frequently. A study performed to replace the stainless-steel insert and drain plug components with composite material is presented. The approach adopted is to treat the problem as a flush composite repair, whereby an area around the drain hole in the GRP canoe is cut out and replaced with a two-piece composite insert that is bonded onto the GRP canoe. Both the insert and plug are made of glass-reinforced composite material. Details of the material selection, design, fabrication, and process specification for the repair, as well as the challenges involved in undertaking this repair are discussed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive bonding.
=650  \0$aComposite material.
=650  \0$aComposite repair.
=650  \0$aCorrosion.
=650  \0$aGlass-reinforced plastics.
=650  \0$aMachining.
=650  \0$aSonar dome.
=650  \0$aStainless steel.
=650  \0$aMetals $xDefects.
=650  \7$aSCIENCE $xNanoscience.
=653  10$aSonar dome.
=653  20$aGlass-reinforced plastics.
=653  20$aComposite material.
=653  20$aAdhesive bonding.
=653  20$aMachining.
=653  20$aComposite repair.
=653  20$aStainless steel.
=653  20$aCorrosion.
=700  1\$aConnor, MJ., $eauthor.
=700  1\$aCorbett, GV., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10123J.htm

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=001  CTR10128J
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=008  161219c19889999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10128J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10128J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGause, LW., $eauthor.
=245  10$aBraided to Net Section Graphite/Epoxy Composite Shapes / $cLW Gause, JM Alper.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (14 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 2 (June 1988)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe fabrication of braided-to-net-shape graphite/epoxy composites has been demonstrated for channel, cruciform, Tee, and hat section geometries. Resin impregnation, cure, and tooling methods were devised, which successfully combined dry-braided AS4 fiber preforms with neat 3501-6 resin to produce the various shapes. The local buckling, post-buckling, and crippling behavior of short thin-walled braided compression members were investigated. The braided composites displayed large scatter in their test data, which may be characteristic of this form of construction. Stiffener pull-off-strength of the braided tee-section approached the transverse strength of the braided composite. Handling during fabrication was much easier with the braid than with conventional prepreg. The braid required only ¼ the time used to layup and bag a similar channel specimen using identical tooling. The high cost of the orthogonal braiding process remains the major barrier to serious structural applications.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aComposite materials.
=650  \0$aCompression.
=650  \0$aFatigue (materials)
=650  \0$aGraphite/epoxy.
=650  \0$aPostbuckling.
=650  \0$aThree-dimensional fabrics.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aThree-dimensional fabrics.
=653  20$aGraphite/epoxy.
=653  20$aCompression.
=653  20$aBuckling.
=653  20$aPostbuckling.
=653  20$aFatigue (materials).
=700  1\$aAlper, JM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10128J.htm

=LDR  03724nam  2200637 i 4500
=001  CTR10129J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19889999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10129J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10129J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKao, WH., $eauthor.
=245  10$aDevelopment of SiC Reinforced Titanium Corrugated Structures / $cWH Kao, DJ Chang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 2 (June 1988)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSilicon carbide (SiC) reinforced Ti-6Al-4V (SiC/Ti-6Al-4V) composite was used to fabricate unidirectional corrugated structural panels. Corrugated structural panels are more efficient than honeycomb sandwich panels under normal (aerodynamic) compressive loading at high load levels that permit relatively thin skins to carry high skin stresses. Elevated temperature compression tests were conducted on the corrugated panels. The results indicated that the load carrying capacity of the SiC/Ti-6Al-4V composite panel was substantially higher than that of the baseline Ti-6Al-4V structure, especially at temperatures above 538°C (1000°F), where titanium alloy properties rapidly degrade. A finite-element stress analysis was also performed to estimate the thermal stress and the mechanical stress at assumed service conditions with three different face sheet thicknesses. The results of the study indicate that the corrugated panel, consisting of SiC/Ti-6Al-4V face sheets and core, can be used for space applications where elevated temperature compressive loads caused by bending moments are critical, such as for the body structure of a reentry vehicle.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aCorrugation.
=650  \0$aStress analysis.
=650  \0$aTitanium.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aSiC.
=653  20$aTitanium.
=653  20$aCorrugation.
=653  20$aStress analysis.
=700  1\$aChang, DJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10129J.htm

=LDR  03604nam  2200649 i 4500
=001  CTR10130J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19889999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10130J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10130J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aChang, C-C, $eauthor.
=245  10$aContinuous Strain Finite-Element Analysis of Free-Edge Effect in Laminated Composite Specimens / $cC-C Chang, RS Sandhu, RL Sierakowski, WE Wolfe.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 2 (June 1988)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA continuous strain finite-element model based on complete cubic polynomial expressions for the displacement field within each element and minimization of potential energy of the system is used to analyze the free-edge stress problem in laminated composites under uniform extension. Validity of the proposed numerical scheme is examined by solving for the stresses in a four-ply laminate and comparing the results obtained with those from Pagano's approximate theory, which is based upon application of Reissner's variational theory satisfying equilibrium of stresses within each lamina and ensuring continuity of displacements as well as tractions. Results from the two approaches agree closely. The finite-element procedure is then applied to a multi-layer laminated specimen to obtain reliable deformation and stress distributions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite laminates.
=650  \0$aContinuous strain model.
=650  \0$aFinite-element analysis.
=650  \0$aFree-edge effects.
=650  \0$aFinite element method.
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aComposite laminates.
=653  20$aContinuous strain model.
=653  20$aFinite-element analysis.
=653  20$aFree-edge effects.
=700  1\$aSandhu, RS., $eauthor.
=700  1\$aSierakowski, RL., $eauthor.
=700  1\$aWolfe, WE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10130J.htm

=LDR  03632nam  2200733 i 4500
=001  CTR10131J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19889999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10131J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10131J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKassapoglou, C., $eauthor.
=245  10$aCompressive Strength of Composite Sandwich Panels After Impact Damage : $bAn Experimental and Analytical Study / $cC Kassapoglou, PJ Jonas, R Abbott.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 2 (June 1988)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effect of low speed impact on the compressive strength of graphite/epoxy sandwich panels was examined experimentally and analytically. Various impactor sizes and impact energy levels were used. Impact damage was found to decrease the compressive strength of panels in this investigation by up to 33%. The use of film adhesive as an interply layer was found to reduce the extent of damage and increase the residual compressive strength. A one-parameter model to predict compressive failure of impact damaged panels is presented. The theoretical predictions are in good agreement with experimental results. Some of the factors affecting the panel behavior are also discussed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aComposite materials.
=650  \0$aDelamination growth.
=650  \0$aImpact damage.
=650  \0$aImpact.
=650  \0$aResidual strength.
=650  \0$aSandwich panels.
=650  \0$aThreshold of detectability.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aImpact.
=653  20$aImpact damage.
=653  20$aDelamination growth.
=653  20$aResidual strength.
=653  20$aThreshold of detectability.
=653  20$aBuckling.
=653  20$aSandwich panels.
=653  20$aComposite materials.
=700  1\$aJonas, PJ., $eauthor.
=700  1\$aAbbott, R., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10131J.htm

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=001  CTR10132J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19889999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10132J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10132J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA405
=082  04$a620.1/12$223
=100  1\$aRotem, A., $eauthor.
=245  14$aThe Strength of Laminated Composite Materials Under Repeated Impact Loading / $cA Rotem.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 2 (June 1988)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWhen low velocity and energy impact is exerted on a laminated composite material, in a perpendicular direction to the plane of the laminate, invisible damage may develop. It is shown analytically and experimentally that the invisible damage occurs during the first stage of contact between the impactor and the laminate and is a result of the contact stresses. However, the residual flexural strength changes only slightly, because it depends mainly on the outer layers, and these remain undamaged. Repeated impact intensifies the damage inside the laminate and causes larger bending under equivalent impact load. Finally, when the damage is most severe, even though it is still invisible, the laminate fails because of bending on the tension side. If the repeated impact is halted before final fracture occurs the residual strength and modulus would decrease by a certain amount.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite impact.
=650  \0$aComposite strength.
=650  \0$aRepeated impact.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite strength.
=653  20$aComposite impact.
=653  20$aRepeated impact.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10132J.htm

=LDR  03131nam  2200721 i 4500
=001  CTR10135J
=003  IN-ChSCO
=005  20161219163000.0
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=008  161219c19889999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10135J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10135J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aChamis, CC., $eauthor.
=245  10$aFiber Composite Sandwich Thermostructural Behavior : $bComputational Simulation / $cCC Chamis, RA Aiello, PLN Murthy.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 3 (September 1988)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSeveral computational levels of progressive sophistication/simplification are described to computationally simulate composite sandwich hygral, thermal, and structural behavior.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aApproximate equations.
=650  \0$aComposite mechanics.
=650  \0$aEquivalent properties.
=650  \0$aHoneycomb core.
=650  \0$aLaminate theory.
=650  \0$aSandwich properties.
=650  \0$aThree-dimensional element.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aThree-dimensional element.
=653  20$aHoneycomb core.
=653  20$aEquivalent properties.
=653  20$aApproximate equations.
=653  20$aComposite mechanics.
=653  20$aLaminate theory.
=653  20$aSandwich properties.
=700  1\$aAiello, RA., $eauthor.
=700  1\$aMurthy, PLN, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10135J.htm

=LDR  03266nam  2200721 i 4500
=001  CTR10136J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19889999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10136J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10136J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aLifshitz, JM., $eauthor.
=245  10$aCompressive Fatigue and Static Properties of a Unidirectional Graphite/Epoxy Composite / $cJM Lifshitz.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 3 (September 1988)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aStatic and fatigue properties of a unidirectional graphite/epoxy composite were determined experimentally under compressive loading. A programable data acquisition system was used to record axial and bending strains and load. When the moduli are calculated from the average axial values, they are shown to be insensitive to the magnitude of bending. When under compressive load, a (±45)s, angle-ply specimen is shown to be suitable for obtaining axial shear properties of a unidirectional lamina.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression.
=650  \0$aFatigue.
=650  \0$aGraphite/epoxy.
=650  \0$aLongitudinal.
=650  \0$aShear.
=650  \0$aStrength.
=650  \0$aTransverse.
=650  \0$aUnidirectional lamina.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aCompression.
=653  20$aFatigue.
=653  20$aGraphite/epoxy.
=653  20$aStrength.
=653  20$aLongitudinal.
=653  20$aTransverse.
=653  20$aShear.
=653  20$aUnidirectional lamina.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10136J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10137J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10137J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aMarshall, RD., $eauthor.
=245  10$aBuckling of a Damaged Sublaminate in an Impacted Laminate / $cRD Marshall, PE Sandorff, KN Lauraitis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 3 (September 1988)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn impacted region of a composite laminated plate is characterized by elliptical ply delamination around a central region of smashed fibers. Delamination occurs through the thickness and increases in size towards the back surface. The loading case that will most easily cause failure of the plate is compressive loading in which case a delaminated section buckles. This gives rise to global buckling of the plate or extensive delamination and fatal loss of residual strength.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aCompressive loading.
=650  \0$aDelamination.
=650  \0$aImpacted laminate.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDelamination.
=653  20$aBuckling.
=653  20$aImpacted laminate.
=653  20$aCompressive loading.
=700  1\$aSandorff, PE., $eauthor.
=700  1\$aLauraitis, KN., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10137J.htm

=LDR  03142nam  2200589 i 4500
=001  CTR10138J
=003  IN-ChSCO
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10138J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10138J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aRosensaft, M., $eauthor.
=245  12$aA One Specimen Mode I Delamination Test for Composite Materials / $cM Rosensaft, G Marom.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 3 (September 1988)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new test specimen for measuring GIc of the delamination of composite materials has been developed and tested. The advantages of the new test specimen are that a single specimen is sufficient to obtain an accurate compliance calibration and that it eliminates the need of continuous viewing of the crack-tip propagation, required for the measurement of the crack lengths. Another utilization of the proposed test specimen is in working with materials with low modulus of elasticity, where the effective notch length under loading is different than the measured length.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompliance calibration.
=650  \0$aFabric-reinforced composites.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMode I delamination.
=653  20$aCompliance calibration.
=653  20$aFabric-reinforced composites.
=700  1\$aMarom, G., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10138J.htm

=LDR  04054nam  2200649 i 4500
=001  CTR10139J
=003  IN-ChSCO
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=007  cr\\\\\\\\\\\\
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10139J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10139J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC415
=082  04$a535.42$223
=100  1\$aGascoigne, HE., $eauthor.
=245  10$aStrain Measurement in Thick-Walled Composite Rocket Motor Case Coupons Using Moire Interferometry / $cHE Gascoigne, MG Abdallah, RJ Nuismer.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 3 (September 1988)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper describes an experimental program which used moire interferometry to measure deformations in the through-the-thickness meridional plane in coupons cut from the transition region near the aft section of thick-walled composite motor cases proposed for the space shuttle solid rocket booster. These coupons were loaded in compression to simulate bending introduced in the casing caused by prelaunch requirements. The design of the transition region incorporates axially graded reinforcement broadgood plies and helical ply drop-offs. The deformation in this region is highly nonuniform, especially near the innermost broadgood termination where the adjacent helical ply experiences localized shear and compression. An understanding of the state of strain in this region is required to understand eventual delamination failures observed in an associated strength test program. Strains are determined by moire interferometry and compared with results using photoelastic coatings and miniature strain gages. Nonlinear strain response was observed in the helical ply adjacent to the innermost broadgood termination at approximately 20% of the coupon failure load. Well defined cracks were also observed to form in the moire grating over the helical ply in the vicinity of the adjacent innermost broadgood termination at approximately 50% of the coupon failure load.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression.
=650  \0$aDeformations.
=650  \0$aMoire interferometry.
=650  \0$aSpace shuttle.
=650  \0$aStrain measurement.
=650  \0$aInterferometry.
=653  10$aStrain measurement.
=653  20$aSpace shuttle.
=653  20$aMoire interferometry.
=653  20$aDeformations.
=653  20$aCompression.
=700  1\$aAbdallah, MG., $eauthor.
=700  1\$aNuismer, RJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10139J.htm

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=001  CTR10140J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10140J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10140J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRay, H., $eauthor.
=245  10$aComposites in Shock and Vibration Isolation / $cH Ray.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 3 (September 1988)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe investigation is concerned with the control of force transmitted to the support caused by central normal impact of a projectile on a plate supported by composite isolators with constrained rattle space. Normally isotropic isolators with appropriate low stiffness will absorb appreciable amount of impact energy. But this requires some space (rattle space) for deflection when the plate is subjected to projectile impact. In certain applications (such as plates used as armor in combat aircraft) there is not enough space for the plate to move normal to the plane of the plate. In the present analysis, by using composite isolators the plate is allowed to rotate in the plane of the plate so that less space (rattle space) is required normal to the plane of the plate. By allowing the plate to rotate in its plane, the impact energy is absorbed in the rotational direction in addition to the usual normal to the plane of the plate; thereby transmitting less force to the support compared to the case with isotropic isolators. A method of controlling the force transmitted to the support is to control the natural frequency of the system. In the present analysis the influence of fiber orientation and material properties on the natural frequency of the plate and composite support system is shown.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aIsolators.
=650  \0$aShock.
=650  \0$aVibration.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aShock.
=653  20$aVibration.
=653  20$aIsolators.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10140J.htm

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=001  CTR10143J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10143J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10143J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aChamis, CC., $eauthor.
=245  10$aMechanics of Composite Materials : $bPast, Present, and Future / $cCC Chamis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 1 (March 1989)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aComposite mechanics disciplines are presented and described at their various levels of sophistication and attendant scales of application. Correlation with experimental data is used as the prime discriminator between alternative methods and level of sophistication. Major emphasis is placed on (1) where composite mechanics has been; (2) what it has accomplished; (3) where it is headed, based on present research activities; and (4) at the risk of being presumptuous, where it should be headed. The discussion is developed using selected, but typical, examples of each composite mechanics discipline identifying degree of success, with respect to correlation with experimental data, and problems remaining. The discussion is centered about fiber/resin composites drawn mainly from the author's research activities and experience spanning two decades at National Aeronautics and Space Administration (NASA) Lewis Research Center.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCombined-stress failure.
=650  \0$aDamage tolerance.
=650  \0$aEnvironmental effects.
=650  \0$aFiber composites.
=650  \0$aFracture toughness.
=650  \0$aInterply hybrids.
=650  \0$aIntraply hybrids.
=650  \0$aLaminate theory.
=650  \0$aLife/durability.
=650  \0$aMacromechanics.
=650  \0$aMicromechanics.
=650  \0$aProgressive fracture.
=650  \0$aResin matrices.
=650  \0$aSingularity mechanics.
=650  \0$aStructural analysis.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFiber composites.
=653  20$aResin matrices.
=653  20$aInterply hybrids.
=653  20$aIntraply hybrids.
=653  20$aMicromechanics.
=653  20$aMacromechanics.
=653  20$aCombined-stress failure.
=653  20$aLaminate theory.
=653  20$aSingularity mechanics.
=653  20$aLife/durability.
=653  20$aFracture toughness.
=653  20$aDamage tolerance.
=653  20$aProgressive fracture.
=653  20$aStructural analysis.
=653  20$aEnvironmental effects.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10143J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10144J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10144J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aMurthy, PLN, $eauthor.
=245  10$aFree-Edge Delamination : $bLaminate Width and Loading Conditions Effects / $cPLN Murthy, CC Chamis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 1 (March 1989)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe width and loading conditions effects on free-edge stress fields in composite laminates are investigated by using a three-dimensional finite element analysis. The analysis includes a special free-edge region refinement or superelement with progressive substructuring (mesh refinement) and finite thickness interply layers. The different loading conditions include in-plane and out-of-plane bending, combined axial tension and in-plane shear, twisting, uniform temperature, and uniform moisture. Results obtained indicate that axial tension causes the smallest magnitude of interlaminar free edge stress compared to other loading conditions; laminates with practical dimensions may not delaminate because of free edge stresses alone since the magnitude of these stresses are found to be quite insignificant.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$a3-D stress fields.
=650  \0$aAxial tension.
=650  \0$aCombined tension/shear.
=650  \0$aFiber composites.
=650  \0$aIn-plane shear.
=650  \0$aInterply layers.
=650  \0$aOut-of-plane bending.
=650  \0$aOut-of-plane shear.
=650  \0$aProgressive substructuring.
=650  \0$aSuperelements.
=650  \0$aTwisting.
=650  \0$aUniform moisture.
=650  \0$aUniform temperature.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$a3-D finite elements.
=653  20$aSuperelements.
=653  20$aProgressive substructuring.
=653  20$aFiber composites.
=653  20$aInterply layers.
=653  20$a3-D stress fields.
=653  20$aAxial tension.
=653  20$aIn-plane shear.
=653  20$aOut-of-plane shear.
=653  20$aOut-of-plane bending.
=653  20$aTwisting.
=653  20$aCombined tension/shear.
=653  20$aUniform temperature.
=653  20$aUniform moisture.
=700  1\$aChamis, CC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10144J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10145J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10145J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.P55
=082  04$a668.4$223
=100  1\$aPenn, LS., $eauthor.
=245  10$aInterpretation of Experimental Results in the Single Pull-out Filament Test / $cLS Penn, SM Lee.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 1 (March 1989)
=504  \\$aIncludes bibliographical references$b35.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe single filament pull-out test is used to directly examine fiber-matrix interface bond strength. The experimental results exhibit a dual behavior in pull-out load as a function of initial embedded length. With increasing embedded length the pull-out load rises, then appears to reach an asymptote. This behavior can be explained by a fracture mechanics argument. In addition, the large experimental scatter is proposed to be inherent in the small test specimen and to be caused by imhomogeneity in surface energy of the smooth fibers tested.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber-matrix interface.
=650  \0$aInherent scatter.
=650  \0$aInterface crack propagation.
=650  \0$aSingle-filament pull-out tests.
=650  \0$aFilament winding.
=650  \0$aGlass-reinforced plastics.
=650  \0$aReinforced plastics.
=653  10$aFiber-matrix interface.
=653  20$aSingle-filament pull-out tests.
=653  20$aInherent scatter.
=653  20$aInterface crack propagation.
=700  1\$aLee, SM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10145J.htm

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=024  7\$a10.1520/CTR10146J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10146J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aJohnson, WS., $eauthor.
=245  10$aScreening of Metal Matrix Composites Using Ultrasonic C-Scans / $cWS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 1 (March 1989)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper will show how ultrasonic C-scans can be used to find some types of defects in continuous fiber reinforced metal matrix composites such as boron/aluminum composites. These defects will then be related to the fatigue behavior and fracture location of each inspected specimen. The C-scan technique was used to determine the relative amount of defects in boron/aluminum composites. The defects were primarily identified as gaps in the fiber spacing. Those specimens with higher defect densities had shorter fatigue lives, lower fatigue endurance limits, and greater reductions in the elastic unloading modulus (that is, stiffness) because of fatigue cycling. This type of data could be used to set accept/reject levels for a composite panel based on C-scan indications.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAluminum matrix.
=650  \0$aBoron fibers.
=650  \0$aDefects.
=650  \0$aFatigue.
=650  \0$aMetal matrix composites.
=650  \0$aNondestructive inspection.
=650  \0$aStiffness.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aMetal matrix composites.
=653  20$aNondestructive inspection.
=653  20$aFatigue.
=653  20$aDefects.
=653  20$aBoron fibers.
=653  20$aAluminum matrix.
=653  20$aStiffness.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10146J.htm

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=024  7\$a10.1520/CTR10147J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10147J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a624.1/7$223
=100  1\$aBatdorf, SB., $eauthor.
=245  10$aNote on Composite Size Effect / $cSB Batdorf.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 1 (March 1989)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe purpose of this note is to propose a relation somewhat similar to the size-strength relationship of brittle materials failing in tension in accordance with the Weibull theory. According to the failure theory of composites, a plot of the natural log of failure stress (ln σf) versus the natural log of volume (ln V) for a uniaxially reinforced composite is a curve that is concave upward. A simple analytical relation representing this concave failure curve could be very useful, since current methods of constructing the line are quite complex and necessitate the adoption of debatable assumptions about the magnitudes of a number of the many parameters that appear in the theory. The relation proposed in this note gives the theoretical failure stress of uniaxial composites to a surprising degree of accuracy.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFailure stress.
=650  \0$aSize-strength relationship.
=650  \0$aUniaxial composites.
=650  \0$aStrains and stresses.
=650  \0$aStructural dynamics.
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aSize-strength relationship.
=653  20$aFailure stress.
=653  20$aUniaxial composites.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10147J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10150J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10150J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aBerg, JS., $eauthor.
=245  13$aAn Evaluation of Composite Material Compression Test Methods / $cJS Berg, DF Adams.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 2 (June 1989)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDiscrepancies concerning the compressive strength of composite materials exist mainly because of the test method used. An experimental evaluation of three compressive test fixtures, namely, the Illinois Institute of Technology Research Institute (IITRI), modified Celanese, and end-loaded side-supported, selected based on a literature search, was performed. Mechanical testing of glass/epoxy and carbon/epoxy composite materials indicated the IITRI test fixture, currently a ASTM Test Method for Compressive Properties of Unidirectional or Crossply Fiber-Resin Composites, (D 3410) to be a very satisfactory method of composite material compressive properties characterization.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aCompression testing.
=650  \0$aLaminates.
=650  \0$aQuasi-isotropic.
=650  \0$aTest methods.
=650  \0$aUnidirectional composites.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aCompression testing.
=653  20$aTest methods.
=653  20$aLaminates.
=653  20$aUnidirectional composites.
=653  20$aQuasi-isotropic.
=700  1\$aAdams, DF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10150J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10151J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10151J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aKim, K-S, $eauthor.
=245  14$aThe Effect of Cooling Rate on Residual Stress in a Thermoplastic Composite / $cK-S Kim, HT Hahn, RB Croman.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 2 (June 1989)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effect of cooling rate on residual stress development in a graphite/thermoplastic matrix composite was studied by monitoring warping of an unsymmetric cross-ply laminate. Being amorphous, the thermoplastic resin showed only a minimal sensitivity to the cooling rates employed. The residual stresses at room temperature were high enough to cause ply cracking. Therefore, the effect of transverse crack on the curvature was evaluated by using a modified stiffness model based on the classical laminate theory.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCooling rate effects.
=650  \0$aPly cracking.
=650  \0$aResidual stresses.
=650  \0$aThermoplastic matrix composites.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aThermoplastic matrix composites.
=653  20$aCooling rate effects.
=653  20$aPly cracking.
=653  20$aResidual stresses.
=700  1\$aHahn, HT., $eauthor.
=700  1\$aCroman, RB., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10151J.htm

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=024  7\$a10.1520/CTR10152J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10152J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aHarris, CE., $eauthor.
=245  10$aPredictions of Poisson's Ratio in Cross-Ply Laminates Containing Matrix Cracks and Delaminations / $cCE Harris, DH Allen, EW Nottorf.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 2 (June 1989)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA damage-dependent constitutive model for laminated composites has been developed for the combined damage modes of matrix cracks and delaminations. The model is based on the concept of continuum damage mechanics and uses second-order tensor valued internal state variables to represent each mode of damage. The internal state variables are defined as the local volume average of the relative crack face displacements. Since the local volume for delaminations is specified at the laminate level, the constitutive model takes the form of laminate analysis equations modified by the internal state variables. Model implementation is demonstrated for Ex and vxy of quasi-isotropic and cross-ply laminates. The model predictions are in close agreement to experimental results obtained for graphite/epoxy laminates.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aContinuum damage mechanics.
=650  \0$aDelaminations.
=650  \0$aGraphite/epoxy.
=650  \0$aMatrix cracks.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aContinuum damage mechanics.
=653  20$aMatrix cracks.
=653  20$aDelaminations.
=653  20$aGraphite/epoxy.
=700  1\$aAllen, DH., $eauthor.
=700  1\$aNottorf, EW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10152J.htm

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=024  7\$a10.1520/CTR10153J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10153J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aRotem, A., $eauthor.
=245  10$aStiffness Change of a Graphite Epoxy Laminate Under Reverse Fatigue Loading / $cA Rotem.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 2 (June 1989)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe stiffness of a flat specimen, made of graphite epoxy (T300/934), was measured during reverse fatigue loading. Laminates of basic layup, unidirectional cross-ply and angle-ply, as well as multidirectional (isotropic) layup, were tested. It was found that all the laminates exhibit rapid stiffness degradation on the last (third) fatigue stage. Except for the [0°] unidirectional laminate, the last stage starts at about 70 to 80% of the fatigue life, regardless of the load level and the final mode of failure (tension or compression). It is shown that for this material, stiffness degradation is a result of crack accumulation, mainly along the fibers, even for the fiber dominated laminates. This general phenomenon can serve to predict usable safe life of laminates under fatigue loading.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite fatigue.
=650  \0$aGraphite epoxy.
=650  \0$aStiffness of laminates.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=653  10$aComposite fatigue.
=653  20$aStiffness of laminates.
=653  20$aGraphite epoxy.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10153J.htm

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=024  7\$a10.1520/CTR10156J$2doi
=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aVizzini, AJ., $eauthor.
=245  13$aAn Elastic Foundation Model to Predict the Growth of Delaminations / $cAJ Vizzini, PA Lagace.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 3 (September 1989)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA study was conducted to determine the growth characteristics of through-the-width delaminations in laminates under uniaxial compression. Twenty-five sandwich columns were manufactured and tested in uniaxial compression. Teflon® inserts were used to cause through-the-width delaminations in one of the two facesheets of each specimen. The buckling and subsequent growth of the delaminations were monitored via strain gage data and edge replications. A delamination growth criterion based on a strength of materials approach is proposed. This allows the incorporation of the behavior of the interply matrix region modeled as an elastic foundation. There is a good correlation between the point at which delamination growth was observed and that predicted by the growth model using a simple linear buckling solution.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aCompression.
=650  \0$aDelaminations.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aDelaminations.
=653  20$aCompression.
=700  1\$aLagace, PA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10156J.htm

=LDR  03367nam  2200637 i 4500
=001  CTR10157J
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=024  7\$a10.1520/CTR10157J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10157J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aTracy, JJ., $eauthor.
=245  14$aThe Effect of Delamination on the Fundamental and Higher Order Buckling Loads of Laminated Beams / $cJJ Tracy, GC Pardoen.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 3 (September 1989)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper presents the results of a study on the effect of prescribed delamination on the fundamental and higher order buckling loads of laminated beam specimens. A simple one-dimensional model was used to determine the first four buckling loads of both homogeneous and laminated beams as a function of delamination position and length. The model results were validated with detailed finite-element analyses and with experimental data. The buckling loads of specimens with prescribed delaminations of various lengths were determined by measurement of load versus lateral deflection for Modes 1 and 2, and indirectly for Modes 1 through 4 by extrapolation of the beam natural frequencies taken under various levels of axial loading below the first mode buckling load.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aDelamination.
=650  \0$aGraphite-epoxy.
=650  \0$aModal analysis.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=653  10$aDelamination.
=653  20$aBuckling.
=653  20$aGraphite-epoxy.
=653  20$aModal analysis.
=700  1\$aPardoen, GC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10157J.htm

=LDR  03674nam  2200637 i 4500
=001  CTR10158J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10158J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10158J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aWhitcomb, JD., $eauthor.
=245  10$aPredicted and Observed Effects of Stacking Sequence and Delamination Size on Instability Related Delamination Growth / $cJD Whitcomb.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 3 (September 1989)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aCompressive loads can cause local buckling in composite laminates that have a near-surface delamination. This local buckling causes load redistribution, which in turn causes interlaminar stresses and delamination growth. In this study, a three-dimensional, geometrically nonlinear finite-element analysis (NONLIN3D) was used to calculate strain-energy release rate distributions for several laminates that exhibited this instability related delamination growth. Two stacking sequences ([0/90/90/0]6 and [90/0/0/90]6) were considered. The specimens were fabricated with a double layer of 0.013-mm Kapton film located between the fourth and fifth plies, thereby simulating a delamination. Initial delamination sizes were 30, 40, or 60 mm in diameter. The static strain corresponding to delamination growth was determined experimentally. Comparison of the analytical and experimental results indicated that delamination growth was governed by the magnitude of GI.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aCompressive loads.
=650  \0$aDelamination growth.
=650  \0$aDelamination.
=650  \0$aStrain-energy release rate.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDelamination.
=653  20$aDelamination growth.
=653  20$aCompressive loads.
=653  20$aBuckling.
=653  20$aStrain-energy release rate.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10158J.htm

=LDR  03901nam  2200709 i 4500
=001  CTR10159J
=003  IN-ChSCO
=005  20161219163000.0
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10159J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10159J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aLifshitz, JM., $eauthor.
=245  10$aDeformational Behavior of a Unidirectional Graphite/Epoxy Composite Under Compressive Fatigue / $cJM Lifshitz.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 3 (September 1989)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDeformations of a unidirectional lamina, loaded in compressive-compressive fatigue in the fiber direction, perpendicular to the fibers, and in shear, were recorded continuously during fatigue tests. The deformations were separated into cyclic (AC) and creep (DC) components, and these values were used to define AC and DC moduli for each of the three modes of loading. The phase between stress and strain was monitored as well. The response to loading in the fiber direction was elastic, with negligible nonlinearity. Perpendicular to the fiber direction, the specimens crept slightly during the initial phase of the loading, and this was accompanied by a minor increase in dynamic stiffness. The shear loading caused large creep deformation, similar to creep observed in metals, and large change in phase, but the change in dynamic stiffness was minor. The results of creep are needed for modelling load transfer between layers in laminated composites, and the measurements of dynamic modulus have a potential for being a nondestructive test method for detecting fatigue life limit.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aCompressive fatigue.
=650  \0$aContinuous data recording.
=650  \0$aCreep.
=650  \0$aDeformation.
=650  \0$aDynamic modulus.
=650  \0$aGraphite/epoxy.
=650  \0$aShear deformations.
=650  \0$aEpoxy.
=650  \0$aPlasma treatment.
=653  10$aComposite materials.
=653  20$aGraphite/epoxy.
=653  20$aCompressive fatigue.
=653  20$aDeformation.
=653  20$aCreep.
=653  20$aDynamic modulus.
=653  20$aShear deformations.
=653  20$aContinuous data recording.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10159J.htm

=LDR  03438nam  2200697 i 4500
=001  CTR10160J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19899999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10160J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10160J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aLeka, LG., $eauthor.
=245  12$aA Close Look at the Embedment of Optical Fibers into Composite Structures / $cLG Leka, E Bayo.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 3 (September 1989)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA way in which to control vibrations at the tip of a flexible beam prompted this research. Polyimide coated multi-mode optical fibers were embedded between layers of the composite beam in order to measure strain as the beam is deformed. A close look at the embedment of the optical fibers between layers of preimpregnated unidirectional carbon fiber tape after cure is shown, and the results discussed. Mechanical tests were performed on composite specimens with embedded optical fibers and photographs of embedded optical fibers after the mechanical tests were performed are shown in detail.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAcrylate.
=650  \0$aDelamination.
=650  \0$aExtensometer.
=650  \0$aGraphite epoxy.
=650  \0$aOptical fiber.
=650  \0$aPolyimide.
=650  \0$aPreimpregnated unidirectional carbon fiber tape.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDelamination.
=653  20$aOptical fiber.
=653  20$aAcrylate.
=653  20$aPolyimide.
=653  20$aPreimpregnated unidirectional carbon fiber tape.
=653  20$aGraphite epoxy.
=653  20$aExtensometer.
=700  1\$aBayo, E., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10160J.htm

=LDR  03962nam  2200841 i 4500
=001  CTR10161J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19899999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10161J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10161J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTN750
=082  04$a671.256$223
=100  1\$aBhagat, RB., $eauthor.
=245  10$aDamping Behavior of Planar Random Carbon Fiber Reinforced 6061 Al Matrix Composites Fabricated by High-Pressure Infiltration Casting / $cRB Bhagat, MF Amateau, EC Smith.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 3 (September 1989)
=504  \\$aIncludes bibliographical references$b26.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper describes the damping behavior of carbon fiber reinforced aluminum matrix composites. The composites were fabricated by high-pressure infiltration casting technique using planar random carbon fiber mats as the reinforcement and 6061 Al as the matrix. The damping measurements were carried out on cantilever beam specimens vibrated at resonant frequencies in the first three modes of flexure vibration. The damping capacity of the matrix aluminum and the composites (0.10 ≤ Vf ≤ 0.36) are reported in terms of loss factor η up to a resonant frequency of 12 kHz.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAluminum.
=650  \0$aDamping behavior.
=650  \0$aDamping mechanisms.
=650  \0$aDamping peaks.
=650  \0$aFlexure vibration.
=650  \0$aHigh-pressure infiltration casting.
=650  \0$aInterface.
=650  \0$aLogarithmic decrement method.
=650  \0$aLoss factor.
=650  \0$aMetal matrix composites.
=650  \0$aPlanar random carbon fiber.
=650  \0$aResonant frequency.
=650  \0$aContinuous casting.
=650  \0$aSteel $xMetallurgy.
=650  \7$aTECHNOLOGY & ENGINEERING $xTechnical & Manufacturing Industries & Trades.
=653  10$aDamping behavior.
=653  20$aMetal matrix composites.
=653  20$aAluminum.
=653  20$aPlanar random carbon fiber.
=653  20$aHigh-pressure infiltration casting.
=653  20$aFlexure vibration.
=653  20$aLogarithmic decrement method.
=653  20$aResonant frequency.
=653  20$aLoss factor.
=653  20$aDamping peaks.
=653  20$aInterface.
=653  20$aDamping mechanisms.
=700  1\$aAmateau, MF., $eauthor.
=700  1\$aSmith, EC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10161J.htm

=LDR  04053nam  2200769 i 4500
=001  CTR10164J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19899999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10164J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10164J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA347.F5
=082  04$a620.00151825$223
=100  1\$aJohnson, MW., $eauthor.
=245  10$aAnalysis of the Localized Buckling in Composite Plate Structures with Application to Determining the Strength of Corrugated Fiberboard / $cMW Johnson, TJ Urbanik.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 4 (December 1989)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis study examines the theory for elastic buckling of composite structures composed of long rectangular flat plate elements. Elements can have nonlinear, orthotropic stress-strain properties characteristic of paper. Element stiffness coefficients add together to form a global structure stiffness matrix. Two methods of element counting and node labeling represent both determinant plate structures and periodic structures. Structure loading is in the axis direction of the plates. The solution gives the local buckling strain in the weakest structure element, which may differ from the weakest independent plate element. A nonlinear finite element method is developed with the finite elements being the plate elements of the structure. The small number of finite elements needed to characterize periodic structures makes the analysis efficient for searching out optimum designs. Corrugated fiberboard is one of the arbitrary structures appropriate for the analysis.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aComponent model.
=650  \0$aCorrugated fiberboard.
=650  \0$aEdgewise compression.
=650  \0$aElastic stability.
=650  \0$aMaterial failure.
=650  \0$aNonlinear finite elements.
=650  \0$aPaper.
=650  \0$aPlate structures.
=650  \0$aShort column.
=650  \0$aFinite element method.
=650  \7$aTECHNOLOGY & ENGINEERING $xEngineering (General.
=653  10$aPlate structures.
=653  20$aElastic stability.
=653  20$aBuckling.
=653  20$aCorrugated fiberboard.
=653  20$aPaper.
=653  20$aMaterial failure.
=653  20$aEdgewise compression.
=653  20$aComponent model.
=653  20$aShort column.
=653  20$aNonlinear finite elements.
=700  1\$aUrbanik, TJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10164J.htm

=LDR  03321nam  2200697 i 4500
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10165J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10165J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aYang, JN., $eauthor.
=245  12$aA Stiffness-Based Statistical Model for Predicting the Fatigue Life of Graphite/Epoxy Laminates / $cJN Yang, SH Yang, DL Jones.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 4 (December 1989)
=504  \\$aIncludes bibliographical references$b23.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA stiffness-based statistical model is proposed for predicting the fatigue life of composite laminates under constant-amplitude tensile cyclic loadings. The model parameters are determined using measured stiffness degradation data. Experiments have been performed on graphite/epoxy [90, +45, -45,0]s laminates to verify the analytical model. It is demonstrated that the correlation between the experimental results and the theoretical predictions for the fatigue life distribution is very reasonable.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aExperimental verification.
=650  \0$aFatigue life.
=650  \0$aGraphite/epoxy laminates.
=650  \0$aLife predictions.
=650  \0$aStatistical model.
=650  \0$aStiffness.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aStatistical model.
=653  20$aStiffness.
=653  20$aFatigue life.
=653  20$aGraphite/epoxy laminates.
=653  20$aLife predictions.
=653  20$aExperimental verification.
=700  1\$aYang, SH., $eauthor.
=700  1\$aJones, DL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10165J.htm

=LDR  03585nam  2200685 i 4500
=001  CTR10166J
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=024  7\$a10.1520/CTR10166J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10166J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aArmanios, EA., $eauthor.
=245  10$aSublaminate Analysis of Interlaminar Fracture in Composites : $bPart I-Analytical Model / $cEA Armanios, LW Rehfield.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 4 (December 1989)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA simple analysis method based upon a transverse shear deformation theory and a sublaminate approach is utilized to analyze a mixed-mode edge delamination specimen. The analysis provides closed form expressions for the interlaminar shear stresses ahead of the crack, the total strain energy release rate, and the strain energy release rate components. The parameters controlling the behavior are identified. The effect of specimen stacking sequence and delamination interface on the strain energy release rate components is investigated. Results are compared with a finite element simulation for reference. The simple nature of the method makes it suitable for preliminary design analyses which require a large number of configurations to be evaluated quickly and economically.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDelamination.
=650  \0$aFiber-reinforced composites.
=650  \0$aFracture mechanics.
=650  \0$aGraphite epoxy.
=650  \0$aInterlaminar stress.
=650  \0$aStrain energy release rate.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=653  10$aInterlaminar stress.
=653  20$aFiber-reinforced composites.
=653  20$aStrain energy release rate.
=653  20$aDelamination.
=653  20$aGraphite epoxy.
=653  20$aFracture mechanics.
=700  1\$aRehfield, LW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10166J.htm

=LDR  03380nam  2200685 i 4500
=001  CTR10167J
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=005  20161219163000.0
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10167J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10167J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA409
=082  04$a620.1/26$223
=100  1\$aArmanios, EA., $eauthor.
=245  10$aSublaminate Analysis of Interlaminar Fracture in Composites : $bPart II-Applications / $cEA Armanios, LW Rehfield, IS Raju, TK O'Brien.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 4 (December 1989)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA validation of the sublaminate analysis method developed earlier is provided in this work by comparison of the predictions with a quasi-three-dimensional finite element analysis. A comparison of the total strain energy release rate with a classical plate model is also provided. Closed-form expressions for the total strain energy rate and the strain energy release rate components are developed. The sublaminate analysis developed in this work is simple and the results are generated using a desktop computer.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDelamination.
=650  \0$aFiber-reinforced composites.
=650  \0$aFracture mechanics.
=650  \0$aGraphite epoxy.
=650  \0$aStrain energy release rate.
=650  \0$aFracture mechanics.
=650  \0$aFracture of materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFiber-reinforced composites.
=653  20$aStrain energy release rate.
=653  20$aDelamination.
=653  20$aGraphite epoxy.
=653  20$aFracture mechanics.
=700  1\$aRehfield, LW., $eauthor.
=700  1\$aRaju, IS., $eauthor.
=700  1\$aO'Brien, TK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10167J.htm

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=001  CTR10168J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19899999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10168J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10168J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aWhitcomb, JD., $eauthor.
=245  10$aComparison of Full 3-D, Thin-Film 3-D, and Thin-Film Plate Analyses of a Postbuckled Embedded Delamination / $cJD Whitcomb.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1989.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 11, Issue 4 (December 1989)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aLocal buckling can cause large interlaminar stresses along the delamination front, which can lead to delamination growth. This paper examines several methods of calculating strain-energy release rates, which are often used to predict delamination growth. The thin-film plate analysis, which was the least expensive analysis to use, calculated the total strain-energy release rate GT quite accurately. However, the stress field along the delamination front is highly mixed mode and has no fixed ratio of GI to GII. Since plate analysis can only calculate GT, plate analysis would not be useful for accurate predictions of delamination growth if mode mix is important.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1989. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDelamination.
=650  \0$aPostbuckling.
=650  \0$aStrain-energy release rates.
=650  \0$aStress analysis.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDelamination.
=653  20$aPostbuckling.
=653  20$aStrain-energy release rates.
=653  20$aStress analysis.
=653  20$aComposites.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10168J.htm

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=001  CTR10172J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10172J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10172J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSchoeppner, GA., $eauthor.
=245  12$aA Review of Compression Test Methods for Organic Matrix Composites / $cGA Schoeppner, RL Sierakowski.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 1 (March 1990)
=504  \\$aIncludes bibliographical references$b35.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aCompression test methods for evaluating the ultimate compression strength of composite materials have been reviewed for the purpose of guidance in the future development of a standardized test methodology. Test considerations, including approximate specimen and test fixture configurations and loading configurations, have been examined to assess the state of the art for compression tests.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aCompression tests.
=650  \0$aStandards.
=650  \0$aTest fixtures.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCompression tests.
=653  20$aComposite materials.
=653  20$aStandards.
=653  20$aTest fixtures.
=700  1\$aSierakowski, RL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10172J.htm

=LDR  04502nam  2200673 i 4500
=001  CTR10173J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10173J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10173J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aBhatt, RT., $eauthor.
=245  10$aLaminate Behavior for SiC Fiber-Reinforced Reaction-Bonded Silicon Nitride Matrix Composites / $cRT Bhatt, RE Phillips.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 1 (March 1990)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe room temperature mechanical properties of SiC fiber reinforced reaction-bonded silicon nitride matrix composite laminates (SiC/RBSN) have been measured. The laminates contained ∼30 vol% fraction of aligned 142-μm diameter SiC fiber in a porous RBSN matrix. Three types of laminates studied were unidirectional laminates ([0]8, [10]8, [45]8, and [90]8), cross piled laminates [02/902]s, and angle plied laminates [+452/−452]s. Each laminate contained eight fiber plies. Results for the unidirectionally reinforced composites tested at various angles to the reinforcement direction indicate large anisotropy in in-plane elastic moduli and strength. In addition, strength properties of these composites along the fiber direction were independent of specimen gage length and were unaffected by notches normal to the fiber direction. Matrix crack deflection along the fiber at the notch tip appears to be the dominant crack blunting mechanism responsible for notch insensitive behavior of these composites. Inplane properties of the composites can be improved by 2-D laminate construction. Mechanical property results for [02/902]s and [+452/−452]s laminates showed that their matrix failure strains were similar to that for [0]s laminates, but their primary elastic moduli, matrix cracking strengths, and ultimate composite strengths were lower. The elastic properties of unidirectional, cross-ply, and angle ply composites can be predicted from modified constitutive equations and laminate theory. Further improvements in laminate properties may be achieved by reducing the matrix porosity and by optimizing the bond strength between the SiC fiber and RBSN matrix.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aGage length effects.
=650  \0$aMechanical properties.
=650  \0$aNotch effects.
=650  \0$aReinforced ceramic matrix composites.
=650  \0$aSiC fibers.
=650  \0$aSilicon nitride matrix.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aReinforced ceramic matrix composites.
=653  20$aSiC fibers.
=653  20$aSilicon nitride (Si3N4) matrix.
=653  20$aMechanical properties.
=653  20$aGage length effects.
=653  20$aNotch effects.
=700  1\$aPhillips, RE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10173J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10174J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10174J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aEl-Zein, MS., $eauthor.
=245  14$aThe Strength Prediction of Composite Laminates Containing a Circular Hole / $cMS El-Zein, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 1 (March 1990)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe notched tensile strength of composite laminates was examined. The behavior and prediction of unidirectional off-axis, angle ply, and [0/ ± θ]s laminates is discussed. It was found that good predictions for off-axis laminates can be obtained since the same failure mode occurs in such laminates. Similar results were also obtained for the [0/ ± θ]s laminates. However, for angle-ply laminates, accurate predictions were not achieved because of the diversity of failure modes among the configurations tested. For fiber dominated laminates, a method for determining the characteristic dimension for the average stress criterion is presented. Moreover, the notched strength of quasi-isotropic composite laminates loaded at an angle φ to the material x axis was investigated. Good correlation between experimental and predicted values was obtained.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite laminates.
=650  \0$aCracks.
=650  \0$aStrength prediction.
=650  \0$aStress.
=650  \0$aTensile strength.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aStrength prediction.
=653  20$aTensile strength.
=653  20$aComposite laminates.
=653  20$aCracks.
=653  20$aStress.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10174J.htm

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=001  CTR10175J
=003  IN-ChSCO
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=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10175J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10175J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSaravanos, DA., $eauthor.
=245  10$aUnified Micromechanics of Damping for Unidirectional and Off-Axis Fiber Composites / $cDA Saravanos, CC Chamis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 1 (March 1990)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn integrated micromechanics methodology for the prediction of damping capacity in fiber-reinforced polymer matrix unidirectional composites has been developed. Explicit micromechanics equations based on hysteretic damping are presented relating the on-axis damping capacities to the fiber and matrix properties and fiber volume ratio. The damping capacities of unidirectional composites subjected to off-axis loading are synthesized from on-axis damping values. Predicted values correlate satisfactorily with experimental measurements. The hygro-thermal effect on the damping performance of unidirectional composites caused by temperature and moisture variations is also modeled. The damping contributions from interfacial friction between broken fibers and matrix are incorporated. Finally, the temperature rise in continuously vibrating composite plies is estimated. Application examples illustrate the significance of various parameters on the damping performance of unidirectional and off-axis fiber reinforced composites.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBroken fiber effects.
=650  \0$aComposites.
=650  \0$aDamping capacity.
=650  \0$aIn-plane damping.
=650  \0$aMoisture effects.
=650  \0$aOff-axis damping.
=650  \0$aOut-of-plane damping.
=650  \0$aTemperature effects.
=650  \0$aTemperature rise.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aIn-plane damping.
=653  20$aOut-of-plane damping.
=653  20$aDamping capacity.
=653  20$aTemperature effects.
=653  20$aMoisture effects.
=653  20$aOff-axis damping.
=653  20$aBroken fiber effects.
=653  20$aTemperature rise.
=700  1\$aChamis, CC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10175J.htm

=LDR  03493nam  2200637 i 4500
=001  CTR10176J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10176J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10176J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aSnyder, BD., $eauthor.
=245  10$aComposite Bolted Joints Analysis Programs / $cBD Snyder, JG Burns, VB Venkayya.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 1 (March 1990)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSeveral different composite bolted joint analysis programs are now available to composite structures designers. All of the programs vary widely in the amount of input required, output received, and required user knowledge of composite materials. Six different bolted joint analysis programs will be examined. The various programs are (1) A4EJ, (2) BJSFM, (3) SASCJ, (4) SAMCJ, (5) SCAN, and (6) JOINT. Other analysis programs exist, but they apply many constraints on the problem definition and depend heavily on empirical test results. The relative merits of each program as well as their disadvantages will be discussed. The most appropriate applications of each of the programs will be presented, and some numerical comparisons of the results will be made. Each of the programs has a useful place in the design and analysis arena. An examination of the programs will be made to help users determine which program will best suit their needs.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnalysis.
=650  \0$aBolted joints.
=650  \0$aComposites.
=650  \0$aDesign.
=650  \0$aBolts and nuts.
=650  \0$aJoints (Engineering)
=653  10$aComposites.
=653  20$aBolted joints.
=653  20$aAnalysis.
=653  20$aDesign.
=700  1\$aBurns, JG., $eauthor.
=700  1\$aVenkayya, VB., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10176J.htm

=LDR  03270nam  2200649 i 4500
=001  CTR10177J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10177J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10177J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSchuster, J., $eauthor.
=245  10$aCorrelations Between Ultrasonic Waveforms and Artificially Implanted Defects in Composite Materials / $cJ Schuster, KV Steiner.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 1 (March 1990)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper presents the results of ultrasonic testing, in particular pulse-echo scans and full waveform scans, performed on composite test specimens. Defects, such as backing paper, excess resin, Teflon®, sand, acetone, and Frekote® spray are implanted artificially in samples manufactured from carbon fiber prepregs. Cracks and delaminations are generated by impact and bending tests. The specimens are scanned in order to find correlations between these defects and their displayed images. Finally, the cut specimens are analyzed under the microscope.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aArtificial flaws.
=650  \0$aComposites.
=650  \0$aFull waveform inspection.
=650  \0$aNondestructive testing.
=650  \0$aUltrasonics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aNondestructive testing.
=653  20$aUltrasonics.
=653  20$aArtificial flaws.
=653  20$aFull waveform inspection.
=700  1\$aSteiner, KV., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10177J.htm

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=001  CTR10181J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10181J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10181J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aRP, Nimmer, $eauthor.
=245  10$aFiber-Matrix Interface Effects in the Presence of Thermally Induced Residual Stresses / $cNimmer RP.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 2 (June 1990)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAnalytical models are presented and used to explore the mechanics of transversely loaded, high-temperature composites with a thermally induced residual stress field and a vanishingly weak fiber-matrix interface strength. Of specific interest in this investigation is the existence of a distinctive, bilinear characteristic of the transverse stress-strain curve for composites of moderate fiber-volume fractions in which the coefficient of thermal expansion of the matrix is larger than the fiber and the interface strength is vanishingly weak. For such a system, it is found that the "knee" in the predicted transverse stress-strain curve separating the two linear response zones is associated with the load at which compressive residual stresses at the interface are overcome and separation of the matrix and fiber occurs. Before this "knee," the transverse modulus of the "weak interface" model is predicted to be the same as for a well-bonded system. The effects of fiber and matrix properties, interface friction, and fiber-volume content are examined.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFinite element.
=650  \0$aHigh-temperature composites.
=650  \0$aMicromechanics.
=650  \0$aResidual stresses.
=650  \0$aTransverse loads.
=650  \0$aWeak interface.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aResidual stresses.
=653  20$aHigh-temperature composites.
=653  20$aWeak interface.
=653  20$aTransverse loads.
=653  20$aMicromechanics.
=653  20$aFinite element.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10181J.htm

=LDR  03788nam  2200637 i 4500
=001  CTR10182J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10182J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10182J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aRotem, A., $eauthor.
=245  10$aResidual Strength of Composite Laminates Subjected to Tensile-Compressive Fatigue Loading / $cA Rotem, HG Nelson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 2 (June 1990)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe residual strengths of graphite epoxy (T300/934) laminates, in tension and in compression, were measured after exposure to tension-compression fatigue loading (R = −1). No direct correlation was found between remaining residual strengths and percentage of average fatigue life. However, a correlation scheme, based on a cumulative damage model and a stiffness change of the material, was developed for the individual specimen under test. This scheme predicts that strength will begin to degrade at about 60 to 80% of the fatigue life of the specimen, depending on the laminate structure. By monitoring stiffness change during fatigue, it was possible to predict the fatigue life of each individual specimen, and to terminate fatigue loading at some preset value of stiffness degradation before failure. It was found that only the strength of the final failure mode was degraded (that is, tension or compression), while the strength in the opposite direction did not change until almost the final failure. It was concluded that monitoring stiffness of a laminated structure will permit more effective use of the laminate and avoid premature failure.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFatigue of composite.
=650  \0$aResidual strength.
=650  \0$aStiffness.
=650  \0$aTensile-compressive fatigue.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aResidual strength.
=653  20$aFatigue of composite.
=653  20$aStiffness.
=653  20$aTensile-compressive fatigue.
=700  1\$aNelson, HG., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10182J.htm

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=001  CTR10183J
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=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10183J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10183J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aKardomateas, GA., $eauthor.
=245  10$aPostbuckling Characteristics in Delaminated Kevlar/Epoxy Laminates : $bAn Experimental Study / $cGA Kardomateas.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 2 (June 1990)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aCompression tests on delaminated kevlar/epoxy specimens were conducted in order to determine the buckling and post-buckling behavior of the system and observe the characteristics of the deformation including growth of the delamination. A broad range of geometric configurations, as far as the location of the delamination through the thickness, was considered. Both the initiation resistance, defined as the applied displacement per specimen length and the growth resistance, defined as the applied displacement per unit delamination growth during the postbuckling stage were quantified for each configuration. For the particular case studied, it was found that the growth resistance is infinite (that is, no growth) for delamination thickness/total thickness ratio H/T = 1/15, becoming 0.52 for H/T = 2/15 and dropping to a value of only 0.07 for H/T = 4/15. The initiation resistance is also lowered as the delamination is located further away from the specimen surface and for H/T = 4/15 growth initiation occurred before peak load. The experimental program investigates also the development of the deformation regarding the postbuckled shape, the load-displacement curve and the corresponding growth of the delamination. Furthermore, a comparison with analytical solutions for the postbuckling behavior at large applied displacements is performed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aComposites.
=650  \0$aCompression.
=650  \0$aDelamination.
=650  \0$aGrowth rate.
=650  \0$aPostbuckling.
=650  \0$aTests.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aDelamination.
=653  20$aBuckling.
=653  20$aPostbuckling.
=653  20$aTests.
=653  20$aGrowth rate.
=653  20$aCompression.
=653  20$aKevlar/epoxy.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10183J.htm

=LDR  03057nam  2200649 i 4500
=001  CTR10184J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10184J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10184J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aZhou, SG., $eauthor.
=245  10$aFailure Analysis of Composite Laminates with Free Edge / $cSG Zhou, CT Sun.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 2 (June 1990)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA failure theory which combines classical lamination theory with free-edge interlaminar stress was employed to predict the strength of laminates with free edges. Laminates studied were [±θ]2s angle-ply laminates, [±θ/90]s laminates, and fiber-dominated π/4 laminates. The present theory was capable of predicting failure loads for [±θ]2s and [±θ/90]s laminates as well as delamination on-set loads for π/4 laminates.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDelamination.
=650  \0$aFailure.
=650  \0$aFree edge.
=650  \0$aInterlaminar stress.
=650  \0$aLaminates.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aLaminates.
=653  20$aFailure.
=653  20$aDelamination.
=653  20$aFree edge.
=653  20$aInterlaminar stress.
=700  1\$aSun, CT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10184J.htm

=LDR  03475nam  2200685 i 4500
=001  CTR10185J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10185J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10185J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aDaniel, IM., $eauthor.
=245  10$aDamage Development in Composite Laminates Under Monotonic Loading / $cIM Daniel, J-W Lee.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 2 (June 1990)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDamage development under monotonic loading was studied in five cross-ply graphite/epoxy laminates. The laminates exhibited three characteristic ranges of varying stiffness. The first range is linear elastic and is characterized by the absence of any measurable damage. The second range is one of decreasing stiffness and corresponds to transverse matrix cracking in the 90° layer up to the characteristic damage state (CDS). The third range is a nearly linear one of stabilized or even slightly increasing stiffness. Ultimate failure was governed by the ultimate tensile strain in the 0° plies with small variations attributed to residual stresses, statistical scatter and local strain concentration.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCrossply laminates.
=650  \0$aDamage development.
=650  \0$aGraphite/epoxy.
=650  \0$aMatrix cracking.
=650  \0$aResidual stresses.
=650  \0$aX-radiography.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aGraphite/epoxy.
=653  20$aCrossply laminates.
=653  20$aMatrix cracking.
=653  20$aDamage development.
=653  20$aResidual stresses.
=653  20$aX-radiography.
=700  1\$aLee, J-W, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10185J.htm

=LDR  03219nam  2200637 i 4500
=001  CTR10189J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10189J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10189J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aDW, Wilson, $eauthor.
=245  10$aEvaluation of the V-Notched Beam Shear Test Through an Interlaboratory Study / $cWilson DW.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 3 (September 1990)
=504  \\$aIncludes bibliographical references$b27.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn recent years two notched beam flexure tests, the Iosipescu and the asymmetric four-point bending (AFPB) methods, have been proposed for the measurement of shear stress-strain behavior and shear strength of fiber reinforced composite materials. The methods have made significant inroads into the testing community for continuous, woven fabric and discontinuous fiber composites, and a test standard is being developed in ASTM Committee D-30. This paper describes the test methods and summarizes the results of a round-robin test program to define the within- and interlaboratory precision and bias.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aShear modulus.
=650  \0$aShear strength.
=650  \0$aShear tests.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aShear tests.
=653  20$aIosipescu.
=653  20$aAsymmetric-four-point bending.
=653  20$aShear strength.
=653  20$aShear modulus.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10189J.htm

=LDR  03618nam  2200685 i 4500
=001  CTR10190J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10190J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10190J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA409
=082  04$a620.1/26$223
=100  1\$aJablonski, DA., $eauthor.
=245  10$aHigh-Temperature Tensile Properties of Fiber Reinforced Reaction Bonded Silicon Nitride / $cDA Jablonski, RT Bhatt.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 3 (September 1990)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA testing technique has been developed for measuring the tensile properties of ceramic matrix composite laminates at temperatures up to 1500°C in air. Using this technique, the tensile properties of unidirectional silicon carbide (SiC) fiber reinforced reaction bonded silicon nitride (SiC/RBSN) composite specimens were measured at 25, 1300, and 1500°C. The composite consists of nearly 30 vol % of aligned 142 μm, chemically vapor deposited SiC fibers (Textron SCS-6). The specimens used were straight section flat specimens with bonded end tabs. A specially designed gripping system was used to minimize bending moment and assured that failure always occurred in the gage section. The specimen extension was measured using a high-temperature capacitive extensometer.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCeramic.
=650  \0$aComposites.
=650  \0$aFiber reinforcement.
=650  \0$aFracture mechanisms.
=650  \0$aReaction bonded silicon nitride.
=650  \0$aScanning electron microscopy.
=650  \0$aFracture.
=650  \0$aFracture of materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCeramic.
=653  20$aComposites.
=653  20$aFiber reinforcement.
=653  20$aFracture mechanisms.
=653  20$aReaction bonded silicon nitride.
=653  20$aScanning electron microscopy tension testing.
=700  1\$aBhatt, RT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10190J.htm

=LDR  03371nam  2200637 i 4500
=001  CTR10191J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10191J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10191J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aEl-Zein, MS., $eauthor.
=245  10$aOn the Prediction of Tensile Strength after Impact of Composite Laminates / $cMS El-Zein, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 3 (September 1990)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new approach to the prediction of tensile strength after impact is presented. The method is based on the premises that the stress concentration associated with the constraint of the undamaged material around the impacted region dominates the remaining strength calculation and that the physical parameter that enters the model should be the size and shape of the damage region. The damaged area resulting from impact was used to evaluate the reduction in the compliance properties of the inclusion. The predictions were made by using a closed-form solution for an infinite plate containing an elliptical inclusion and by invoking an average stress criterion applied at the ply level. The laminates studied were [0/±45/90]2s, [0/±450/0]2s, and [(0/90)4]s.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aImpact.
=650  \0$aLaminates.
=650  \0$aStress.
=650  \0$aTensile strength.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aTensile strength.
=653  20$aImpact.
=653  20$aLaminates.
=653  20$aStress.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10191J.htm

=LDR  03541nam  2200673 i 4500
=001  CTR10192J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10192J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10192J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aLittle, RE., $eauthor.
=245  10$aFatigue of Bolted Joints in SMC-R18 Sheet Molding Compound Composites / $cRE Little, PK Mallick.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 3 (September 1990)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aBolted joints in SMC-R18 sheet molding compound composites were studied with the goal of determining joint proportions that provide long fatigue lives. The joint parameters considered were the edge margin in terms of the (e/d) ratio (where e is the edge margin and d is the hole parameter), the lateral pitch in terms of the (w/d) ratio (where w is the specimen width) and the washer geometry. It was observed that (e/d) should be at least three, and the lateral pitch should be at least six to eight to assure a fatigue failure originating at the edge of the washer. Smaller margins lead to bearing failures almost immediately or to splitting failures at relatively short fatigue lives. It was also observed that washer geometry (larger diameter) can lead to significantly longer fatigue lives.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBolted joints.
=650  \0$aConventional automotive fasteners.
=650  \0$aFatigue.
=650  \0$aJoint proportions.
=650  \0$aSheet molding compound.
=650  \0$aTightening torque.
=650  \0$aBolts and nuts.
=650  \0$aJoints (Engineering)
=653  10$aBolted joints.
=653  20$aSheet molding compound.
=653  20$aConventional automotive fasteners.
=653  20$aFatigue.
=653  20$aJoint proportions.
=653  20$aTightening torque.
=700  1\$aMallick, PK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10192J.htm

=LDR  03526nam  2200673 i 4500
=001  CTR10193J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10193J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10193J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aPenn, LS., $eauthor.
=245  10$aIdentification of Factors Affecting Single Filament Pull-Out Test Results / $cLS Penn, C-T Chou.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 3 (September 1990)
=504  \\$aIncludes bibliographical references$b26.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this paper, computer generated plots of pull-out load Pm versus embedded length l are used to identify important factors influencing the experimental results obtained in the single filament pull-out test. The computer results suggest that random variation in the initial crack size is an important source of scatter in the experimental data. Furthermore, variation in fiber surface energy was computed to play a much smaller role than crack size variation in producing the observed data scatter. The results also suggest that the initial crack size corresponding to observed pull-out loads is surprisingly large. Finally, residual stress detrimental to the interfacial bond was identified as the factor causing an apparent displacement of the data points to the right, as observed experimentally.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesion.
=650  \0$aComposites.
=650  \0$aFracture energy.
=650  \0$aInterface.
=650  \0$aResidual stress.
=650  \0$aSingle filament pull-out tests.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aSingle filament pull-out tests.
=653  20$aInterface.
=653  20$aResidual stress.
=653  20$aAdhesion.
=653  20$aComposites.
=653  20$aFracture energy.
=700  1\$aChou, C-T, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10193J.htm

=LDR  03658nam  2200709 i 4500
=001  CTR10194J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10194J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10194J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aDaniel, IM., $eauthor.
=245  10$aDetermination of Chemical Cure Shrinkage in Composite Laminates / $cIM Daniel, T-M Wang, D Karalekas, JT Gotro.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 3 (September 1990)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aResidual stresses in composites (microscopic and macroscopic) result from shrinkage of the matrix during cure. It is usual to distinguish between the chemical and thermal components of shrinkage. The former depends on the polymerization reaction, whereas the latter is caused by the difference between the thermal expansion coefficients of the reinforcement and the matrix. A method was developed for determination of the chemical cure shrinkage. A prepreg layer is applied on an identical layer of the same material that has already been cured and postcured. The assembled laminate is then cured, and the resulting warpage is recorded by means of the shadow moiré method. The resulting warpage, consisting of elliptical equal deflection contours, is related to the chemical shrinkage.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aChemical shrinkage.
=650  \0$aComposite materials.
=650  \0$aMatrix shrinkage.
=650  \0$aPolymerization shrinkage.
=650  \0$aResidual stresses.
=650  \0$aWarpage.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aResidual stresses.
=653  20$aWarpage.
=653  20$aComposite materials.
=653  20$aMatrix shrinkage.
=653  20$aChemical shrinkage.
=653  20$aPolymerization shrinkage.
=653  20$aMoiré method.
=700  1\$aWang, T-M, $eauthor.
=700  1\$aKaralekas, D., $eauthor.
=700  1\$aGotro, JT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10194J.htm

=LDR  03487nam  2200637 i 4500
=001  CTR10195J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10195J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10195J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQD181.N6
=082  04$a546/.625$223
=100  1\$aWheeler, NS., $eauthor.
=245  10$aReview of the Nickel-Graphite Interface / $cNS Wheeler.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 3 (September 1990)
=504  \\$aIncludes bibliographical references$b31.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe degradation of the mechanical properties of graphite fibers in intimate contact with nickel at high temperatures is due to the interdiffusion of carbon and nickel. There are two mechanisms by which the damage occurs: diffusion of carbon into the nickel and recrystallization of the fibers. There has been much disagreement in the literature and seemingly conflicting data. These apparent conflicts in data have lead to two different schools of thought, each favoring one mechanism over the other. On careful analysis of the entire body of the literature, however, a unified picture emerges. Below a critical temperature Tg the fiber is weakened by diffusion into the nickel matrix. Above Tg, the fiber recrystallizes at an appreciable rate, catalyzed by the diffusion of nickel into the fiber. The value of Tg varies with the type of fiber, and it is significantly higher for high modulus fibers than for high tensile strength fibers.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDiffusion.
=650  \0$aGraphite fiber.
=650  \0$aInterface.
=650  \0$aMetal matrix composites.
=650  \0$aNickel.
=650  \0$aChemical elements.
=650  \0$aGeneral and inorganic chemistry.
=653  10$aNickel.
=653  20$aGraphite fiber.
=653  20$aInterface.
=653  20$aMetal matrix composites.
=653  20$aDiffusion.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10195J.htm

=LDR  03497nam  2200625 i 4500
=001  CTR10199J
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=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10199J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10199J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aRotem, A., $eauthor.
=245  10$aTensile and Compressive Failure Modes of Laminated Composites Loaded by Fatigue with Different Mean Stress / $cA Rotem.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 4 (December 1990)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aLaminated composite materials tend to fail differently under tensile or compressive load. Under tension, the material accumulates cracks and fiber fractures, while under compression, the material delaminates and buckles. Tensile-compressive fatigue may cause either of these failure modes depending on the specific damage occurring in the laminate. This damage depends on the stress ratio of the fatigue loading. Analysis of the fatigue behavior of the composite laminate under tension-tension, compression-compression, and tension-compression had led to the development of a fatigue envelope presentation of the failure behavior. This envelope indicates the specific failure mode for any stress ratio and number of loading cycles. The construction of the fatigue envelope is based on the applied stress-cycles to failure (S-N) curves of both tensile-tensile and compressive-compressive fatigue. Test results are presented to verify the theoretical analysis.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFailure modes.
=650  \0$aFatigue.
=650  \0$aLaminates.
=650  \0$aMean stress.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aFatigue.
=653  20$aLaminates.
=653  20$aFailure modes.
=653  20$aMean stress.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10199J.htm

=LDR  03803nam  2200709 i 4500
=001  CTR10200J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10200J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10200J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aThompson, DM., $eauthor.
=245  10$aCross-Ply Laminates with Holes in Compression : $bStraight Free-Edge Stresses Determined by Two- to Three-Dimensional Global/Local Finite Element Analysis / $cDM Thompson, O Hayden Griffin, MA Vidussoni.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 4 (December 1990)
=504  \\$aIncludes bibliographical references$b22.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA practical example of applying two- to three-dimensional (2- to 3-D) global/local finite element analysis to laminated composites is presented. Cross-ply graphite/epoxy laminates of 0.1-in. (0.254-cm) thickness with central circular holes ranging from 1 to 6 in. (2.54 to 15.2 cm) in diameter, subjected to in-plane compression were analyzed. Guidelines for full 3-D finite element analysis and 2- to 3-D global/local analysis of interlaminar stresses at straight free edges of laminated composites are included. The larger holes were found to reduce substantially the interlaminar stresses at the straight free-edge in proximity to the hole. Three-dimensional stress results were obtained for thin laminates which require prohibitive computer resources for full 3-D analyses of comparative accuracy.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression.
=650  \0$aFinite element analysis.
=650  \0$aGraphite/epoxy composites.
=650  \0$aHoles.
=650  \0$aInterlaminar stresses.
=650  \0$aLaminates.
=650  \0$aFinite element analysis.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aLaminates.
=653  20$aCompression.
=653  20$aGlobal/local finite element analysis.
=653  20$aGraphite/epoxy composites.
=653  20$aHoles.
=653  20$aFinite element analysis.
=653  20$aInterlaminar stresses.
=700  1\$aHayden Griffin, O., $eauthor.
=700  1\$aVidussoni, MA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10200J.htm

=LDR  03800nam  2200769 i 4500
=001  CTR10201J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10201J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10201J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.S7
=082  04$a668.4/233$223
=100  1\$aMaldas, D., $eauthor.
=245  10$aEffect of Fiber Treatment on the Mechanical Properties of Hybrid Fiber-Reinforced Polystyrene Composites : $bI. Use of Mica and Wood Pulp as Hybrid Filler / $cD Maldas, BV Kokta.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 4 (December 1990)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe feasibility of mixing hardwood aspen pulp [chemithermomechanical pulp (CTMP)] and surface-treated mica as the hybrid reinforcing filler for polystyrene composites has been investigated by evaluating the mechanical properties of the resulting composite materials. Compatibility of wood fiber and polystyrene, as well as mica, was improved by surface treatments of CTMP, for example, coating with polystyrene + isocyanate or with silane and grafting with polymer. Mechanical properties deteriorated when nontreated CTMP was used in addition to treated mica. However, properties improved when surface-treated CTMP was used as a hybrid filler. Experimental results indicate good compatibility between treated CTMP/mica and polystyrene composites.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCoupling agent.
=650  \0$aHybrid effect.
=650  \0$aHybrids.
=650  \0$aMechanical properties.
=650  \0$aMica.
=650  \0$aPolystyrene.
=650  \0$aSurface coating.
=650  \0$aThermoplastic composites.
=650  \0$aWood pulp.
=650  \0$aThermoplastics.
=650  \0$aPolymerized styrene.
=650  \0$aStyrenic polymers.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aThermoplastic composites.
=653  20$aPolystyrene.
=653  20$aWood pulp.
=653  20$aMica.
=653  20$aHybrids.
=653  20$aHybrid effect.
=653  20$aCoupling agent.
=653  20$aSurface coating.
=653  20$aMechanical properties.
=700  1\$aKokta, BV., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10201J.htm

=LDR  03708nam  2200685 i 4500
=001  CTR10203J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10203J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10203J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aES-M, Chim, $eauthor.
=245  10$aResidual Strength and Residual Fracture Toughness of Random Short-Fiber Composites during Cyclic Fatigue / $cChim ES-M, Wang SS.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 4 (December 1990)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe present study is part of a series of research work on microscopic damage evolution and associated macroscopic property degradation of random short-fiber composites under cyclic fatigue loading. In this paper, the effects of fatigue damage on the tensile failure strength and the opening mode fracture toughness of an SMC-R50 composite were investigated. Test specimens, which had been conditioned to various preselected fatigue damage stages, were measured for their residual properties. The results indicated that both the failure strength and fracture toughness were degraded during the cyclic fatigue loading. The reduction in strength was appreciable, but was less than that observed in the matrix-controlled elastic properties. The reduction of the residual fracture toughness, as a result of the local high-stress field, was affected even less appreciably.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCyclic fatigue.
=650  \0$aFatigue damage.
=650  \0$aRandom short-fiber composites.
=650  \0$aResidual fracture toughness.
=650  \0$aResidual tensile strength.
=650  \0$aSheet-molding compounds.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aCyclic fatigue.
=653  20$aResidual tensile strength.
=653  20$aResidual fracture toughness.
=653  20$aFatigue damage.
=653  20$aRandom short-fiber composites.
=653  20$aSheet-molding compounds.
=700  1\$aSS, Wang, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10203J.htm

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=001  CTR10204J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10204J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10204J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aJC, Lynn, $eauthor.
=245  10$aPolymer Composite Characterization for Automotive Structural Applications / $cLynn JC.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 4 (December 1990)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper addresses the need to create new test methods pertinent to automotive structural application and standardize the existing test methods. Ten cases in point are briefly discussed. A list of selected tests has been proposed covering static short-term properties as well as long-term durability properties.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCombined effect.
=650  \0$aCompressive.
=650  \0$aDynamic mechanical analysis (DMA).
=650  \0$aFatigue.
=650  \0$aFracture toughness.
=650  \0$aGlass transition temperature.
=650  \0$aInstrumented impact.
=650  \0$aMatrix.
=650  \0$aPolymer composites.
=650  \0$aReinforcement.
=650  \0$aShear.
=650  \0$aStandardization.
=650  \0$aTensile.
=650  \0$aTest methods.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aPolymer composites.
=653  20$aTest methods.
=653  20$aStandardization.
=653  20$aReinforcement.
=653  20$aMatrix.
=653  20$aGlass transition temperature.
=653  20$aDynamic mechanical analysis (DMA).
=653  20$aTensile.
=653  20$aCompressive.
=653  20$aShear.
=653  20$aFracture toughness.
=653  20$aInstrumented impact.
=653  20$aFatigue.
=653  20$aCombined effect.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10204J.htm

=LDR  03715nam  2200733 i 4500
=001  CTR10205J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10205J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10205J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aJ, Lu., $eauthor.
=245  10$aStudy on the Effect of the Surface Treatment on the Residual Stress Gradient in Silicon Carbide (SiC) Reinforced Aluminum Metal Matrix Composites / $cLu J, Miege B, Flavenot J-F, Thery S.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 4 (December 1990)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSilicon carbide (SiC) whiskers and particule-reinforced aluminum alloys show promise as metal matrix composites (MMC) stiff and in high-strength lightweight applications. When a MMC is cooled down to room temperature from the fabrication or annealing temperature, residual stresses are induced in the composite as a result of the mismatch of the thermal expansion coefficients between the metal matrix and fibers. The magnitude of the residual stresses has a very important effect on the yield stress and fatigue strength of the MMC. Many techniques are available for residual stress measurement on mechanical parts. X-ray diffraction, bending deflection, and hole drilling are three techniques that are commonly used.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aHole drilling method.
=650  \0$aMetal matrix composite.
=650  \0$aResidual stresses.
=650  \0$aShot peening.
=650  \0$aVolume fraction.
=650  \0$aX-ray method.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aResidual stresses.
=653  20$aMetal matrix composite.
=653  20$aX-ray method.
=653  20$aHole drilling method.
=653  20$a2124.
=653  20$a6061.
=653  20$aShot peening.
=653  20$aVolume fraction.
=700  1\$aB, Miege, $eauthor.
=700  1\$aJ-F, Flavenot, $eauthor.
=700  1\$aS, Thery, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10205J.htm

=LDR  03883nam  2200625 i 4500
=001  CTR10206J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19909999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10206J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10206J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.C9
=082  04$a624.1/7762$223
=100  1\$aF-K, Chang, $eauthor.
=245  10$aStudy on the Crushing Response of Cylindrical Composite Shells Subjected to Transverse Loading / $cChang F-K, Kutlu Z.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1990.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 12, Issue 4 (December 1990)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn investigation was performed to study the load-carrying capability of fiber-reinforced composite shells subjected to quasi-static transverse crushing loads. Both experimental and analytical work have been performed. Experiments on T300/934 and T300/976 graphite/epoxy materials were first conducted on composite cylinders subjected to crushing loads. An analytical model was also developed which was based on a progressive damage analysis. The model consists of a stress analysis and a failure analysis. Deformations, stresses, and strains in the composite cylinders were analyzed based on the large deformation theory. Damage accumulation and the residual stiffness and strength of the tubes were evaluated by a combination of appropriate failure criteria with property degradation models. Based on the model, a nonlinear finite element program, designated as "PDTUBE," was developed. The code is capable of assessing damage in the laminates and predicting residual stiffness and strength of composite cylinders subjected to transverse crushing loads. An excellent agreement was found between the computer simulations and the test results. A parametric study was also conducted to determine the effects of material properties, ply orientation, and geometries on the response of cylindrical composite shells.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1990. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite shells.
=650  \0$aCylinders.
=650  \0$aFailure.
=650  \0$aTransverse loading.
=650  \0$aMetals.
=650  \0$aStructural engineering.
=653  10$aComposite shells.
=653  20$aTransverse loading.
=653  20$aCylinders.
=653  20$aFailure.
=700  1\$aZ, Kutlu, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10206J.htm

=LDR  03641nam  2200637 i 4500
=001  CTR10210J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10210J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10210J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418
=082  04$a620.1/1232$223
=100  1\$aKaw, AK., $eauthor.
=245  14$aThe Semi-Infinite Strip Problem in the Mechanics of Composite Materials / $cAK Kaw, JG Goree.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 2 (June 1991)
=504  \\$aIncludes bibliographical references$b39.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aMany problems, ranging from interface-fiber fracture to determining the strength of fiber-matrix interfaces in composites, can be greatly assisted by a complete understanding of the boundary value problem of a semi-infinite strip. The specific boundary value problem of a semi-infinite strip with symmetric tractions on the transverse edges and normal loads on the end is investigated in the present study. The nature of the singular behavior in the slope of the end vertical displacement at the corner points is found. An asymptotic analysis of the solution shows that, depending on the nature of the applied stresses in the vicinity of the corner points, the singularity in the slope of the end vertical displacement may either be a power or logarithmic type, both, or not exist at all. Illustrative examples, for which exact or numerical results are known, are given. Numerical procedures are also given. The direct application of the results of the paper are illustrated for several problems in the mechanics of composite materials.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBimaterial interface.
=650  \0$aElasticity.
=650  \0$aSemi-infinite strip.
=650  \0$aSingularities.
=650  \0$aStrength of materials.
=650  \0$aEngineering.
=650  \7$aSCIENCE $xNanoscience.
=653  10$aElasticity.
=653  20$aBimaterial interface.
=653  20$aSemi-infinite strip.
=653  20$aSingularities.
=700  1\$aGoree, JG., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10210J.htm

=LDR  03810nam  2200673 i 4500
=001  CTR10211J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10211J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10211J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.84
=082  04$a620.1/127$223
=100  1\$aSandhu, RS., $eauthor.
=245  10$aEdge Delamination of (± θm/90n/2)s Laminates Subjected to Tensile Loading / $cRS Sandhu, GP Sendeckyj.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 2 (June 1991)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aInitiation of edge delamination of symmetric laminates consisting of angle and 90° plies was investigated. Five independent criteria were used to determine delamination initiation for a given set of m and n of angle and 90° plies. In Criteria 1 and 2, delamination moment rates (delamination moment coefficients or DMCs) relative to the applied average axial stress and strain in the laminates with intact 90° plies were maximized. The same approach was used in Criteria 3 and 4 except that the laminates had cracked 90° plies. Criterion 5 was based on establishing the maximum mismatch of Poisson's ratios of angle and 90° plies. The expressions derived on the basis of the criteria were numerically evaluated. The results of these studies indicated that the laminates designed on the basis of Criterion 5 had the minimum tendency to delaminate. In addition, it was found that an increase in thickness of laminates tended to increase the delamination tendency.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAcoustic emission.
=650  \0$aDelamination initiation criteria.
=650  \0$aDelamination moment coefficient.
=650  \0$aEdge delamination.
=650  \0$aGraphite-epoxy laminates.
=650  \0$aAcoustical engineering.
=650  \0$aEmission, Acoustic.
=650  \0$aAcoustic emission testing.
=653  10$aEdge delamination.
=653  20$aDelamination initiation criteria.
=653  20$aDelamination moment coefficient.
=653  20$aGraphite-epoxy laminates.
=653  20$aAcoustic emission.
=653  20$aPenetrant enhanced X-ray photography.
=700  1\$aSendeckyj, GP., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10211J.htm

=LDR  03641nam  2200757 i 4500
=001  CTR10212J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19919999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10212J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10212J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aChan, WS., $eauthor.
=245  10$aDesign Approaches for Edge Delamination Resistance in Laminated Composites / $cWS Chan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 2 (June 1991)
=504  \\$aIncludes bibliographical references$b25.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper reviews the material and structural approaches to increase resistance of delamination initiation and growth. In the material approach, it was found that currently available toughened thermosets and thermoplastic composites can significantly improve delamination resistance for static, but not fatigue, loading. In the structural approach, it was concluded that stitching and interleafing are effective ways to resist delamination as a result of impact. However, terminating and discretizing the critical ply, as well as selective interleafing, are the most effective ways to increase delamination resistance for both static and fatigue in-plane loadings.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite design.
=650  \0$aComposite structures.
=650  \0$aDamage tolerance.
=650  \0$aDelamination growth.
=650  \0$aDelamination resistance.
=650  \0$aDelamination.
=650  \0$aDurability.
=650  \0$aFatigue loads.
=650  \0$aInterleaving.
=650  \0$aStitching.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDelamination.
=653  20$aDelamination resistance.
=653  20$aComposite structures.
=653  20$aComposite design.
=653  20$aDelamination growth.
=653  20$aFatigue loads.
=653  20$aInterleaving.
=653  20$aStitching.
=653  20$aDamage tolerance.
=653  20$aDurability.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10212J.htm

=LDR  03649nam  2200661 i 4500
=001  CTR10213J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c19919999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10213J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10213J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aVarna, J., $eauthor.
=245  10$aMultiple Transverse Cracking and Stiffness Reduction in Cross-Ply Laminates / $cJ Varna, L Berglund.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 2 (June 1991)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe stiffness reduction as a result of multiple transverse cracking in cross-ply laminates and the crack density dependence on the applied tensile stress are analyzed by linear elastic fracture mechanics. The stress field distribution is obtained by the principle of minimum complementary energy. Two models are suggested which describe the non-uniform stress distribution in the thickness direction of the 0° layer. They contain the variational approach presented by Hashin as a particular case. Elastic ply properties and the Mode I critical strain energy release rate GIc for transverse cracking are the experimental data needed. Model predictions are compared with experimental data for glass fiber/epoxy, AS4/3502, and AS/3501-06 carbon fiber/epoxy cross-ply laminates. The predictions from the suggested models describe both the constraint effect and the crack saturation phenomenon.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aLaminates.
=650  \0$aLinear elastic fracture mechanics.
=650  \0$aStiffness reduction.
=650  \0$aStress distribution.
=650  \0$aTransverse cracking.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aLaminates.
=653  20$aLinear elastic fracture mechanics.
=653  20$aTransverse cracking.
=653  20$aStiffness reduction.
=653  20$aStress distribution.
=700  1\$aBerglund, L., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10213J.htm

=LDR  03696nam  2200685 i 4500
=001  CTR10214J
=003  IN-ChSCO
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=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19919999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10214J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10214J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNaik, NK., $eauthor.
=245  10$aFailure Behavior of Woven Fabric Composites / $cNK Naik, PS Shembekar, MV Hosur.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 2 (June 1991)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWoven fabrics are now considered important reinforcing materials for use as unidirectional (UD) tapes in composites technology. The understanding of the failure mechanisms in woven fabric composites, however, is not complete. The tensile behavior of onaxis and off-axis specimens of E-glass/epoxy and carbon/epoxy plain weave fabric composites with and without a hole is studied. The failure behavior of woven fabric composites differs from UD tape composites. Because of the interlaced nature of warp and weft fibers, their reorientation along the loading direction is possible in off-axis specimens. The reorientation of fibers may increase the notched strength over the unnotched strength. The failure modes in angle-ply laminates of UD tape are mostly matrix cracking, fiber pullout, delamination, and to some extent, fiber breakage, whereas in woven fabric composites, the ultimate failure is always due to fiber breakage which, in general, is a preferred failure mode.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aOff-axis.
=650  \0$aReorientation.
=650  \0$aTwisting.
=650  \0$aUnbalanced plain weave.
=650  \0$aWoven fabric.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aWoven fabric.
=653  20$aUnbalanced plain weave.
=653  20$aOff-axis.
=653  20$aReorientation.
=653  20$aTwisting.
=700  1\$aShembekar, PS., $eauthor.
=700  1\$aHosur, MV., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10214J.htm

=LDR  03405nam  2200673 i 4500
=001  CTR10219J
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=006  m\\\\\\\\\\\\\\\\\
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=008  161219c19919999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10219J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10219J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aMilke, JA., $eauthor.
=245  10$aThermal Response of Fire-Exposed Composites / $cJA Milke, AJ Vizzini.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 3 (January 1991)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aTo evaluate the impact of fire on the structural response of a composite component, the thermal response of that component must first be determined. Given a moderate-intensity, short-duration, radiant heat flux with an arbitrary distribution, a three-dimensional heat transfer analysis is essential to predict properly the thermal response. A three-dimensional heat transfer model is formulated to examine the thermal response of an anisotropic composite laminate. The model permits temperature-dependent material properties, arbitrary locations of heat sources and sinks, and a wide variety of realistic boundary conditions. Good agreement between predictions and experimental results are obtained.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aFire exposure.
=650  \0$aGraphite/epoxy.
=650  \0$aHeat transfer.
=650  \0$aThermal conductivity.
=650  \0$aThree-dimensional.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aComposites.
=653  20$aFire exposure.
=653  20$aGraphite/epoxy.
=653  20$aHeat transfer.
=653  20$aThermal conductivity.
=653  20$aThree-dimensional.
=700  1\$aVizzini, AJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10219J.htm

=LDR  03817nam  2200733 i 4500
=001  CTR10220J
=003  IN-ChSCO
=005  20161219163000.0
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=008  161219c19919999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10220J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10220J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aFisher, JM., $eauthor.
=245  12$aA Study of Failure Characteristics in Thermoplastic Composite Material at 250°F (121°C) / $cJM Fisher, AN Palazotto, RS Sandhu.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 3 (January 1991)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA study was conducted to investigate the failure characteristics of thermoplastic composite graphite/polyetheretherketone (Gr/PEEK) at 250°F (121°C). The stacking sequences of specimens used in the study were [0°]16, [90°]16, [±45°]45, and [0°/±45°/90°]2s. Specimens of the first three ply layups, namely, [0°]16, [90°]16, and [±45°]4s were used to determine the basic stress-strain data at 250°F (121°C). In addition, specimens containing a hole (one-third diameter-to-width ratio) corresponding to all the four stacking sequences were manufactured to determine the stress-strain response, the progression of failure, and ultimate tensile strengths. Testing the specimens with ply layups of [±45°]4s and [0°/±45°/90°]2s containing ±45° plies was complicated by the development of high strains, thereby causing the strain gages to peel off during tests.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFailure characteristics.
=650  \0$aHigh-temperature testing.
=650  \0$aLaminates.
=650  \0$aStereo X-rays.
=650  \0$aTesting.
=650  \0$aThermal effects.
=650  \0$aThermoplastics.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aHigh-temperature testing.
=653  20$aComposite materials.
=653  20$aThermoplastics.
=653  20$aFailure characteristics.
=653  20$aStereo X-rays.
=653  20$aTesting.
=653  20$aThermal effects.
=653  20$aLaminates.
=700  1\$aPalazotto, AN., $eauthor.
=700  1\$aSandhu, RS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10220J.htm

=LDR  03419nam  2200661 i 4500
=001  CTR10221J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c19919999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10221J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10221J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.52
=082  04$a620.1/1296$223
=100  1\$aJohnson, WS., $eauthor.
=245  10$aComparison of Some Micromechanics Models for Discontinuously Reinforced Metal Matrix Composites / $cWS Johnson, MJ Birt.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 3 (January 1991)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA systematic experimental evaluation of whisker- and particulate-reinforced aluminum matrix composites was conducted to assess the variation in tensile properties with reinforcement type, volume fraction, and specimen thickness. Each material was evaluated in three thicknesses, 1.8, 3.18, and 6.35 mm, to determine the size, distribution, and orientation of the reinforcements. This information was used to evaluate several micromechanics models that predict composite moduli. The longitudinal and transverse moduli were predicted for 15 volume percent (v/%) SiCp-reinforced aluminum and for 15 and 30 v/% SiCw-reinforced aluminum. The Paul, Cox, and Halpin-Tsai models were evaluated.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAluminum matrix.
=650  \0$aMicrostructure.
=650  \0$aModuli.
=650  \0$aSilicon-carbide particulate.
=650  \0$aSiliconcarbide whiskers.
=650  \0$aMaterials $xThermal properties.
=650  \0$aThermodynamics.
=650  \7$aSCIENCE $xNanoscience.
=653  10$aAluminum matrix.
=653  20$aSilicon-carbide particulate.
=653  20$aSiliconcarbide whiskers.
=653  20$aMicrostructure.
=653  20$aModuli.
=700  1\$aBirt, MJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10221J.htm

=LDR  03933nam  2200673 i 4500
=001  CTR10222J
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=024  7\$a10.1520/CTR10222J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10222J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aGdoutos, EE., $eauthor.
=245  10$aMicromechanical Analysis of Filamentary Metal Matrix Composites Under Longitudinal Loading / $cEE Gdoutos, D Karalekas, IM Daniel.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 3 (January 1991)
=504  \\$aIncludes bibliographical references$b26.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA two-material composite cylinder model (CCM) was considered for the study of the mechanical behavior at different temperatures of a fiber-reinforced silicon carbide/aluminum (SiC/Al) composite. An elastoplastic analysis of the model was performed in which the fiber was assumed to be linear elastic and the matrix elastoplastic with work-hardening. The analysis was based on the deformation theory of plasticity in conjunction with the von-Mises yield criterion. Experimental stress-strain curves of a SiC/Al composite were obtained at 24 and 288°C (75 and 550°F). The complete three-dimensional stress distribution in the composite using the CCM was determined. It was found that, in addition to longitudinal stresses, transverse stresses in both the fiber and the matrix were developed as a result of the different Poisson's ratios of the two materials. The transverse stresses, although much smaller than the longitudinal stresses, contributed to the plastic deformation of the matrix. The experimental stress-strain curves were favorably compared with the theoretical predictions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aElastoplastic analysis.
=650  \0$aHigh-temperature behavior.
=650  \0$aMetal-matrix composites.
=650  \0$aMicromechanics.
=650  \0$aSilicon carbide/aluminum.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMetal-matrix composites.
=653  20$aMicromechanics.
=653  20$aSilicon carbide/aluminum.
=653  20$aElastoplastic analysis.
=653  20$aHigh-temperature behavior.
=700  1\$aKaralekas, D., $eauthor.
=700  1\$aDaniel, IM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10222J.htm

=LDR  03217nam  2200697 i 4500
=001  CTR10223J
=003  IN-ChSCO
=005  20161219163000.0
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=008  161219c19919999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10223J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10223J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aWhitcomb, JD., $eauthor.
=245  10$aDelamination Growth in a Laminate with a Postbuckled Edge Delamination / $cJD Whitcomb.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 3 (January 1991)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAlthough there have been numerous studies of edge delamination growth as a result of tensile loads, edge delamination growth as a result of compressive loads that cause local buckling has not been addressed. This paper discusses the potential for delamination growth in terms of calculated strain-energy release rates. These predictions are compared qualitatively with experimental results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression.
=650  \0$aEdge delamination.
=650  \0$aFinite element analysis.
=650  \0$aFracture mechanics.
=650  \0$aLaminates.
=650  \0$aLocal buckling.
=650  \0$aStrain-energy release rates.
=650  \0$aFinite element method.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aLaminates.
=653  20$aEdge delamination.
=653  20$aFinite element analysis.
=653  20$aFracture mechanics.
=653  20$aStrain-energy release rates.
=653  20$aLocal buckling.
=653  20$aCompression.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10223J.htm

=LDR  03065nam  2200649 i 4500
=001  CTR10224J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19919999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10224J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10224J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQH212.S3
=082  04$a502/.8$223
=100  1\$aUnderwood, JH., $eauthor.
=245  10$aDegradation and Failure Modes of Carbon/Bismaleimide Laminates Subjected to a Tropical Environment / $cJH Underwood, AA Kapusta.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 3 (January 1991)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe scanning electron microscope (SEM) was used to characterize the degradation of the outermost layers of carbon/bismaleimide laminates as the result of exposure to a natural tropical environment. The surface that was exposed to the sun for 4000 h suffered complete degradation of the bismaleimide matrix to a shallow depth.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon/bismaleimide.
=650  \0$aComposite laminates.
=650  \0$aFailure mechanisms.
=650  \0$aScanning electron microscopy.
=650  \0$aTropical exposure.
=650  \0$aMicroscopy, Electron, Scanning.
=650  \0$aElectron microscopy.
=653  10$aComposite laminates.
=653  20$aCarbon/bismaleimide.
=653  20$aScanning electron microscopy.
=653  20$aFailure mechanisms.
=653  20$aTropical exposure.
=700  1\$aKapusta, AA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10224J.htm

=LDR  03103nam  2200625 i 4500
=001  CTR10225J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19919999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10225J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10225J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aChiang, YJ., $eauthor.
=245  10$aCrack Speed Calculations for Unidirectional Laminae / $cYJ Chiang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 3 (January 1991)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aBased on the physical hypotheses that (a) the random properties of fracture in composite materials can be described by a nominal crack size and (b) the surplus of applied work to create new crack surfaces is converted into kinetic energy, an equation for crack speeds in orthotropic composites subjected to a uniform constant normal stress is derived. When the crack length in a composite increases and gets longer than the critical crack length, the crack speed increases asymptotically and finally reaches a limiting speed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aCrack speeds.
=650  \0$aCritical crack lengths.
=650  \0$aWave-propagation speeds.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aCrack speeds.
=653  20$aCritical crack lengths.
=653  20$aKinetic energy.
=653  20$aWave-propagation speeds.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10225J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10226J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10226J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA1637
=082  04$a621.36/7$223
=100  1\$aChai, GB., $eauthor.
=245  10$aStability Study of Coupling Responses in Laminates / $cGB Chai, PW Khong.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 3 (January 1991)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aCoupling responses in laminated panels complicate theoretical analysis and render closed form solution virtually impossible. The assumption that coupling can be ignored (especially orthotropic case) simplifies the analysis, but unconservative results are obvious, especially for laminates with a small number of layers. In this paper, the flexibility of the finite strip method is presented for the analysis of laminated composites in compression. Coupling responses in laminates are taken into consideration in the analysis via the use of the "reduced bending stiffness" concept. Parametric study of laminates subjected to various loading and boundary conditions are presented and discussed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite structures.
=650  \0$aCoupling responses.
=650  \0$aFinite strip.
=650  \0$aLaminates.
=650  \0$aReduced bending stiffness concept.
=650  \0$aStability.
=650  \0$aFinite strip method.
=650  \0$aFinite strip.
=650  \7$aTECHNOLOGY & ENGINEERING $vImaging Systems.
=653  10$aFinite strip.
=653  20$aLaminates.
=653  20$aCoupling responses.
=653  20$aStability.
=653  20$aComposite structures.
=653  20$aReduced bending stiffness concept.
=700  1\$aKhong, PW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10226J.htm

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=001  CTR10230J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10230J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10230J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aShi, N., $eauthor.
=245  14$aThe Effect of Thermal Residual Stresses on the Asymmetric Constitutive Behavior of Metal-Matrix Composites / $cN Shi, RJ Arsenault.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (16 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 4 (December 1991)
=504  \\$aIncludes bibliographical references$b39.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn analytical investigation of the difference in the constitutive behavior of silicon carbide-aluminum (SiC-Al) composites under uniaxial compressive and tensile loading was carried out, and the associated changes of the residual stresses were studied. It is suggested that the observed asymmetric response of the constitutive behavior is primarily due to the existence of residual stresses in the composite. These residual stresses are initially introduced because of the differences in the coefficients of thermal expansion (ΔCTE) during the cooling process and subsequently changed after the external load is applied. A two-dimensional (2-D) finite element analysis of a hexagonal array of SiC whiskers in an Al matrix was performed, the result of which testifies to the appropriateness of the proposed explanation. It is concluded that the 2-D finite element analysis is an economical way of adequately reproducing the most prominent features of the material's constitutive behavior. Based upon the theory of mechanics of composite material, simplified analytical models were developed which can be used to investigate the influences of the whisker-matrix interface shear load transfer and the volume mismatch on the residual stresses. It is concluded that the mechanism of load transfer in terms of normal stress at the whisker tip, which is governed by the volume (bulk) mismatch between the matrix and the whisker, is predominantly responsible for altering the specific pattern of the residual stresses under the applied load. In contrast, the effect of shear load transfer at the longitudinal whisker-matrix interface is only restricted to a very small region in the vicinity of the whisker and does not influence the overall symmetry of the constitutive behavior.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDeformation induced residual stress.
=650  \0$aInterface load transfer (shear lag).
=650  \0$aThermal residual stress.
=650  \0$aVolume mismatch.
=650  \0$aWhisker-reinforced metalmatrix composites.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aThermal residual stress.
=653  20$aDeformation induced residual stress.
=653  20$aAsymmetric constitutive behavior.
=653  20$aWhisker-reinforced metalmatrix composites.
=653  20$aFEM.
=653  20$aVolume mismatch.
=653  20$aInterface load transfer (shear lag).
=700  1\$aArsenault, RJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10230J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10231J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10231J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aChiang, YJ., $eauthor.
=245  10$aFinite Element Analysis of Mixed-Mode Fracture of Bolted Composite Joints / $cYJ Chiang, RE Rowlands.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 4 (December 1991)
=504  \\$aIncludes bibliographical references$b46.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe presence of a flaw or crack near a bolt-loaded hole can significantly reduce the strength of a mechanical joint. Stress intensity factors of mixed-mode cracks emanating from a bolt-loaded hole in a loaded finite composite are evaluated here using the finite element method. Both a horizontal crack adjacent to the bolt and a vertical crack beneath the bolt of a mechanical joint are studied. Linear elastic fracture mechanics is used, and the bolt is assumed to be rigid. The contact stresses are evaluated rather than assumed. Effects of friction, both clearance, geometric nonlinearity between the bolt and the composite, variations in geometry (end distance, crack length, and edge distance), and material properties are accommodated. The magnitudes of the stress intensity factors are found to be highly influenced by variations in the material properties, crack length, and in-plane geometry.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBolted joints.
=650  \0$aBolts.
=650  \0$aComposites.
=650  \0$aCracks.
=650  \0$aFinite element method.
=650  \0$aFracture.
=650  \0$aFrictional contact.
=650  \0$aMechanical joints.
=650  \0$aStress intensity factors.
=650  \0$aBolts and nuts.
=650  \0$aJoints (Engineering)
=653  10$aFinite element method.
=653  20$aComposites.
=653  20$aMechanical joints.
=653  20$aBolted joints.
=653  20$aStress intensity factors.
=653  20$aFrictional contact.
=653  20$aBolts.
=653  20$aCracks.
=653  20$aFracture.
=700  1\$aRowlands, RE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10231J.htm

=LDR  03231nam  2200685 i 4500
=001  CTR10232J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10232J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10232J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aSerabian, SM., $eauthor.
=245  14$aThe Effects of Nonlinear Intralaminar Shear Behavior on the Modeling Accuracy of [(0/90)3,0]s and [(+45/−45)]3s Pin-Loaded Laminates / $cSM Serabian.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 4 (December 1991)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effects of nonlinear intralaminar shear behavior on the modeling accuracy of pin-loaded [(0/90)3,0]s and [(+45/−45)]3s fiberglass epoxy composite laminates was quantitatively examined. The comparison of net, bearing, and shearout sectional strains from linear and nonlinear elastic three-dimensional finite-element approximations with similar front surface experimental geometric moire sectional strains formed the basis of this investigation.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBolted joints.
=650  \0$aComposites.
=650  \0$aDamage.
=650  \0$aFailure.
=650  \0$aMoire.
=650  \0$aNonlinear materials.
=650  \0$aThree-dimensional finiteelement analysis.
=650  \0$aBolts and nuts.
=650  \0$aJoints (Engineering)
=653  10$aComposites.
=653  20$aBolted joints.
=653  20$aThree-dimensional finiteelement analysis.
=653  20$aNonlinear materials.
=653  20$aMoire.
=653  20$aDamage.
=653  20$aFailure.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10232J.htm

=LDR  03458nam  2200661 i 4500
=001  CTR10233J
=003  IN-ChSCO
=005  20161219163000.0
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10233J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10233J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aFortson, BH., $eauthor.
=245  10$aDamage Processes in a Quasi-Isotropic Composite Short Beam Under Three-Point Loading / $cBH Fortson, EA Armanios.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 4 (December 1991)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aComposite materials have complex failure modes that include delamination, fiber debonding and breakage, and matrix microcracking. In this paper, the influence of these damage modes on the failure of the short-beam three-point bend test is investigated for a composite with a quasi-isotropic layup. Failure is found to initiate in a region near the point of application of the load, a location where classical-type analytical descriptions of specimen behavior are unreliable. Furthermore, the locations of failure show little reproducibility. Observed fracture behavior is explained in terms of the overall stress state in the beam before fracture, and failure is predicted from the stress map, using the maximum strain criterion.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDelamination.
=650  \0$aFailure analysis.
=650  \0$aFinite element analysis.
=650  \0$aFractography.
=650  \0$aFinite element method.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aComposites.
=653  20$aDelamination.
=653  20$aFractography.
=653  20$aFinite element analysis.
=653  20$aFailure analysis.
=700  1\$aArmanios, EA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10233J.htm

=LDR  03503nam  2200685 i 4500
=001  CTR10234J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19919999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10234J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10234J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aDharani, LR., $eauthor.
=245  10$aMultiple Cracks in Three-Dimensional (3-D) Unidirectional Composites : $bCompliance and Energy Release Rates / $cLR Dharani, L Chai.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1991.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 13, Issue 4 (December 1991)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA three-dimensional unidirectional composite with fibers aligned along the loading direction and containing planar multiple cracks is analyzed for its fracture behavior. The stresses and displacements are determined using a consistent shear lag formulation that accounts for the load-carrying capacity of the matrix in the longitudinal and transverse directions. The cracks are of equal size and distributed uniformly along the load axis. The change in compliance and energy release rates are obtained as functions of crack size (area) and spacing (crack density). The results show that the growth of existing cracks occurs more easily than multiplication of cracks, that is, formation of new cracks.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1991. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompliance.
=650  \0$aEmbedded cracks.
=650  \0$aEnergy release rate.
=650  \0$aMultiple cracks.
=650  \0$aShear lag.
=650  \0$aUnidirectional composites.
=650  \0$aComposite material.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMultiple cracks.
=653  20$aUnidirectional composites.
=653  20$aCompliance.
=653  20$aEnergy release rate.
=653  20$aEmbedded cracks.
=653  20$aShear lag.
=700  1\$aChai, L., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10234J.htm

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=001  CTR10239J
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10239J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10239J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aVoleti, SR., $eauthor.
=245  10$aEffect of Fiber Fracture and Matrix Yielding on Load Sharing in Continuous Fiber Metal Matrix Composites / $cSR Voleti, CR Ananth, N Chandra.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 4 (October 1998)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper addresses the issue of stress redistribution in the presence of a fiber fracture in a composite lamina. Stress elevation in the fiber adjacent to the broken fiber is the focus of this study. The stress concentration effects in the vicinity of the fiber break and its influence on the neighboring intact fiber is analyzed using the finite element method as a function of fiber volume fraction. The role of the inelastic behavior of the matrix in causing the stress elevation is studied. It is found that the state of stress in the intact fiber is affected significantly by the propagation of the plastic front due to matrix yielding. The local stress field is affected also if the fiber break is followed by interfacial debonding. Titanium matrix reinforced with continuous fibers of silicon carbide is chosen as the metal matrix composite system for this study. Experimental comparisons are made with tension tests conducted using a single-ply lamina.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aLoad sharing.
=650  \0$aMatrix yielding.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aLoad sharing.
=653  20$aMatrix yielding.
=653  20$aMMCs.
=700  1\$aAnanth, CR., $eauthor.
=700  1\$aChandra, N., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10239J.htm

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=001  CTR10240J
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=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10240J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10240J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aArola, DD., $eauthor.
=245  10$aNet-Shape Machining and the Process-Dependent Failure of Fiber-Reinforced Plastics Under Static Loads / $cDD Arola, M Ramulu.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effects of net-shape machining on the mechanical properties of a graphite/bismaleimide (Gr/Bmi) laminate were investigated under pure bending. An experimental evaluation of the acoustic emission during loading, bend load and energy to failure, and optical documentation of first ply failure was conducted. Experimental results were also compared with predictions for failure from a finite element model using conventional failure criteria. It was found that surface texture has a significant influence on the mechanical properties of fiber-reinforced plastics (FRPs) and that the static bend strength decreased with increasing surface roughness. Acoustic emission prior to the onset of failure indicated that damage accumulation was clearly dependent on the method of machining. It was also found that the location of first ply failure was influenced by the process-dependent surface structure, but not by the magnitude of surface roughness.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aMachining.
=650  \0$aSurface integrity.
=650  \0$aSurface texture.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aMachining.
=653  20$aSurface texture.
=653  20$aSurface integrity.
=700  1\$aRamulu, M., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10240J.htm

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=001  CTR10241J
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=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10241J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10241J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aO'Brien, TK., $eauthor.
=245  10$aTension-Torsion Behavior of Glass Epoxy Flexbeam Laminates / $cTK O'Brien, JK Sen.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 4 (October 1998)
=504  \\$aIncludes bibliographical references$b1.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aQuasi-static tension-torsion and tension-torsion fatigue tests were conducted on several candidate S2/F584 glass-epoxy flex-beam layups to establish their torsional strength and fatigue behavior in the presence of an axial load, determine typical damage mechanisms, and provide a database for developing predictive analytical methods. Tension-torsion specimens contained 0° longitudinal plies and 15, 30, or 45° angle plies in seven different stacking sequences. The angle plies were ±45 woven cloth in one layup and prepreg tape in the other layups. In the tape laminates, fatigue failures began with matrix cracks forming on the edge that initiated delaminations in the interfaces between the angle plies and 0° plies. In the cloth laminates, a series of small "stair step" delaminations formed between the ±45 cloth layers and initiated delaminations in the neighboring 0/45 interfaces. Tests indicated that the three layups with only 0° and ±45° plies had the highest torsional strength in the presence of a constant axial load. Of the three strongest layups, the one in which the ±45° plies were made of woven cloth fabric instead of prepreg tape was the strongest and had the longest fatigue life.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFatigue.
=650  \0$aGlass epoxy.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aGlass epoxy.
=653  20$aFatigue.
=700  1\$aSen, JK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10241J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10246J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10246J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aLagace, P., $eauthor.
=245  14$aThe Effect of Thickness on Interlaminar Stresses and Delamination in Straight-Edged Laminates / $cP Lagace, J Brewer, C Kassapoglou.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 3 (September 1987)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effect of ply and laminate thickness on the fracture of graphite/epoxy laminates induced by delamination was investigated. Five laminate types were manufactured from AS1/3501-6 graphite/epoxy and tested: [±15n]s, [±15n/0n]s, [0n/±15n]s, [±45n/0n]s, and [[0/±15]s]n. "Effective ply thickness" was varied by stacking several plies of the same angular orientation together. It was found that an increase in effective ply thickness caused a decrease in fracture stress resulting from delamination in all cases. Interlaminar stress calculations indicate that this results from the fact that the region of high interlaminar stresses increases as the effective ply thickness increases. These calculations also suggest that interlaminar shear stresses are at least as important in causing delamination as interlaminar normal stresses. "Back-to-back" [[0/±15]s]n laminates were found to have the same strength for values of n from one to three. This indicates that reductions in strength are not simply a laminate thickness phenomenon but are related to the effective ply thickness.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDelamination.
=650  \0$aEffective ply thickness.
=650  \0$aFailure.
=650  \0$aGraphite/epoxy.
=650  \0$aInterlaminar stresses.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDelamination.
=653  20$aInterlaminar stresses.
=653  20$aGraphite/epoxy.
=653  20$aComposites.
=653  20$aFailure.
=653  20$aEffective ply thickness.
=700  1\$aBrewer, J., $eauthor.
=700  1\$aKassapoglou, C., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10246J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10247J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10247J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aAdams, DF., $eauthor.
=245  10$aIn-Plane and Interlaminar losipescu Shear Properties of Various Graphite Fabric/Epoxy Laminates / $cDF Adams, DE Walrath.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 3 (September 1987)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe Iosipescu shear test method was used to measure the in-plane and interlaminar shear properties of four T300 graphite fabric/Fiberite 934 epoxy composite materials. Weave geometries tested included an Oxford weave, a 5-harness satin weave, an 8-harness satin weave, and a plain weave with auxiliary warp yarns. Both orthogonal and quasi-isotropic layup laminates were tested.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFabric composites.
=650  \0$aInterlaminar shear.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aIosipescu shear.
=653  20$aFabric composites.
=653  20$aInterlaminar shear.
=700  1\$aWalrath, DE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10247J.htm

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=001  CTR10248J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10248J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10248J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTE7
=082  04$a625.7/08 s$223
=100  1\$aAkhtar, A., $eauthor.
=245  10$aFailure Analysis of Brittle Fracture in Nonceramic Insulators / $cA Akhtar, JY Wong.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 3 (September 1987)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aTime dependent transverse cracking of the glass reinforced polymer (GRP) core rod in nonceramic insulators (NCI) under low mechanical loads, commonly referred to as brittle fracture, has been investigated. Tension tests were performed on GRP core rods with E glass, ECR glass as well as epoxy and polyester matrices using nitric and oxalic acid environments in order to obtain the relationship between applied stress and the time to rupture. While both E glass and ECR glass remain prone to brittle fracture, ECR has a substantially superior resistance to stress corrosion cracking than E glass. Scanning electron microscopy of fracture surfaces has produced a quantitative relationship between the stress history and the fracture mirror size on the fibers. Results of an epoxy cone insulator end fitting are presented, and the mechanism of brittle fracture is discussed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFracture mirror.
=650  \0$aNonceramic insulators.
=650  \0$aStress corrosion cracking.
=650  \0$aTime load.
=650  \0$aStress corrosion.
=650  \0$aCorrosion and anti-corrosives.
=653  10$aNonceramic insulators.
=653  20$aStress corrosion cracking.
=653  20$aFracture mirror.
=653  20$aTime load.
=700  1\$aWong, JY., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10248J.htm

=LDR  03824nam  2200625 i 4500
=001  CTR10249J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10249J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10249J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.P55
=082  04$a620.1/923$223
=100  1\$aWoo, M., $eauthor.
=245  10$aWater Absorption of Resins and Composites : $bI. Epoxy Homopolymers and Copolymers / $cM Woo, MR Piggott.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 3 (September 1987)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWater absorption experiments have been carried out on three DGEBA type epoxy resins. A reactive diluent added to the resin increased water permeation, while a monomer that expanded on cure decreased it. Exposure at 97% relative humidity (RH) gave results that closely paralleled those obtained by water immersion, though the resin had higher solubility for water and lower activation energy for diffusion when immersed, over the temperature range investigated, that is, 23 to 75°C. The activation energy for diffusion was independent of relative humidity, but the diffusion constant was directly proportional to it. The solubility of water was not determined by Henry's law, but instead was determined by relative humidity to the 1.4th power. The water does not appear to be bound to polar groups in the resin, or hydrogen bonding sites, although dielectric tests indicate that it does not behave as free water, since its polarizability is much reduced. The amount of reduction in effective dielectric constant of the water was only about 55 to 77% indicating that there was some clustering of the water molecules in the polymer, rather than complete separation of the molecules.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber composites.
=650  \0$aWater absorption.
=650  \0$aWater diffusion.
=650  \0$aFiber-reinforced plastics.
=650  \0$aPolymeric composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFiber composites.
=653  20$aWater diffusion.
=653  20$aWater absorption.
=653  20$aAbsorption fiber-matrix interface.
=700  1\$aPiggott, MR., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10249J.htm

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=001  CTR10250J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10250J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10250J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA405
=082  04$a620.1/12$223
=100  1\$aMallick, PK., $eauthor.
=245  10$aStrength and Failure Modes in Notched Pultruded Rod Tension Specimens / $cPK Mallick, RE Little, E Haupt.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 3 (September 1987)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFailure mode in a notched pultruded rod containing unidirectional E-glass fibers depends on the ratio of gage length L to specimen diameter d at the notch. For a tensile failure, a large L/d ratio is required. At smaller L/d ratios, long pull-out or crushing at the grips occurs. Based on the failure mode observation and tensile strength evaluation, development of a V-notched tension test with large L/d ratio is suggested as a possible replacement for the current ASTM tension test (ASTM Test Method for Tensile Properties of Pultruded Glass Fiber-Reinforced Plastic Rod [D 3916])
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFailure.
=650  \0$aPultrusion process.
=650  \0$aRods.
=650  \0$aStrength.
=650  \0$aTension tests.
=650  \0$aStrength of materials.
=650  \7$aSCIENCE $xNanoscience.
=653  10$aPultrusion process.
=653  20$aTension tests.
=653  20$aRods.
=653  20$aStrength.
=653  20$aFailure.
=700  1\$aLittle, RE., $eauthor.
=700  1\$aHaupt, E., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10250J.htm

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=001  CTR10268J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10268J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10268J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRazvan, A., $eauthor.
=245  10$aInfluence of Cyclic Load Amplitude on Damage Accumulation and Fracture of Composite Laminates / $cA Razvan, CE Bakis, L Wagnecz, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 1 (March 1988)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIt has become a common practice in the design and certification of composite laminate components to assume that long-term inservice response can be implied from short-term test results. The variable in this extrapolation of behavior is often the cyclic or quasi-static applied load level. These variations in load level can be the source of changes in the damage accumulation and fracture modes associated with the corresponding response. The present paper brings together results from a series of investigations of several composite laminate and material system types in an effort to identify some of the fundamental differences in the damage accumulation and fracture associated with cyclic loading of continuous fiber reinforced composite laminates at high and low cyclic load amplitudes.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDamage.
=650  \0$aFatigue.
=650  \0$aFracture.
=650  \0$aLaminates.
=650  \0$aReliability.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aLaminates.
=653  20$aFatigue.
=653  20$aDamage.
=653  20$aFracture.
=653  20$aReliability.
=700  1\$aBakis, CE., $eauthor.
=700  1\$aWagnecz, L., $eauthor.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10268J.htm

=LDR  03422nam  2200673 i 4500
=001  CTR10269J
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=008  161219c19889999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10269J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10269J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMurphy, K., $eauthor.
=245  12$aA Rugged Optical Fiber Interferometer for Strain Measurements Inside a Composite Material Laminate / $cK Murphy, JC Duke.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 1 (March 1988)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA simple Mach-Zehnder Interferometer has been constructed entirely of single-mode optical fibers. The signal arm was successfully embedded inside a graphite-epoxy laminate. Tensile and compressive strains internal to the laminate were measured for the deformation of a cantilevered beam to demonstrate the system functionality. Difficulties encountered during the measurement of the compressive strains are discussed. The resulting optical system eliminates entirely the need for conventional optical components, while maintaining the conditions required to obtain optical interference necessary for strain measurement.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aCompressive strain.
=650  \0$aFiber optics.
=650  \0$aInterferometers.
=650  \0$aInternal strain measurements.
=650  \0$aMach-Zehnder interferometer.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aInterferometers.
=653  20$aFiber optics.
=653  20$aCompressive strain.
=653  20$aInternal strain measurements.
=653  20$aMach-Zehnder interferometer.
=653  20$aComposite materials.
=700  1\$aDuke, JC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10269J.htm

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=001  CTR10270J
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=008  161219c19889999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10270J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10270J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aWoo, M., $eauthor.
=245  10$aWater Absorption of Resins and Composites : $bIII. Water Distribution as Indicated by Capacitance Measurement / $cM Woo, MR Piggott.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 1 (March 1988)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aGlass fiber reinforced epoxy pultrusions were made with a range of fiber volume fractions. They were immersed in water at temperatures in the range 23 to 100°C until saturated, and their dielectric properties measured. Tests on the saturated resins themselves indicated that 60 to 75% of the water was concentrated in disk-shaped regions. The remainder of the water was probably molecularly dispersed; the proportion of this phase depended on the presence of polar groups in the polymer. In the case of the composites, the water provided conducting paths, probably caused by the inter-connection of regions of water concentration at the fiber-matrix interface by the water "disks" that exist in the resin. Dielectric tests appear thus to be a potent tool for providing information about the morphology of resins and composites containing water. In the absence of significant conducting paths, the permittivity obeys simple mixture rules, and the mixture rule giving the best fit to the experimental results gives information about the morphology of the dispersed phase in a composite.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber composite.
=650  \0$aWater absorption.
=650  \0$aWater diffusion.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aFiber composite.
=653  20$aWater diffusion.
=653  20$aWater absorption.
=653  20$aAbsorption fiber-matrix interface.
=700  1\$aPiggott, MR., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10270J.htm

=LDR  03984nam  2200625 i 4500
=001  CTR10271J
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=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aWoo, M., $eauthor.
=245  10$aWater Absorption of Resins and Composites : $bIV. Water Transport in Fiber Reinforced Plastics / $cM Woo, MR Piggott.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 1 (March 1988)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn analysis of diffusivity of composites is described in which an electrical resistance analogy is used. This leads to an expression for diffusivity, which takes into account the contributions of fiber diffusivity, matrix diffusivity, and the diffusivity of the interphase, when this is different from that of the polymer matrix. The case involving the interphase requires numerical integration for its solution. However, the effect of the interphase can be very accurately simulated in a more approximate model; a closed form expression for composite diffusivity is obtained that agrees with the numerical analysis within better than 1% if an appropriate adjustment for interphase width is made. The same approach was used for including voids in the analysis, and it is shown that, in some experiments described previously with glass and carbon fiber pultrusions, the results can be explained on the basis of the voids in the composite providing an enhanced diffusion path for water. This "void path" apparently has a diffusivity of 15 times that of the polymer. Since the results obtained using the interphase diffusion model do not agree so well with the experimental data as does the void path model, it is concluded that, at least for carbon-epoxy and glass-epoxy pultrusions, the most important conducting path for water is provided by the voids.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAbsorption.
=650  \0$aFiber composites.
=650  \0$aFiber-matrix interface.
=650  \0$aWater diffusion.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aFiber composites.
=653  20$aWater diffusion.
=653  20$aAbsorption.
=653  20$aFiber-matrix interface.
=700  1\$aPiggott, MR., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10271J.htm

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=024  7\$a10.1520/CTR10275J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA347.F5
=082  04$a620.00151825$223
=100  1\$aSalpekar, SA., $eauthor.
=245  10$aStrain Energy Release Rate Analysis of the End-Notched Flexure Specimen Using the Finite-Element Method / $cSA Salpekar, IS Raju, TK O'Brien.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
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=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 4 (December 1988)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aTwo-dimensional finite-element analysis of the end-notched flexure specimen was performed using 8-node isoparametric, parabolic elements to evaluate compliance and Mode II strain energy release rates GII. The GII values were computed using two different techniques: the virtual crack-closure technique (VCCT) and the rate of change of compliance with crack length (compliance derivative method). The analysis was performed for various crack-length-to-semispan (a/L) ratios ranging from 0.2 to 0.9. Three material systems representing a wide range of material properties were analyzed. The compliance and strain energy release rates of the specimen calculated with the present finite-element analysis agree very well with beam theory equations including transverse shear. The GII values calculated using the compliance derivative method compared extremely well with those calculated using the virtual crack-closure technique. The GII values obtained by the compliance derivative method using the top or bottom beam deflections agreed closely with each other. The strain energy release rates from a plane-stress analysis were higher than the plane-strain values by only a small percentage, indicating that either assumption may be used in the analysis. The GII values for one material system calculated from the finite-element analysis agreed with one solution in the literature and disagreed with the other solution in the literature.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCracks.
=650  \0$aDelamination.
=650  \0$aEnergy release rate.
=650  \0$aFinite-element analysis.
=650  \0$aFlexure.
=650  \0$aStrain.
=650  \0$aFinite element method.
=650  \7$aTECHNOLOGY & ENGINEERING $xEngineering (General.
=653  10$aFinite-element analysis.
=653  20$aFlexure.
=653  20$aDelamination.
=653  20$aCracks.
=653  20$aEnergy release rate.
=653  20$aStrain.
=700  1\$aRaju, IS., $eauthor.
=700  1\$aO'Brien, TK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10275J.htm

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=024  7\$a10.1520/CTR10276J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aArsenault, RJ., $eauthor.
=245  10$aRelationship Between Strengthening Mechanisms and Fracture Toughness of Discontinuous SiC/Al Composites / $cRJ Arsenault.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 4 (December 1988)
=504  \\$aIncludes bibliographical references$b28.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn all cases of discontinuous silicon carbide (SiC/Al) metal matrix it was shown that classical composite strengthening mechanisms could not be used to explain the data. A high dislocation density model was proposed to account for the strengthening, but other factors, such as residual stress and texture, could contribute. These were investigated, and it was shown that texture had no effect and residual stress reduced the tensile yield stress. The fracture process in the composites is controlled by fracture of the matrix up to SiC particle sizes of 20 μm and for larger SiC size particles fracture of SiC begins to dominate. The fracture process in the matrix is influenced by residual hydrostatic tension and high density of dislocations generated at SiC/Al interfaces. Crack initiation fracture toughness does not depend on SiC particle size, for particle sizes less than 20 μm. Crack growth resistance increases as the size of the SiC particles increases.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDiscontinuous SiC/Al composites.
=650  \0$aFracture toughness.
=650  \0$aResidual stress.
=650  \0$aStrengthening mechanisms.
=650  \0$aTexture.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDiscontinuous SiC/Al composites.
=653  20$aStrengthening mechanisms.
=653  20$aFracture toughness.
=653  20$aResidual stress.
=653  20$aTexture.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10276J.htm

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=024  7\$a10.1520/CTR10277J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aLifshitz, JM., $eauthor.
=245  10$aDetermination of Nonlinear Shear Modulus of a Fiber-Reinforced Lamina from the Axial Behavior of (±45)s Specimens / $cJM Lifshitz.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 4 (December 1988)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA method for calculating the nonlinear shear modulus of a fiber-reinforced composite lamina, shown to be insensitive to the value of Poisson's ratio, is developed for use in conjunction with testing of (±45)s, specimens. The axial shear strain is calculated from measured values of the axial strain and the known values of the other three basic properties of the lamina (longitudinal and transverse moduli and Poisson's ratio). The method is verified by comparing calculated results to measured values obtained from compression tests of (±45)4s T300-934 graphite/epoxy specimens.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aFiber-reinforced lamina.
=650  \0$aGraphite/epoxy.
=650  \0$aNonlinear shear modulus.
=650  \0$aPoisson's ratio.
=650  \0$aShear modulus.
=650  \0$aShear strain.
=650  \0$aSpecimens.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aComposites.
=653  20$aShear modulus.
=653  20$aShear strain.
=653  20$aNonlinear shear modulus.
=653  20$aFiber-reinforced lamina.
=653  20$a(±45)s.
=653  20$aSpecimens.
=653  20$aPoisson's ratio.
=653  20$aGraphite/epoxy.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10277J.htm

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=024  7\$a10.1520/CTR10278J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10278J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aEl-Zein, MS., $eauthor.
=245  10$aEvaluation of GIC of a DCB Specimen Using an Anisotropic Solution / $cMS El-Zein, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 4 (December 1988)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn equation for the strain energy release rate G1 of a double cantilever beam (DCB) specimen for an anisotropic material is obtained. Results show that for an orthotropic material, the solution coincides with the isotropic one. However, for a more general anisotropic case, an additional term appears, which is a function of the crack length, the material anisotropy, and the thickness of the cantilever beam. Interpretations of these results show that the additional term is fairly small and could be neglected for crack length to thickness ratios greater than 4.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnisotropic solution.
=650  \0$aDelamination.
=650  \0$aStrain energy release rate.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDouble cantilever beam specimen.
=653  20$aAnisotropic solution.
=653  20$aDelamination.
=653  20$aStrain energy release rate.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10278J.htm

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=024  7\$a10.1520/CTR10279J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10279J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aReifsnider, KL., $eauthor.
=245  10$aCompressive Strength and Mode of Failure of 8H Celion 3000/PMR15 Woven Composite Material / $cKL Reifsnider, F Mirzadeh.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 4 (December 1988)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aCenter-notched and unnotched specimens cut from Celion 3000/PMR15 woven composite panels with 60% fiber volume fraction were tested under quasi-static compressive load to failure at room temperature. Micrographic evidence clearly identifies the mode of compressive failure as fiber kinking. Each fiber in the kink fractures because of a combination of compressive and shear stresses. A post failure mechanism follows the local fiber bundle failures, which completely deforms the material by large cracks. In center notched specimens, fiber kinks start from the notch and propagate to some distance from the notch before the post failure takes place.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBundle.
=650  \0$aComposite materials.
=650  \0$aCompressive strength.
=650  \0$aEight-harness.
=650  \0$aFailure mode.
=650  \0$aFiber fracture.
=650  \0$aWoven.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aEight-harness.
=653  20$aWoven.
=653  20$aCelion3000.
=653  20$aPMR15.
=653  20$aKink.
=653  20$aBundle.
=653  20$aCompressive strength.
=653  20$aFailure mode.
=653  20$aFiber fracture.
=700  1\$aMirzadeh, F., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10279J.htm

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=024  7\$a10.1520/CTR10280J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10280J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aWolff, EG., $eauthor.
=245  10$aPrediction of the Microyield Strength of Polymer Matrix Composites / $cEG Wolff, ST Crane.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 4 (December 1988)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA theory for the prediction of creep and microyield strength of composite laminates with visco-elastic matrices has been developed and tested. Precise creep curves from three laminates with arbitrary orientations provide the necessary input data. The time dependent lamina properties are derived for subsequent use with standard laminate codes. Both the level and shape of creep and strain recovery curves can be predicted. Extensions of the theory to include the effects of microcracking are outlined.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aCompression.
=650  \0$aCreep.
=650  \0$aInterferometers.
=650  \0$aLaminates.
=650  \0$aLinear viscoelasticity.
=650  \0$aMicroyield.
=650  \0$aRecovery.
=650  \0$aTubes.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMicroyield.
=653  20$aLinear viscoelasticity.
=653  20$aCreep.
=653  20$aLaminates.
=653  20$aRecovery.
=653  20$aCompression.
=653  20$aTubes.
=653  20$aInterferometers.
=653  20$aComposite materials.
=700  1\$aCrane, ST., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10280J.htm

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=001  CTR10281J
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=008  161219c19889999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10281J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10281J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aSadat, AB., $eauthor.
=245  14$aThe Effect of Cutting Speed and Width of Cut on Interlaminar Tensile Strength of Graphite/Epoxy Composite Material / $cAB Sadat.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1988.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 10, Issue 4 (December 1988)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effect of cutting speed and width of cut on the machining characteristics of a graphite/epoxy composite material were investigated. The interlaminar tensile strengths of the machined specimens were measured. Damage in the form of cracks, delamination, and fiber rotation were detected in the machined region. The depth of the affected zone and the severity of the damage decreases with an increase in cutting speed. The interlaminar tensile strength of the machined specimens increases with an increase in cutting speed. The results are interpreted in terms of the tool force generated during the machining operation.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1988. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCutting.
=650  \0$aDelamination.
=650  \0$aGraphite epoxy composites.
=650  \0$aInterlaminar tensile strength.
=650  \0$aMachining.
=650  \0$aSawing.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMachining.
=653  20$aCutting.
=653  20$aSawing.
=653  20$aDelamination.
=653  20$aInterlaminar tensile strength.
=653  20$aGraphite epoxy composites.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10281J.htm

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=001  CTR10286J
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=024  7\$a10.1520/CTR10286J$2doi
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=037  \\$aCTR10286J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aConle, A., $eauthor.
=245  10$aEffects of Mean Stress on the Fatigue of Composite Materials / $cA Conle, JP Ingall.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 1 (March 1985)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA parametric stress-fatigue life relationship developed for metals has been adapted to composite material systems and validated by using data from the literature and an extensive test program on XMC polyester/glass. The employed parameter accounts for the effects of mean stress in a fatigue history and results in simplified design curves.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aFatigue (materials)
=650  \0$aMean stress.
=650  \0$aStresses.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFatigue (materials).
=653  20$aComposites.
=653  20$aStresses.
=653  20$aMean stress.
=700  1\$aIngall, JP., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10286J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10287J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10287J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aRosensaft, M., $eauthor.
=245  10$aEvaluation of Bending Test Methods for Composite Materials / $cM Rosensaft, G Marom.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 1 (March 1985)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe present study is an evaluation of the applicability of bending test methods to composite materials. The evaluation is based on examining the effect of the material, using three different reinforcing fibers, and on comparing between two loading configurations, namely, three-point versus four-point loading. It is shown that the results depend on the combination of fracture mechanism comprising each failure mode, and that reliable values of either the shear or the tensile/compressive stresses can be obtained only if the contributions of those mechanisms are accounted for.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon fiber-reinforced composites.
=650  \0$aFour-point bending.
=650  \0$aGlass fiber-reinforced composites.
=650  \0$aShear stress.
=650  \0$aTensile/compressive stress.
=650  \0$aThree-point bending.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aTensile/compressive stress.
=653  20$aShear stress.
=653  20$aThree-point bending.
=653  20$aFour-point bending.
=653  20$aCarbon fiber-reinforced composites.
=653  20$aKevlar fiber-reinforced composites.
=653  20$aGlass fiber-reinforced composites.
=700  1\$aMarom, G., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10287J.htm

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=001  CTR10288J
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=007  cr\\\\\\\\\\\\
=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10288J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10288J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aMorgan, RJ., $eauthor.
=245  10$aCharacterization of the Cure of Carbon Fiber/Epoxy Composite Prepregs by Differential Scanning Calorimetry / $cRJ Morgan, CM Walkup, TH Hoheisel.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 1 (March 1985)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy compounds.
=650  \0$aFireproofing agents.
=650  \0$aProperties.
=700  1\$aWalkup, CM., $eauthor.
=700  1\$aHoheisel, TH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10288J.htm

=LDR  02264nam  2200517 i 4500
=001  CTR10289J
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=005  20161219163000.0
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=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10289J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10289J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTS510
=082  04$a624.1/71$223
=100  1\$aForal, RF., $eauthor.
=245  10$aBiaxial Stress Testing of Intraply Hybrid Composites / $cRF Foral, WD Humphrey.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 1 (March 1985)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aHybrid composites.
=700  1\$aHumphrey, WD., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10289J.htm

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=007  cr\\\\\\\\\\\\
=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10290J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10290J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aTalreja, R., $eauthor.
=245  12$aA Conceptual Framework for the Interpretation of Fatigue Damage Mechanisms in Composite Materials / $cR Talreja.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 1 (March 1985)
=504  \\$aIncludes bibliographical references$b27.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10290J.htm

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=001  CTR10293J
=003  IN-ChSCO
=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10293J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10293J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aChamis, CC., $eauthor.
=245  10$aDesign Concepts for Low-Cost Composite Engine Frames / $cCC Chamis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 2 (June 1985)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDesign concepts of low-cost lightweight composite engine frames were applied to the design requirements for the frame of commercial transport high-bypass turbine engines. The concepts included generic-type components and subcomponents that could be adapted for use in different locations in the engine and to different engine sizes. A variety of materials and manufacturing methods were assessed with a goal of having the lowest number of parts possible at the lowest possible cost. Evaluation of the design concepts resulted in the identification of a hybrid composite frame that would weigh about 20% less than the state of the art metal and cost about 40% less.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aDetail design.
=650  \0$aEngines.
=650  \0$aGeneric design concepts.
=650  \0$aPreliminary design.
=650  \0$aStructural analysis.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aStructural analysis.
=653  20$aEngines.
=653  20$aPreliminary design.
=653  20$aDetail design.
=653  20$aGeneric design concepts.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10293J.htm

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=001  CTR10294J
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=007  cr\\\\\\\\\\\\
=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10294J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10294J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGibson, RF., $eauthor.
=245  10$aLaboratory Production of Discontinuous-Aligned Fiber Composite Plates Using an Autoclave-Style Press Cure / $cRF Gibson, LR Deobald, SA Suarez.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 2 (June 1985)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe objectives of this article are twofold: to describe a procedure that we have developed for producing laboratory quantities of discontinuous-aligned fiber composite materials and to discuss the autoclave-style press cure as an inexpensive laboratory-scale alternative to the industrial autoclave cure. We have produced discontinuous-aligned fiber composite plates from continuous fiber prepreg tapes of graphite/epoxy, Kevlar/epoxy, and boron/epoxy using a vacuum-bagged mold in a small laboratory press. Procedures and apparatus are described, and the quality of autoclave-cured samples is compared with that of autoclave-style press cured samples.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite fabrication.
=650  \0$aComposite materials.
=650  \0$aDiscontinuous fiber reinforcement.
=650  \0$aShort fiber composites.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aComposite fabrication.
=653  20$aShort fiber composites.
=653  20$aDiscontinuous fiber reinforcement.
=700  1\$aDeobald, LR., $eauthor.
=700  1\$aSuarez, SA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10294J.htm

=LDR  03771nam  2200709 i 4500
=001  CTR10295J
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=024  7\$a10.1520/CTR10295J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10295J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKriz, RD., $eauthor.
=245  10$aInfluence of Damage on Mechanical Properties of Woven Composites at Low Temperatures / $cRD Kriz.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 2 (June 1985)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aLarge quantities of nonmetallic woven composites will be used in magnetic fusion energy (MFE) structures at low temperatures. Understanding variations in mechanical properties will provide useful information to the MFE designer. Here we study the influence of crack formation, residual thermal stresses, and weave curvature on the mechanical performance of G10-CR glass/epoxy laminates. Improved material performance is suggested by studying the load-deformation response of a unit cell of plain weave. A generalized plane strain finite-element model was used to predict crack-tip singularities and redistribution of stresses within a thin slice of warp-fill fiber bundles. The model predicts that warp curvature and thermal stresses at low temperatures are beneficial in reducing crack-tip singularities of fill cracks. The opposite is true for stiffness, which is decreased both by curvature and fill cracks. Results of this model provide the designer a tradeoff between stiffness and strength.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCracks.
=650  \0$aGlass/epoxy.
=650  \0$aLocal stresses.
=650  \0$aLow temperature.
=650  \0$aStiffness.
=650  \0$aStrain.
=650  \0$aThermal contraction.
=650  \0$aWoven composites.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCracks.
=653  20$aStrain.
=653  20$aStiffness.
=653  20$aWoven composites.
=653  20$aLow temperature.
=653  20$aGlass/epoxy.
=653  20$aLocal stresses.
=653  20$aThermal contraction.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10295J.htm

=LDR  02272nam  2200505 i 4500
=001  CTR10296J
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=005  20161219163000.0
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10296J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10296J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aVinson, JR., $eauthor.
=245  10$aRecent Advances in Technology for Composite Materials in the United States / $cJR Vinson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 2 (June 1985)
=504  \\$aIncludes bibliographical references$b37.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10296J.htm

=LDR  02267nam  2200505 i 4500
=001  CTR10297J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10297J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10297J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTN752.T54
=082  04$a669$223
=100  1\$aWhitcomb, JD., $eauthor.
=245  12$aA Simple Calculation of Strain-Energy Release Rate for a Nonlinear Double Cantilever Beam / $cJD Whitcomb.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 2 (June 1985)
=504  \\$aIncludes bibliographical references$b1.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aChemical Engineering and Technology.
=650  \0$aMaterials.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10297J.htm

=LDR  03277nam  2200721 i 4500
=001  CTR10301J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10301J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10301J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aHarris, CE., $eauthor.
=245  12$aA Damage Tolerant Design Parameter for Graphite/Epoxy Laminated Composites / $cCE Harris, DH Morris.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 3 (September 1985)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe results of an extensive experimental investigation of the fracture behavior of notched graphite/epoxy laminates are presented. Twenty-seven laminates with different stacking sequences and laminate thicknesses have been studied. The data presented herein suggest that a damage tolerant design parameter exists that is relatively independent of ply stacking sequence and laminate thickness.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDamage tolerant design.
=650  \0$aFracture mechanics.
=650  \0$aFracture toughness.
=650  \0$aGraphite composites.
=650  \0$aGraphite/epoxy.
=650  \0$aLaminates.
=650  \0$aThick laminates.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aComposites.
=653  20$aGraphite composites.
=653  20$aLaminates.
=653  20$aGraphite/epoxy.
=653  20$aFracture mechanics.
=653  20$aFracture toughness.
=653  20$aDamage tolerant design.
=653  20$aThick laminates.
=700  1\$aMorris, DH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10301J.htm

=LDR  03701nam  2200709 i 4500
=001  CTR10302J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10302J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10302J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGürdal, Z., $eauthor.
=245  14$aThe Effect of Slots on the Buckling and Postbuckling Behavior of Laminated Plates / $cZ Gürdal, RT Haftka, JH Starnes.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 3 (September 1985)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn experimental study was conducted to evaluate the effect of lateral slots on the buckling response, the postbuckling response, and the failure characteristics of flat rectangular graphite-epoxy plates loaded in compression. The slots did not significantly affect the prebuckling and buckling behavior of the plates. The slots caused local changes in the strain distribution and out-of-plane deformations near the slot. Failure loads and modes were strongly affected by slot location. Centrally located slots did not affect the failure loads or failure modes of the plates. Slots located close to an unloaded edge of a plate reduced the postbuckling strength of the plate and affected the failure mode. For one slightly offset slot location, interaction of out-of-plane deformations with the slot tip was observed to affect the failure mode significantly without affecting the failure load.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aCompressive loading.
=650  \0$aCracks.
=650  \0$aDamage.
=650  \0$aPostbuckling.
=650  \0$aShear crippling.
=650  \0$aSlots.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aDamage.
=653  20$aCracks.
=653  20$aSlots.
=653  20$aCompressive loading.
=653  20$aPostbuckling.
=653  20$aShear crippling.
=700  1\$aHaftka, RT., $eauthor.
=700  1\$aStarnes, JH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10302J.htm

=LDR  03120nam  2200649 i 4500
=001  CTR10303J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10303J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10303J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNomura, S., $eauthor.
=245  12$aA Method to Estimate the Overall Behavior of Fiber-Reinforced Hybrid Composites / $cS Nomura, N Oshima.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 3 (September 1985)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA simple and realistic model for estimating the effective modulus of fiber-reinforced hybrid composites is proposed. Based upon a two-phase model developed earlier by micromechanical analysis, a new approach to deal with hybrid composites is adopted by introducing an "equivalent virtual volume fraction." The obtained results reflect the matrix effect more adequately than previous "self-consistent" theories.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aEffective modulus.
=650  \0$aHybrid composites.
=650  \0$aMicromechanical analysis.
=650  \0$aModulus of elasticity.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aModulus of elasticity.
=653  20$aComposites.
=653  20$aHybrid composites.
=653  20$aMicromechanical analysis.
=653  20$aEffective modulus.
=700  1\$aOshima, N., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10303J.htm

=LDR  03570nam  2200625 i 4500
=001  CTR10304J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10304J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10304J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKoyama, M., $eauthor.
=245  10$aLong-Term Characteristics of Fiber-Reinforced Plastic Under Mechanical Stress and an Acidic Environment / $cM Koyama, C De Tourreil.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 3 (September 1985)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aGlass fiber-reinforced plastic (GRP) rods are used in the manufacture of composite insulators for high voltage transmission lines. Should they come in contact with an acid solution their strength can be drastically reduced and the insulator may be unable to perform. Bending and tension tests are used to evaluate the long-term performance of GRP in contact with dilute sulfuric acid. The crack propagation velocity da/dt depends on the stress intensity factor KI. In both bending and tension tests the crack growth velocity is a linear function of KIn where the exponent n = 3.1. In both bending and tension tests, the total fracture time may be separated into an incubation time t1 and a propagation time t2 given by tf = t1 + t2 = (C1/pm) + [C2H( )/pn] where p is applied load, C1, C2, m, and n are constants, and H( ) is a constant that can be calculated from the initial crack length and the critical crack length.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAcid rain.
=650  \0$aComposite materials.
=650  \0$aGlass fiber-reinforced plastics.
=650  \0$aInsulation.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aGlass fiber-reinforced plastics.
=653  20$aComposite materials.
=653  20$aAcid rain.
=653  20$aInsulation.
=700  1\$aDe Tourreil, C., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10304J.htm

=LDR  03116nam  2200721 i 4500
=001  CTR10307J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10307J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10307J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aBlikstad, M., $eauthor.
=245  14$aThe Influence of Moisture and Toughened Resin on the Mixed Mode Fracture of Unidirectional Graphite/Epoxy Laminates / $cM Blikstad, TR Johannesson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 4 (December 1985)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aHygrothermal effects on the fracture toughness of unidirectional graphite/epoxy laminates of two different grades have been investigated. The material systems used are Fiberite T300/1034 and the more ductile Fibredux T300/920.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCrack propagation.
=650  \0$aCracks.
=650  \0$aDuctile matrix.
=650  \0$aFracture toughness.
=650  \0$aGraphite/epoxy.
=650  \0$aMixed mode.
=650  \0$aMoisture.
=650  \0$aUnidirectional.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aCrack propagation.
=653  20$aCracks.
=653  20$aMoisture.
=653  20$aGraphite/epoxy.
=653  20$aUnidirectional.
=653  20$aFracture toughness.
=653  20$aMixed mode.
=653  20$aDuctile matrix.
=700  1\$aJohannesson, TR., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10307J.htm

=LDR  03235nam  2200685 i 4500
=001  CTR10308J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19859999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10308J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10308J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aWood, JD., $eauthor.
=245  10$aDetection of Delamination Onset in a Composite Laminate Using Moiré Interferometry / $cJD Wood.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 4 (December 1985)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aMoiré interferometry was used to detect and measure delaminations in a graphite-epoxy composite laminate. The laminate used was a [(±30)2/¯9¯0]s layup. A uniform strain was subtracted from the full-field moiré pattern by changing the frequency of the reference grating. This technique accentuated the nonuniform strains allowing very high resolution measurements of strain concentrations. These strain concentrations include free-edge effects, resin rich regions and delaminations.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aDamage.
=650  \0$aDelamination.
=650  \0$aEdge effects.
=650  \0$aGraphite-epoxy.
=650  \0$aMoire interferometry.
=650  \0$aStrain concentrations.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMoiré interferometry.
=653  20$aDamage.
=653  20$aComposite materials.
=653  20$aGraphite-epoxy.
=653  20$aDelamination.
=653  20$aEdge effects.
=653  20$aStrain concentrations.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10308J.htm

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=001  CTR10309J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10309J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10309J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aChamis, CC., $eauthor.
=245  10$aLongitudinal Compressive Failure Modes in Fiber Composites : $bEnd Attachment Effects on IITRI Type Test Specimens / $cCC Chamis, JH Sinclair.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 4 (December 1985)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe end-attachment effects on longitudinal compressive strength of IITRI type specimen unidirectional fiber composites are formally assessed using finite-element analysis (FEA) in conjunction with composite mechanics. Sixteen different cases were analyzed to evaluate end-attachment effects (such as degree of misalignment, type of misalignment, progressive end-tab debonding, and specimen thickness) on stress distribution, peak stresses, buckling loads, and buckling mode shapes. The results obtained from the FEA and comparisons with fractured specimens show that eccentricities induce bending-type stresses which peak near the end-tabs and cause flexural type fracture. Also, guidelines are included for placing back-to-back strain gages to measure the presence/absence of possible end-attachment and eccentricity effects.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompressive strength.
=650  \0$aEpoxy.
=650  \0$aFibers.
=650  \0$aFracture modes.
=650  \0$aStresses.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aCompressive strength.
=653  20$aFibers.
=653  20$aStresses.
=653  20$aEpoxy.
=653  20$aFracture modes.
=700  1\$aSinclair, JH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10309J.htm

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=001  CTR10310J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10310J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10310J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aGuess, TR., $eauthor.
=245  10$aComparison of Interlocked Fabric and Laminated Fabric Kevlar 49/Epoxy Composites / $cTR Guess, ED Reedy.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1985.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 7, Issue 4 (December 1985)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe mechanical properties of a multilayered, interlocked Kevlar 49 fabric reinforced epoxy composite with roughly a 4% fiber volume fraction in the through-the-thickness direction are reported. These results are compared to those of a standard Kevlar fabric laminate containing the same overall fiber volume fraction. Through-the-thickness reinforcement increases the apparent short beam shear strength by 25%. Actually, the shear failure mode is suppressed by the through-the-thickness reinforcement, and failure is due to yarn kinking on the compressive side of the beam. In contrast, the in-plane properties of the interlocked fabric reinforced composite are lower than those of the standard fabric laminate. For example, the initial tensile modulus is reduced by 35% while the ultimate tensile strength is reduced by roughly 25%. This loss in properties is thought to be due to both the relatively greater crimp in the interlocked fabric used in this study and fiber stress concentrations introduced by the binder yarns.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1985. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy laminates.
=650  \0$aFabric laminates.
=650  \0$aInterlocked fabric.
=650  \0$aMechanical properties.
=650  \0$aShear strength.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aEpoxy laminates.
=653  20$aFabric laminates.
=653  20$aShear strength.
=653  20$aMechanical properties.
=653  20$aKevlar composites.
=653  20$aInterlocked fabric.
=700  1\$aReedy, ED., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10310J.htm

=LDR  04012nam  2200697 i 4500
=001  CTR10314J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19869999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10314J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10314J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aJohnson, WS., $eauthor.
=245  10$aInfluence of Interface Ply Orientation on Fatigue Damage of Adhesively Bonded Composite Joints / $cWS Johnson, S Mall.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 1 (March 1986)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn experimental study of cracked-lap-shear specimens was conducted to determine the influence of adherend stacking sequence on debond initiation and damage growth in a composite-to-composite bonded joint. Specimens consisted of quasi-isotropic graphite/epoxy adherends bonded together with either FM-300 or EC 3445 adhesives. The stacking sequence of the adherends was varied such that 0°, 45°, or 90° plies were present at the adherend-adhesive interfaces. Fatigue damage initiated in the adhesive layer in those specimens with 0° and 45° interface plies. Damage initiated in the form of ply cracking in the strap adherend for the specimens with 90° interface plies. The fatigue-damage growth was in the form of delamination within the composite adherends for specimens with the 90° and 45° plies next to the adhesive, while debonding in the adhesive resulted for the specimens with 0° plies next to the adhesive. Those joints with the 0° and 45° plies next to either adhesive had essentially the same fatigue-damage-initiation stress levels. These stress levels were 13 and 71% higher, respectively, than those for specimens with 90° plies next to the EC 3445 and FM-300 adhesives.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive bonding.
=650  \0$aComposite materials.
=650  \0$aDebonding.
=650  \0$aDelamination.
=650  \0$aFatigue (materials)
=650  \0$aFracture mechanics.
=650  \0$aStacking sequence.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aAdhesive bonding.
=653  20$aComposite materials.
=653  20$aDelamination.
=653  20$aDebonding.
=653  20$aStacking sequence.
=653  20$aFatigue (materials).
=653  20$aFracture mechanics.
=700  1\$aMall, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10314J.htm

=LDR  04602nam  2201045 i 4500
=001  CTR10315J
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=008  161219c19869999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10315J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10315J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aMurthy, PLN, $eauthor.
=245  10$aICAN : $bIntegrated Composites Analyzer / $cPLN Murthy, CC Chamis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 1 (March 1986)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA computer code, ICAN (Integrated Composites Analyzer), has been developed to analyze/design fiber composite structures. The program includes composite mechanics theories that resulted from extensive research that has been conducted over the past 15 years at the National Aeronautics and Space Administration (NASA) Lewis Research Center. These theories account for environmental effects and are applicable to intraply hybrid composites, interply hybrid composites and combinations of these, as well as conventional laminate analysis. Key features and capabilities of ICAN are described. A sample input data set and selected output are provided to illustrate its generality/versatility and user friendly structure.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite mechanics.
=650  \0$aComputer codes.
=650  \0$aData base.
=650  \0$aDelamination.
=650  \0$aEnvironmental effects.
=650  \0$aFailure criteria.
=650  \0$aFree edge stresses.
=650  \0$aHygothermal degradation.
=650  \0$aHygothermomechanical response.
=650  \0$aHygral properties.
=650  \0$aInfluence coefficients.
=650  \0$aInterply hybrid composites.
=650  \0$aIntraply hybrid composites.
=650  \0$aLaminate analysis.
=650  \0$aMacromechanics.
=650  \0$aMechanical properties.
=650  \0$aMicromechanics.
=650  \0$aMicrostresses.
=650  \0$aStress concentration factor.
=650  \0$aStructural analysis.
=650  \0$aThermal properties.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComputer codes.
=653  20$aComposite mechanics.
=653  20$aMicromechanics.
=653  20$aMacromechanics.
=653  20$aStructural analysis.
=653  20$aStress concentration factor.
=653  20$aFree edge stresses.
=653  20$aHygothermomechanical response.
=653  20$aInfluence coefficients.
=653  20$aLaminate analysis.
=653  20$aMicrostresses.
=653  20$aHygothermal degradation.
=653  20$aDelamination.
=653  20$aFailure criteria.
=653  20$aEnvironmental effects.
=653  20$aIntraply hybrid composites.
=653  20$aInterply hybrid composites.
=653  20$aMechanical properties.
=653  20$aThermal properties.
=653  20$aHygral properties.
=653  20$aData base.
=700  1\$aChamis, CC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10315J.htm

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=001  CTR10316J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10316J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10316J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRebello, CJ., $eauthor.
=245  10$aFactors Influencing the Ultrasonic Stress Wave Factor Evaluation of Composite Material Structures / $cCJ Rebello, JC Duke.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 1 (March 1986)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSome of the factors influencing the stress wave factor measurement and other integrative techniques are boundary conditions, type of damage, severity of damage, and area of damage. This paper suggests that a finite-element model can be used to study some of the factors influencing the ultrasonic stress wave evaluation of materials. To demonstrate this, a hypothetical case of the resonant frequencies on damaged and undamaged plates was studied. Finite-element modeling, which is the most widely used technique for incorporating local discontinuities, was used. The first step was to check the conformity of the finite-element results with those obtained experimentally and by exact methods. This was attained by studying the resonant frequencies of two undamaged plates, which were simply supported on all edges. The two plates studied were a 0.2667- by 0.2667- by 0.003175-m, aluminum plate and a 0.2667- by 0.2667- by 0.0001036-m graphite-epoxy (08) plate. Good correlation was obtained between the approximate and exact methods (within 8%). The frequencies predicted by the finite-element model were observed in the experiment with the aluminum and graphite-epoxy plates. Additional frequencies were observed in the graphite-epoxy plate, which could not be accounted for.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aDesign applications.
=650  \0$aExperimental analysis.
=650  \0$aFinite-element analysis.
=650  \0$aResonant frequency.
=650  \0$aStress waves.
=650  \0$aVibration.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aStress waves.
=653  20$aResonant frequency.
=653  20$aVibration.
=653  20$aFinite-element analysis.
=653  20$aExperimental analysis.
=653  20$aDesign applications.
=700  1\$aDuke, JC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10316J.htm

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=024  7\$a10.1520/CTR10317J$2doi
=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aJohnson, LL., $eauthor.
=245  10$aComposite Standards Activities of the Society of Automotive Engineers / $cLL Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 1 (March 1986)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe Composite Committee of the Aerospace Materials Division of the Society of Automotive Engineers (SAE) is actively involved in the development and publication of composite material standards. Currently 150 specifications covering composite materials or processes are published, including 40 new or revised specifications being added in the past year. Participants in this composite specification development include representatives from leading aerospace and defense contractors, from the principal government military agencies, as well as from major manufacturers of these materials, representing the viewpoints of user, consumer, producer, and regulator.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aComposite processes.
=650  \0$aStandards.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aStandards.
=653  20$aComposite materials.
=653  20$aComposite processes.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10317J.htm

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=037  \\$aCTR10320J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aO'Brien, TK., $eauthor.
=245  10$aResidual Thermal and Moisture Influences on the Strain Energy Release Rate Analysis of Edge Delamination / $cTK O'Brien, IS Raju, DP Garber.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 2 (June 1986)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA laminated plate theory analysis is developed to calculate the strain energy release rate associated with edge delamination growth in a composite laminate. The analysis includes the contribution of residual thermal and moisture stresses to the strain energy released. The strain energy release rate G increased when residual thermal effects were combined with applied mechanical strains, but then decreased when increasing moisture content was included. A quasi-three-dimensional finite-element analysis indicated identical trends and demonstrated these same trends for the individual strain energy release rate components. G1 and G11, associated with interlaminar tension and shear. An experimental study indicated that for T300/5208 graphiteepoxy composites, the inclusion of residual thermal and moisture stresses did not significantly alter the calculation of interlaminar fracture toughness from strain energy release rate analysis of edge delamination data taken at room-temperature ambient conditions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDelamination.
=650  \0$aFracture mechanics.
=650  \0$aGraphite composites.
=650  \0$aGraphite epoxy.
=650  \0$aMoisture.
=650  \0$aResidual stress.
=650  \0$aStrain energy release rate.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aResidual stress.
=653  20$aMoisture.
=653  20$aGraphite composites.
=653  20$aStrain energy release rate.
=653  20$aDelamination.
=653  20$aGraphite epoxy.
=653  20$aFracture mechanics.
=700  1\$aRaju, IS., $eauthor.
=700  1\$aGarber, DP., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10320J.htm

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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.F5
=082  04$a620/.5$223
=100  1\$aBoll, DJ., $eauthor.
=245  10$aCharacterizing Matrix Resin Flow in Carbon Fiber Prepreg / $cDJ Boll, B Motiee, WD Bascom.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 2 (June 1986)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA study was made of a tetraglycidylmethylene dianiline (TGMDA) matrix prepreg and a diglycidylether of bisphenol A (DGEBA) matrix prepreg with various carbon fibers using parallel plate dynamic mechanical spectroscopy (DMS). The matrix resins were also tested. The neat resin DMS indicates large changes in resin viscosity during cure that are not reflected in the corresponding prepreg spectra. Thus, the local flow of resin between fiber tows and plys, which is critically important to the compaction and consolidation of prepreg during vacuum bag/autoclave curing, cannot be characterized from prepreg samples with the type of rheometer now in wide use in the continuous fiber composite industry.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber composites.
=650  \0$aFiber tows.
=650  \0$aMatrix composites.
=650  \0$aPolymers.
=650  \0$aPrepreg plys.
=650  \0$aEngineering materials.
=650  \0$aOrganic polymers.
=653  10$aPolymers.
=653  20$aMatrix composites.
=653  20$aFiber composites.
=653  20$aFiber tows.
=653  20$aPrepreg plys.
=700  1\$aMotiee, B., $eauthor.
=700  1\$aBascom, WD., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10321J.htm

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=024  7\$a10.1520/CTR10322J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10322J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aMall, S., $eauthor.
=245  10$aFinite-Element Analysis of End-Notch Flexure Specimens / $cS Mall, NK Kochhar.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 2 (June 1986)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA finite-element analysis of the end-notch flexure speciment for Mode II interlaminar fracture toughness measurement was conducted. The effects of friction between the crack faces and large deflection on the evaluation of GIIc from this specimen were investigated. Results of this study are presented in this paper.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCracks.
=650  \0$aDelamination.
=650  \0$aEndnotch flexure specimen.
=650  \0$aInterlaminar fracture toughness.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aInterlaminar fracture toughness.
=653  20$aDelamination.
=653  20$aEndnotch flexure specimen.
=653  20$aCracks.
=700  1\$aKochhar, NK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10322J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10323J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10323J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.F5
=082  04$a620/.5$223
=100  1\$aMangalgiri, PD., $eauthor.
=245  10$aPreliminary Design of Cracked-Lap Shear Specimen Thickness for Determination of Interlaminar Fracture Toughness / $cPD Mangalgiri, WS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 2 (June 1986)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper outlines a technique for preliminary sizing of the adherends for cracked-lap-shear specimen to assure delamination instead of adherend failure. The cracked-lap-shear specimen is a popular specimen used for determination of mixed mode interlaminar fracture toughness of composites. Thin adherends, on the order of three plies thick, have been used successfully in the past for determination of fracture toughness of rather brittle matrix systems. However, the tougher matrices now being considered for composite applications require thicker adherends in order to get composite delamination rather than adherend failure. The optimum thickness is obtained on the basis that the critical value of the strain energy release rate is reached at the delamination front before the ultimate strength is reached in the adherend. By proper design the specimen would delaminate and not use excessive material or load. A simple analysis for the optimum adherend thickness and experimental verification are included.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAerospace industry.
=650  \0$aFracture toughness.
=650  \0$aPolymers.
=650  \0$aThickness.
=650  \0$aEngineering materials.
=650  \0$aOrganic polymers.
=653  10$aPolymers.
=653  20$aFracture toughness.
=653  20$aAerospace industry.
=653  20$aThickness.
=700  1\$aJohnson, WS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10323J.htm

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=001  CTR10326J
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=007  cr\\\\\\\\\\\\
=008  161219c19869999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10326J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10326J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aCaruso, JJ., $eauthor.
=245  10$aAssessment of Simplified Composite Micromechanics Using Three-Dimensional Finite-Element Analysis / $cJJ Caruso, CC Chamis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 3 (September 1986)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThree-dimensional finite-element analyses are used to assess the accuracy of simplified composite micromechanics equations (SME) for hygral, thermal, and mechanical properties of unidirectional composites with orthotropic fibers. The properties predicted by the SME are in reasonably good agreement with those predicted by the three-dimensional finite-element analyses. This correlation demonstrates that the SME can be used with confidence in predicting the hygral, thermal, and mechanical behavior of unidirectional fiber composites.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aMicromechanics equations.
=650  \0$aMicromechanics properties.
=650  \0$aOrthotropic fibers.
=650  \0$aSupplement analysis.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aMicromechanics equations.
=653  20$aOrthotropic fibers.
=653  20$aMicromechanics properties.
=653  20$aAS-graphite epoxy.
=653  20$aSupplement analysis.
=700  1\$aChamis, CC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10326J.htm

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=007  cr\\\\\\\\\\\\
=008  161219c19869999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10327J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10327J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSharif-Bakhtiar, M., $eauthor.
=245  10$aPreliminary Noise Control Guidelines for the Design of High-Speed Machinery / $cM Sharif-Bakhtiar, BS Thompson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 3 (September 1986)
=504  \\$aIncludes bibliographical references$b29.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aGovernment regulations limiting the acoustical noise radiation from machinery have further complicated the already complex design process associated with successfully synthesizing high-speed mechanism systems. This is because few design guidelines exist for noise control purposes. This experimental comparative study demonstrates how the surface accelerations of the links of a four-bar linkage and the level of acoustical radiation from the mechanism may be reduced by fabricating the members from composite materials possessing both high values of material damping and also large stiffness-to-weight ratios. This is the first design guideline. The investigation is based on a four-bar linkage with clearance in the coupler-rocker joint, and the apparatus accommodates flexible link specimens of different materials. Experimental results are presented for the dynamic deflections of the flexible links and also the impactive excitation at the coupler-rocker joint. The second design guideline distilled from the study is that the noise radiation from a machine may be qualitatively evaluated by performing an elastodynamic simulation of the mechanism, rather than undertaking a complex coupled acoustoelastodynamic analysis of the complete mechanical-fluid system.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aFlexible linkages.
=650  \0$aLaminates.
=650  \0$aMechanisms.
=650  \0$aNoise control.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aNoise control.
=653  20$aFlexible linkages.
=653  20$aMechanisms.
=653  20$aComposites.
=653  20$aLaminates.
=700  1\$aThompson, BS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10327J.htm

=LDR  03416nam  2200649 i 4500
=001  CTR10328J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19869999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10328J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10328J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aFunk, JG., $eauthor.
=245  14$aThe Effects of Radiation on the Interlaminar Fracture Toughness of a Graphite/Epoxy Composite / $cJG Funk, GF Sykes.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 3 (September 1986)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effects of electron radiation on the interlaminar fracture toughness of a graphite/epoxy (T300/934) composite were investigated using the double cantilever beam (DCB) test to determine the Mode I critical strain energy release rate GIc and the edge delamination tension (EDT) test to determine the mixed Mode I and II critical strain energy release rate Gc. The effects of test temperature on the Gc of both the nonirradiated and irradiated material were determined. A miniature DCB and EDT test specimen was developed, and the results from the miniature specimens were compared with those from standard DCB and EDT test specimen geometries.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCritical strain energy release rates.
=650  \0$aGraphite/epoxy.
=650  \0$aInterlaminar fracture toughness.
=650  \0$aRadiation effects.
=650  \0$aSpecimen geometry.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aInterlaminar fracture toughness.
=653  20$aRadiation effects.
=653  20$aGraphite/epoxy.
=653  20$aSpecimen geometry.
=653  20$aCritical strain energy release rates.
=700  1\$aSykes, GF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10328J.htm

=LDR  03291nam  2200625 i 4500
=001  CTR10329J
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=024  7\$a10.1520/CTR10329J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10329J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aNK4870
=082  04$a736/.7/094$223
=100  1\$aLark, RF., $eauthor.
=245  10$aFabrication and Quality Assurance Processes for Superhybrid Composite Fan Blades / $cRF Lark, CC Chamis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 3 (September 1986)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn investigation was conducted to evaluate the feasibility of fabricating full-scale fan blades from superhybrid composites (SHC) for use in large commercial gas turbine engines. The type of blade construction selected was a metal-spar/SHC-shell configuration, in which the outer shell was adhesively bonded to a short, internal, titanium spar. This report describes various aspects of blade fabrication, inspection, and quality assurance procedures developed in the investigation. Conclusions from this investigation indicate that the SHC concept is feasible for the fabrication of prototype, full-scale, metal-spar/SHC-shell fan blades that have good structural properties and meet dimensional requirements.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBlade fabrication.
=650  \0$aFans.
=650  \0$aStructural properties.
=650  \0$aSuperhybrid composites.
=650  \0$aQuality Assurance.
=650  \0$aFabrication.
=653  10$aSuperhybrid composites.
=653  20$aFans.
=653  20$aBlade fabrication.
=653  20$aStructural properties.
=700  1\$aChamis, CC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10329J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10330J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10330J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aKasen, MB., $eauthor.
=245  10$aHigh Quality Organic Matrix Composite Specimens for Research Purposes / $cMB Kasen.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 3 (September 1986)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn efficient method for producing and testing organic-matrix composite specimens for research purposes is described. The production method is adaptable to in-house manufacturing and provides complete control over a large variety of material and processing variables. The rod-shape, uniaxially reinforced or neat-resin specimens may be cut to length and tested without further machining. Conventional short-beam shear, flexural strength, and compression test methods may be used. Development of test methods for performing torsional shear tests and for determining the fracture energy GIc are described. Test results at room temperature and at cryogenic temperature are presented.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCryogenics.
=650  \0$aFiber-reinforced specimens.
=650  \0$aFracture energy.
=650  \0$aNeat resin specimens.
=650  \0$aOrganic-matrix composites.
=650  \0$aResearch specimen production.
=650  \0$aShort-beam shear.
=650  \0$aTest methodology.
=650  \0$aTorsional shear.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aCryogenics.
=653  20$aFiber-reinforced specimens.
=653  20$aFracture energy.
=653  20$aNeat resin specimens.
=653  20$aOrganic-matrix composites.
=653  20$aResearch specimen production.
=653  20$aShort-beam shear.
=653  20$aTest methodology.
=653  20$aTorsional shear.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10330J.htm

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=024  7\$a10.1520/CTR10331J$2doi
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=037  \\$aCTR10331J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.E6
=082  04$a668/.374$223
=100  1\$aPapirno, R., $eauthor.
=245  10$aAverage Stress-Strain Curves for Resin Matrix Composites / $cR Papirno.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 3 (September 1986)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThere is a substantial government and industry cooperative effort to document the mechanical properties of advanced composites materials. As part of this effort the stress-strain properties for these materials are being measured. In this paper some initial results are presented. Average stress-strain curves are given for a number of resin-matrix composites reinforced with S2 Glass, AS4 carbon, and T300 carbon fibers and Kevlar 285-weave cloth. There are data for tension, compression, and in-plane shear. Individual curves are given for various environmental conditioning treatments before testing. A total of 43 separate stress-strain curves are presented in 20 figures. Analytical expressions for each of the curves are given with the appropriate constants. The majority of curves presented are discontinuous and are best described by two-part functions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression.
=650  \0$aFiber reinforced epoxy.
=650  \0$aIn-plane shear.
=650  \0$aStress-strain curves.
=650  \0$aTension.
=650  \0$aEpoxy resins.
=650  \7$aTECHNOLOGY & ENGINEERING / Chemical & Biochemical.
=653  10$aStress-strain curves.
=653  20$aTension.
=653  20$aCompression.
=653  20$aIn-plane shear.
=653  20$aFiber reinforced epoxy.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10331J.htm

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=024  7\$a10.1520/CTR10334J$2doi
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=037  \\$aCTR10334J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aWang, SS., $eauthor.
=245  10$aDeformation and Fracture of Random Short-Fiber SMC Composite Under Multiaxial Loading / $cSS Wang, A Dasgupta.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 4 (December 1986)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aMultiaxial deformation and failure behavior of a random short-fiber sheet molding compound (SMC) composite are studied. Experiments are conducted on an SMC-R50 glass-fiber reinforced polyester composite system under various combinations of multiaxial stresses. A sandwich specimen, consisting of SMC-R50 composite face plates adhesively bonded with aluminum honeycomb core, is specially designed for the multiaxial test. Analytical and numerical studies are performed to insure proper specimen design and to determine multiaxial stress in the SMC composite during deformation and fracture. The analytical study is formulated on the basis of elastic theory of bending and torsion of a multiphase composite system with the aid of a finite-element technique. The general nature and unique characteristics of the SMC-R50 composite deformation and fracture under multiaxial loading are determined. A multiaxial stress failure criterion for the composite material is also obtained from the test and analysis of the sandwich specimen.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBending torsion experiment.
=650  \0$aFailure criterion.
=650  \0$aFiber composites.
=650  \0$aMultiaxial fracture.
=650  \0$aTheoretical analysis.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFiber composites.
=653  20$aMultiaxial fracture.
=653  20$aFailure criterion.
=653  20$aBending torsion experiment.
=653  20$aTheoretical analysis.
=700  1\$aDasgupta, A., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10334J.htm

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=024  7\$a10.1520/CTR10335J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10335J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNahas, MN., $eauthor.
=245  10$aSurvey of Failure and Post-Failure Theories of Laminated Fiber-Renforced Composites / $cMN Nahas.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (16 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 4 (December 1986)
=504  \\$aIncludes bibliographical references$b86.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper reviews the existing theories of failure of laminated fiber-reinforced composite materials. The failure theories of isotropic materials are also reviewed. There exist at least 30 failure theories for laminated composites. Some of these theories are applied directly to the laminate while the rest of the theories are applied to the individual layers of the laminate. In addition, the paper reviews the theories of the post-failure behavior of laminated composites, that is, the behavior of laminated composites beyond first ply failure. For this analysis there exist at least twelve theories, which are included in this survey.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFailure criteria.
=650  \0$aFailure theories.
=650  \0$aLamina strength.
=650  \0$aLaminate strength.
=650  \0$aLaminates.
=650  \0$aPost-failure theories.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aFailure theories.
=653  20$aFailure criteria.
=653  20$aPost-failure theories.
=653  20$aLamina strength.
=653  20$aLaminate strength.
=653  20$aLaminates.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10335J.htm

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=024  7\$a10.1520/CTR10336J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10336J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aR857.M3
=082  04$a610.28$223
=100  1\$aTsiang, T-H, $eauthor.
=245  10$aSurvey of Sand and Rain Erosion of Composite Materials / $cT-H Tsiang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 4 (December 1986)
=504  \\$aIncludes bibliographical references$b58.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA survey of sand and rain erosion of polymeric composites is presented. The testing techniques and results are gathered from 61 papers and reports. The analytical methods of solid and liquid particle erosion are reviewed and discussed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnalytical method.
=650  \0$aErosion mechanisms.
=650  \0$aPolymeric composite materials.
=650  \0$aRain erosion.
=650  \0$aReviews.
=650  \0$aSand erosion.
=650  \0$aTesting techniques.
=650  \0$aPolymeric composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xBiomedical.
=653  10$aReviews.
=653  20$aSand erosion.
=653  20$aRain erosion.
=653  20$aPolymeric composite materials.
=653  20$aTesting techniques.
=653  20$aAnalytical method.
=653  20$aErosion mechanisms.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10336J.htm

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=024  7\$a10.1520/CTR10337J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10337J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA664
=082  04$a620.1/18$223
=100  1\$aReifsnider, KL., $eauthor.
=245  12$aA Stiffness-Based Approximate Method for Sizing of Nonuniform-Thickness Sandwich Components / $cKL Reifsnider, T Loumont.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 4 (December 1986)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe application of composite materials to a variety of commercial components is growing rapidly. A convenient construction technique for large panels and structures is sandwich construction, especially for such things as lightly loaded fuselage structures, platforms, doors, hatches, bulkheads, and other structural parts. A variety of sizing techniques for these components is available. The present technical note suggests an unusually straightforward approximate method to size certain components with nonuniform thickness and offers the advantages of simple visualization, close association with engineering performance, exploitation of previous analytical and computational results, and ease of application of the method. The concept is based on the idea of sizing simply supported nonuniform thickness components subjected to out-of-plane distributed loading in proportion to the deflection under the same loading of uniform thickness components with the same geometry.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite beams.
=650  \0$aComposite plates.
=650  \0$aNonuniform thickness.
=650  \0$aOptimization.
=650  \0$aSandwich construction.
=650  \0$aStiffness.
=650  \0$aComposite materials.
=650  \0$aComposite construction.
=653  10$aNonuniform thickness.
=653  20$aSandwich construction.
=653  20$aComposite beams.
=653  20$aComposite plates.
=653  20$aOptimization.
=653  20$aStiffness.
=700  1\$aLoumont, T., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10337J.htm

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=001  CTR10338J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10338J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10338J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aReedy, ED., $eauthor.
=245  10$aAdditional Comparisons of Interlocked Fabric and Laminated Fabric Kevlar 49/Epoxy Composites / $cED Reedy, TR Guess.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1986.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 8, Issue 4 (December 1986)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aCompression, gas gun planar impact, and post-impact short beam shear test results are presented for a novel interlocked fabric reinforced Kevlar 49/epoxy composite. This material has roughly 4% fiber volume fraction in the through-the-thickness direction. For the purpose of comparison, similar results are also presented for a laminated Kevlar 49/epoxy composite. Both materials have a compressive stress-strain curve that can be approximated as bilinear with a secondary modulus of on the order of 10% of the initial modulus. Although the materials have comparable yield strengths (∼ 10% difference), their respective initial and secondary moduli are not in as close agreement (up to 50% difference). Gas gun planar impact spall test data indicate that relatively low levels of impact stress (∼1 kbar, ∼100 MPa) generate matrix cracking in both materials. The interlocked fabric's binder yarns, however, show no visible sign of damage even at an impact stress level of 5.1 kbar (510 MPa). Post-impact short beam shear test data for both materials show that once a threshold impact level is exceeded (∼1 kbar, ∼100MPa), specimen stiffness and load carrying capacity decrease as the impact level is increased. This is presumably because of mid-plane matrix cracks of increasing size and density. Even though the properties of the interlocked fabric reinforced composite are substantially reduced by impact at the 5.1-kbar (510-MPa) level, the binder yarns give the material a degree of integrity that would not otherwise exist. The interlocked fabric reinforced Kevlar 49/epoxy composite has a higher residual load carrying capacity than the laminated Kevlar 49/epoxy at all impact levels.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1986. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression.
=650  \0$aEpoxy laminates.
=650  \0$aFiber laminates.
=650  \0$aImpact.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aFiber laminates.
=653  20$aCompression.
=653  20$aEpoxy laminates.
=653  20$aImpact.
=700  1\$aGuess, TR., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10338J.htm

=LDR  04362nam  2200685 i 4500
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aJayaraman, K., $eauthor.
=245  10$aElastic and Thermal Effects in the Interphase : $bPart I. Comments on Characterization Methods / $cK Jayaraman, KL Reifsnider, RE Swain.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 1 (March 1993)
=504  \\$aIncludes bibliographical references$b46.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe complexity of the fiber-matrix interphase in a composite is largely due to the myriad of variables (material, processing, and design) that affect its formation. The interphase, thus formed, has to be characterized at several levels (microstructural, chemical, and mechanical) for one to understand fully the nature of the bond between the fiber and matrix and perform a stress analysis of the fiber-interphase-matrix assemblage. A cursory glance at the literature shows that great progress has been made in all of the three levels of characterization mentioned above for various composite systems. The progress in mechanical characterization is manifested in the development of several methods of interphasial shear strength measurement and a better understanding of the local failure process, which often initiates global composite failure. A thorough thermomechanical characterization of the interphase is difficult, at present, because of the necessity of studying the interphase in situ, its small dimension (usually on the order of a micrometer), and its general complexity. This article presents a brief review of the principal interphasial characterization methods (microstructural, chemical, and mechanical) and discusses several recent techniques for the physical characterization (evaluation of volume fraction, thickness, Young's modulus, shear modulus, and coefficient of thermal expansion) of the interphase.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFiber-matrix adhesion.
=650  \0$aFiber-matrix interface.
=650  \0$aFiber-matrix interphase.
=650  \0$aInterphasial property characterization.
=650  \0$aUnidirectional fiber composites.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aUnidirectional fiber composites.
=653  20$aFiber-matrix adhesion.
=653  20$aFiber-matrix interface.
=653  20$aFiber-matrix interphase.
=653  20$aInterphasial property characterization.
=700  1\$aReifsnider, KL., $eauthor.
=700  1\$aSwain, RE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10348J.htm

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=001  CTR10349J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10349J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10349J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aJayaraman, K., $eauthor.
=245  10$aElastic and Thermal Effects in the Interphase : $bPart II. Comments on Modeling Studies / $cK Jayaraman, KL Reifsnider, RE Swain.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 1 (March 1993)
=504  \\$aIncludes bibliographical references$b41.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn Part I of this article, the authors have reviewed several methods of interphase characterization; the review consisted of principal interphasial characterization methods and several recent techniques for the physical characterization (evaluation of thickness, volume fraction, Young's modulus, shear modulus, and coefficient of thermal expansion) of the interphase. Models of physical properties (thickness, Young's modulus, Poisson's ratio, and coefficient of thermal expansion) of the interphase have been considered by several researchers in an effort to study the influence of the interphase on overall composite properties and behavior. Hypotheses on interphase formation and properties have been proposed and tested by some researchers. This article presents a review of these interphase models and discusses their salient features. Both experimental characterization as well as modeling studies are necessary to achieve a more profound understanding of the interphase and its behavior.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFiber-matrix adhesion.
=650  \0$aFiber-matrix interface.
=650  \0$aFiber-matrix interphase.
=650  \0$aInterphasial property modeling.
=650  \0$aUnidirectional fiber composites.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aUnidirectional fiber composites.
=653  20$aFiber-matrix adhesion.
=653  20$aFiber-matrix interface.
=653  20$aFiber-matrix interphase.
=653  20$aInterphasial property modeling.
=700  1\$aReifsnider, KL., $eauthor.
=700  1\$aSwain, RE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10349J.htm

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=001  CTR10350J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10350J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10350J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aShembekar, PS., $eauthor.
=245  10$aElastic Analysis of Woven Fabric Laminates : $bPart I. Off-Axis Loading / $cPS Shembekar, NK Naik.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 1 (March 1993)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aTwo-dimensional woven fabric composite models are presented for the elastic analysis of orthogonal plain weave fabric lamina/laminate. Yarn continuity along both warp and fill directions and the actual yarn cross-sectional geometry and fabric geometry are considered in the analysis. Off-axis elastic properties are determined by coordinate transformation. Comparison is made between the off-axis elastic properties of plain weave fabric laminates and cross-ply laminates. It is found that the elastic properties of the plain weave fabric laminates are superior as compared to those of equivalent cross-ply laminates over a large range of off-axis angles.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aOff-axis loading.
=650  \0$aOff-axis range.
=650  \0$aTwo-dimensional woven fabric composite models.
=650  \0$aWoven fabric composites.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aWoven fabric composites.
=653  20$aTwo-dimensional woven fabric composite models.
=653  20$aOff-axis loading.
=653  20$aOff-axis range.
=700  1\$aNaik, NK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10350J.htm

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=001  CTR10351J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10351J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10351J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNaik, NK., $eauthor.
=245  10$aElastic Analysis of Woven Fabric Laminates : $bPart II. Mixed Composites / $cNK Naik, PS Shembekar.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 1 (March 1993)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aMixed composites are formed by the combination of unidirectional tapes and woven fabrics. In this paper, a method is presented for predicting the elastic properties of mixed composites. The elastic properties of the mixed composites are compared with those of equivalent unidirectional composites. It was found that, along with impact and postimpact properties, mixed composites can also offer higher elastic properties than equivalent unidirectional composites.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aMixed composites.
=650  \0$aTwo-dimensional woven fabric composite models.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aMixed composites.
=653  20$aTwo-dimensional woven fabric composite models.
=700  1\$aShembekar, PS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10351J.htm

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=001  CTR10352J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10352J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10352J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aDelfosse, D., $eauthor.
=245  10$aInstrumented Impact Testing at High Velocities / $cD Delfosse, G Pageau, R Bennett, A Poursartip.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 1 (March 1993)
=504  \\$aIncludes bibliographical references$b23.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aImpact loading of carbon fiber-reinforced plastic (CFRP) aicraft parts is a major concern. Birds or hailstones striking an aircraft generally have a low mass and a high velocity, whereas typically instrumented impact experiments are performed with a high mass and a low velocity. Our aim has been to build an instrumented impact facility with a low-mass projectile capable of simulating these impact events, since there is evidence that a low-velocity impact will not always result in the same amount or even type of damage as a high-velocity impact.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon fiber-reinforced plastic.
=650  \0$aComposite materials.
=650  \0$aInstrumented impact testing.
=650  \0$aLow-mass impact.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aInstrumented impact testing.
=653  20$aLow-mass impact.
=653  20$aComposite materials.
=653  20$aCarbon fiber-reinforced plastic.
=700  1\$aPageau, G., $eauthor.
=700  1\$aBennett, R., $eauthor.
=700  1\$aPoursartip, A., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10352J.htm

=LDR  04217nam  2200757 i 4500
=001  CTR10353J
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=005  20161219163000.0
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=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10353J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10353J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.7
=082  04$a620.1/126$223
=100  1\$aSalivar, GC., $eauthor.
=245  14$aThe Influence of Stress Ratio and Temperature on the Fatigue Crack Growth Rate Behavior of ARALL® / $cGC Salivar, CA Gardini.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 1 (March 1993)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe fatigue crack growth rate behavior of ARALL® (aramid-reinforced aluminum laminate) was investigated as a function of stress ratio and temperature. The particular material was ARALL-3, a 7475-T76 aluminum alloy laminate. Tests were conducted for stress ratios of 0.1 and 0.5 at temperatures of 21, 82, and 93°C (70, 180, and 200°F) using a center-cracked panel geometry (measurements were made in English units and converted to SI units). The objective was to examine the contributions of the effects of crack closure and fiber bridging of the crack on the material behavior. Crack closure was monitored throughout the tests using compliance measurements. Fractography was used to investigate the influence of temperature on the integrity of the aluminum to epoxy/fiber bond to try to identify the effects of fiber bridging. Some crack closure, in the traditional metallic material sense, was evident through compliance measurements. However, the crack tip bridging by the fibers appears to be the dominant mechanism influencing the fatigue crack growth rate behavior in this material under these test conditions. Fractography indicates a considerable difference in fiber-bridging behavior between the room temperature and the elevated temperature tests.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAramid fibers.
=650  \0$aCompliance.
=650  \0$aComposite material.
=650  \0$aCrack closure.
=650  \0$aFatigue crack growth.
=650  \0$aFiber bridging.
=650  \0$aFractography.
=650  \0$aStress intensity range.
=650  \0$aStress ratio.
=650  \0$aMicrofractography.
=650  \0$aElectron microscopy.
=653  10$aComposite material.
=653  20$aFatigue crack growth.
=653  20$aStress intensity range.
=653  20$aARALL.
=653  20$aStress ratio.
=653  20$aCrack closure.
=653  20$aCompliance.
=653  20$aAramid fibers.
=653  20$aFiber bridging.
=653  20$aFractography.
=700  1\$aGardini, CA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10353J.htm

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=024  7\$a10.1520/CTR10354J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10354J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aHo, H., $eauthor.
=245  13$aAn Experimental Procedure for the Iosipescu Composite Specimen Tested in the Modified Wyoming Fixture / $cH Ho, M-Y Tsai, J Morton, GL Farley.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 1 (March 1993)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA detailed description of the experimental procedure for testing composite Iosipescu specimens in the modified Wyoming fixture is presented. Specimen preparation and strain gage instrumentation are addressed. Interpretation of the experimental results is discussed. With the proper experimental setup and procedure, consistent and repeatable shear properties are obtained.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aModified Wyoming fixture.
=650  \0$aShear properties.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aIosipescu composite specimens.
=653  20$aIosipescu shear test.
=653  20$aModified Wyoming fixture.
=653  20$aShear properties.
=700  1\$aTsai, M-Y, $eauthor.
=700  1\$aMorton, J., $eauthor.
=700  1\$aFarley, GL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10354J.htm

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=024  7\$a10.1520/CTR10355J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10355J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aFilatovs, GJ., $eauthor.
=245  10$aSmall Specimen Technique for Composites Testing / $cGJ Filatovs, RL Sadler.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 1 (March 1993)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA test method has been developed for evaluating the mechanical properties of composites using small specimens with a test volume of ∼5 mm3. Mechanical testing can be performed in situ observing the specimen with scanning electron or optical microscopy. A description of the test system, associated test procedure, and fabrication procedure and tooling for the preparation of 48 000 fiber (four 12k tows) transverse tension specimens are given. Illustrative data are presented to indicate the capabilities of the technique. The method has potential for obtaining mechanical property profiles of thick section and inservice components, the study of microdefects, and obtaining through-the-thickness properties of a single ply.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon fiber/epoxy composites.
=650  \0$aFiber treatment.
=650  \0$aLow temperature plasma.
=650  \0$aSmall-scale tests.
=650  \0$aTest methods.
=650  \0$aTransverse testing.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aSmall-scale tests.
=653  20$aTransverse testing.
=653  20$aFiber treatment.
=653  20$aCarbon fiber/epoxy composites.
=653  20$aLow temperature plasma.
=653  20$aTest methods.
=700  1\$aSadler, RL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10355J.htm

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=001  CTR10358J
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=024  7\$a10.1520/CTR10358J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10358J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aReddy, YS., $eauthor.
=245  10$aThree-Dimensional Finite Element Progressive Failure Analysis of Composite Laminates Under Axial Extension / $cYS Reddy, JN Reddy.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (15 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 2 (June 1993)
=504  \\$aIncludes bibliographical references$b23.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA three-dimensional (3-D) progressive failure algorithm is developed where the Layerwise Laminate Theory of Reddy [1] is used for kinematic description. The finite element model based on the layerwise theory predicts both inplane and interlaminar stresses with the same accuracy as that of a conventional 3-D finite element model. Besides, it provides a convenient format for modeling the 3-D stress fields in composite laminates [2]. The progressive failure algorithm is based on the assumption that the material behaves like a stable progressively fracturing solid. The stiffness reduction is carried out at the reduced integration gauss points of the finite element mesh depending on the mode of failure. A parametric study is conducted to investigate the effect of out-of-plane material properties, 3-D stiffness reduction methods, and boundary conditions on the failure loads and strains of a composite laminate under axial extension. The results indicate that different parameters have a different degree of influence on the failure loads and strains. Finally, the predictive ability of various phenomenological failure criteria is evaluated in the light of experimental results available in the literature, and the predictions of the Layerwise Laminate Theory (LWLT) are compared with those of the First-Order Shear Deformation Theory (FSDT). The study concludes that a 3-D stress analysis is necessary to predict accurately the failure behavior of composite laminates.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite laminates.
=650  \0$aFailure criteria.
=650  \0$aFinite element method.
=650  \0$aLayerwise theory.
=650  \0$aProgressive failure analysis.
=650  \0$aStiffness reduction methods.
=650  \0$aFinite element analysis.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aComposite laminates.
=653  20$aFinite element method.
=653  20$aLayerwise theory.
=653  20$aProgressive failure analysis.
=653  20$aStiffness reduction methods.
=653  20$aFailure criteria.
=700  1\$aReddy, JN., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10358J.htm

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=001  CTR10359J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10359J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10359J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aSalpekar, SA., $eauthor.
=245  10$aAnalysis of Delamination in Cross-Ply Laminates Initiating from Impact Induced Matrix Cracking / $cSA Salpekar.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 2 (June 1993)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSeveral two-dimensional finite element analyses of (02/908/02) glass/epoxy and graphite/epoxy composite laminates were performed to investigate some of the characteristics of damage development due to an impact load. A cross section through the thickness of the laminate with fixed ends, and carrying a transverse load in the center, was analyzed. Inclined matrix cracks, such as those produced by a low-velocity impact, were modeled in the 90° ply group. The introduction of the matrix cracks caused large interlaminar tensile and shear stresses in the vicinity of both crack tips in the 0/90 and 90/0 interfaces. The large interlaminar stresses at the ends of the matrix cracks indicate that matrix cracking may give rise to delamination. The ratio of Mode I to total strain energy release rate, GI/Gtotal, at the beginning of delamination, calculated at the two (top and bottom) matrix crack tips was 60 and 28%, respectively, in the glass/epoxy laminate. The corresponding ratio was 97 and 77% in the graphite/epoxy laminate. Thus, a significant Mode I component of strain energy release rate may be present at the delamination initiation due to an impact load. The value of strain energy release rate at either crack tip increased due to an increase in the delamination length at the other crack tip and may give rise to an unstable delamination growth under constant load.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDelamination.
=650  \0$aFinite element analysis.
=650  \0$aImpact.
=650  \0$aMatrix crack.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aImpact.
=653  20$aDelamination.
=653  20$aMatrix crack.
=653  20$aFinite element analysis.
=653  20$aComposites.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10359J.htm

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=001  CTR10360J
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=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10360J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10360J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aSalpekar, SA., $eauthor.
=245  10$aAnalysis of Matrix Cracking and Local Delamination in (0/ϑ/ − ϑ)s Graphite Epoxy Laminates Under Tensile Load / $cSA Salpekar, TK O'Brien.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 2 (June 1993)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSeveral three-dimensional element analyses of (0/ϑ/−ϑ), graphite epoxy laminates, where ϑ = 15, 20, 25, 30, and 45°, subjected to axial tensile load, were performed. The interlaminar stresses in the ϑ/−ϑ interface were calculated with and without a matrix crack in the central −ϑ plies. The interlaminar normal stress changes from a small compressive stress when no matrix crack is present to a high tensile stress at the intersection of the matrix crack and the free edge. The analysis of local delamination from the −ϑ matrix crack indicates a high strain energy release rate and a localized Mode I component near the free edge, within one-ply distance from the matrix crack. To examine the stress state causing the matrix cracking, the maximum principal normal stress in a plane perpendicular to the fiber direction in the −ϑ ply was calculated in an uncracked laminate. The corresponding shear stress parallel to the fiber was also calculated. The principal normal stress at the laminate edge increased through the ply thickness and reached a very high tensile value at the ϑ/−ϑ interface indicating that the crack in the −ϑ ply may initiate at the ϑ/−ϑ interface. Predicted crack profiles on the laminate edge in the −ϑ ply were constructed from the principal stress directions. The cracks were found to be more curved for layups with smaller ϑ angles, which is consistent with experimental observations in the literature.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aDelamination.
=650  \0$aFinite element analysis.
=650  \0$aGraphite epoxy.
=650  \0$aLaminate.
=650  \0$aMatrix crack.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMatrix crack.
=653  20$aDelamination.
=653  20$aLaminate.
=653  20$aComposite.
=653  20$aFinite element analysis.
=653  20$aGraphite epoxy.
=700  1\$aO'Brien, TK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10360J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10361J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10361J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aKwon, YS., $eauthor.
=245  10$aIndentation-Flexure and Low-Velocity Impact Damage in Graphite Epoxy Laminates / $cYS Kwon, BV Sankar.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 2 (June 1993)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aStatic indentation-flexure and low-velocity impact tests were performed on quasi-isotropic and cross-ply graphite/epoxy composite laminates. The load-deflection relations in static tests and impact force history in impact tests were recorded. The damage was assessed by using ultrasonic C-scanning and photo-micrographic techniques. Some features of the static behavior were explained by simple analytical models. A good correlation existed between the load-deflection curves for static and impact loading. It was found that results from a few static indentation-flexure tests can be used to predict the impact force history and delamination radius in composite laminates due to low-velocity impact.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite laminates.
=650  \0$aDelamination.
=650  \0$aGraphite/epoxy.
=650  \0$aImpact damage.
=650  \0$aIndentation damage.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aIndentation damage.
=653  20$aImpact damage.
=653  20$aComposite laminates.
=653  20$aGraphite/epoxy.
=653  20$aDelamination.
=700  1\$aSankar, BV., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10361J.htm

=LDR  04128nam  2200805 i 4500
=001  CTR10362J
=003  IN-ChSCO
=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10362J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10362J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aMasters, JE., $eauthor.
=245  10$aMechanical Properties of Triaxially Braided Composites : $bExperimental and Analytical Results / $cJE Masters, RL Foye, CM Pastore, YA Gowayed.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 2 (June 1993)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper investigates the unnotched tensile properties of two-dimensional (2-D) triaxial braid-reinforced composites from both an experimental and an analytical viewpoint. The materials are graphite fibers in an epoxy matrix. Three different reinforcing fiber architectures were considered. Specimens were cut from resin transfer molded composite panels made from each briad. There were considerable differences in the observed elastic constants from different size strain gage and extensometer readings. Larger strain gages gave more consistent results and correlated better with the extensometer readings. Experimental strains correlated reasonably well with analytical predictions in the longitudinal, 0°, fiber direction but not in the transverse direction. Tensile strength results were not always predictable even in reinforcing directions. Minor changes in braid geometry led to disproportionate strength variations.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDiagonal brick analysis.
=650  \0$aFiber waviness.
=650  \0$aFinite element analysis.
=650  \0$aLaminated plate theory.
=650  \0$aPoisson's ratio.
=650  \0$aStiffness.
=650  \0$aStrength.
=650  \0$aTextile-reinforced composites.
=650  \0$aTriaxially briad.
=650  \0$aUnit cell.
=650  \0$aFinite element method.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aTextile-reinforced composites.
=653  20$aTriaxially briad.
=653  20$aUnit cell.
=653  20$aStiffness.
=653  20$aStrength.
=653  20$aPoisson's ratio.
=653  20$aLaminated plate theory.
=653  20$aFiber waviness.
=653  20$aDiagonal brick analysis.
=653  20$aFinite element analysis.
=700  1\$aFoye, RL., $eauthor.
=700  1\$aPastore, CM., $eauthor.
=700  1\$aGowayed, YA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10362J.htm

=LDR  03474nam  2200649 i 4500
=001  CTR10363J
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=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10363J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10363J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKlosner, JM., $eauthor.
=245  10$aEffect of Thermal Stresses on the Vibration of Composite Cantilevered Plates / $cJM Klosner, T-H Cheng.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 2 (June 1993)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis study explores the effects of thermal stresses on the dynamic characteristics of composite cantilevered plates. The induced thermal stresses are determined by appealing to the principle of minimum strain energy, while the Raleigh-Ritz procedure is used to obtain the plate frequencies. Extensive numerical calculations have been carried out in order to gain quantitative understanding of how different choices of aspect ratios (AR) and temperature change intensities (T0) influence the natural frequencies of composite cantilevered plates. It has been shown that the first bending mode frequencies are unaffected by the induced stresses, while the first torsional mode frequencies decrease quite significantly with increasing values of T0, and therefore with increased magnitudes of the thermal stresses.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAerodynamic heating.
=650  \0$aCantilevered plates.
=650  \0$aComposites.
=650  \0$aLaminates.
=650  \0$aThermal stress.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aThermal stress.
=653  20$aCantilevered plates.
=653  20$aComposites.
=653  20$aLaminates.
=653  20$aAerodynamic heating.
=700  1\$aCheng, T-H, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10363J.htm

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=001  CTR10364J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10364J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10364J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aBlackketter, DM., $eauthor.
=245  10$aModeling Damage in a Plain Weave Fabric-Reinforced Composite Material / $cDM Blackketter, DE Walrath, AC Hansen.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 2 (June 1993)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA method for describing damage propagation in a woven fabric-reinforced composite material subjected to tension or shear loading is presented. A three-dimensional unit cell description of a plain weave graphite/epoxy fabric-reinforced composite was constructed. From this description, finite element models were generated. An incremental iterating finite element algorithm was developed to analyze loading response. This finite element program included capabilities to model nonlinear constitutive material behavior (anisotropic plasticity), and a scheme to estimate the effects of damage propagation by stiffness reduction. Tension and shear loadings were modeled. Results from the finite element analysis compared favorably with experimental data. Nonlinear shear stress-strain behavior of the fabric composite was shown to be principally caused by damage propagation rather than by plastic deformation of the matrix.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFabric.
=650  \0$aFinite element.
=650  \0$aMicromechanics.
=650  \0$aStrength.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aFabric.
=653  20$aStrength.
=653  20$aMicromechanics.
=653  20$aFinite element.
=700  1\$aWalrath, DE., $eauthor.
=700  1\$aHansen, AC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10364J.htm

=LDR  03392nam  2200721 i 4500
=001  CTR10365J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10365J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10365J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA367
=082  04$a620.28$223
=100  1\$aSchuster, J., $eauthor.
=245  10$aUltrasonic Backscattering Using Digitized Full-Waveform Scanning Technique / $cJ Schuster, KV Steiner.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 2 (June 1993)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper presents the results of backscattering tests based on full-waveform scans performed on composite specimens. Five samples were manufactured with varying fiber directions and different numbers of laminae per direction. Ultrasonic backscattering tests of these samples were performed using digitized full-waveform scans. An algorithm was developed to determine the fiber direction with a tolerance of 2 to 3° and the number of laminae within a range of ± 0.5 lamina for sections close to the front surface.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBackscattering.
=650  \0$aComposites.
=650  \0$aFiber direction.
=650  \0$aFull-waveform inspection.
=650  \0$aLamina determination.
=650  \0$aNondestructive testing.
=650  \0$aUltrasonics.
=650  \0$aSupersonics.
=650  \0$aLevel indicators.
=650  \0$aTechnology.
=650  \7$aTECHNOLOGY & ENGINEERING $xAcoustics & Sound.
=653  10$aComposites.
=653  20$aNondestructive testing.
=653  20$aUltrasonics.
=653  20$aBackscattering.
=653  20$aFull-waveform inspection.
=653  20$aFiber direction.
=653  20$aLamina determination.
=700  1\$aSteiner, KV., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10365J.htm

=LDR  03800nam  2200733 i 4500
=001  CTR10368J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10368J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10368J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aRobertson, DD., $eauthor.
=245  10$aMicromechanical Relations for Fiber-Reinforced Composites Using the Free Transverse Shear Approach / $cDD Robertson, S Mall.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 3 (September 1993)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe formulation of a new three-dimensional micromechanical model for fiber reinforced material is presented. It is based on the relaxation of the coupling effect between the normal and shear stresses. The simplicity of the model lends itself very well to the inclusion of nonlinear behavior while maintaining the three-dimensional capability. Present nonlinear capabilities that have been added to the model include a thermoelastic-plastic analysis employing the Prandtl-Reuss flow relations with a strain hardening parameter and both isotropic and kinematic hardening. Results from the present analysis are compared in different cases with their counterparts from finite element solutions and experiment. In addition, this micromechanical analysis is extended to model a weak fiber/matrix bond.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite micromechanics.
=650  \0$aConstitutive equations.
=650  \0$aElastoplasticity.
=650  \0$aFiber composites.
=650  \0$aInterfacial effects.
=650  \0$aMechanical properties.
=650  \0$aMicrostresses.
=650  \0$aResidual thermal stresses.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite micromechanics.
=653  20$aMicrostresses.
=653  20$aInterfacial effects.
=653  20$aElastoplasticity.
=653  20$aResidual thermal stresses.
=653  20$aConstitutive equations.
=653  20$aFiber composites.
=653  20$aMechanical properties.
=700  1\$aMall, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10368J.htm

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=001  CTR10369J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10369J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10369J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aLee, SM., $eauthor.
=245  13$aAn Edge Crack Torsion Method for Mode III Delamination Fracture Testing / $cSM Lee.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 3 (September 1993)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new fracture toughness test, the edge crack torsion method, has been developed for characterizing the mode III delamination behavior of composites. The test is based on a laminate specimen subjected to torsion to propagate an edge delamination crack in its midplane. The crack growth mode of the specimen has been deduced to be mode III from fracture mechanics principles. The torsional behavior and the corresponding fracture parameter GIIIC have been analyzed on the basis of plate torsion and laminate theory. Edge crack torsion tests were performed to measure GIIIC of several carbon fiber/epoxy composite systems. Laminate layups were optimized to yield linear elastic fracture behavior of the specimens. The specimens were also sufficiently compliant to allow GIIIC to be readily obtained by using the compliance calibration method. The deformation characteristics of the specimens were found to follow the laminate torsion description. SEM observations showed fracture surface morphology varying with resin microstructures and, for the case of an untoughened matrix, were consistent with what was reported in the literature for other proposed mode III fracture tests.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aDelamination.
=650  \0$aFracture mechanics.
=650  \0$aFracture toughness.
=650  \0$aFracture.
=650  \0$aLaminates.
=650  \0$aTorsional deformation.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFracture.
=653  20$aLaminates.
=653  20$aComposite materials.
=653  20$aDelamination.
=653  20$aMode III testing.
=653  20$aFracture toughness.
=653  20$aFracture mechanics.
=653  20$aTorsional deformation.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10369J.htm

=LDR  03026nam  2200637 i 4500
=001  CTR10370J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10370J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10370J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aHu, H-T, $eauthor.
=245  10$aBuckling Analyses of Fiber-Composite Laminate Shells with Material Nonlinearity / $cH-T Hu.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 3 (September 1993)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA nonlinear material constitutive model, including a nonlinear in-plane shear formulation and a failure criterion, for fiber-composite laminate materials is employed to carry out finite-element buckling analyses for composite shells under hydrostatic compressive loads. It has been shown that the nonlinear in-plane shear together with the failure criterion have significant influence on the buckling behavior of composite shells.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aComposite shell.
=650  \0$aConstitutive model.
=650  \0$aFailure criterion.
=650  \0$aIn-plane shear.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aBuckling.
=653  20$aIn-plane shear.
=653  20$aConstitutive model.
=653  20$aFailure criterion.
=653  20$aComposite shell.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10370J.htm

=LDR  02277nam  2200505 i 4500
=001  CTR10371J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10371J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10371J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTN4
=082  04$a620.11$223
=100  1\$aJohnson, WS., $eauthor.
=245  10$aIntroduction to Workshop on Crack Growth Behavior of Continuous Fiber Reinforced Titanium Matrix Composites (TMCs) / $cWS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (1 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 3 (September 1993)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber.
=650  \7$aTitanium Matrix Composites.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10371J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10372J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10372J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aHillberry, BM., $eauthor.
=245  10$aFatigue Crack Spacing in the Matrix of a Continuous Fiber SCS-6/Ti Composite / $cBM Hillberry, WS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 3 (September 1993)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this study the extensive matrix fatigue cracking that has been observed in notched SCS-6/Ti-15-3 composites is investigated. Away from the notch a uniform spacing of the fatigue cracks develop. Closer to the notch, fiber-matrix debonding occurs, increasing distance between the cracks. Crack spacing predicted from cylinder models compare favorably with experimental observations. SEM fractography showed that the principal fatigue crack initiation occurred around the 0° fibers. Primary fatigue cracking does not appear to be due to interface failure in the 90° plies.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aContinuous fiber.
=650  \0$aCrack.
=650  \0$aFatigue.
=650  \0$aMetal matrix.
=650  \0$aSpacing.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aComposite.
=653  20$aMetal matrix.
=653  20$aContinuous fiber.
=653  20$aFatigue.
=653  20$aCrack.
=653  20$aSpacing.
=700  1\$aJohnson, WS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10372J.htm

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=001  CTR10373J
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=024  7\$a10.1520/CTR10373J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10373J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aJeng, SM., $eauthor.
=245  10$aFatigue Cracking of Fiber-Reinforced Titanium Matrix Composites / $cSM Jeng, T-HB Nguyen, O Dana, J-M Yang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 3 (September 1993)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe fatigue crack growth behavior of a unidirectional SCS-6-fiber-reinforced Ti-6Al-2Sn-4Zr-2Mo composite has been characterized. A fatigue cracking map for several unidirectional SCS-6-fiber-reinforced titanium and titanium aluminide composites under tension-tension fatigue loading has been developed. The map is constructed based upon the fiber strength to interfacial shear strength ratio versus the applied maximum stress intensity factor. Also, the effect of fiber bridging on the effective crack driving force in the matrix is analyzed using the shear-lag model and finite element analysis.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFatigue cracking.
=650  \0$aFinite element analysis.
=650  \0$aTitanium matrix composites.
=650  \0$aFinite element method.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aFatigue cracking.
=653  20$aTitanium matrix composites.
=653  20$aFinite element analysis.
=700  1\$aNguyen, T-HB, $eauthor.
=700  1\$aDana, O., $eauthor.
=700  1\$aYang, J-M, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10373J.htm

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=001  CTR10374J
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=024  7\$a10.1520/CTR10374J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10374J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aHarmon, DM., $eauthor.
=245  10$aDifferences in Fatigue and Fracture Behavior of Woven-Mat and Acrylic Binder SCS-6/Ti-15-3 Composites / $cDM Harmon, MA Finefield, JA Harter, DL Buchanan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 3 (September 1993)
=504  \\$aIncludes bibliographical references$b26.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper summarizes testing performed on SCS-6/Ti-15-3 composites that were fabricated using two different methods of fiber alignment. One composite used an acrylic binder to hold the fibers straight and parallel to each other while the second method used a Ti-6-4 ribbon weave which produced a SCS-6 woven fiber mat. Fatigue test results indicated that the woven mat composite was more likely to develop Mode I cracks which would propagate through the specimen failing fibers. This led to catastrophic failures. Conversely, the acrylic binder composite was subject to multiple matrix cracking in which fibers did not fail, but bridged the cracks and resulted in longer fatigue lives.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCrack growth.
=650  \0$aCrack initiation.
=650  \0$aDamage.
=650  \0$aFailure modes.
=650  \0$aFatigue.
=650  \0$aStrength.
=650  \0$aTitanium matrix composites.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aTitanium matrix composites (TMCs) SCS-6 fiber.
=653  20$aStrength.
=653  20$aFatigue.
=653  20$aCrack initiation.
=653  20$aCrack growth.
=653  20$aDamage.
=653  20$aFailure modes.
=700  1\$aFinefield, MA., $eauthor.
=700  1\$aHarter, JA., $eauthor.
=700  1\$aBuchanan, DL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10374J.htm

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=001  CTR10375J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10375J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10375J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aTelesman, J., $eauthor.
=245  10$aMethodology for Prediction of Fiber Bridging Effects in Composites / $cJ Telesman, LJ Ghosn, P Kantzos.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 3 (September 1993)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA review of three different methods used at NASA Lewis to account for the effect of fiber bridging on fatigue crack growth (FCG) in metallic and intermetallic titanium-based composites is presented. Of the three methods, the fiber pressure model (FPM) was the only one able to accurately predict both crack opening displacements (CODs) and the FCG rates for both composites under the various applied loading conditions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aCrack propagation.
=650  \0$aFiber bridging.
=650  \0$aFiber pressure model (FPM).
=650  \0$aMetal matrix composite.
=650  \0$aShear strength coefficient.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aCrack propagation.
=653  20$aFiber bridging.
=653  20$aFiber pressure model (FPM).
=653  20$aMetal matrix composites (MMCs).
=653  20$aShear lag model (SLM).
=653  20$aShear strength coefficient.
=700  1\$aGhosn, LJ., $eauthor.
=700  1\$aKantzos, P., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10375J.htm

=LDR  04547nam  2200697 i 4500
=001  CTR10376J
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=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10376J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10376J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aBakuckas, JG., $eauthor.
=245  10$aApplication of Fiber Bridging Models to Fatigue Crack Growth in Unidirectional Titanium Matrix Composites / $cJG Bakuckas, WS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (14 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 3 (September 1993)
=504  \\$aIncludes bibliographical references$b30.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSeveral fiber bridging models were reviewed and applied in this research to study the matrix fatigue crack growth behavior in center notched [0]8 SCS-6/Ti-15-3 and [0]4 SCS-6/Ti-6AI-4V titanium matrix composites (TMCs). Observations revealed that fatigue damage consisted primarily of matrix cracks and fiber-matrix interfacial failure in the unidirectional TMC. Fiber-matrix interface failure included fracture of the brittle reaction zone and cracking between the two carbon-rich fiber coatings. Intact fibers in the wake of the matrix cracks reduce the stress intensity factor range. Thus, an applied stress intensity factor range (ΔKapp=ΔSπa) is inappropriate to characterize matrix crack growth behavior. Fiber bridging models were used to determine the matrix stress intensity factor range in the unidirectional TMC. In these models, the fibers in the wake of the crack are idealized as a closure pressure. An unknown constant frictional shear stress is assumed to act along the debond or slip length of the bridging fibers. In this study, the frictional shear stress was used as a curve fitting parameter to available data (crack growth data, crack opening displacement (COD) data, and debond length data). Large variations in the frictional shear stress required to fit the experimental data indicate that the fiber bridging models in their present form lack predictive capabilities. However, these models provide an efficient and relatively simple engineering method for conducting parametric studies of the matrix crack growth behavior based on constituent properties.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aContinuum fracture mechanics.
=650  \0$aDiscrete-continuum relations.
=650  \0$aFiber-matrix debonding.
=650  \0$aInterfacial frictional shear stress.
=650  \0$aMatrix cracking.
=650  \0$aMicromechanics.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMatrix cracking.
=653  20$aFiber-matrix debonding.
=653  20$aMatrix stress intensity factor.
=653  20$aContinuum fracture mechanics.
=653  20$aMicromechanics.
=653  20$aInterfacial frictional shear stress.
=653  20$aDiscrete-continuum relations.
=700  1\$aJohnson, WS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10376J.htm

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=001  CTR10379J
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=005  20161219163000.0
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=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10379J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10379J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aO'Brien, TK., $eauthor.
=245  10$aRound Robin Testing for Mode I Interlaminar Fracture Toughness of Composite Materials / $cTK O'Brien, RH Martin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 4 (December 1993)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis report summarizes the results of several interlaboratory "round robin" test programs for measuring the Mode I interlaminar fracture toughness of advanced fiber-reinforced composite materials. Double cantilever beam (DCB) tests were conducted by participants in ASTM Committee D-30 on High Modulus Fibers and Their Composites and by representatives of the European Group on Fracture (EGF) and the Japanese Industrial Standards Group (JIS). DCB tests were performed on three AS4 carbon fiber-reinforced composite materials: AS4/3501-6 with a brittle epoxy matrix, AS4/BP907 with a tough epoxy matrix, and AS4/PEEK with a tough thermoplastic matrix. Difficulties encountered in manufacturing panels, as well as conducting the tests, are discussed. Critical issues that developed during the course of the testing are highlighted. Results of the round robin testing used to determine the precision of the ASTM DCB test standard are summarized.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aDelamination.
=650  \0$aDouble cantilever beam.
=650  \0$aInterlaminar fracture toughness.
=650  \0$aStandard test method.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aDouble cantilever beam (DCB).
=653  20$aInterlaminar fracture toughness.
=653  20$aDelamination.
=653  20$aStandard test method.
=700  1\$aMartin, RH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10379J.htm

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=001  CTR10380J
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=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10380J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10380J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aJackson, WC., $eauthor.
=245  14$aThe Use of Impact Force as a Scale Parameter for the Impact Response of Composite Laminates / $cWC Jackson, CC Poe.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 4 (December 1993)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe building block approach is currently used to design composite structures. With this approach, the data from coupon tests are scaled up to determine the design of a structure. Current standard impact tests and methods of relating test data to other structures are not generally understood and are often used improperly. A methodology is outlined for using impact force as a scale parameter for delamination damage for impacts of simple plates. Dynamic analyses were used to define ranges of plate parameters and impact parameters where quasi-static analyses are valid. These ranges include most low-velocity impacts where the mass of the impacter is large and the size of the specimen is small. For large-mass impacts of moderately thick (0.35 to 0.70 cm) laminates, the maximum extent of delamination damage increased with increasing impact force and decreasing specimen thickness. For large-mass impact tests at a given kinetic energy, impact force and hence delamination size depends on specimen size, specimen thickness, layup, boundary conditions, and indenter size and shape. If damage is reported in terms of impact force instead of kinetic energy, large-mass test results can be applied directly to other plates of the same thickness and layup.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon epoxy.
=650  \0$aComposite material.
=650  \0$aDelamination.
=650  \0$aImpact.
=650  \0$aTransverse shear force.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite material.
=653  20$aCarbon epoxy.
=653  20$aImpact.
=653  20$aDelamination.
=653  20$aTransverse shear force.
=700  1\$aPoe, CC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10380J.htm

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=024  7\$a10.1520/CTR10381J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10381J$bASTM
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRadford, DW., $eauthor.
=245  10$aCure Shrinkage Induced Warpage in Flat Uni-Axial Composites / $cDW Radford.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 4 (December 1993)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAutoclave cured uni-axial carbon fiber/epoxy samples are observed to warp during production even though classical laminated plate theory predicts that such composites should have no such tendency. Particularly in thin laminates the observed convex up curvature can be quite pronounced, but measurable warpage does exist even in thicker composites. Distorted uni-axial laminates produced by top bleed autoclave cure have been analyzed using quantitative optical microscopy and have shown volume fraction gradients related to laminate through-thickness position. The results of these preliminary quantitative observations indicate that many laminates are measurably resin-rich at the composite/tool interface, and resin-poor at the laminate top surface near where bleeding takes place. However, the present metallographic technique does not yield a precise through-thickness resin fraction profile. Modeling of the magnitude of this warpage has been undertaken to investigate the likely through-thickness volume fraction profiles. The approach used has included a number of volume fraction variations in a classical laminated plate analysis and determines the mid-plane curvatures predicted based on general composite thermal expansion and matrix shrinkages. The results of this analysis for long uni-axial carbon fiber/epoxy sample strips of varying thickness match the curvature experimentally observed and substantiate the idea that the volume fraction gradient is not linear through the laminate thickness, but rather is locally resin-rich near the tooling, uniform through most of the thickness, and resin-poor at the top surface adjacent to the bleeder. Further, the results show that volume fraction gradients induced during top bleed autoclave cure are an important component of composite part warpage.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon fiber composites.
=650  \0$aCure distortion.
=650  \0$aFiber reinforced composites.
=650  \0$aHomogeneity.
=650  \0$aManufacturing warpage.
=650  \0$aTooling design.
=650  \0$aVolume fraction gradient.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFiber reinforced composites.
=653  20$aVolume fraction gradient.
=653  20$aManufacturing warpage.
=653  20$aCure distortion.
=653  20$aCarbon fiber composites.
=653  20$aHomogeneity.
=653  20$aTooling design.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10381J.htm

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=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10382J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10382J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aJohnson, WS., $eauthor.
=245  10$aStress-Strain Analysis of a [0/90]2s Titanium Matrix Laminate Subjected to a Generic Hypersonic Flight Profile / $cWS Johnson, M Mirdamadi, YA Bahei-El-Din.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 4 (December 1993)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aCross-ply laminate behavior of Ti-15V-3Cr-3Al-3Sn (Ti-15-3) matrix reinforced with continuous silicon-carbide fibers (SCS-6) subjected to a generic hypersonic flight profile was evaluated experimentally and analytically. Thermomechanical fatigue (TMF) test techniques were developed to conduct a simulation of a generic hypersonic flight profile. A micromechanical analysis was used. The analysis predicts the stress-strain response of the laminate and of the constituents in each ply during thermal and mechanical cycling by using only constituent properties as input. The fiber was modeled as elastic with transverse orthotropic and temperature-dependent properties. The matrix was modeled using a thermo-viscoplastic constitutive relation. The fiber transverse modulus was reduced in the analysis to simulate the fiber-matrix interface failure. Excellent correlation was found between measured and predicted laminate stress-strain response due to generic hypersonic flight profile when fiber debonding was modeled.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aInterface.
=650  \0$aResidual stresses.
=650  \0$aSilicon-carbide fibers.
=650  \0$aThermal strains.
=650  \0$aViscoplasticity theory.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aSilicon-carbide fibers.
=653  20$aInterface.
=653  20$aResidual stresses.
=653  20$aThermal strains.
=653  20$aViscoplasticity theory.
=700  1\$aMirdamadi, M., $eauthor.
=700  1\$aBahei-El-Din, YA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10382J.htm

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=001  CTR10383J
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=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10383J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10383J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aBigelow, CA., $eauthor.
=245  10$aThermal Residual Stresses in a Silicon-Carbide/Titanium [0/90] Laminate / $cCA Bigelow.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 4 (December 1993)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe current work formulated a micromechanical analysis of a cross-ply laminate and calculated the thermal residual stress in a very thick [0/90]ns silicon-carbide/titanium laminate. Results were also shown for a unidirectional laminate of the same material. Discrete fiber-matrix models assuming a rectangular array of fibers with a fiber volume fraction of 32.5% and a three-dimensional, finite element analysis were used. Significant differences in the trends and magnitudes for the fiber, matrix, and interface stresses were calculated for the unidirectional and [0/90] models. Larger hoop stresses calculated for the [0/90] model indicate that it may be more susceptible to radial cracking when subjected to mechanical loading than the unidirectional model. The axial stresses in the matrix were calculated to be slightly larger for the [0/90] model. The compressive axial stresses in the fiber were significantly larger in the [0/90] model. The presence of the cross-ply in the [0/90] model reduced the constraint on the fiber, producing radial interface stresses that were less compressive, which could lead to earlier failure of the fiber-matrix interface.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCross-ply.
=650  \0$aFinite element analysis.
=650  \0$aMicromechanics.
=650  \0$aStress contours.
=650  \0$aUnidirectional.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCross-ply.
=653  20$aUnidirectional.
=653  20$aFinite element analysis.
=653  20$aMicromechanics.
=653  20$aStress contours.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10383J.htm

=LDR  03053nam  2200673 i 4500
=001  CTR10384J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19939999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10384J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10384J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aEl-Habak, AMA, $eauthor.
=245  10$aCompressive Resistance of Unidirectional GFRP Under High Rate of Loading / $cAMA El-Habak.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1993.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 15, Issue 4 (December 1993)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn an attempt to determine composite strength at high strain rates, unidirectional glass/polyester and glass/epoxy composites have been tested using the Split Hopkinson Pressure Bar (SHPB) apparatus at room temperature. The tested materials of the polyester-based matrix are in the range of fiber volume fraction from 0.49 to 0.67, while the epoxy composites have the fiber volume fraction of 0.61.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1993. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression.
=650  \0$aEpoxy.
=650  \0$aGlass fiber.
=650  \0$aPolyester.
=650  \0$aStrain rate.
=650  \0$aUnidirectional.
=650  \0$aPlasma treatment.
=650  \0$aKevlar fiber.
=653  10$aUnidirectional.
=653  20$aGlass fiber.
=653  20$aPolyester.
=653  20$aEpoxy.
=653  20$aStrain rate.
=653  20$aCompression.
=653  20$aSplit Hopkinson Pressure Bar (SHPB).
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10384J.htm

=LDR  03858nam  2200745 i 4500
=001  CTR10390J
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=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10390J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10390J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aNaik, NK., $eauthor.
=245  10$aFailure Behavior of Plain Weave Fabric Laminates Under In-Plane Shear Loading / $cNK Naik, VK Ganesh.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (18 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 1 (January 1994)
=504  \\$aIncludes bibliographical references$b47.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA two-dimensional (2-D) woven fabric composite strength model is presented for the prediction of in-plane shear strength of 2-D orthogonal plain weave fabric laminates under inplane shear loading. The shear strength studies were carried out for three idealized laminate configurations. The possible shift of layers with respect to each other along x-, y-, and z-directions were considered for the laminates. The shear moduli were predicted for the three idealized laminate configurations using the 2-D woven fabric composite stiffness model. A comprehensive experimental program was carried out on different material systems using 10° and ±45° off-axis tension tests and the Iosipescu test. A good correlation is observed between the predicted and the experimental results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aExperimental determination.
=650  \0$aIn-plane shear loading.
=650  \0$aInplane shear modulus.
=650  \0$aIn-plane shear strength.
=650  \0$aLaminate configuration.
=650  \0$aPrediction.
=650  \0$aTwo-dimensional (2-D) woven fabric (WF) composite strength model.
=650  \0$aWoven fabric laminate.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aComposite.
=653  20$aWoven fabric laminate.
=653  20$aLaminate configuration.
=653  20$aTwo-dimensional (2-D) woven fabric (WF) composite strength model.
=653  20$aIn-plane shear loading.
=653  20$aIn-plane shear strength.
=653  20$aInplane shear modulus.
=653  20$aPrediction.
=653  20$aExperimental determination.
=700  1\$aGanesh, VK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10390J.htm

=LDR  04215nam  2200709 i 4500
=001  CTR10391J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10391J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10391J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aJayaraman, K., $eauthor.
=245  14$aThe Interphase in Unidirectional Fiber-Reinforced Epoxies : $bEffect on Local Stress Fields / $cK Jayaraman, Z Gao, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 1 (January 1994)
=504  \\$aIncludes bibliographical references$b25.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe "interphase" in a composite is usually modeled as a homogeneous region, despite the fact that it may have spatial property variations. However, it is important to the understanding of composite behavior to incorporate a realistic interphasial region into the micromechanical analyses of composite systems. The authors have recently proposed a model for the interphase properties in fiber-reinforced thermosets; the Young's modulus and coefficient of thermal expansion of the interphase are assumed to vary as functions of distance from the fiber in this model. In the current study, the authors' model is used along with Mori-Tanaka analyses for the determination of "nondilute" local stress fields in unidirectional fiber-reinforced epoxies under thermomechanical loading situations. The governing field equations in terms of displacements are solved in "closed form." It is found that property variations in the interphase have a distinct effect on the local stresses. This is significant, considering the fact that local stresses play an important role in controlling the structural performance of a composite. The ideas behind this study can be extended to characterize and analyze the interphase in metal matrix and ceramic matrix composites.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFiber-matrix adhesion.
=650  \0$aFiber-matrix interphase.
=650  \0$aFiber-reinforced epoxies.
=650  \0$aInterphase mechanics.
=650  \0$aLocal stresses.
=650  \0$aSpatial property variation.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aFiber-reinforced epoxies.
=653  20$aFiber-matrix adhesion.
=653  20$aFiber-matrix interphase.
=653  20$aSpatial property variation.
=653  20$aLocal stresses.
=653  20$aInterphase mechanics.
=700  1\$aGao, Z., $eauthor.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10391J.htm

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=001  CTR10392J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10392J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10392J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aPastore, CM., $eauthor.
=245  12$aA Self-Consistent Fabric Geometry Model : $bModification and Application of a Fabric Geometry Model to Predict the Elastic Properties of Textile Composites / $cCM Pastore, YA Gowayed.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 1 (January 1994)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA method for predicting the elastic properties of textile-reinforced composites is presented with applications. The method is a modification of a Fabric Geometry Model (FGM) [1-3] that relates fiber architecture and material properties of textile-reinforced composites to its global stiffness matrix through micromechanics and stiffness averaging technique. The FGM, although proven to be a quick and successful method [4], suffers two major drawbacks:.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aElastic properties.
=650  \0$aMicromechanics.
=650  \0$aStiffness tensor.
=650  \0$aTextiles.
=650  \0$aTransformation tensor.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite.
=653  20$aMicromechanics.
=653  20$aElastic properties.
=653  20$aTextiles.
=653  20$aStiffness tensor.
=653  20$aTransformation tensor.
=653  20$aFabric geometry model (FGM).
=700  1\$aGowayed, YA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10392J.htm

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=001  CTR10393J
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=030  \\$aJCTRER
=037  \\$aCTR10393J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aChandra, N., $eauthor.
=245  10$aMicromechanical Modeling of Process-Induced Residual Stresses in Ti-24Al-11Nb/SCS-6 Composite / $cN Chandra, CR Ananth, H Garmestani.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 1 (January 1994)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA crucial problem in the application of Metallic and Intermetallic Matrix Composites (MMCs and IMCs) is the presence of high levels of residual stresses induced during the fabrication process. This process-induced stress is essentially thermal in nature, and is caused by a significant difference in the coefficients of thermal expansion (CTE) of the fiber and the matrix and the large temperature differential of the cooling process. Residual stresses may lead to the development of matrix cracking, and may also have an adverse effect on the thermomechanical properties of the composites, e.g., stress-strain behavior, fracture toughness, fatigue, and creep. A micromechanical analysis is needed to study the effects of residual stresses, since phenomena like damage are local in nature even though they affect the macro properties. An elastic-plastic finite element analysis is performed to model the thermal stresses induced during fabrication of Ti-24Al-11Nb/SCS-6 unidirectional composite and the effect of these stresses on subsequent transverse loading. The state of residual stress induced in this intermetallic composite is found to be quite different from that in Ti-6Al-4V/SCS-6 metal matrix composite which is extensively discussed in the literature. The influence of fiber-matrix interfacial bonding and fiber arrangement on the thermomechanical behavior of Ti-24Al-11Nb/SCS-6 composite is also studied.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aElastic-plastic.
=650  \0$aFiber arrangement.
=650  \0$aFinite element analysis.
=650  \0$aInterface.
=650  \0$aIntermetallic matrix.
=650  \0$aMetal matrix.
=650  \0$aResidual stress.
=650  \0$aSilicon carbide.
=650  \0$aTransverse tension.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aResidual stress.
=653  20$aMetal matrix.
=653  20$aIntermetallic matrix.
=653  20$aSilicon carbide.
=653  20$aFinite element analysis.
=653  20$aElastic-plastic.
=653  20$aInterface.
=653  20$aTransverse tension.
=653  20$aFiber arrangement.
=700  1\$aAnanth, CR., $eauthor.
=700  1\$aGarmestani, H., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10393J.htm

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=024  7\$a10.1520/CTR10394J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10394J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aRangaswamy, P., $eauthor.
=245  10$aResidual Stresses in SCS-6/Ti-24Al-11Nb Composite : $bPart I-Experimental / $cP Rangaswamy, WC Revelos, N Jayaraman.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 1 (January 1994)
=504  \\$aIncludes bibliographical references$b28.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aResidual stress analysis of an as-received and thermally cycled SCS-6/Ti-24Al-11Nb (at.%) [0]8 metal matrix composite (MMC) was performed using the X-ray diffraction (sin2ψ) technique. Residual stresses were measured in the α2 phase of the matrix in orientations parallel, transverse, and 45° to the fiber direction. Stress profiles were determined by successive removal of the matrix from the composite surface by electropolishing. Within 10 to 30 μm of the first fiber plane, the stress levels were found to be lower than those far from the fiber plane. Residual stress measurements performed on the matrix between the first two fiber rows revealed lower stress levels than those in the outermost matrix layers. The presence of stress gradients normal to the surface of the composite was also revealed. Measurement of residual stress levels in the composite subjected to thermal cycling from 150°C to 815°C in an inert atmosphere revealed almost complete stress relaxation after 500 cycles.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCoefficient of thermal expansion (CTE).
=650  \0$aMetal matrix composite.
=650  \0$aResidual stress analysis.
=650  \0$aX-ray diffraction.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aResidual stress analysis.
=653  20$aMetal matrix composite (MMC).
=653  20$aCoefficient of thermal expansion (CTE).
=653  20$aX-ray diffraction.
=700  1\$aRevelos, WC., $eauthor.
=700  1\$aJayaraman, N., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10394J.htm

=LDR  04254nam  2200697 i 4500
=001  CTR10395J
=003  IN-ChSCO
=005  20161219163000.0
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=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10395J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10395J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aRangaswamy, P., $eauthor.
=245  10$aResidual Stresses in SCS-6/Ti-24Al-11Nb Composite : $bPart II-Finite Element Modeling / $cP Rangaswamy, N Jayaraman.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (14 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 1 (January 1994)
=504  \\$aIncludes bibliographical references$b40.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn metal matrix composites (MMCs) residual stresses developing during the cool-down process after consolidation due to mismatch in thermal expansion coefficients between the ceramic fibers and metal matrix have been predicted using finite element analysis. Conventionally, unit cell models (UCMs) consisting of a quarter fiber surrounded by the matrix material have been developed for analyzing this problem. Such models have successfully predicted the stresses at the fiber-matrix interface. However, experimental work to measure residual stresses has always been on surfaces far away from the interface region. In this paper, models based on the conventional unit cell (one quarter fiber), one fiber, two fibers, four-plys, and eight-plys have been analyzed. In addition, using the element birth/death options available in the FEM code, the surface layer removal process that is conventionally used in the residual stress measuring technique has been simulated in the model. Such layer removal technique allows us to determine the average surface residual stress after each layer is removed and a direct comparison with experimental results are therefore possible. The predictions are compared with experimental results of a unidirectional composite with Ti-24Al-11Nb as matrix material reinforced with SCS-6 fibers.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCoefficient of thermal expansion (CTE).
=650  \0$aComposites.
=650  \0$aFinite element modeling.
=650  \0$aResidual stress.
=650  \0$aTitanium matrix.
=650  \0$aX-ray stress measurements.
=650  \0$aFinite element method.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aResidual stress.
=653  20$aFinite element modeling (FEM).
=653  20$aTitanium matrix.
=653  20$aComposites.
=653  20$aCoefficient of thermal expansion (CTE) mismatch.
=653  20$aX-ray stress measurements.
=653  20$aMaterial removal effects.
=700  1\$aJayaraman, N., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10395J.htm

=LDR  03981nam  2200685 i 4500
=001  CTR10396J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10396J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10396J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMirzadeh, F., $eauthor.
=245  10$aResponse of Metal Matrix Laminates with Temperature-Dependent Properties / $cJ Aboudi, F Mirzadeh, CT Herakovich.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 1 (January 1994)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn analytical, inelastic micromechanical model, with temperature-dependent matrix properties, is employed to study metal matrix composite (MMC) laminates subjected to thermomechanical loading. The predictions are based on knowledge of the thermomechanical response of transversely isotropic, elastic graphite or silicon carbide fibers and elastic-viscoplastic, work-hardening, temperature-dependent titanium or aluminum matrix. The model is applied to predict initial yielding and thermomechanical response of silicon carbide/titanium and graphite/aluminum laminates. The results demonstrate the effect of cooling from a stress-free temperature and the mismatch of thermal and mechanical properties of the constituent phases on the laminate's subsequent mechanical response. Typical results are presented for [±45], laminates subjected to monotonic tension, cyclic tension/compression, biaxial tension, and thermal loadings. It is shown that inclusion of temperature-dependent properties has a significant influence on both the initial yield surface and the inelastic response of metal matrix composites. It is also shown that the degree of applied biaxial loading has a significant effect on the response of laminates.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aLaminates.
=650  \0$aMetal matrix.
=650  \0$aNonlinear response.
=650  \0$aThermal effects.
=650  \0$aYielding.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aMetal matrix.
=653  20$aLaminates.
=653  20$aYielding.
=653  20$aNonlinear response.
=653  20$aThermal effects.
=700  1\$aMirzadeh, F., $eauthor.
=700  1\$aHerakovich, CT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10396J.htm

=LDR  03426nam  2200673 i 4500
=001  CTR10397J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10397J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10397J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aVarna, J., $eauthor.
=245  10$aThermo-Elastic Properties of Composite Laminates with Transverse Cracks / $cJ Varna, LA Berglund.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 1 (January 1994)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDifferent models based on variational analysis are compared with respect to the thermo-elastic properties of cross-ply laminates with transverse cracks in the 90°-layer. This approach, pioneered by Hashin, applies the principle of minimum complementary energy to describe the stress state in a cross-ply laminate with transverse cracks. Apart from material data, only laminate geometry data and stress distribution assumptions are required. The model developed in the present study contains stress distribution assumptions that are closer to reality than previous models. Non-uniform stress distributions are included through-the-thickness of both the 0°- and the 90°-layers.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aCross-ply laminates.
=650  \0$aLocal delamination.
=650  \0$aStiffness reduction.
=650  \0$aThermo-elastic.
=650  \0$aTransverse cracks.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aThermo-elastic.
=653  20$aComposite.
=653  20$aTransverse cracks.
=653  20$aCross-ply laminates.
=653  20$aLocal delamination.
=653  20$aStiffness reduction.
=700  1\$aBerglund, LA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10397J.htm

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=001  CTR10400J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10400J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10400J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGiurgiutiu, V., $eauthor.
=245  10$aDevelopment of Strength Theories for Random Fiber Composites / $cV Giurgiutiu, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 2 (April 1994)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA ressessment of existing theories for calculating the strength of random and quasi-random fiber composites is presented. Fundamental aspects regarding the physical model, macromechanics analysis, fiber distribution functions, generalized failure criterion, and progressive versus sudden failure models are covered first. Progressive ductile failure, progressive brittle failure, and sudden brittle failure are treated in detail. In each case, the original theory is briefly reviewed, and then its extensions accompanied by numerical examples are presented. Several limitations originally imposed by Hahn, such as the monotonically nonincreasing requirement on the failure strain curve, are lifted and the mathematical formulations are generalized. Some common misconceptions are also highlighted and clarified. Comparison with experimental data is given for the SMC-R50 material system. Good reproduction of the experimental results and of the stress-strain response are illustrated. A review of the main points and opportunities for further work are presented in conclusion.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aEffective properties.
=650  \0$aRandom orientation fibers.
=650  \0$aStrength.
=650  \0$aStress-strain response.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aStrength.
=653  20$aRandom orientation fibers.
=653  20$aStress-strain response.
=653  20$aEffective properties.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10400J.htm

=LDR  03931nam  2200721 i 4500
=001  CTR10401J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10401J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10401J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aRousseau, CQ., $eauthor.
=245  14$aThe Micromechanics of Ambient Temperature Cyclic Fatigue Loading in a Composite of CAS Glass Ceramic Reinforced with Nicalon Fibers / $cCQ Rousseau, DL Davidson, JB Campbell.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 2 (April 1994)
=504  \\$aIncludes bibliographical references$b23.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe behavior of a Nicalon fiber reinforced glass ceramic composite cyclicly loaded has been evaluated at ambient temperature using high-resolution micromechanical test methods. On this basis, the events leading to fracture have been found to be similar to those accompanying fracture in unidirectional tension tests. Matrix strains were determined locally at the point of matrix fracture. Crack opening displacements (CODs) were measured as a function of loading cycles, and fiber strains were determined, in some cases. It is concluded that debonding of fibers begins at the point of matrix cracking and rapidly increases. Most of the cyclic lifetime of the material is spent with fibers debonded over large distances (fractions of a millimeter); these fibers are pulled out of the matrix on each loading cycle. Final debond length, as determined by fractography, is a function of the number of cycles to fracture, and of the applied stress level.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCeramic matrix composite.
=650  \0$aCrack opening displacements (CODs).
=650  \0$aFatigue.
=650  \0$aFiber strains.
=650  \0$aGlass ceramic matrix.
=650  \0$aNicalon fibers.
=650  \0$aStereoimaging technique.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aCeramic matrix composite (CMC).
=653  20$aFatigue.
=653  20$aCrack opening displacements (CODs).
=653  20$aFiber strains.
=653  20$aGlass ceramic matrix.
=653  20$aNicalon fibers.
=653  20$aStereoimaging technique.
=700  1\$aDavidson, DL., $eauthor.
=700  1\$aCampbell, JB., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10401J.htm

=LDR  03766nam  2200697 i 4500
=001  CTR10402J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10402J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10402J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.84
=082  04$a620.1/127$223
=100  1\$aSundaresan, MJ., $eauthor.
=245  10$aPrediction of Fatigue Life of Composite Femoral Prostheses Using Acoustic Emission Technique / $cMJ Sundaresan, EG Henneke, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 2 (April 1994)
=504  \\$aIncludes bibliographical references$b23.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new proof test procedure that has the potential for estimating the fatigue life of individual composite structural members has been developed. Acoustic emission (AE) data collected during a described proof loading sequence were used for providing such estimates. The structural element used in the study was a composite hip prosthesis fabricated from carbon/thermoplastic composite material. These prostheses were subjected to fatigue under an eccentrically applied load that induced compression, bending, and torsion. Factors that influence AE data interpretation are discussed. Of the three different types of proof test procedures that were studied, the procedure which used a combination of static and cyclic loads for generating the AE data was found to be superior. For the majority of the test specimens the fatigue life was found to be inversely proportional to the level of AE activity during this proof loading sequence.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAcoustic emission.
=650  \0$aComposite materials.
=650  \0$aFatigue.
=650  \0$aHip prosthesis.
=650  \0$aLife prediction.
=650  \0$aProof test.
=650  \0$aAcoustical engineering.
=650  \0$aEmission, Acoustic.
=650  \0$aAcoustic emission testing.
=653  10$aComposite materials.
=653  20$aAcoustic emission (AE).
=653  20$aFatigue.
=653  20$aLife prediction.
=653  20$aHip prosthesis.
=653  20$aProof test.
=700  1\$aHenneke, EG., $eauthor.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10402J.htm

=LDR  03225nam  2200745 i 4500
=001  CTR10403J
=003  IN-ChSCO
=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10403J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10403J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aAbu-Farsakh, GA., $eauthor.
=245  12$aA New Failure Criterion for Nonlinear Composite Materials / $cGA Abu-Farsakh, YA Abdel-Jawad.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 2 (April 1994)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new failure criterion based on the total strain energy density approach is introduced for an equivalent linear elastic material. The total strain energy is composed of the elastic strain energy and the plastic strain energy. The proposed criterion can be used to predict failure of fibrous composite materials subject to uniaxial, biaxial, or multiaxial stress state.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFailure.
=650  \0$aFibrous composites.
=650  \0$aModeling.
=650  \0$aMultiaxial.
=650  \0$aNonlinear.
=650  \0$aSecant modulus.
=650  \0$aStrain energy.
=650  \0$aStrains.
=650  \0$aStresses.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFailure.
=653  20$aStrain energy.
=653  20$aFibrous composites.
=653  20$aMultiaxial.
=653  20$aNonlinear.
=653  20$aStresses.
=653  20$aStrains.
=653  20$aModeling.
=653  20$aSecant modulus.
=700  1\$aAbdel-Jawad, YA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10403J.htm

=LDR  03447nam  2200649 i 4500
=001  CTR10404J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10404J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10404J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aWilson, DW., $eauthor.
=245  13$aAn Analytical and Experimental Evaluation of 0/90 Laminate Tests for Compression Characterization / $cDW Wilson, V Altstädt, M Maier, J Prandy, K Thoma, D Vinckier.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 2 (April 1994)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFor materials development and specification, accurate compressive property measurement with low variability is important, especially if the accuracy is improved by elimination of premature failure by buckling. Existing compression test methods do not satisfy these needs. For this reason the effectiveness of using 0/90 laminates for the determination of unidirectional (0°) compressive strength of composites was evaluated. The concept of using 0/90 laminates to evaluate lamina compressive strength exploits the transverse constraint provided by the 90° plies in combination with increased buckling stability obtained by positioning the 0° plies away from the neutral axis.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite material.
=650  \0$aCompressive strength.
=650  \0$aLaminate strength.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCompressive strength.
=653  20$aComposite material.
=653  20$aLaminate strength.
=700  1\$aAltstädt, V., $eauthor.
=700  1\$aMaier, M., $eauthor.
=700  1\$aPrandy, J., $eauthor.
=700  1\$aThoma, K., $eauthor.
=700  1\$aVinckier, D., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10404J.htm

=LDR  03893nam  2200709 i 4500
=001  CTR10405J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10405J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10405J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aHD9155.A2
=082  04$a338.4/767702832$223
=100  1\$aKaram, GN., $eauthor.
=245  10$aEffect of Fiber-Fiber Interaction on the Strength Properties of Short Fiber Reinforced Cements / $cGN Karam.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 2 (April 1994)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA general modification to the models used for the study of the effect of fiber volume on the strength properties of short fiber reinforced cements is presented. It considers the composite as a mix of cement paste, fibers, and voids. The matrix contribution to the strength of the composite is expressed as a function of the void and fiber volume fractions. A modification to the strength contribution of the fibers is proposed based on the reduction of interfacial surfaces due to fiber-fiber and fiber-void interactions. Furthermore, the void volume fraction is related experimentally to the fiber volume fraction. The effect of these modifications on the different measures of strength and toughness in fiber-reinforced cements is briefly discussed. The experimentally observed nonlinear variation of the bending strength of wood fiber reinforced cement (WFRC) with fiber volume fraction can be predicted by applying the proposed modifications to the rule of mixtures traditionally used to predict that strength.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBending strength.
=650  \0$aEfficiency factor.
=650  \0$aFiber volume fraction.
=650  \0$aFiber-fiber interaction.
=650  \0$aFiber-reinforced cement.
=650  \0$aFiber-void interaction.
=650  \0$aInterfacial surfaces.
=650  \0$aWood fiber.
=650  \0$aPlant fiber industry.
=650  \7$aWOOD PRODUCTS.
=653  10$aBending strength.
=653  20$aEfficiency factor.
=653  20$aFiber-fiber interaction.
=653  20$aFiber-void interaction.
=653  20$aFiber-reinforced cement.
=653  20$aFiber volume fraction.
=653  20$aInterfacial surfaces.
=653  20$aWood fiber.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10405J.htm

=LDR  04086nam  2200625 i 4500
=001  CTR10406J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10406J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10406J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aZalameda, JN., $eauthor.
=245  12$aA Field Deployable Nondestructive Impact Damage Assessment Methodology for Composite Structures / $cJN Zalameda, GL Farley, BT Smith.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 2 (April 1994)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA technique is being developed for rapid in-service detection and quantification of damage in composite airframe structures combining thermal and ultrasonic nondestructive evaluation (NDE). Thermal inspection techniques can be used to identify impact damage areas because it is fast, inspects large areas, and is noncontacting. Once an area of concern is identified, characterization of the depth and extent of the damage can be determined using ultrasonic volumetric imaging. Ultrasonic volumetric imaging quantifies the damage by giving a ply-by-ply view of the damage. Single-sided measurements were made on two types of samples, flat panels with through-the-thickness reinforcements and a "Y"-stiffened skin. These samples were impacted with an aluminum ball at various velocities. The thermal results were compared with ultrasonic C-scans and the ultrasonic volumetric results were compared with destructive tests. The thermal images compared well with the C-scan images in both relative size and shape. It was found that the ultrasonic volumetric results gave a better indication of damage than achievable with the destructive specimen evaluation method. It has been shown that a multidisciplinary approach using thermal and ultrasonic NDE techniques is an efficient and informative inspection method for identifying and quantifying damage.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aThermal nondestructive evaluation (NDE).
=650  \0$aUltrasonic volumetric imaging.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aThrough-the-thickness (TTT) reinforcement.
=653  20$aThermal nondestructive evaluation (NDE).
=653  20$aUltrasonic volumetric imaging.
=653  20$aComposites.
=700  1\$aFarley, GL., $eauthor.
=700  1\$aSmith, BT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10406J.htm

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=001  CTR10409J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10409J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10409J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRoush, JT., $eauthor.
=245  10$aFracture Behavior of a Fiber-Reinforced Titanium Matrix Composite with Open and Filled Holes at Room and Elevated Temperatures / $cJT Roush, S Mall.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 3 (July 1994)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA study was conducted to experimentally investigate the fracture behavior of a titanium-based metal matrix composite (MMC), SCS-9/β21s, with open and filled holes subjected to static tensile load. This study was conducted with unidirectional, crossply, and quasi-isotropic laminates. Unnotched and notched coupons having specimen width to hole diameter ratio of six were tested at room temperature, 482°C, and 650°C. Pins of materials 7075-T6 and Mar-m-246 were employed for filled hole tests. Tests were also conducted on unnotched off-axis and angle-ply laminates to obtain experimental data for the shear strength and the shear modulus of the laminae. Material integrity, residual stresses, interfacial failures, failure progression, and notch sensitivity of the tested MMC were addressed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDamage mechanisms.
=650  \0$aFilled hole.
=650  \0$aFracture behavior.
=650  \0$aHole effects.
=650  \0$aMetal matrix composite.
=650  \0$aNotched strength.
=650  \0$aOpen hole.
=650  \0$aTemperature effects.
=650  \0$aTensile strength.
=650  \0$aTitanium metal matrix composites.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aNotched strength.
=653  20$aTensile strength.
=653  20$aHole effects.
=653  20$aMetal matrix composites (MMCs).
=653  20$aFracture behavior.
=653  20$aOpen hole.
=653  20$aFilled hole.
=653  20$aDamage mechanisms.
=653  20$aTitanium metal matrix composites.
=653  20$aTemperature effects.
=700  1\$aMall, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10409J.htm

=LDR  04420nam  2200709 i 4500
=001  CTR10410J
=003  IN-ChSCO
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=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10410J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10410J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aNeu, RW., $eauthor.
=245  10$aEffect of Laminate Orientation on the Thermomechanical Fatigue Behavior of a Titanium Matrix Composite / $cRW Neu, T Nicholas.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 3 (July 1994)
=504  \\$aIncludes bibliographical references$b23.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThermomechanical fatigue (TMF) tests were conducted on the silicon carbide fiber and titanium alloy matrix composite, SCS-6/TIMETAL®21S. Three different laminate orientations were considered: [0]4, [0/90]s, and [0/±45/90]s. Both in-phase and out-of-phase stress-controlled tests were conducted under a temperature cycle of 150° to 650°C and a stress ratio of 0.1. The fatigue lives for these different orientations can be consolidated within a factor of 3 by normalizing the maximum applied stress (Smax) by the ultimate tensile strength at the Smax temperature of the TMF cycle. For all laminate orientations, the maximum and minimum strain increase during in-phase cycling, whereas only maximum strain increases during out-of-phase cycling. Damage accumulation under inphase cycling is attributed to a combination of the increasing stress carried by the [0] fibers due to cyclic matrix stress relaxation and the gradual breakage of [0] fibers. The damage during out-of-phase cycling is attributed to matrix cracks which initiate at the surface with the aid of the environment and/or initiate internally at the transverse fibers in [0/90]s and [0/±45/90]s composites. A simple model to compute cyclic strain accumulation based on the proposed mechanisms successfully captures the experimentally observed behavior. TMF life is shown to be sensitive to fiber volume fraction under inphase cycling, but not under out-of-phase cycling. TMF conditions are shown to be more severe than isothermal fatigue.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber volume fraction.
=650  \0$aLaminate orientation.
=650  \0$aLife prediction.
=650  \0$aMetal matrix composite.
=650  \0$aSilicon carbide/titanium.
=650  \0$aStrain accumulation.
=650  \0$aThermomechanical fatigue.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aMetal matrix composites (MMCs).
=653  20$aSilicon carbide/titanium.
=653  20$aThermomechanical fatigue (TMF).
=653  20$aLaminate orientation.
=653  20$aLife prediction.
=653  20$aStrain accumulation.
=653  20$aFiber volume fraction.
=700  1\$aNicholas, T., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10410J.htm

=LDR  03885nam  2200685 i 4500
=001  CTR10411J
=003  IN-ChSCO
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=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10411J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10411J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aLi, DS., $eauthor.
=245  10$aUnidirectional Tensile Stress-Strain Response of BP-SiC Fiber Reinforced Ti-6Al-4V / $cDS Li, MR Wisnom.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 3 (July 1994)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe BP C/TiB2 coated SiC fiber reinforced Ti-6Al-4V composite has been studied experimentally and analytically. A good understanding of the material's room temperature mechanical properties has been achieved. The tests include longitudinal tension and transverse tension with both monotonic loading and cyclic loading cases. Micromechanical models have also been developed and give good correlation with test results for longitudinal and transverse tension. Loading-unloading-reloading tests enabled the interfacial strength to be determined. The transverse cyclic loading case was modeled and the friction coefficient at the failed interface was evaluated. In addition, the effect of the C/TiB2 coating on the transverse tensile properties was studied. The low stiffness carbon with anisotropic thermal properties reduced the interfacial radial residual stresses, and therefore decreased the composite stress at interfacial debonding. The composite transverse modulus was also reduced by the coating. Possible ways of improving the material properties are considered.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber coating effects.
=650  \0$aFinite element modeling.
=650  \0$aInterface debonding.
=650  \0$aMetal matrix composites.
=650  \0$aMicromechanics.
=650  \0$aTension tests.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMetal matrix composites.
=653  20$aMicromechanics.
=653  20$aTension tests.
=653  20$aFinite element modeling.
=653  20$aFiber coating effects.
=653  20$aInterface debonding.
=700  1\$aWisnom, MR., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10411J.htm

=LDR  03231nam  2200673 i 4500
=001  CTR10412J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10412J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10412J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC183
=082  04$a541/.33$223
=100  1\$aFernlund, G., $eauthor.
=245  10$aMixed Mode Energy Release Rates for Adhesively Bonded Beam Specimens / $cG Fernlund, JK Spelt.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 3 (July 1994)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper presents closed-form solutions for the energy release rate and the mode ratio of an equal adherend adhesively bonded beam specimen subject to a mixed mode bending load. The developed expressions explicitly account for the thickness and the material properties of the adhesive layer using a beam on an elastic foundation model. The accuracy of the expressions is verified using dimensional analysis and comparison with finite element results, and it is shown that they correlate well with experimental fracture data from adhesively bonded beam specimens with varying crack lengths.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive joints.
=650  \0$aEnergy release rate.
=650  \0$aFracture.
=650  \0$aMixed mode.
=650  \0$aMode ratio.
=650  \0$aTesting.
=650  \0$aAdhesion.
=650  \0$aAdsorption.
=653  10$aAdhesive joints.
=653  20$aFracture.
=653  20$aTesting.
=653  20$aMixed mode.
=653  20$aEnergy release rate.
=653  20$aMode ratio.
=700  1\$aSpelt, JK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10412J.htm

=LDR  03664nam  2200709 i 4500
=001  CTR10413J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10413J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10413J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGirshovich, S., $eauthor.
=245  10$aResidual Strength of Impacted Composites : $bAnalysis and Tests / $cT Gottesman, S Girshovich, E Drukker, N Sela, J Loy.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 3 (July 1994)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe influence of impact damage on the structural performance of composite laminates was investigated by a joint effort including nondestructive evaluation (NDE), mechanical testing, and analysis. The impacted NASA-Industry Standard Compression After Impact test specimen was chosen. Damage characterization was based on ultrasonic methods. Computerized ultrasonic inspection from both sides of the test panels provided accurate information on the damage area. From the NDE data a simplified damage model was constructed and analyzed for strength and stability. Failure loads and modes were predicted. Compression after impact tests were performed for various materials and applied impact energies. All test results were in very good agreement with the analytical predictions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aFailure analysis.
=650  \0$aImpact damage.
=650  \0$aNondestructive evaluation.
=650  \0$aUltrasonic testing.
=650  \0$aX-ray testing.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aImpact damage.
=653  20$aNondestructive evaluation (NDE).
=653  20$aUltrasonic testing.
=653  20$aX-ray testing.
=653  20$aFailure analysis.
=700  1\$aGirshovich, S., $eauthor.
=700  1\$aDrukker, E., $eauthor.
=700  1\$aSela, N., $eauthor.
=700  1\$aLoy, J., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10413J.htm

=LDR  03467nam  2200685 i 4500
=001  CTR10414J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10414J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10414J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA480.A6
=082  04$a620.1/86$223
=100  1\$aValente, T., $eauthor.
=245  10$aMeasurement of Interfacial Properties for Aluminum and Titanium Matrix Alloy Composites Manufactured by Vacuum Plasma Spray / $cT Valente.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 3 (July 1994)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aContinuous fiber silicon carbide/titanium and aluminum matrix composite monolayers were tested by means of an indentation technique to measure the interfacial shear strength. Experimental results were interpreted using two analytical models and compared to results of other researches in order to evaluate the interface quality obtained with a vacuum plasma spray fabrication method. The separate contribution of chemical bond and friction to the mechanical shear strength of the fiber-matrix interface is discussed. For aluminum matrix composites, the interface strength is mainly controlled by frictional force. For titanium matrix composites, chemical bond plays a primary role.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAluminum matrix.
=650  \0$aInterface strength.
=650  \0$aMetal matrix composites.
=650  \0$aPush-back.
=650  \0$aPush-out.
=650  \0$aSilicon carbide fibers.
=650  \0$aTitanium matrix.
=650  \0$aAluminum alloys.
=650  \0$aMetal matrix composites.
=653  10$aMetal matrix composites.
=653  20$aInterface strength.
=653  20$aPush-out.
=653  20$aPush-back.
=653  20$aSilicon carbide fibers.
=653  20$aAluminum matrix.
=653  20$aTitanium matrix.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10414J.htm

=LDR  04041nam  2200673 i 4500
=001  CTR10415J
=003  IN-ChSCO
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=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10415J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10415J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNorman, TL., $eauthor.
=245  10$aEffect of Notch on Failure of Two-Dimensional ±45° Triaxial Braided Textile Composite Materials / $cTL Norman, M Patrick.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 3 (July 1994)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe unnotched and notched (open hole) tensile strength and failure mechanisms of two-dimensional (2-D) triaxial braided composites are examined. The effects of notch size and notch position within the macroscopically nonhomogeneous textile material are investigated. Damage initiation and propagation in notched and unnotched coupons are also examined. Two different fiber architectures are considered, both of similar braid geometry but one with larger longitudinal yarns (approximately six times) and larger percent of longitudinal yarns (approximately four times). The 2-D braided coupons exhibited notch and notch position sensitivity that were architecture dependent. Notch sensitivity occurred in coupons with notch size greater than the unit cell size and increased with hole diameter. Results suggested notch position sensitivity in one of the architectures tested. Cracking was found to initiate in braider yarns in unnotched and notched coupons, and to propagate in the direction of the braider yarns until failure. Fracture occurred along the braider yarn in both architectures but differed in size and appearance, suggesting architectural influences on damage mechanisms. Our results show the damage initiation and propagation is most likely to occur within the braider yarns.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDamage initiation.
=650  \0$aDamage propagation.
=650  \0$aFailure.
=650  \0$aNotched.
=650  \0$aTextile composite materials.
=650  \0$aTriaxial braided.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aTextile composite materials.
=653  20$aTriaxial braided.
=653  20$aNotched.
=653  20$aDamage initiation.
=653  20$aDamage propagation.
=653  20$aFailure.
=700  1\$aPatrick, M., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10415J.htm

=LDR  03480nam  2200709 i 4500
=001  CTR10416J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10416J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10416J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aOrso, J., $eauthor.
=245  14$aThe Effects of an Expanding Monomer on the Tensile Properties of Graphite/Epoxy / $cJ Orso, AJ Vizzini.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 3 (July 1994)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aGraphite/epoxy specimens with shrinkage controlled matrix were manufactured and tested in uniaxial tension. The resin used was Epon 813 with dinorbornene spiro orthocarbonate (DNSOC) as the expanding monomer in quantities of 0%, 5%, and 10% by weight. Two different laminates were studied. Unidirectional laminates, [0]4, were tested to determine the effects on longitudinal, fiber-dominated properties. Cross-ply laminates, [0/902]8, were tested to determine the effects on transverse, matrix-dominated properties. The key effects of the addition of DNSOC are the reduction of the longitudinal tensile ultimate strength and the delay of the onset of cracks by reducing the average residual stress.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCrack density.
=650  \0$aCure shrinkage.
=650  \0$aCure stresses.
=650  \0$aExpanding monomer.
=650  \0$aGraphite/epoxy.
=650  \0$aRing-opening polymer.
=650  \0$aTension.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=653  10$aTension.
=653  20$aGraphite/epoxy.
=653  20$aExpanding monomer.
=653  20$aCrack density.
=653  20$aRing-opening polymer.
=653  20$aCure stresses.
=653  20$aCure shrinkage.
=700  1\$aVizzini, AJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10416J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10420J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10420J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aPost, D., $eauthor.
=245  10$aDeformation of a Metal-Matrix Tensile Coupon with a Central Slot : $bAn Experimental Study / $cD Post, R Czarnek, D Joh, J Jo, Y Guo.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 1 (March 1987)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA metal-matrix specimen was investigated using high-sensitivity moire interferometry. The specimen was a 6-ply [0/±45]s boron-aluminum tensile coupon with a central slot. In-plane displacement fields were analyzed at various load levels from 15 to 95% of the failure load. Normal and shear strains were determined from displacement gradients. Highly localized plastic slip zones occurred in the ductile aluminum matrix tangent to the ends of the slot. Shear strains in the slip zone were an order of magnitude greater than the largest normal strains in the specimen. The shear-strain concentration factor γxy/ϵff rose dramatically with the onset of plastic slip and continued to rise gradually with load to 95% of the failure load. Upon unloading, shear strains in the slip zone remained precariously high. The maximum normal strain occurred at the end of the slot, where the normal-strain concentration factor ϵy/ϵff diminished as the load increased.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBoron-aluminum.
=650  \0$aCentral slot.
=650  \0$aComposites.
=650  \0$aDeformation fields.
=650  \0$aElastic-plastic.
=650  \0$aExperimental analysis.
=650  \0$aMetal-matrix composites.
=650  \0$aMicromechanics.
=650  \0$aMoire interferometry.
=650  \0$aPlastic slip.
=650  \0$aStrain concentration factors.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aMetal-matrix composites.
=653  20$aBoron-aluminum.
=653  20$aCentral slot.
=653  20$aElastic-plastic.
=653  20$aDeformation fields.
=653  20$aPlastic slip.
=653  20$aStrain concentration factors.
=653  20$aMoire interferometry.
=653  20$aExperimental analysis.
=653  20$aMicromechanics.
=700  1\$aCzarnek, R., $eauthor.
=700  1\$aJoh, D., $eauthor.
=700  1\$aJo, J., $eauthor.
=700  1\$aGuo, Y., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10420J.htm

=LDR  04133nam  2200661 i 4500
=001  CTR10421J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10421J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10421J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aHF5415.153
=082  04$a658.5$223
=100  1\$aJohnson, WS., $eauthor.
=245  10$aInvestigation of Fiber Bridging in Double Cantilever Beam Specimens / $cWS Johnson, PD Mangalgiri.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 1 (March 1987)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn investigation was conducted to (1) see if fiber bridging could be eliminated or at least reduced and (2) evaluate an alternative approach for determination of in-situ Mode I fracture toughness values of composite matrix materials. Toward this end, double cantilever beam (DCB) specimens were made using unidirectional layups of T6C/Hx205 composite material in which the delaminating halves were placed at angles of 0°, 1.5°, and 3° to each other. The small angles between the delaminating plies were used to avoid fiber nesting without significantly affecting Mode I behavior. A starter delamination was introduced by using a thin Teflon® insert. DCB specimens were also fabricated and tested with a 0.0254-mm thick bondline of Hx205 between aluminum adherends. This study resulted in the following conclusions: the extent that fiber bridging and interlaminar toughness increase with crack length can be reduced by slight cross ply at the delamination plane to reduce fiber nesting; some fiber bridging may occur even in the absence of fiber nesting; the first values of toughness measured ahead of the thin Teflon® insert were observed to be very close to the toughness of the matrix material with no fiber bridging; and thin (0.0254-mm) adhesive bondline of matrix material appears to give toughness values equal to the interlaminar toughness of the composite matrix without fiber bridging.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aFiber bridging.
=650  \0$aFracture mechanics.
=650  \0$aInterlaminar fracture toughness.
=650  \0$aStrain energy release rate.
=650  \0$aComposites.
=650  \0$aFracture mechanics.
=653  10$aComposites.
=653  20$aInterlaminar fracture toughness.
=653  20$aFiber bridging.
=653  20$aDouble cantilever beam specimen.
=653  20$aStrain energy release rate.
=653  20$aFracture mechanics.
=700  1\$aMangalgiri, PD., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10421J.htm

=LDR  03226nam  2200673 i 4500
=001  CTR10422J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10422J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10422J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHyer, MW., $eauthor.
=245  10$aTemperature and Deflection Data From the Asymmetric Heating of Cross-Ply Composite Tubes / $cMW Hyer, DE Cooper, D Cohen, SS Tompkins.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 1 (March 1987)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aData generated while heating several cross-ply graphiteepoxy tubes on one side, along their lengths, and cooling them on the other side are presented. This heating arrangement produces a circumferential temperature gradient, and the data show that the gradient can be represented by a cosinusoidal temperature distribution. The thermally induced bending deflections caused by the temperature gradient are also presented.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite tubes.
=650  \0$aDefections.
=650  \0$aTemperature gradients.
=650  \0$aThermal effects.
=650  \0$aThermally induced deflections.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite tubes.
=653  20$aThermal effects.
=653  20$aDefections.
=653  20$aThermally induced deflections.
=653  20$aTemperature gradients.
=700  1\$aCooper, DE., $eauthor.
=700  1\$aCohen, D., $eauthor.
=700  1\$aTompkins, SS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10422J.htm

=LDR  03471nam  2200697 i 4500
=001  CTR10423J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10423J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10423J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aYaniv, G., $eauthor.
=245  10$aMethod for Hygromechanical Characterization of Graphite/Epoxy Composite / $cG Yaniv, G Peimanidis, IM Daniel.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 1 (March 1987)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn experimental method is described for measuring hygroscopic swelling strains and mechanical strains of moisture-conditioned composite specimens. The method consists of embedding encapsulated strain gages in the midplane of the composite laminate; thus it does not interfere with normal moisture diffusion. It is particularly suited for measuring moisture swelling coefficients and for mechanical testing of moisture-conditioned specimens at high strain rates. Results obtained by the embedded gage method were shown to be more reliable and reproducible than those obtained by surface gages, dial gages, or extensometers.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEmbedded gages.
=650  \0$aEnvironmental effects.
=650  \0$aGraphite/epoxy composites.
=650  \0$aHygroscopic expansion.
=650  \0$aHygrothermal characterization.
=650  \0$aMoisture content.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=653  10$aGraphite/epoxy composites.
=653  20$aEnvironmental effects.
=653  20$aMoisture content.
=653  20$aHygroscopic expansion.
=653  20$aEmbedded gages.
=653  20$aHygrothermal characterization.
=700  1\$aPeimanidis, G., $eauthor.
=700  1\$aDaniel, IM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10423J.htm

=LDR  03446nam  2200661 i 4500
=001  CTR10426J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10426J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10426J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTS283
=082  04$a681/.760410288$223
=100  1\$aLewis, G., $eauthor.
=245  10$aFilament-Wound Spherical Pressure Vessels : $bA State-of-the-Art Review / $cG Lewis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 2 (June 1987)
=504  \\$aIncludes bibliographical references$b34.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFilament-wound composite materials offer practical alternatives to metals for pressure vessel applications where weight, service, environment, or other factors limit the use of metals. In particular, such pressure vessels with a spherical geometry are used in applications in the space shuttle and for storage of various fluids. For these vessels, typical composite materials and filament-winding procedures currently in use are described, and a brief primer on their stress analysis and failure criteria is presented. Details of the behavior and statistics of failure of these vessels under static internal pressurization are given. Finally, the latest concepts in the monitoring and modeling of internal damage are summarized.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFilament-winding.
=650  \0$aInternal damage.
=650  \0$aSolid rocket booster motor case.
=650  \0$aSpherical pressure vessels.
=650  \0$aStatic pressurization.
=650  \0$aStress analysis.
=650  \0$aPressure Vessels.
=650  \0$aFilament winding.
=653  10$aFilament-winding.
=653  20$aSpherical pressure vessels.
=653  20$aStress analysis.
=653  20$aSolid rocket booster motor case.
=653  20$aStatic pressurization.
=653  20$aInternal damage.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10426J.htm

=LDR  03429nam  2200649 i 4500
=001  CTR10427J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10427J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10427J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA409
=082  04$a620.1/26$223
=100  1\$aJoshi, SP., $eauthor.
=245  10$aImpact-Induced Fracture in a Quasi-Isotropic Laminate / $cSP Joshi, CT Sun.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 2 (June 1987)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA systematic study of impact-induced fracture in a quasi-isotropic laminated composite is carried out. The main focus of the study is to understand damage initiation when a laminate is subjected to the impact of a foreign object. The total incipient damage of a laminate subjected to impact at higher than threshold velocity is also presented. The incipient damage is restricted to small growth from the initiation of the damage. The experimentally collected data are interpreted using a two-dimensional plane-strain finite-element analysis. The qualitative comparison suggests that the skew cracks in the proximal layers are primarily due to transverse shear stress. Skew cracks in the middle layers are also due to transverse shear stress. Vertical cracks in the distal layer are due to flexural stress transverse to the fiber orientation of the layer.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCracks.
=650  \0$aDamage.
=650  \0$aFracture.
=650  \0$aImpact.
=650  \0$aLaminate composites.
=650  \0$aFracture mechanics.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aLaminate composites.
=653  20$aImpact.
=653  20$aFracture.
=653  20$aDamage.
=653  20$aCracks.
=700  1\$aSun, CT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10427J.htm

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=001  CTR10428J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10428J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10428J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$ados Reis, HLM, $eauthor.
=245  10$aThin-Walled Laminated Composite Cylindrical Tubes : $bPart I-Boundary Value Problems / $cHLM dos Reis, RB Goldman.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 2 (June 1987)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA procedure is presented for solving two-point boundary value problems of filamentary wound composite cylindrical shells of finite length subjected to general edge loadings. The three Donnell's equilibrium equations, written in terms of the displacements, are reduced to a set of 16 first order coupled ordinary differential equations. This set of equations, together with the prescribed boundary conditions at each circular end of the composite cylinder, is then numerically solved using a variable step size finite difference scheme. Two examples are presented and discussed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBoundary value problems.
=650  \0$aComposite cylinders.
=650  \0$aCylindrical tubes.
=650  \0$aFinite difference scheme.
=650  \0$aLaminated composites.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCylindrical tubes.
=653  20$aBoundary value problems.
=653  20$aLaminated composites.
=653  20$aFinite difference scheme.
=653  20$aComposite cylinders.
=700  1\$aGoldman, RB., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10428J.htm

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=001  CTR10429J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10429J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10429J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA347.B69
=082  04$a620$223
=100  1\$ados Reis, HLM, $eauthor.
=245  10$aThin-Walled Laminated Composite Cylindrical Tubes : $bPart II-Bending Analysis / $cHLM dos Reis, RB Goidman.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 2 (June 1987)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA beam-type stiffness matrix for thin-walled filamentary wound laminated composite tubes of any layup is derived. This beam-type stiffness matrix has degrees of freedom that are consistent with stiffness matrices used in classical matrix analysis of structures, and it is numerically constructed from results of two-point boundary value problems using Donnell's shell theory. Using this stiffness matrix, numerical results are obtained for the deflections of a simply supported composite tube loaded at its center. It is noted that for certain layups the beam theory approach using a longitudinal equivalent Young's modulus tends to mask fundamental characteristics that govern the static response of laminated composite tubes.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBending.
=650  \0$aBoundary-value problems.
=650  \0$aComposite tubes.
=650  \0$aDonnell shell theory.
=650  \0$aLaminated tubes.
=650  \0$aStiffness matrix.
=650  \0$aBoundary-value problems.
=650  \0$aBoundary conditions (Differential equations)
=653  10$aComposite tubes.
=653  20$aStiffness matrix.
=653  20$aBending.
=653  20$aLaminated tubes.
=653  20$aDonnell shell theory.
=653  20$aBoundary-value problems.
=700  1\$aGoidman, RB., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10429J.htm

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=001  CTR10430J
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=024  7\$a10.1520/CTR10430J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10430J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$ados Reis, HLM, $eauthor.
=245  10$aThin-Walled Laminated Composite Cylindrical Tubes : $bPart III-Bending Analysis / $cHLM dos Reis, RB Goldman, PH Verstrate.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 2 (June 1987)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA numerical procedure to evaluate the rotordynamic performance of thin-walled filamentary wound laminated composite circular cylindrical shafts of any layup is presented. The rotordynamic formulation follows Ruhl's approach modified to include a beam-type stiffness matrix that is numerically constructed from the solution of two-point boundary value problems of composite circular cylinders. Numerical results for the critical speeds and the unbalance response of a sample composite shaft are obtained and compared with predictions based on classical methods of analysis and experimental results found in the literature. It was observed that for certain layups the classical methods of analysis tend to mask fundamental characteristics that govern the rotordynamic response of composite shafts.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite shafts.
=650  \0$aComposite tubes.
=650  \0$aCritical speeds.
=650  \0$aRotordynamic response.
=650  \0$aUnbalance response.
=650  \0$aWhirl orbits.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCritical speeds.
=653  20$aComposite shafts.
=653  20$aRotordynamic response.
=653  20$aWhirl orbits.
=653  20$aComposite tubes.
=653  20$aUnbalance response.
=700  1\$aGoldman, RB., $eauthor.
=700  1\$aVerstrate, PH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10430J.htm

=LDR  03730nam  2200637 i 4500
=001  CTR10433J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10433J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10433J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aCaslini, M., $eauthor.
=245  10$aStudy of Matrix Cracking and Delamination in Glass/Epoxy Laminates / $cM Caslini, C Zanotti, TK O'Brien.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 4 (December 1987)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis study focused on characterizing matrix cracking and delamination behavior in multidirectional laminates. Static tension and tension-tension fatigue tests were conducted on two different layups. Damage onset, accumulation, and residual properties were measured. Matrix cracking was shown to have a considerable influence on residual stiffness of glass epoxy laminates and could be predicted reasonably well for cracks in 90° plies using a simple shear lag analysis. A fracture mechanics analysis for the strain energy release rate associated with 90° ply matrix crack formation was developed and was shown to correlate the onset of 90° ply cracks in different laminates. The linear degradation of laminate modulus with delamination area, previously observed for graphite epoxy laminates, was predicted for glass epoxy laminates using a simple rule of mixtures analysis. The strain energy release rate associated with edge delamination formation under static and cyclic loading was difficult to analyze because of the presence of several contemporary damage phenomena.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDamage.
=650  \0$aDelamination.
=650  \0$aFracture mechanics.
=650  \0$aGlass-epoxy.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aGlass-epoxy.
=653  20$aFracture mechanics.
=653  20$aDelamination.
=653  20$aDamage.
=700  1\$aZanotti, C., $eauthor.
=700  1\$aO'Brien, TK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10433J.htm

=LDR  03125nam  2200637 i 4500
=001  CTR10434J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10434J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10434J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a624.1/7$223
=100  1\$aReddy, JN., $eauthor.
=245  12$aA Mixed Updated Lagrangian Formulation for Plane Elastic Problems / $cJN Reddy, PR Heyliger.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 4 (December 1987)
=504  \\$aIncludes bibliographical references$b23.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA mixed finite-element model based on the incremental nonlinear theory of solid bodies is developed and its numerical accuracy is evaluated by applying the model to a number of plane elastic problems. The theoretical basis of the finite-element model is developed using a mixed updated Lagrangian formulation. The mixed model contains the displacements and stresses as the nodal degrees of freedom. Such mixed models prove to be convenient in the solution of contact stress problems.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDisplacements.
=650  \0$aLagrangian formulations.
=650  \0$aPlane elastic problems.
=650  \0$aStresses.
=650  \0$aStrains and stresses.
=650  \0$aStructural dynamics.
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aLagrangian formulations.
=653  20$aPlane elastic problems.
=653  20$aDisplacements.
=653  20$aStresses.
=700  1\$aHeyliger, PR., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10434J.htm

=LDR  04302nam  2200673 i 4500
=001  CTR10435J
=003  IN-ChSCO
=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10435J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10435J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGause, LW., $eauthor.
=245  10$aStructural Properties of Braided Graphite/Epoxy Composites / $cLW Gause, JM Alper.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 4 (December 1987)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe mechanical, impact, and fatigue properties of graphite/epoxy composites manufactured using a general braiding process are being evaluated for possible flight vehicle applications. This new process achieves a fully integrated, multi-dimensional orientation of the fibers and allows the braiding of complex shapes, such as I-beams and cylinders. Motivating this study is the desire to improve the impact resistance, thickness-direction strength, and overcome the delamination tendencies of conventional, laminated composites. Two styles of braided test coupons have been fabricated and tested. Style I is the basic (1 × 1 × 1) braid pattern. Style II is constructed by holding half of the yarns as straight columns and braiding the rest of the yarns about the fixed yarns. Some difficulties were encountered developing the processing methods to vacuum draw the hot melt Hercules 3501 resin into the "Celion 12000" graphite braided preforms and obtain a satisfactory autoclave cure. Results show the braid to have similar strength and elastic properties to corresponding, angle-plied laminates while greatly limiting the extent of impact damage. The braid does not increase the impact damage threshold, however. Tests performed on braided specimens with 6.35 mm (¼ in.) diameter open holes show no tensile strength reduction because of the hole. Bearing strength, transverse strength, and transverse stiffness properties are lower than laminated composites. Tensile fatigue properties are similar to conventional laminates, but compressive fatigue performance is worse.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFatigue (materials)
=650  \0$aGraphite/epoxy.
=650  \0$aImpact.
=650  \0$aStatic strength.
=650  \0$aThree-dimensional fabrics.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aThree-dimensional fabrics.
=653  20$aImpact.
=653  20$aFatigue (materials).
=653  20$aGraphite/epoxy.
=653  20$aStatic strength.
=700  1\$aAlper, JM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10435J.htm

=LDR  04016nam  2200637 i 4500
=001  CTR10436J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10436J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10436J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aDavidson, JA., $eauthor.
=245  14$aThe Challenge and Opportunity for Composites in Structural Orthopaedic Applications / $cJA Davidson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 4 (December 1987)
=504  \\$aIncludes bibliographical references$b77.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aOrthopaedics, the science that deals with the functional preservation and restoration of the skeletal system, has historically relied on high-strength, corrosion-resistant metals. A better understanding of skeletal forces and bone remodeling has recently led scientists to consider the potential application of polymer matrix composite materials for orthopaedic applications. The attractive characteristics of composites include a relatively lower elastic modulus compared to current implant metals, no potential for metal ion release in the body environment, and the ability to custom tailor strength and other mechanical properties to best suit a particular design requirement. While these features are attractive, the harsh service conditions imposed by the human body require that development of an acceptable composite implant be well researched. This study presents details of these research areas, thus presents the challenge. The most appropriate opportunities for composites as an alternative implant material are also discussed. There is a definite need for improved implant materials and one that is increasing yearly as the life expectancy increases and the population of the elderly expands. Improved orthopaedic implants are needed to meet the needs of these patients, primarily arthritic, and thus provide a capability to further improve their quality of life.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aFatigue integrity.
=650  \0$aHip loading.
=650  \0$aIn-vivo environment.
=650  \0$aOrthopaedic implants.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aOrthopaedic implants.
=653  20$aComposites.
=653  20$aHip loading.
=653  20$aIn-vivo environment.
=653  20$aFatigue integrity.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10436J.htm

=LDR  03734nam  2200625 i 4500
=001  CTR10437J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c19879999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10437J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10437J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aWoo, MSW, $eauthor.
=245  10$aWater Absorption of Resins and Composites : $bII. Diffusion in Carbon and Glass Reinforced Epoxies / $cMSW Woo, MR Piggott.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1987.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 9, Issue 4 (December 1987)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe diffusion of water in carbon and glass reinforced epoxies was investigated over a range of humidities from about 33 to 97%, by immersion, and at temperatures in the range 23 to 100°C. (The water absorption properties of the resins themselves were described in the first paper of the series.) The composites obeyed Fick's law, that is, water absorbed was determined by the square root of the immersion time during the initial absorption. The volume of water absorbed at equilibrium by the composites was usually determined by the polymer matrix volume. Where there were exceptions to this, there was evidence of water being concentrated at the fiber-matrix interface. The results otherwise indicated that there was a linear relation between water absorbed at the interface and the temperature. Diffusivities decreased linearly with the square root of fiber volume fraction for both carbon and glass fibers, and under all conditions tested. The fibers thus appeared to act as barriers to diffusion. However, there was strong evidence that these composites had regions with enhanced diffusivity.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1987. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAbsorption.
=650  \0$aFiber composites.
=650  \0$aFiber-matrix interface.
=650  \0$aWater diffusion.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aFiber composites.
=653  20$aWater diffusion.
=653  20$aAbsorption.
=653  20$aFiber-matrix interface.
=700  1\$aPiggott, MR., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10437J.htm

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=001  CTR10448J
=003  IN-ChSCO
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=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10448J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10448J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a624.1/8$223
=100  1\$aWang, Y., $eauthor.
=245  10$aProperties and Analysis of Composites Reinforced with E-Glass Weft-Knitted Fabrics / $cY Wang, Y Gowayed, X Kong, J Li, D Zhao.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 4 (October 1995)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWeft-knitted 1 × 1 rib-fabrics are manufactured from E-glass rovings and are consolidated into flat panels using the resin transfer molding (RTM) process. The panels, with about 50% fiber volume fraction, are tested for their mechanical properties in tension, flexure, compression, and short-beam shear. The property values are reported and the failure mechanisms under different loading conditions are identified and compared. The elastic properties of the knitted composites are analyzed by geometric modeling followed by the finite element analysis (FEA). Good predictions are obtained.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFailure mechanisms.
=650  \0$aMechanical properties.
=650  \0$aTextile composites.
=650  \0$aTheoretical analysis.
=650  \0$aComposite materials $xMechanical properties.
=650  \0$aMechanical properties.
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aTextile composites.
=653  20$aWeft knit.
=653  20$aMechanical properties.
=653  20$aFailure mechanisms.
=653  20$aTheoretical analysis.
=700  1\$aGowayed, Y., $eauthor.
=700  1\$aKong, X., $eauthor.
=700  1\$aLi, J., $eauthor.
=700  1\$aZhao, D., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10448J.htm

=LDR  04121nam  2200685 i 4500
=001  CTR10449J
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=024  7\$a10.1520/CTR10449J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10449J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSubramanian, S., $eauthor.
=245  10$aTensile Strength of Unidirectional Composites : $bThe Role of Efficiency and Strength of Fiber-Matrix Interface / $cS Subramanian, KL Reifsnider, WW Stinchcomb.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 4 (October 1995)
=504  \\$aIncludes bibliographical references$b28.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA micromechanics model has been developed to predict the tensile strength of unidirectional composites. The local stresses are calculated using shear lag analysis, including the effects of interfacial debonding. The tensile strength of the composite is estimated by considering the accumulation of fiber fractures as a function of applied load. A new parameter called 'efficiency' of the interface is introduced to account for the effectiveness of load transfer from the matrix to the fiber. A simple scheme is described to estimate this efficiency parameter η using the experimentally measured tensile stiffness in the concentric cylinders model. It is postulated that the interface can be completely characterized by two parameters: interfacial shear strength τi and efficiency of the interface η. Results indicate that the interfacial strength and efficiency can be optimized to maximize the tensile strength of a unidirectional composite. The proposed model was used to predict tensile strength of three different sets of materials that possessed carefully tailored interphase variations. The predicted tensile strengths agree well with the experimental data. The predicted failure modes in these material systems are also consistent with experimental observations.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDebonding.
=650  \0$aFiber fractures.
=650  \0$aIneffective length.
=650  \0$aInterface.
=650  \0$aStress concentration.
=650  \0$aTensile strength.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aTensile strength.
=653  20$aInterface.
=653  20$aDebonding.
=653  20$aFiber fractures.
=653  20$aStress concentration.
=653  20$aIneffective length.
=700  1\$aReifsnider, KL., $eauthor.
=700  1\$aStinchcomb, WW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10449J.htm

=LDR  03082nam  2200649 i 4500
=001  CTR10450J
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=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10450J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10450J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aWheeler, NS., $eauthor.
=245  10$aElectrodeposited Cobalt-Tungsten as a Diffusion Barrier Between Graphite Fibers and Nickel / $cNS Wheeler, DS Lashmore.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 4 (October 1995)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn electrodeposited cobalt alloy coating having a composition of 7.1 ± 0.8 at % tungsten was developed to serve as a diffusion barrier between graphite fibers and nickel. A nickel matrix was electrodeposited around the fibers, and the resulting composite was annealed in vacuum under various time/temperature conditions. The coating was shown to inhibit interdiffusion for up to 24 h at 800°C. This represents an improvement of 200° over the uncoated fibers.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCobalt.
=650  \0$aComposite.
=650  \0$aDiffusion.
=650  \0$aNickel.
=650  \0$aTungsten.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCobalt.
=653  20$aTungsten.
=653  20$aNickel.
=653  20$aComposite.
=653  20$aDiffusion.
=700  1\$aLashmore, DS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10450J.htm

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=001  CTR10451J
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=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10451J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10451J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.S25
=082  04$a624$223
=100  1\$aKassapoglou, C., $eauthor.
=245  10$aWrinkling of Composite Sandwich Structures Under Compression / $cC Kassapoglou, SC Fantle, JC Chou.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 4 (October 1995)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe phenomenon of wrinkling as a failure mode of sandwich composite structures under compression is examined using analysis verified by testing. Two cases are considered. In the first case, the facesheets are assumed flat and the wrinkling compression load is determined as a buckling load along with the associated short wavelength. This solution is then compared to finite element predictions and is shown to be in very good agreement. In the second case, the facesheets are assumed to have a wavy shape of known amplitude and wavelength. The various failure modes possible (core tension, compression or shear, adhesive tension or shear, and facesheet bending) are modeled in an effort to predict failure. Test specimens were fabricated and the waviness of the facesheets was measured. The specimens were then tested in compression. Reasonable agreement was found with theoretical predictions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression failure.
=650  \0$aLocal buckling.
=650  \0$aSandwich structure.
=650  \0$aShort wavelength buckling.
=650  \0$aWaviness.
=650  \0$aWrinkling.
=650  \0$aSandwich construction.
=650  \0$aSandwich construction $vPeriodicals.
=653  10$aSandwich structure.
=653  20$aWrinkling.
=653  20$aWaviness.
=653  20$aCompression failure.
=653  20$aLocal buckling.
=653  20$aShort wavelength buckling.
=700  1\$aFantle, SC., $eauthor.
=700  1\$aChou, JC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10451J.htm

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=001  CTR10452J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10452J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10452J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC183
=082  04$a541/.33$223
=100  1\$aFernlund, G., $eauthor.
=245  10$aMixed Mode II-Mode III Fracture of Adhesive Joints / $cG Fernlund, H Lanting, JK Spelt.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (14 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 4 (October 1995)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper presents approximate closed-form expressions for the local energy release rate in Mode I, Mode II, and Mode III along the idealized straight crack front of a cracked generalized adhesive joint. The development is based on beam theory, the J-integral, and a beam-on-an-elastic-foundation model. Fracture experiments were performed with adhesively bonded split-cantilever-beam (SCB) specimens of different adherend widths and thickness ratios using two different adhesives, and it was seen that the fracture surface had a peculiar stepped arrowhead shape. The analysis and the experiments showed that both the energy release rate and the mode mix vary along the crack front of an SCB specimen, making it unsuitable for the determination of fundamental fracture properties. However, the SCB specimen provided a useful means to test an engineering approach to predict the out-of-plane fracture loads of adhesive joints.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive joints.
=650  \0$aEnergy release rate.
=650  \0$aFailure prediction.
=650  \0$aFracture testing.
=650  \0$aMixed mode.
=650  \0$aSplit cantilever beam.
=650  \0$aAdhesion.
=650  \0$aAdsorption.
=653  10$aAdhesive joints.
=653  20$aMixed mode.
=653  20$aMode I.
=653  20$aMode II.
=653  20$aMode III.
=653  20$aSplit cantilever beam.
=653  20$aEnergy release rate.
=653  20$aFailure prediction.
=653  20$aFracture testing.
=700  1\$aLanting, H., $eauthor.
=700  1\$aSpelt, JK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10452J.htm

=LDR  03606nam  2200673 i 4500
=001  CTR10453J
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=005  20161219163000.0
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=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10453J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10453J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTS283
=082  04$a681/.760410288$223
=100  1\$aCohen, D., $eauthor.
=245  10$aPressurized Ring Test for Composite Pressure Vessel Hoop Strength and Stiffness Evaluation / $cD Cohen, YT Toombes, AK Johnson, MF Hansen.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 4 (October 1995)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWith the expanding use of composite pressure vessels, including space, tactical, and civil applications, accurate prediction of performance becomes increasingly important. A critical parameter in performance prediction is the burst strength, as measured by the hoop fiber ultimate strain-to-failure. This paper discusses a newly developed test method that is capable of pressure testing 50.8-cm diameter rings with representative composite pressure vessels' laminate thicknesses and lay-ups. Tests of rings with various laminate thicknesses and lay-ups showed excellent agreement with measured delivered fiber strength and stiffness in full-scale composite pressure vessels. Test data show nearly a one-to-one scaling in strength.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite pressure vessel.
=650  \0$aFilament wound vessel.
=650  \0$aFull-scale and sub-scale vessels.
=650  \0$aHoop fiber strength and stiffness.
=650  \0$aPressurized ring test.
=650  \0$aPressure Vessels.
=650  \0$aFilament winding.
=653  10$aPressurized ring test.
=653  20$aComposite pressure vessel.
=653  20$aHoop fiber strength and stiffness.
=653  20$aFilament wound vessel.
=653  20$aFull-scale and sub-scale vessels.
=700  1\$aToombes, YT., $eauthor.
=700  1\$aJohnson, AK., $eauthor.
=700  1\$aHansen, MF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10453J.htm

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=001  CTR10454J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10454J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10454J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aAdams, DF., $eauthor.
=245  10$aExperimental Study of Three- and Four-Point Shear Test Specimens / $cDF Adams, EQ Lewis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 4 (October 1995)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe measured short beam (three-point) shear strength was found to be strongly influenced by the support span-to-specimen thickness l/t ratio, and to a lesser extent, by the specimen thickness and the diameters of the loading and support cylinders. As the l/t ratio decreased, the shear strength increased. Transverse compressive stresses, induced by the support and loading cylinders, may have progressively inhibited shear failures as the separation of the cylinders decreased with decreasing l/t ratio. Nevertheless, shear failure modes were typically observed. Local compressive damage under the loading cylinder was a minor secondary event, if it occurred at all. Similar results were obtained for the four-point shear test specimen configuration. The four-point shear test method yielded shear strengths similar to those for the short-beam shear test for the unidirectional glass/epoxy composite but lower shear strengths for the unidirectional carbon/epoxy composite.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon/epoxy test methods.
=650  \0$aComposite materials.
=650  \0$aFour-point shear.
=650  \0$aShear tests.
=650  \0$aShort-beam shear.
=650  \0$aShear (Mechanics)
=650  \0$aDeformations (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aShort-beam shear.
=653  20$aFour-point shear.
=653  20$aComposite materials.
=653  20$aShear tests.
=653  20$aCarbon/epoxy test methods.
=700  1\$aLewis, EQ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10454J.htm

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=001  CTR10459J
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=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10459J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10459J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aRA785
=082  04$a616.89$223
=100  1\$aJohnson, WS., $eauthor.
=245  14$aThe Wayne W. Stinchcomb Memorial Lecture and Award / $cWS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (1 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 1 (January 1996)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aTechnology.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10459J.htm

=LDR  03230nam  2200661 i 4500
=001  CTR10460J
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=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10460J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10460J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGowayed, Y., $eauthor.
=245  10$aSurface Inspection of Textile Composite Materials Using Image Analysis Techniques / $cY Gowayed, DV Schreibman, M Roberts.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 1 (January 1996)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this paper, a novel visual quality control technique for production of textile composite materials is presented. This technique is based on the idea of automated image processing. The approach starts by acquiring images of the surface of a composite product using a combination of a microscope and a frame grabbing board connected to a computer. Image processing is then applied to the acquired images to extract important features. In the current study, the features of importance are orientation of surface yarns.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aHough transform.
=650  \0$aImage analysis.
=650  \0$aQuality control.
=650  \0$aTextiles.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aImage analysis.
=653  20$aComposites.
=653  20$aTextiles.
=653  20$aHough transform.
=653  20$aQuality control.
=700  1\$aSchreibman, DV., $eauthor.
=700  1\$aRoberts, M., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10460J.htm

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=024  7\$a10.1520/CTR10461J$2doi
=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aSanders, BP., $eauthor.
=245  10$aTransverse Fatigue Response of a Metal Matrix Composite Under Strain-Controlled Mode at Elevated Temperature : $bPart I-Experiments / $cBP Sanders, S Mall.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 1 (January 1996)
=504  \\$aIncludes bibliographical references$b25.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe transverse fatigue characteristics of a unidirectional titanium-based metal matrix composite (MMC) (SCS-6/Ti-15-3) were investigated under an isothermal condition. Fatigue tests were performed using a hybrid strain-controlled loading mode. In this hybrid control mode, the specimen was always in a tension-tension state of stress perpendicular to the fiber direction. This prevented any possible buckling effects. A systematic approach that involved fatigue tests, microscopic evaluation, and micromechanical analysis, was taken to characterize the fatigue response (that is, fatigue life, stress-strain response, and so forth) and identify the damage and deformation mechanisms. The analysis involved a unique method to model the fiber-matrix interfacial damage. It was found that the fatigue response was initially dominated by the amount of fiber-matrix interfacial damage that occurred during the first loading cycle. The subsequent response was dependent on the rate at which this interfacial damage progressed, the development and propagation of matrix cracks, and matrix inelastic deformation (plasticity and creep). The chronology and accumulation of these damage mechanisms were dependent on the applied strain level. Using the combined approach involving experiments, microscopy, and analysis, the correlation among applied strain levels, fatigue life, damage mechanisms, and macroscopic response (stress and stiffness) were established in this paper. In Part II, the details and results of the micromechanical analysis are presented.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFatigue.
=650  \0$aMetal matrix composite.
=650  \0$aStrain-control mode.
=650  \0$aTitanium matrix composite.
=650  \0$aTransverse behavior.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aMetal matrix composites (MMCs).
=653  20$aTransverse behavior.
=653  20$aStrain-control mode.
=653  20$aTitanium matrix composite.
=653  20$aFatigue.
=700  1\$aMall, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10461J.htm

=LDR  03696nam  2200661 i 4500
=001  CTR10462J
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=024  7\$a10.1520/CTR10462J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10462J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aSanders, BP., $eauthor.
=245  10$aTransverse Fatigue Response of a Metal Matrix Composite Under Strain-Controlled Mode at Elevated Temperature : $bPart II-Analysis / $cBP Sanders, S Mall.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 1 (January 1996)
=504  \\$aIncludes bibliographical references$b22.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe present paper is a continuation of Part I to investigate the transverse fatigue behavior of a unidirectional titanium-based metal matrix composite (MMC) (SCS-6/Ti-15-3) at elevated temperature. In Part I of this paper, fatigue tests were conducted under the strain-controlled mode, and a systematic microscopic evaluation was undertaken to identify the damage and deformation mechanisms. In this paper (Part II), the fatigue response is modeled using a micromechanical approach where the fiber-matrix interfacial damage is incorporated along with the inelastic behavior of the matrix. The analysis provided additional insight into the transverse fatigue response of the MMC. Combining the results obtained from this micromechanical analysis, and that obtained from the macroscopic response (that is, stress and modulus) and microscopic evaluation in Part I, the transverse fatigue response of the MMC was thoroughly characterized.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFatigue.
=650  \0$aMetal matrix composite.
=650  \0$aStrain-control mode.
=650  \0$aTitanium matrix composite.
=650  \0$aTransverse behavior.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aMetal matrix composites (MMCs).
=653  20$aTransverse behavior.
=653  20$aStrain-control mode.
=653  20$aTitanium matrix composite.
=653  20$aFatigue.
=700  1\$aMall, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10462J.htm

=LDR  03525nam  2200697 i 4500
=001  CTR10463J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10463J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10463J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aCernyar, J., $eauthor.
=245  10$aFracture and Fatigue Crack Growth Behavior of SiCW/2124A1 Composite / $cJ Cernyar, F Yang, A Saxena.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 1 (January 1996)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe combination of superior properties and relative ease of manufacture has made metal matrix composites candidate materials for the weight-critical, damage-tolerant, and high stiffness structural applications. In this paper, the fatigue crack growth and fracture resistance obtained from single-edge notch bend specimens of the 2124 aluminum alloy reinforced with 20 wt% discontinuous silicon carbide whiskers is presented. The testing and data analyses were conducted in accordance with the ASTM standards initially designed for testing monolithic metallic materials. The suitability of these standards for testing composites is evaluated. The mechanisms of the fatigue crack propagation and stable crack growth under monotonic loading are also characterized.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAluminum alloys.
=650  \0$aCrack growth.
=650  \0$aFatigue.
=650  \0$aFracture.
=650  \0$aMetal matrix composites.
=650  \0$aSilicon carbide whisker.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aMetal matrix composites.
=653  20$aFatigue.
=653  20$aFracture.
=653  20$aCrack growth.
=653  20$aSilicon carbide whisker.
=653  20$aAluminum alloys.
=700  1\$aYang, F., $eauthor.
=700  1\$aSaxena, A., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10463J.htm

=LDR  03900nam  2200661 i 4500
=001  CTR10464J
=003  IN-ChSCO
=005  20161219163000.0
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=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10464J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10464J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNorman, TL., $eauthor.
=245  10$aStrength and Damage Mechanisms of Notched Two-Dimensional Triaxial Braided Textile Composites and Tape Equivalents Under Tension / $cTL Norman, C Anglin, D Gaskin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 1 (January 1996)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe unnotched and notched (open hole) tensile strength and failure mechanisms of two-dimensional (2D) triaxial braided composites were examined. The effect of notch size and notch position were investigated. Damage initiation and propagation in notched and unnotched coupons were also examined. Four different fiber architectures were considered; braid angle, yarn and braider size, and percentage of longitudinal yarns, and braider angle varied. Tape laminates equivalent to textile composites were also constructed for comparison. Unnotched tape equivalents were stronger than braided textiles but exhibited greater notch sensitivity. Notched textiles and tape equivalents have roughly the same strength at large notch sizes. Two common damage mechanisms were found: braider yarn cracking and near notch longitudinal yarn splitting. Cracking was found to initiate in braider yarns in unnotched and notched coupons, and propagate in the direction of the braider yarns until failure. Longitudinal yarn splitting occurred in three of four architectures that were longitudinally fiber dominated. Damage initiation stress decreased with increasing braid angle.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFailure mechanisms.
=650  \0$aNotched.
=650  \0$aOpen hole.
=650  \0$aStrength.
=650  \0$aTextile composites.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aTextile composites.
=653  20$aNotched.
=653  20$aOpen hole.
=653  20$aStrength.
=653  20$aFailure mechanisms.
=700  1\$aAnglin, C., $eauthor.
=700  1\$aGaskin, D., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10464J.htm

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=001  CTR10465J
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=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10465J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10465J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGraesser, DL., $eauthor.
=245  10$aDamage Tolerance Predictions for Stiffened Composite Panels : $bPart I-Strain Field Predictions / $cDL Graesser, ME Tuttle.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 1 (January 1995)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn analysis method suitable for prediction of strain fields in a stiffened composite panel containing a center crack is presented. The analysis is based on the superposition of anisotropic elasticity solutions for an infinite plate. Strain field predictions are made for two panel configurations and compared with strain gage data. Reasonable comparisons between predictions and measurements are obtained. This paper lays the foundation for the predictions of the damage tolerance of stiffened composite panels that will be discussed further in a second paper.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite panels.
=650  \0$aDamage tolerance.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDamage tolerance.
=653  20$aComposite panels.
=700  1\$aTuttle, ME., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10465J.htm

=LDR  03805nam  2200649 i 4500
=001  CTR10469J
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=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10469J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10469J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA417.7.C65
=082  04$a620.1/1242$223
=100  1\$aXie, M., $eauthor.
=245  10$aEffect of Specimen Tab Configuration on Compression Testing of Composite Materials / $cM Xie, DF Adams.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 2 (April 1995)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aStandard Test Method for Compressive Properties of Unidirectional or Cross-Ply Fiber-Resin Composites (ASTM D 3410) for compression testing of composite materials recommends that low-carbon steel or a glass/epoxy composite be used as the tab material, and that the tabs be tapered. However, many details remain unspecified. An analytical study of tab configurations was performed in the present study to determine the effect of type of tabbing material and tab-taper angle on the stress distributions within a unidirectional composite specimen in compression. More compliant tab materials and shallower tab-taper angles yielded less stress concentration in the tab-tip region of the specimen. Therefore, specimens with these tab configurations should yield higher measured compressive strengths since premature failure at the tab tip is less likely to occur. Although there are relatively few experimental data available for different tab materials and tab-taper angles, those that are available show the same trends as predicted by the present analytical study.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression testing.
=650  \0$aCompressive strength.
=650  \0$aFinite element analysis.
=650  \0$aTab configuration.
=650  \0$aUnidirectional composite materials.
=650  \0$aCompression testing.
=650  \0$aMaterials $xCompression testing.
=653  10$aUnidirectional composite materials.
=653  20$aCompression testing.
=653  20$aCompressive strength.
=653  20$aTab configuration.
=653  20$aFinite element analysis (FEA).
=700  1\$aAdams, DF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10469J.htm

=LDR  03056nam  2200625 i 4500
=001  CTR10470J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10470J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10470J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC183
=082  04$a541/.33$223
=100  1\$aWilkinson, S., $eauthor.
=245  10$aSize and Geometry Effects in Transverse Flexural Testing of Unidirectional Graphite/Thermoplastic / $cS Wilkinson, JA Hinkley.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 2 (April 1995)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aOver 140 flex tests were conducted on IM7/polysulfone laminates to determine the effects of specimen dimensions and resin content on measured strength. The only statistically significant size effect found was a decrease in strength with increase of the total stressed volume. A Weibull parameter of 7.9 could be fit to the data. Recommendations were made for the use of the flex test to quantify resin/matrix adhesion.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesion.
=650  \0$aFiber/matrix interface strength.
=650  \0$aThermoplastic composites.
=650  \0$aTransverse flex test.
=650  \0$aAdhesive joints.
=650  \0$aAdsorption.
=653  10$aThermoplastic composites.
=653  20$aTransverse flex test.
=653  20$aAdhesion.
=653  20$aFiber/matrix interface strength.
=700  1\$aHinkley, JA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10470J.htm

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=024  7\$a10.1520/CTR10471J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aAbu-Farsakh, G., $eauthor.
=245  10$aModes of Failure of Fibrous Composite Materials as Affected by the Orientation-Angle of Fiber / $cG Abu-Farsakh, YA Abdel-Jawad.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 2 (April 1995)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn energy-based failure criterion has been recently developed by the authors. At any stress level, the model deals with the actual composite material as an equivalent linear elastic material. The total strain energy density of the system is considered to be composed of two parts, elastic and plastic. In this paper, the model has been used to identify the modes of failure based on the relative magnitudes of the various energy terms appearing in the failure criterion equation. Accordingly, three types of failure are anticipated: fiber failure, matrix failure (tension or compression), and matrix failure in shear. The critical fiber orientation for a given stress state can be predicted as well.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFibrous composites.
=650  \0$aModes of failure.
=650  \0$aNonlinear.
=650  \0$aOrientation-angle of fiber.
=650  \0$aStrain energy.
=650  \0$aStress-strain response.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFibrous composites.
=653  20$aModes of failure.
=653  20$aNonlinear.
=653  20$aStress-strain response.
=653  20$aStrain energy.
=653  20$aOrientation-angle of fiber.
=700  1\$aAbdel-Jawad, YA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10471J.htm

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=001  CTR10472J
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=024  7\$a10.1520/CTR10472J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKarbhari, VM., $eauthor.
=245  10$aEffects of Short-Term Environmental Exposure on Axial Strengthening Capacity of Composite Jacketed Concrete / $cVM Karbhari, DA Eckel.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 2 (April 1995)
=504  \\$aIncludes bibliographical references$b35.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aRecent studies from the U.S. Department of Transportation (USDOT) estimate that of the 575 000 bridges in the nation, 230 000 (or 40%) are either structurally deficient or functionally obsolete. The deterioration has been caused by a variety of factors including corrosion due to marine environments, high chloride content in the air and use of de-icing salts, alkali-silica reactions (ASR), environmental effects on materials, poor initial design, and poor construction and maintenance, or both. Cracking and spalling of concrete columns is often seen with corrosion of internal reinforcement steel due to moisture and chloride ingress. The loss of cementitious material, as well as the reduction in steel cross-section, leads to drastic reductions in the structural efficiency and load-carrying capacity of columnar supporting elements. The high stiffness-to-weight and strength-to-weight ratios of advanced composites, combined with their inherent corrosion resistance, environmental durability, and tailorability make them attractive for use in infrastructure renewal. In this paper, we investigate the effect of environmental exposure on the strengthening efficiency of composite-jacketed concrete column stubs. The effects of short-term exposure to ambient and 0°F conditions as well as to water and sea water on glass-, carbon-, and aramid-epoxy jackets is investigated.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aDurability.
=650  \0$aEnvironmental effects.
=650  \0$aInfrastructure.
=650  \0$aJackets.
=650  \0$aRehabilitation.
=650  \0$aStrengthening efficiency.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aInfrastructure.
=653  20$aRehabilitation.
=653  20$aComposite.
=653  20$aJackets.
=653  20$aWrap.
=653  20$aStrengthening efficiency.
=653  20$aDurability.
=653  20$aEnvironmental effects.
=700  1\$aEckel, DA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10472J.htm

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=001  CTR10473J
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=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10473J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10473J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aCappelletti, C., $eauthor.
=245  10$aEnvironmental Effects on Mechanical Properties of Thick Composite Structural Elements / $cC Cappelletti, A Rivolta, G Zaffaroni.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 2 (April 1995)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this work a consolidated composite structural analysis theory and a suitable treatment of the experimental data obtained from material characterization standard tests has made it possible to the assess the effects of the operating temperature and absorbed moisture on the elastic and ultimate properties of thick composite elements.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \0$aHygrothermal effects.
=650  \0$aMoisture absorption.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aEpoxy composites.
=653  20$aHygrothermal effects.
=653  20$aMoisture absorption.
=700  1\$aRivolta, A., $eauthor.
=700  1\$aZaffaroni, G., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10473J.htm

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=024  7\$a10.1520/CTR10474J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10474J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aMasters, JE., $eauthor.
=245  10$aIntroduction to Symposium on Bolted and Bonded Joints in Composite Materials / $cJE Masters.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (1 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 2 (April 1995)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBolted joints.
=650  \0$aJoints (Engineering)
=650  \0$aBolts and nuts.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10474J.htm

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=001  CTR10475J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10475J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10475J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGuess, TR., $eauthor.
=245  10$aTesting Composite-to-Metal Tubular Lap Joints / $cTR Guess, ED Reedy, AM Slavin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 2 (April 1995)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aProcedures were developed to fabricate, nondestructively evaluate, and mechanically test composite-to-metal tubular joints. The axially loaded tubular lap joint specimen consisted of two metal tubes bonded within each end of a fiberglass composite tube. Joint specimens with both tapered and untapered aluminum adherends and a plain weave E-glass/epoxy composite were tested in tension, compression, and flexure. Other specimens with tapered and untapered steel adherends and a triaxially reinforced E-glass/epoxy composite were tested in tension and compression. Test results include joint strength and failure mode data. A finite element analysis (FEA) of the axially loaded joints explains the effect of adherend geometry and material properties on measured joint strength. The flexural specimen was also analyzed; calculated surface strains are in good agreement with measured values, and joint failure occurs in the region of calculated peak peel stress.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesives.
=650  \0$aBonded joints.
=650  \0$aComposites.
=650  \0$aFinite element analysis.
=650  \0$aFlexural testing.
=650  \0$aStatic testing.
=650  \0$aTubular joints.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aTubular joints.
=653  20$aStatic testing.
=653  20$aFlexural testing.
=653  20$aBonded joints.
=653  20$aAdhesives.
=653  20$aFinite element analysis (FEA).
=700  1\$aReedy, ED., $eauthor.
=700  1\$aSlavin, AM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10475J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10476J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10476J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aHoa, SV., $eauthor.
=245  10$aBiaxial Bearing/Bypass Testing of Graphite/Epoxy Plates / $cSV Hoa.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 2 (April 1995)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aBolted graphite/epoxy plates were subjected to in-plane biaxial loading. Cruciform shape samples were used. Testing was performed on a biaxial machine developed and built at Concordia University. The bolt hole was constrained using a rigid structure. Four arms of the cruciform samples were independently loaded. Equal and opposite lateral loads were applied along one direction (y). Along the other direction (x), load is applied on one arm (right arm of the cruciform), while the opposite arm (left arm of the cruciform) was held fixed in the grip without applied load. This was possible because the bolt hole at the center of the cruciform sample was held fixed. This opposite arm measured whichever load that was bypassed around the constrained hole (called bypass load). Acoustic emission was used to measure the onset of failure. The applied load in the x direction at the onset of failure is called the joint strength. Subsequent to the onset of failure, the bypass load increased significantly. Also after onset of failure, the bypass load on reloading was larger than the bypass load on previous loading. Results obtained showed that the existence of lateral loads (load along the y direction) had significant effect on the joint strength. Increasing the lateral load decreased the joint strength. These results show that data obtained using uniaxial test are nonconservative.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBearing load.
=650  \0$aBearing/bypass.
=650  \0$aBiaxial.
=650  \0$aBypass load.
=650  \0$aComposite.
=650  \0$aGraphite/epoxy.
=650  \0$aJoint strength.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=653  10$aBiaxial.
=653  20$aBearing/bypass.
=653  20$aComposite.
=653  20$aJoint strength.
=653  20$aGraphite/epoxy.
=653  20$aBypass load.
=653  20$aBearing load.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10476J.htm

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=024  7\$a10.1520/CTR10477J$2doi
=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aKoudela, KL., $eauthor.
=245  12$aA Novel Joining Method for Smooth-Bore Composite Pressure Hulls / $cKL Koudela, J Sabo, LH Strait, ML Karasek.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 2 (April 1995)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFilament wound smooth-bore composite pressure hulls offer the potential for increasing the displacement-to-weight ratios of externally loaded, hydrostatic pressure hulls well beyond those achievable with conventional metal alloys. Increasing the displacement-to-weight ratio affords the ability to extend the operational pressure without a corresponding weight penalty. However, for viable hydrostatic pressure hull designs, reliable attachment methods for interfacing the composite structure with existing metallic components must be developed. While significant work has been done in composite-to-metal joining, developmental thrusts have not focused on problems specific to the design and fabrication of circular joints. The present paper discusses a novel circular composite-to-metal bonded joint developed for smooth-bore composite pressure hulls. Details of the concurrent engineering approach, fabrication method, and validation testing of the cylindrical joint are presented. Validation test results demonstrate that the novel circular joint is a viable alternative to more complex and costly composite-to-metal circular bonded joints.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBonded joints.
=650  \0$aComposite design.
=650  \0$aComposite fabrication.
=650  \0$aFilament winding.
=650  \0$aPressure hull.
=650  \0$aBolted joints.
=650  \0$aJoints (Engineering)
=650  \0$aBolts and nuts.
=653  10$aBonded joints.
=653  20$aComposite design.
=653  20$aComposite fabrication.
=653  20$aPressure hull.
=653  20$aFilament winding.
=700  1\$aSabo, J., $eauthor.
=700  1\$aStrait, LH., $eauthor.
=700  1\$aKarasek, ML., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10477J.htm

=LDR  03846nam  2200733 i 4500
=001  CTR10478J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10478J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10478J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRufin, AC., $eauthor.
=245  10$aFastener Hole Reinforcement in Composites Using Cold-Expanded Inserts / $cAC Rufin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 2 (April 1995)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aCold expansion, a technique widely used to increase the fatigue life of holes in metal structures, has been adapted to composite materials as a means to install metal inserts in fastener holes. Thin-walled cold expanded inserts (grommets) are used to reinforce fastener holes that may be sensitive to damage, for example, from repeated fastener installation and removal, or from lightning strike. Thicker inserts with a nut-anchoring feature are a cost-effective alternative to riveted nut plates currently used in composite-fastened assemblies. A comprehensive test program involving mechanically fastened joints in composites with adhesive bonded and cold expanded grommets showed that, in general, cold expanded grommets perform comparably to, or better than, bonded grommets. In the areas of installation costs and resistance to lightning strike damage, cold expanded grommets significantly out-performed bonded grommets. Work on cold expanded rivetless nut plates in carbon/epoxy has proven the viability of the concept.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCold expansion.
=650  \0$aComposites.
=650  \0$aFasteners.
=650  \0$aFatigue.
=650  \0$aHole reinforcement.
=650  \0$aInterference fit.
=650  \0$aLightning strike.
=650  \0$aNut plates.
=650  \0$aTesting.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aCold expansion.
=653  20$aInterference fit.
=653  20$aFasteners.
=653  20$aHole reinforcement.
=653  20$aNut plates.
=653  20$aTesting.
=653  20$aFatigue.
=653  20$aLightning strike.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10478J.htm

=LDR  03045nam  2200601 i 4500
=001  CTR10481J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10481J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10481J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aCarman, GP., $eauthor.
=245  10$aReview of the Mechanics of Embedded Optical Sensors / $cGP Carman, GP Sendeckyj.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 3 (July 1995)
=504  \\$aIncludes bibliographical references$b76.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe published literature on the effect of optical sensors and fibers embedded in host composite materials is reviewed. The literature indicates that improperly embedded optical fibers produce local distortions and resin-rich regions in the host composite that cause structural performance degradation. This is especially true for compressive loading of relatively thin composite laminates. Tensile strength is at most only slightly degraded. The available data are inconclusive for fatigue loading.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aEmbedded optical fibers.
=650  \0$aStrength degradation.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aEmbedded optical fibers.
=653  20$aStrength degradation.
=700  1\$aSendeckyj, GP., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10481J.htm

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=001  CTR10482J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10482J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10482J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aLi, J., $eauthor.
=245  10$aStudy of the Residual Stress in Cold-Rolled 7075 Al-SiC Whisker-Reinforced Composites by X-Ray and Neutron Diffraction / $cJ Li, J Lu, M Perrin, M Ceretti, A Lodini.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 3 (July 1995)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aMany surface treatment techniques are used to improve the mechanical behavior of metal matrix composites (MMC) under dynamic loading. Mill machining, shot-peening, hammering, and cold-rolling are the four techniques commonly used. In this paper, we study the effect of the surface treatment with the cold-rolled technique on the residual stresses in an aluminum alloy 7075 reinforced with 27% vol fraction SiC whiskers.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCold-rolled technique.
=650  \0$aMetal matrix composite.
=650  \0$aNeutron diffraction method.
=650  \0$aResidual stresses.
=650  \0$aX-ray diffraction method.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMetal matrix composite.
=653  20$aResidual stresses.
=653  20$aNeutron diffraction method.
=653  20$aX-ray diffraction method.
=653  20$aCold-rolled technique.
=700  1\$aLu, J., $eauthor.
=700  1\$aPerrin, M., $eauthor.
=700  1\$aCeretti, M., $eauthor.
=700  1\$aLodini, A., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10482J.htm

=LDR  03852nam  2200625 i 4500
=001  CTR10483J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10483J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10483J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aIfju, PG., $eauthor.
=245  10$aShear Testing of Textile Composite Materials / $cPG Ifju.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 3 (July 1995)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new in-plane shear-test methodology, developed for laminated composite materials, was extended to textile composites. The methodology incorporates two recently developed advances: a new specimen and a special strain gage. When used together, they produce accurate and consistent shear characterization of laminated and textile composite materials. The "compact shear specimen" incorporates many of the advantages of the similar Iosipescu shear specimen but has a larger test section. A special strain gage called the "shear gage" integrates the shear strain across the entire test section of the specimen to obtain the average shear strain, regardless of the shear-strain distribution in the test section. The methodology was used to test both 2-D braided and 3-D woven textile composites. The entire shear stress-strain response, including the shear modulus and shear strength, was measured for nine textile composite architectures. The variation in shear modulus and shear strength were low and were comparable to the variation of tensile and compressive modulus for the respective materials. Moiré interferometry, a full-field optical method, was used to validate the test methodology. Enhanced X-rays were used to document the damage accumulated during failure of the specimens.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompact shear specimen.
=650  \0$aShear gage.
=650  \0$aShear testing.
=650  \0$aTextile composite materials.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aShear testing.
=653  20$aTextile composite materials.
=653  20$aShear gage.
=653  20$aCompact shear specimen.
=653  20$aIosipescu specimen.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10483J.htm

=LDR  03692nam  2200685 i 4500
=001  CTR10484J
=003  IN-ChSCO
=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10484J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10484J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aWard, GT., $eauthor.
=245  10$aFatigue-Life Behavior and Matrix Fatigue Crack Spacing in Unnotched SCS-6/Timetal®21S Metal Matrix Composites / $cGT Ward, DJ Herrmann, BM Hillberry.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 3 (July 1995)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFatigue tests of the SCS-6/Timetal®21S composite system were performed to characterize the fatigue behavior for unnotched specimens. The stress-life behavior of the unnotched [0/90]2S laminates was investigated for stress ratios of R = 0.1 and R = 0.3. No difference in fatigue lives was observed when comparing the two stress ratios on a stress-range basis. The unnotched SCS-6/Timetal 21S composites had shorter fatigue lives than those reported in the literature for the SCS-6/Ti-15-3 composites; however, the neat Timetal 21S matrix material had a longer fatigue life than those reported for the neat Ti-15-3. Multiple matrix crack initiation sites were observed throughout the composite, as well as evenly spaced transverse fatigue cracks along the length of the specimens. The spacing between fatigue cracks was investigated, as were the effects of surface cracking on composite stiffness.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCross-ply laminates.
=650  \0$aFatigue.
=650  \0$aSilicon-carbide fibers.
=650  \0$aTitanium matrix.
=650  \0$aUnnotched.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aFatigue.
=653  20$aTitanium matrix.
=653  20$aSilicon-carbide fibers.
=653  20$aUnnotched.
=653  20$aCross-ply laminates.
=653  20$aMatrix fatigue crack spacing.
=700  1\$aHerrmann, DJ., $eauthor.
=700  1\$aHillberry, BM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10484J.htm

=LDR  03392nam  2200661 i 4500
=001  CTR10485J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10485J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10485J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aFleck, NA., $eauthor.
=245  10$aCompressive Failure of Laminated and Woven Composites / $cNA Fleck, PM Jelf, PT Curtis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 3 (July 1995)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effect of fiber architecture upon the compressive failure mechanisms is investigated for a wide range of fiber composites. Compressive tests are performed on both notched and unnotched specimens made from T800 carbon fiber-924C epoxy laminates, AS4 carbon fiber-PEEK laminates, 2D woven T800 carbon fiber-924 epoxy, and 3D woven AS4 carbon fiber-LY564 epoxy. Additionally, unnotched and notched compressive tests are performed on beechwood and birch plywood. In all cases, the dominant failure mechanism is by fiber microbuckling. An infinite band kinking model is used to estimate the unnotched strength and a large-scale crack bridging analysis is used to predict the notched strength.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCohesive zone model.
=650  \0$aComposites.
=650  \0$aCompressive failure.
=650  \0$aFracture mechanics.
=650  \0$aMicrobuckling.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCompressive failure.
=653  20$aComposites.
=653  20$aFracture mechanics.
=653  20$aCohesive zone model.
=653  20$aMicrobuckling.
=700  1\$aJelf, PM., $eauthor.
=700  1\$aCurtis, PT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10485J.htm

=LDR  03515nam  2200745 i 4500
=001  CTR10486J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10486J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10486J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aTiwari, A., $eauthor.
=245  10$aDamage Characterization of a Cross-Ply SiC/CAS-II Ceramic Composite Under Fatigue Loading Using a Real-Time Acousto-Ultrasonic NDE Technique / $cA Tiwari, EG Henneke, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 3 (July 1995)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe application of a real-time acousto-ultrasonic (AU) nondestructive evaluation (NDE) technique to monitor damage during fatigue without stopping the test is presented in this paper. Real-time AU parameters were used to decipher the true nature of damage mechanisms occurring during cyclic loading of a SiC/CAS-II cross-ply ceramic composite. The results of AU were complemented by other NDE techniques. The S-N curve for a SiC/CAS-II cross-ply ceramic composite at room temperature was generated and a study of the failure process during cyclic loading was performed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAcousto-ultrasonic.
=650  \0$aCeramic composites.
=650  \0$aCross-ply.
=650  \0$aDamage.
=650  \0$aFatigue.
=650  \0$aNondestructive evaluation.
=650  \0$aReal-time.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aReal-time.
=653  20$aAcousto-ultrasonic.
=653  20$aNondestructive evaluation.
=653  20$aCeramic composites.
=653  20$aFatigue.
=653  20$aCross-ply.
=653  20$aSiC/CAS.
=653  20$aS-N curve.
=653  20$aDamage.
=700  1\$aHenneke, EG., $eauthor.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10486J.htm

=LDR  04036nam  2200673 i 4500
=001  CTR10487J
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=024  7\$a10.1520/CTR10487J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10487J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aWalsh, TF., $eauthor.
=245  14$aThe Effect of High-Temperature Degradation on the Mode I Critical Strain Energy Release Rate of a Graphite/Epoxy Composite / $cTF Walsh, CE Bakis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 3 (July 1995)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe double cantilever beam (DCB) test was used to determine the effects of high-temperature degradation on the Mode I critical strain energy release rate (GIC) of a continuous fiber-reinforced polymer-matrix composite material. The composite material investigated was IM7/8551-7A graphite/rubber-toughened epoxy system. Delamination starter films of two different thicknesses were used: 25.4 µm and 12.7 µm. High-temperature degradation was accomplished by placing the specimens on a wire rack in a forced-air convection oven held at 177°C. A continuous flow of fresh laboratory air existed at all times. GIC decreased with increased exposure, showing a 40% reduction after 8000 h. The specimens with thicker inserts showed a higher GIC. Weight loss of the material occurred throughout the aging cycle, indicating that thermo-oxidation was occurring. GIC was not affected by the wedging open of the precrack during exposure. Crack propagation in the unexposed specimens occurred in the matrix material, whereas for the exposed specimens, it occurred along the fiber-matrix interface. This indicated possible exposure-induced interfacial degradation.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDelamination.
=650  \0$aDouble cantilever beam.
=650  \0$aFiber-reinforced plastics.
=650  \0$aGraphite/epoxy.
=650  \0$aHigh-temperature degradation.
=650  \0$aStrain energy release rate.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFiber-reinforced plastics.
=653  20$aDelamination.
=653  20$aStrain energy release rate.
=653  20$aGraphite/epoxy.
=653  20$aHigh-temperature degradation.
=653  20$aDouble cantilever beam.
=700  1\$aBakis, CE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10487J.htm

=LDR  02273nam  2200505 i 4500
=001  CTR10488J
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=024  7\$a10.1520/CTR10488J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10488J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMasters, JE., $eauthor.
=245  10$aIntroduction to Symposium on Bolted and Bonded Joints in Composite Materials / $cJE Masters.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (1 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 3 (July 1995)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10488J.htm

=LDR  04106nam  2200709 i 4500
=001  CTR10489J
=003  IN-ChSCO
=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10489J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10489J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aCohen, D., $eauthor.
=245  10$aFailure Criterion for Thick Multifastener Graphite-Epoxy Composite Joints / $cD Cohen, MW Hyer, MJ Shuart, OH Griffin, C Prasad, SR Yalamanchili.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 3 (July 1995)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA method for accurately predicting the strength of multifastener, thick composite joints is discussed. The method is based on the average stress criterion applied around the hole circumference. Basic laminate strength data are obtained from single-fastener and reduced-section notched specimens. Using ABAQUS finite element analyses (FEA), the stress-field distribution around the fastener-loaded hole in both the single-fastener and multifastener joints is determined. The single-fastener test data in conjunction with this FEA and the average stress criterion are then used to predict the multifastener joint strength. Multifastener joint strength of three different laminate layups is predicted to within 1% accuracy. However, the results show that the average stress criterion cannot accurately predict the location of failure initiation. In the current investigation, the maximum strain criterion is used to locate possible sites of failure initiation. When this information is used in conjunction with the average stress criterion, the predicted multifastener joint strength based on single-fastener net-tension data is reasonably accurate.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite average stress criterion.
=650  \0$aMaterial strength.
=650  \0$aMaximum strain criterion.
=650  \0$aMultifastener joints.
=650  \0$aSingle-fastener joints.
=650  \0$aBolted joints.
=650  \0$aJoints (Engineering)
=650  \0$aBolts and nuts.
=653  10$aComposite average stress criterion.
=653  20$aMultifastener joints.
=653  20$aSingle-fastener joints.
=653  20$aMaterial strength.
=653  20$aMaximum strain criterion.
=700  1\$aHyer, MW., $eauthor.
=700  1\$aShuart, MJ., $eauthor.
=700  1\$aGriffin, OH., $eauthor.
=700  1\$aPrasad, C., $eauthor.
=700  1\$aYalamanchili, SR., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10489J.htm

=LDR  03377nam  2200637 i 4500
=001  CTR10490J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10490J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10490J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aHamada, H., $eauthor.
=245  10$aEffects of Stacking Sequences on Mechanically Fastened Joint Strength in Quasi-Isotropic Carbon-Epoxy Laminates / $cH Hamada, K Haruna, Z Maekawa.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 3 (July 1995)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe desire to develop adequate strength, particularly at bolt hole, tends to restrict the choice of fiber patterns to those that do not deviate very far from a quasi-isotropic pattern. The weakest parts of a composite structure are the joint parts; therefore, the effective stacking sequences on joint strength while maintaining the isotropic nature have to be cleared. In this study, the effect of stacking sequences on quasi-isotropic T300/2500 joint strength was examined. Two joint geometries that exhibited bearing failure and net-tension failure under pin-bearing loads were chosen. Six types of laminate configurations were examined in quasi-isotropic patterns.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBolted joints.
=650  \0$aCarbon fiber-reinforced plastics.
=650  \0$aQuasi-isotropic pattern.
=650  \0$aStacking sequence.
=650  \0$aBolts and nuts.
=650  \0$aJoints (Engineering)
=653  10$aCarbon fiber-reinforced plastics.
=653  20$aBolted joints.
=653  20$aQuasi-isotropic pattern.
=653  20$aStacking sequence.
=700  1\$aHaruna, K., $eauthor.
=700  1\$aMaekawa, Z., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10490J.htm

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=001  CTR10491J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10491J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10491J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aShyprykevich, P., $eauthor.
=245  10$aCharacterization of Bolted Joint Behavior : $bMIL-HDBK-17 Accomplishments at Standardization / $cP Shyprykevich.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 3 (July 1995)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA testing approach is presented that will provide the user with sufficient data to design bolted joints in composite structures against various failure modes and interactions between them. Test methods for characterizing bolted joint behavior are described. These include double- and single-shear bearing, notched tension and compression, bearing/bypass (tension and compression), shear-out, and fastener pull-through. In addition to test specimens and procedures, test matrices are presented that recommend laminates to be tested, environmental conditions, and replication. The replications represent the minimum data requirements to design bolted joints in composite structures given today's analytic capability. The test methods and testing requirements were established through a working group consensus and approved by the full committee of MIL-HDBK-17.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBearing.
=650  \0$aBearing/by-pass.
=650  \0$aBolted joints.
=650  \0$aComposites.
=650  \0$aFastener pull-through.
=650  \0$aNotch tension/compression.
=650  \0$aShear-out.
=650  \0$aTest matrices.
=650  \0$aBolted joints.
=650  \0$aJoints (Engineering)
=650  \0$aBolts and nuts.
=653  10$aComposites.
=653  20$aBolted joints.
=653  20$aBearing.
=653  20$aBearing/by-pass.
=653  20$aNotch tension and compression.
=653  20$aShear-out.
=653  20$aFastener pull-through.
=653  20$aTest matrices.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10491J.htm

=LDR  04168nam  2200661 i 4500
=001  CTR10494J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10494J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10494J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aJohnson, WS., $eauthor.
=245  13$aAn Investigation into the Fatigue of a Hybrid Titanium Composite Laminate / $cE Li, WS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 1 (January 1998)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aHybrid composite laminates consisting of layers of metal foils bonded together with fiber-reinforced resin show great promise as a fatigue-resistant material. The hybrid titanium composite laminate (HTCL) incorporates the mechanical advantages of existing hybrid composite laminates such as ARALL and GLARE while extending their applications to elevated temperatures. Titanium layers are bonded by prepreg layers of high-temperature resin reinforced with carbon fibers. The constituent materials used in this study are a metastable β titanium alloy (Ti-15-3), a high-temperature polyimide (LARC™-IAX), and an intermediate modulus carbon fiber (IM7). This study includes quasi-static and fatigue testing of HTCL materials at room temperature and 177°C (350°F). Experimental stress-strain response of HTCL laminates are compared with predicted results by a laminate analysis code called AGLPLY. A stress-based fatigue study was performed to determine the fatigue properties of HTCL laminates. The roles of residual stress in the mechanical behavior and fatigue properties of HTCL are addressed. The development of damage in HTCL specimens during fatigue is shown to include titanium ply cracking, interfacial debonding, and PMC layer failure. The influence of the fatigue properties of titanium layers on the fatigue of HTCL is discussed. The performance of HTCL laminates in fatigue is shown superior to that of the monolithic titanium alloy for room-temperature and elevated-temperature conditions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDamage tolerant.
=650  \0$aElevated temperature.
=650  \0$aFatigue.
=650  \0$aHybrid composite laminate.
=650  \0$aTitanium.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aHybrid composite laminate.
=653  20$aTitanium.
=653  20$aFatigue.
=653  20$aDamage tolerant.
=653  20$aElevated temperature.
=700  1\$aJohnson, WS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10494J.htm

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=001  CTR10495J
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10495J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10495J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aChen, J., $eauthor.
=245  10$aSensitivity of Mechanical Properties to Braid Misalignment in Triaxial Braid Composite Panels / $cJ Chen, TM McBride, SB Sanchez.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 1 (January 2006)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA significant portion of the cost of composite structures is embedded in manufacturing, inspection, and maintenance. Much of this cost is due to unfamiliarity with the expected behavior of the material. Unlike with metals, for which there is a relative wealth of experimental and process data, the results from testing of composites and in particular, textile composites, often defy intuition. If proper specifications and manufacturing process controls are to be placed such that the costs of achieving those specifications are not prohibitive, it must be understood how sensitive mechanical properties are to these parameters. In this paper, results from a series of tests on 2D triaxial braid composite panels are presented. The focus of these experiments is to determine the sensitivity of strength and fiber volume fraction to a small degree of misalignment (±1 to 5°) in braid angle.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBraided composites.
=650  \0$aFiber volume fraction.
=650  \0$aManufacturing defects.
=650  \0$aStrength.
=650  \0$aTextile composites.
=650  \0$aTow misalignment.
=650  \0$aTriaxial braid.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aBraided composites.
=653  20$aTextile composites.
=653  20$aTriaxial braid.
=653  20$aTow misalignment.
=653  20$aManufacturing defects.
=653  20$aStrength.
=653  20$aFiber volume fraction.
=700  1\$aMcBride, TM., $eauthor.
=700  1\$aSanchez, SB., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10495J.htm

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=024  7\$a10.1520/CTR10496J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10496J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aR857.M3
=082  04$a610.28$223
=100  1\$aVoleti, SR., $eauthor.
=245  10$aEffect of Interfacial Properties on the Fiber Fragmentation Process in Polymer Matrix Composites / $cSR Voleti, CR Ananth, N Chandra.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 1 (January 1998)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFiber Fragmentation test or Single Fiber Composite test (SFC) has been widely used to characterize the interfacial behavior in composites. Though it is accepted that SFC gives useful information about the interfacial bond quality and the fiber strength, there is no clear consensus on how to interpret the data and quantify the interfacial properties. In this paper, the fiber fragmentation test is modeled with the objective of studying the effect of interfacial bond strength and post-debonding frictional effects on the progress of the fragmentation process. The load transfer at the fiber-matrix interface is modeled using the shear-lag principles and the statistical variation of fiber strength is incorporated using Weibull theory. A parametric study of the variation of interfacial shear properties on the mean fragment length and debond progression with applied strain is conducted. It is found that in the case of weak interfaces saturation of fiber fragments occurs at much lower applied strain values and is usually associated with extensive debonding. The numerical simulation shows that the fragmentation results are very much sensitive to the frictional effects as it controls the debonded length. The results from the model are correlated with experimental data to validate the model and for extracting the interfacial properties from the test data.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDebonding.
=650  \0$aFiber fragmentation test.
=650  \0$aFriction.
=650  \0$aInterface.
=650  \0$aPolymer matrix composites.
=650  \0$aShear-lag theory.
=650  \0$aPolymeric composites.
=650  \7$aTECHNOLOGY & ENGINEERING $vBiomedical.
=653  10$aFiber fragmentation test.
=653  20$aPolymer matrix composites.
=653  20$aShear-lag theory.
=653  20$aInterface.
=653  20$aDebonding.
=653  20$aFriction.
=700  1\$aAnanth, CR., $eauthor.
=700  1\$aChandra, N., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10496J.htm

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=024  7\$a10.1520/CTR10497J$2doi
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=037  \\$aCTR10497J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMartin, R., $eauthor.
=245  10$aIntroduction to Symposium on Non-Aerospace Applications for Composite Materials / $cR Martin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 1 (January 2006)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10497J.htm

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=001  CTR10498J
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=024  7\$a10.1520/CTR10498J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10498J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA683.5.B3
=082  04$a624.1/83423$223
=100  1\$aBakis, CE., $eauthor.
=245  10$aEffect of Cyclic Loading on Bond Behavior of GFRP Rods Embedded in Concrete Beams / $cCE Bakis, SU Al-Dulaijan, A Nanni, TE Boothby, MM Al-Zahrani.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 1 (January 1998)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThree types of glass fiber-reinforced plastic (GFRP) rods with different surface configurations were embedded in concrete beams to determine their bond behavior under cyclic loading. Load amplitudes and numbers of cycles were chosen based on the GFRP rod type and its bond behavior in virgin beams loaded monotonically to failure. After completion of cyclic loading, all beams were tested quasi-statically to failure to determine the residual bond strength. Results were presented as load-slip curves, load-midspan displacement curves, and slip versus number of cycles curves. In all types of GFRP rod evaluated, cumulative slip increased as the number of cycles and/or loading amplitude increased. The bond strength in cyclically loaded beams increased relative to the bond strength in virgin beams.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBond.
=650  \0$aCyclic loading.
=650  \0$aFRP reinforcement.
=650  \0$aReinforced concrete.
=650  \0$aResidual bond strength.
=650  \0$aConcrete beams $vTesting.
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aBond.
=653  20$aCyclic loading.
=653  20$aFRP reinforcement.
=653  20$aReinforced concrete.
=653  20$aRILEM beams.
=653  20$aResidual bond strength.
=700  1\$aAl-Dulaijan, SU., $eauthor.
=700  1\$aNanni, A., $eauthor.
=700  1\$aBoothby, TE., $eauthor.
=700  1\$aAl-Zahrani, MM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10498J.htm

=LDR  04378nam  2200769 i 4500
=001  CTR10499J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10499J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10499J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.P6
=082  04$a668.4/225$223
=100  1\$aGentry, TR., $eauthor.
=245  10$aAccelerated Test Methods to Determine the Long-Term Behavior of Composite Highway Structures Subject to Environmental Loading / $cTR Gentry, LC Bank, A Barkatt, L Prian.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 1 (January 1998)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aResearch on fiber-reinforced plastic composites has explored the effects of selected aqueous environments on the mechanical and physical properties of these composites. The composite materials tested were produced using the pultrusion process. Resins included in the study were polyester and vinylester. Fibers included were E-glass, carbon, and aramid. Environments considered were air, deionized water, acetic acid at two concentrations, and ammonia at two concentrations. Temperatures considered were room temperature, 50 and 80°C. Mechanical testing included tension, flexure, and short beam shear tests. Weight loss, thermogravimetric, and calorimetric measurements were made to determine whether degradation was taking place in the fiber or matrix phases of the composite. Accelerating factors for the various environments were calculated using the framework outlined in ASTM E 632, Standard Practice for Developing Accelerated Tests to Aid in the Prediction of the Service Life of Building Components and Materials. It was observed that a combination of weight loss and thermogravimetric measurements are useful in determining whether degradation in the composite is due to fiber or matrix degradation. Trends in weight loss closely parallel loss of mechanical properties in polyester/glass rods.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAccelerated testing.
=650  \0$aAging.
=650  \0$aComposites.
=650  \0$aDegradation.
=650  \0$aFiber-reinforced plastics thermogravimetric analysis.
=650  \0$aPolyester.
=650  \0$aPolymer.
=650  \0$aPultrusion.
=650  \0$aVinylester.
=650  \0$aPolyester.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aComposites.
=653  20$aAccelerated testing.
=653  20$aAging.
=653  20$aDegradation.
=653  20$aPolymer.
=653  20$aFiber-reinforced plastics thermogravimetric analysis.
=653  20$aPultrusion.
=653  20$aPolyester.
=653  20$aVinylester.
=700  1\$aBank, LC., $eauthor.
=700  1\$aBarkatt, A., $eauthor.
=700  1\$aPrian, L., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10499J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10500J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10500J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aR857.M3
=082  04$a610.28$223
=100  1\$aBradley, SW., $eauthor.
=245  10$aViscoelastic Creep Characteristics of Neat Thermosets and Thermosets Reinforced with E-Glass / $cSW Bradley, PM Puckett, WL Bradley, HJ Sue.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 1 (January 1998)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe long-term creep behavior of vinyl esters and polyesters have been studied as a function of curing conditions using flexural creep tests at ambient temperature (23°C). Vinyl esters that have been cured at room temperature had a greater creep exponent (n ∼ 0.20) for power law creep (tn) than vinyl esters that were postcured to crosslink completion at 93°C (n ∼ 0.12). Reinforcements using woven glass fabric in the room temperature cured vinyl ester and the vinyl ester postcured at 93°C gave much lower compliances, but with approximately the same time exponents (n ∼ 0.20 and 0.13, respectively). The vinylester without reinforcement was tested in creep after a variety of curing conditions: one day, one week, one month at room temperature; 49°C for 4 h, 71°C for 4 h, and 93°C for 4 h. The total creep compliance as well as the time exponent n decreased systematically with increasing cure condition and time, with a creep compliance for room temperature cure for one day that is 250% more than that for a neat vinyl ester cured for 4 h at 93°C.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aE-glass.
=650  \0$aGlass transition temperature.
=650  \0$aPolyester.
=650  \0$aPolymeric composites.
=650  \0$aPostcure.
=650  \0$aVinyl ester.
=650  \0$aComposite materials.
=650  \0$aBiomedical materials.
=650  \7$aTECHNOLOGY & ENGINEERING $vBiomedical.
=653  10$aPolymeric composites.
=653  20$aVinyl ester.
=653  20$aPolyester.
=653  20$aPostcure.
=653  20$aE-glass.
=653  20$aGlass transition temperature.
=700  1\$aPuckett, PM., $eauthor.
=700  1\$aBradley, WL., $eauthor.
=700  1\$aSue, HJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10500J.htm

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=001  CTR10501J
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=024  7\$a10.1520/CTR10501J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10501J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.84
=082  04$a620.1/127$223
=100  1\$aPuh, JS., $eauthor.
=245  14$aThe Effect of Biofouling on Graphite/Epoxy Composites / $cJS Puh, PA Wagner, BJ Little, WL Bradley.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 1 (January 1998)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis research program seeks to determine if the presence of marine microorganisms and the biofouling they produce will accelerate the degradation of graphite/epoxy composite materials. Graphite/epoxy samples were conditioned for 4 months in sterilized seawater (no microorganisms), natural seawater (with microorganisms), and air. In addition, half of the tested samples were also subjected to three-point bending while conditioning.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAcoustic emission.
=650  \0$aBiodeterioration.
=650  \0$aCarbon fiber.
=650  \0$aMechanical testing.
=650  \0$aMicrobial.
=650  \0$aMicrobiologically influenced corrosion.
=650  \0$aPolymeric composites.
=650  \0$aSeawater.
=650  \0$aAcoustical engineering.
=650  \0$aEmission, Acoustic.
=650  \0$aAcoustic emission testing.
=653  10$aPolymeric composites.
=653  20$aMicrobiologically influenced corrosion.
=653  20$aBiodeterioration.
=653  20$aMechanical testing.
=653  20$aAcoustic emission.
=653  20$aMicrobial.
=653  20$aCarbon fiber.
=653  20$aSeawater.
=700  1\$aWagner, PA., $eauthor.
=700  1\$aLittle, BJ., $eauthor.
=700  1\$aBradley, WL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10501J.htm

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=024  7\$a10.1520/CTR10508J$2doi
=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKarasek, ML., $eauthor.
=245  10$aEffect of Temperature and Moisture on the Impact Behavior of Graphite/Epoxy Composites : $bPart I-Impact Energy Absorption / $cML Karasek, LH Strait, MF Amateau, JP Runt.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 1 (January 1995)
=504  \\$aIncludes bibliographical references$b32.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDropped weight impact testing has been used to evaluate the influence of temperature and moisture on the impact resistance of unmodified and modified epoxy/graphite fiber composites. At ambient and low temperatures, moisture was found to have little effect on damage initiation energy or subsequent energy absorption. At elevated temperature, the presence of moisture has a significant effect on damage initiation energy, with the change depending on the particular energy adsorption characteristics of the matrix and the 'wet' epoxy phase glass transition temperature. The energy required to initiate damage was found to decrease with temperature, and this is consistent with a reduction in matrix properties at elevated temperatures.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDropped weight impact.
=650  \0$aEnvironmental effects.
=650  \0$aImpact resistance.
=650  \0$aPolymer composite.
=650  \0$aSeawater exposure.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aPolymer composite.
=653  20$aEnvironmental effects.
=653  20$aDropped weight impact.
=653  20$aSeawater exposure.
=653  20$aImpact resistance.
=700  1\$aStrait, LH., $eauthor.
=700  1\$aAmateau, MF., $eauthor.
=700  1\$aRunt, JP., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10508J.htm

=LDR  03290nam  2200661 i 4500
=001  CTR10509J
=003  IN-ChSCO
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=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10509J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10509J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aR857.M3
=082  04$a610.28$223
=100  1\$aKarasek, ML., $eauthor.
=245  10$aEffect of Temperature and Moisture on the Impact Behavior of Graphite/Epoxy Composites : $bPart II-Impact Damage / $cML Karasek, LH Strait, MF Amateau, JP Runt.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 1 (January 1995)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn Part I of this paper (this publication), dropped weight impact testing was used to evaluate the influence of temperature and moisture on the impact resistance of various graphite/epoxy composites. In the present paper, subpenetration impact testing and subsequent damage characterization using ultrasonic c-scan and microscopic techniques are used to provide additional insight into the nature of the impact damage and to identify critical parameters affecting impact performance.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDropped weight impact.
=650  \0$aEnvironmental effects.
=650  \0$aPolymer composite.
=650  \0$aSeawater exposure.
=650  \0$aComposite materials.
=650  \0$aBiomedical materials.
=650  \7$aTECHNOLOGY & ENGINEERING $vBiomedical.
=653  10$aPolymer composite.
=653  20$aEnvironmental effects.
=653  20$aDropped weight impact.
=653  20$aSeawater exposure.
=700  1\$aStrait, LH., $eauthor.
=700  1\$aAmateau, MF., $eauthor.
=700  1\$aRunt, JP., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10509J.htm

=LDR  04685nam  2200937 i 4500
=001  CTR10510J
=003  IN-ChSCO
=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10510J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10510J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aSchulz, KC., $eauthor.
=245  12$aA Statistical Analysis of Bushing, Sleeve, and Oversize Hole Effects on the Bolted Joint Strength of Graphite/Epoxy Laminates / $cKC Schulz, HJ Hietala, PF Packman.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (16 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 1 (January 1995)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA test program was conducted to determine the influence of metallic hole inserts (bushings and sleeves) and over-sized fastener holes on the ultimate strength of bolted joints in IM7/8551 graphite/epoxy. Single-shear specimens were used to simulate in-service constraints; the test fixture was designed to load the test specimen at the geometric center in the thickness direction minimizing the single-shear bending problem. Protruding-head and countersunk-head fastener tests were conducted on laminate lay-ups with ply percentages of 42/50/8 and 12/80/8. The width-to-diameter ratio was held constant at 4.0, but four distinct edge distance-to-diameter ratios, 1.0, 1.5, 2.0, and 3.0, were tested for each factor. Three replicate tests were conducted for each set of parameter combinations. An analysis-of-variance of the data was conducted for each factor to determine whether or not that factor significantly influenced ultimate joint strength. Fisher's Protected Least Significant Difference procedure was then applied to the geometric and laminate lay-up parameter combinations for each factor to identify the parameter combinations where significant joint strength differences exist between the standard and nonstandard hole joints.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnalysis of variance.
=650  \0$aBolted joint.
=650  \0$aBushing.
=650  \0$aComposite.
=650  \0$aFastener.
=650  \0$aGraphite/epoxy.
=650  \0$aHead-type.
=650  \0$aLaminate.
=650  \0$aMean square.
=650  \0$aMetallic insert.
=650  \0$aNull hypothesis.
=650  \0$aOver-sized hole.
=650  \0$aSleeve.
=650  \0$aSum of squares.
=650  \0$aUltimate strength.
=650  \0$aBolted joints.
=650  \0$aJoints (Engineering)
=650  \0$aBolts and nuts.
=653  10$aBolted joint.
=653  20$aFastener.
=653  20$aComposite.
=653  20$aGraphite/epoxy.
=653  20$aLaminate.
=653  20$aHead-type.
=653  20$aMetallic insert.
=653  20$aBushing.
=653  20$aSleeve.
=653  20$aOver-sized hole.
=653  20$aAnalysis of variance.
=653  20$aF-Test.
=653  20$aNull hypothesis.
=653  20$aFisher's protected least significant difference (LSD).
=653  20$aSum of squares.
=653  20$aMean square.
=653  20$aUltimate strength.
=700  1\$aHietala, HJ., $eauthor.
=700  1\$aPackman, PF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10510J.htm

=LDR  03309nam  2200649 i 4500
=001  CTR10511J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10511J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10511J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.2
=082  04$a620.1/1232$223
=100  1\$aGates, TS., $eauthor.
=245  10$aTime-Dependent Behavior of a Graphite/Thermoplastic Composite and the Effects of Stress and Physical Aging / $cTS Gates, M Feldman.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 1 (January 1995)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aExperimental studies were performed to determine the effects of stress and physical aging on the matrix dominated time-dependent properties of IM7/8320 composite. Isothermal tensile creep/aging test techniques developed for polymers were adapted for testing of the composite material. Time-dependent transverse (S22) and shear (S66) compliance's for an orthotropic plate were found from short-term creep compliance measurements at constant, sub-Tg temperatures. These compliance terms were shown to be affected by physical aging. Aging time shift factors and shift rates were found to be a function of temperature and applied stress.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aCreep compliance.
=650  \0$aPhysical aging.
=650  \0$aSuperposition.
=650  \0$aViscoelasticity.
=650  \0$aElasticity.
=650  \7$aSCIENCE $xNanoscience.
=653  10$aPhysical aging.
=653  20$aComposite materials.
=653  20$aViscoelasticity.
=653  20$aCreep compliance.
=653  20$aSuperposition.
=700  1\$aFeldman, M., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10511J.htm

=LDR  03945nam  2200757 i 4500
=001  CTR10512J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10512J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10512J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRangaswamy, P., $eauthor.
=245  10$aResidual Stresses in SCS-6/Beta-21S Composites / $cP Rangaswamy, N Jayaraman.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 1 (January 1995)
=504  \\$aIncludes bibliographical references$b22.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aResidual stress profiles were determined using X-ray diffraction (XRD) procedures in SCS-6/Beta-21S composites in unidirectional [0]4, cross-ply [0/90]s, and quasi-isotropic [0/±45/90]s lay-ups by sequentially electropolishing matrix layers off the outer surface. These experimental results were compared with the finite element model (FEM) calculations. Generally, the longitudinal stresses in the unidirectional [0]4 composite was almost twice the transverse stresses, while for the cross-ply [0/90]s, composite, the logitudinal and the transverse stresses were similar in magnitude. The stress profile for the quasi-isotropic [0/±45/90]s lay-up were intermediate between the unidirectional and cross-ply composites. These results show the strong influence of the underlying ply on the residual stresses in the outer ply. A 90° ply has greater influence than a 45° ply on the outer 0° ply of the composite.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCoefficient of thermal expansion (CTE).
=650  \0$aComposites.
=650  \0$aCross-ply.
=650  \0$aFinite element modeling.
=650  \0$aQuasi-isotropic.
=650  \0$aResidual stress.
=650  \0$aTitanium matrix.
=650  \0$aUndirectional.
=650  \0$aX-ray stress measurements.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aResidual stress.
=653  20$aFinite element modeling (FEM).
=653  20$aTitanium matrix.
=653  20$aComposites.
=653  20$aCoefficient of thermal expansion (CTE) mismatch.
=653  20$aX-ray stress measurements.
=653  20$aMaterial removal effects.
=653  20$aUndirectional.
=653  20$aCross-ply.
=653  20$aQuasi-isotropic.
=700  1\$aJayaraman, N., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10512J.htm

=LDR  03475nam  2200745 i 4500
=001  CTR10513J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10513J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10513J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aConant, NR., $eauthor.
=245  13$aAn Improved Iosipescu Shear Test Fixture / $cNR Conant, EM Odom.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 1 (January 1995)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new Iosipescu shear test fixture design that can be used to perform the test procedure outlined in Test Method for Shear Properties of Composite Materials by the V-Notched Beam Method (ASTM D 5379) was designed, fabricated, and tested. The new fixture solves the often reported problems of specimen twisting, variability of results, and differences in measured shear modulus between [0]16, [0/90]4s, and [90]16 laminates. Lateral instability of the Iosipescu specimen is explored as the main agent causing the undesirable effects observed with the previous fixture design.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFront-to-back difference.
=650  \0$aGraphite/epoxy composites.
=650  \0$aInstability.
=650  \0$aShear modulus.
=650  \0$aShear strain.
=650  \0$aShear testing.
=650  \0$aStrain gage.
=650  \0$aTwisting.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aIosipescu fixture.
=653  20$aGraphite/epoxy composites.
=653  20$aTwisting.
=653  20$aShear testing.
=653  20$aInstability.
=653  20$aShear modulus.
=653  20$aShear strain.
=653  20$aIosipescu specimen.
=653  20$aFront-to-back difference.
=653  20$aStrain gage.
=700  1\$aOdom, EM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10513J.htm

=LDR  03533nam  2200625 i 4500
=001  CTR10514J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19959999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10514J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10514J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aGowayed, Y., $eauthor.
=245  10$aThermal Conductivity of Textile Composites with Arbitrary Preform Structures / $cY Gowayed, J-C Hwang, D Chapman.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1995.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 17, Issue 1 (January 1995)
=504  \\$aIncludes bibliographical references$b28.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this paper, a model is constructed to predict the thermal conductivity of textile composite materials under steady state heat transfer conditions. First, the composite under consideration is geometrically characterized to identify relative volume fraction and spatial orientation of each yarn along its path. This is followed by applying finite element analysis (FEA) and virtual work to a "unit cell" of the textile composite. Hybrid hexahedra brick elements with fibers and matrix around each integration point are employed in the finite element formulation by means of micro-level homogenization. Thermal conductivity predictions using this approach are found to agree with experimental results for polymer and ceramic composites. The same approach can be used to solve other field problems including electrical conductivity, electrostatics, and moisture diffusion.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1995. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aConductivity.
=650  \0$aFinite element analysis.
=650  \0$aTextile composites.
=650  \0$aFinite element method.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aTextile composites.
=653  20$aConductivity.
=653  20$aFinite element analysis (FEA).
=700  1\$aHwang, J-C, $eauthor.
=700  1\$aChapman, D., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10514J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10517J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10517J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aBakuckas, JG., $eauthor.
=245  10$aThermal Residual Stresses in the Analysis of Fiber-Bridged Matrix Crack Growth in Titanium Matrix Composites / $cJG Bakuckas, WS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 2 (April 1996)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this research, thermal residual stresses were incorporated in an analysis of fiber-bridged matrix cracks in unidirectional and cross-ply titanium matrix composites (TMC) containing center holes or center notches. Two TMCs were investigated, namely, SCS-6/Ti-15-3 and SCS-6/Timetal-21S laminates. Experimentally, matrix crack initiation and growth were monitored during tension-tension fatigue tests conducted at room temperature and at an elevated temperature of 200°C. Analytically, thermal residual stresses were included in a fiber bridging (FB) model. The local R-ratio and stress-intensity factor in the matrix due to thermal and mechanical loadings were calculated and used to evaluate the matrix crack growth behavior in the two materials studied. The frictional shear stress term τ assumed in this model was used as a curve-fitting parameter to matrix crack growth data. The scatter band in the values of τ used to fit the matrix crack growth data was significantly reduced when thermal residual stresses were included in the fiber-bridging analysis. For a given material system, lay-up and temperature, a single value of τ was sufficient to analyze the crack growth data. It was revealed in this study that thermal residual stresses are an important factor overlooked in the original FB models.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aMatrix crack growth.
=650  \0$aThermal residual stresses.
=650  \0$aTitanium matrix composites.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aTitanium matrix composites.
=653  20$aThermal residual stresses.
=653  20$aMatrix crack growth.
=700  1\$aJohnson, WS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10517J.htm

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=024  7\$a10.1520/CTR10518J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10518J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA656
=082  04$a624.1/7$223
=100  1\$aUrbanik, TJ., $eauthor.
=245  10$aMachine Direction Strength Theory of Corrugated Fiberboard / $cTJ Urbanik.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
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=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 2 (April 1996)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aLinerboard elements between the corrugations of corrugated fiberboard can be viewed as short wide columns when the fiberboard is loaded perpendicular to the axes of the corrugations. Column ends are elastically restrained by the corrugated medium. A theory of buckling of nonlinear corrugated fiberboard material, with compression perpendicular to the corrugation axes, was developed. This theory is consistent with a previous theory applied to fiberboard with compression parallel to the corrugations. The theory matched strength data of corrugated fiberboard using paper compression strength, extensional stiffness, and bending stiffness data as inputs. The theory was further improved by empirically correcting for interactions between material crush failure and structure buckling failure. The correction equation predicts an optimum form of the linerboard stress-strain curve from initial slope and maximum stress data and predicts an element slenderness that varies with the mode of failure.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aElastic stability.
=650  \0$aFiberboard.
=650  \0$aPaper.
=650  \0$aPlate structure.
=650  \0$aStructural stability.
=650  \0$aElastic analysis (Engineering)
=650  \0$aThin-walled structures.
=653  10$aPlate structure.
=653  20$aElastic stability.
=653  20$aBuckling.
=653  20$aFiberboard.
=653  20$aPaper.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10518J.htm

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=001  CTR10519J
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=024  7\$a10.1520/CTR10519J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aValente, T., $eauthor.
=245  10$aHot Pressing of Plasma-Sprayed SiC Fiber-Reinforced Ti-6Al-4V Alloy / $cT Valente, F Carassiti.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
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=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 2 (April 1996)
=504  \\$aIncludes bibliographical references$b31.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAdvanced titanium alloy metal matrix composites offer significant mechanical improvements over many conventional materials. In order to minimize fiber-matrix chemical reactions due to high temperatures involved in the fabrication methods, the final component can be obtained using two different steps: (1) fabrication of preforms (monotapes) by inert plasma spraying and (2) hot pressing of the fabricated preforms.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFactorial design.
=650  \0$aHot pressing.
=650  \0$aInert plasma spraying.
=650  \0$aMetal matrix composites.
=650  \0$aSilicon-carbide fibers.
=650  \0$aTitanium alloy matrix.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMetal matrix composites.
=653  20$aInert plasma spraying.
=653  20$aHot pressing.
=653  20$aFactorial design.
=653  20$aSilicon-carbide fibers.
=653  20$aTitanium alloy matrix.
=700  1\$aCarassiti, F., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10519J.htm

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=024  7\$a10.1520/CTR10520J$2doi
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aLi, J., $eauthor.
=245  10$aSimplified Data Reduction Methods for the ECT Test for Mode III Interlaminar Fracture Toughness / $cJ Li, TK O'Brien.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 2 (April 1996)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSimplified expressions for the parameter controlling the load-point compliance and strain energy release rate were obtained for the edge crack torsion (ECT) specimen for Mode III interlaminar fracture toughness. Data reduction methods for Mode III toughness based on the present analysis are proposed. The effect of the transverse shear modulus G23 on Mode III interlaminar fracture toughness characterization was evaluated. Parameters influenced by the transverse shear modulus were identified. Analytical results indicate that a higher value of G23 results in a lower load point compliance and lower Mode III toughness estimation. The effect of G23 on the Mode III toughness using the ECT specimen is negligible when an appropriate initial delamination length is chosen. A conservative estimation of the Mode III toughness can be obtained by assuming G23 = G12 for any initial delamination length.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompliance.
=650  \0$aComposites.
=650  \0$aStrain energy release rate.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aCompliance.
=653  20$aStrain energy release rate.
=653  20$aMode III fracture toughness.
=700  1\$aO'Brien, TK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10520J.htm

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=024  7\$a10.1520/CTR10521J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10521J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGraesser, DL., $eauthor.
=245  10$aDamage Tolerance Predictions for Stiffened Composite Panels-Part II : $bApplication of a Failure Criteria / $cDL Graesser, ME Tuttle.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn analysis method suitable for prediction of the residual strength of a stiffened composite panel containing a center crack is presented. The analysis is based on the superposition of anisotropic elasticity solutions for an infinite plate. Strength predictions are made for two panel configurations and compared with experimental data. Reasonable comparisons between predictions and data are obtained for a panel with relatively small tear straps and little crack tip damage growth prior to final failure. However, the model shows some unconservative predictions for a panel with relatively large tear straps and crack tip damage growth.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite panels.
=650  \0$aDamage tolerance.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDamage tolerance.
=653  20$aComposite panels.
=700  1\$aTuttle, ME., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10521J.htm

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=024  7\$a10.1520/CTR10522J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10522J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHighsmith, AL., $eauthor.
=245  10$aLow Velocity Impact Damage in Filament-Wound Composite Pressure Bottles / $cAL Highsmith, FE Ledbetter, A Nettles, SS Russell.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 2 (April 1996)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn an effort to better understand the damage that develops in filament-wound composite structures when they are subjected to low velocity impact loads, a series of low velocity impact experiments was performed on small (146 mm (5.75 in.) diameter) filament wound pressure bottles. Three different material systems, IM7/3501-6ATL, IM7/X8553-45, and IM7/977-2, were evaluated. Three impact energy levels, 4.07 J (3.0 ft-lb), 6.78 J (5.0 ft-lb), and 9.49 J (7.0 ft-lb), were applied. Dye penetrant enhanced X-ray radiography was used to assess the damage that resulted from the impact loading. The through-the-thickness location of damage was assessed by means of stereo radiography.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite material.
=650  \0$aDamage.
=650  \0$aDelamination.
=650  \0$aFiber fracture.
=650  \0$aFilament-wound composite.
=650  \0$aImpact.
=650  \0$aMatrix cracking.
=650  \0$aX-ray radiography.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite material.
=653  20$aFilament-wound composite.
=653  20$aImpact.
=653  20$aDamage.
=653  20$aDelamination.
=653  20$aMatrix cracking.
=653  20$aFiber fracture.
=653  20$aX-ray radiography.
=700  1\$aLedbetter, FE., $eauthor.
=700  1\$aNettles, A., $eauthor.
=700  1\$aRussell, SS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10522J.htm

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=024  7\$a10.1520/CTR10523J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aChelikani, S., $eauthor.
=245  10$aHydrodynamic Machining of Fiber-Reinforced Composites / $cS Chelikani, S Kalpakjian.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 2 (April 1996)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper presents the results of an experimental investigation aimed at studying the applicability of waterjet machining to reinforced plastics. Representative samples of plastics over a wide range of matrices and fibers of various thicknesses were chosen. The machined samples were studied under a scanning electron microscope (SEM) for surface characteristics. Some samples were measured for roughness using a stylus profilometer and later non-contact laser holography for confirmation. The SEM study revealed that under conditions of excessive cutting speed, high stand-off distance, low water pressure, small nozzle diameter, which are considered nonoptimum, the surfaces displayed signs of fiber debonding, pull-out, matrix chipping, and delamination. Roughness readings revealed that surface quality improves with larger-diameter nozzles and at low machining speeds.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber debonding.
=650  \0$aFiber pullout.
=650  \0$aGlass-epoxy composites.
=650  \0$aGraphite-peek composites.
=650  \0$aHydrodynamic machining.
=650  \0$aSurface roughness.
=650  \0$aWaterjet machining.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aHydrodynamic machining.
=653  20$aWaterjet machining.
=653  20$aGlass-epoxy composites.
=653  20$aGraphite-peek composites.
=653  20$aFiber pullout.
=653  20$aFiber debonding.
=653  20$aSurface roughness.
=700  1\$aKalpakjian, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10523J.htm

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=001  CTR10524J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10524J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10524J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aVure, NRS, $eauthor.
=245  10$aEffect of Cooling Rate and Stacking Sequence on the Fatigue Behavior of Notched Quasi-Isotropic AS4/PEEK Laminates / $cNRS Vure, RD Kriz.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 2 (April 1996)
=504  \\$aIncludes bibliographical references$b35.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effect of cooling rate and stacking sequence on fatigue behavior was analyzed for notched quasi-isotropic AS4/PEEK laminates. The fatigue behavior of fast (475°F/min) and slow (1°F/min) cooled specimens of the following two lay-ups was studied: Layup A of (−45/0/45/90)s and Layup B of (45/90/−45/0)s. All specimens were subjected to a load-controlled, tension-tension fatigue loading with a stress ratio R = 0.1 at a frequency of 5 Hz. Damage was monitored by the reduction in dynamic stiffness and penetrant enhanced X-radiography. Post-failure analysis was carried out by scanning electron microscopy (SEM). Influence of cooling rate on the fatigue properties was different in the two stacking sequences investigated. The fatigue behavior changed drastically with the variation in the stacking sequence. A model, based on a constant strain-to-failure, was developed for life prediction and the predicted lives are in good agreement with the experimental values. To help understand the fatigue behavior of the two stacking sequences studied, the interlaminar stress distributions were calculated with a quasi-3D finite element analysis (FEA) for the regions around the hole. Specimens of Lay-up A were predicted to be more prone to delamination as compared to those of Lay-up B and this is consistent with experimental observations.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aConstant strain-to-failure.
=650  \0$aCooling rate.
=650  \0$aCrystallinity.
=650  \0$aFatigue.
=650  \0$aFinite element analysis.
=650  \0$aSemicrystalline.
=650  \0$aStacking sequence.
=650  \0$aThermoplastic.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aThermoplastic.
=653  20$aSemicrystalline.
=653  20$aFatigue.
=653  20$aCooling rate.
=653  20$aStacking sequence.
=653  20$aAS4/PEEK laminates.
=653  20$aFinite element analysis.
=653  20$aCrystallinity.
=653  20$aConstant strain-to-failure.
=700  1\$aKriz, RD., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10524J.htm

=LDR  03175nam  2200661 i 4500
=001  CTR10525J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10525J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10525J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT50
=082  04$a530.8$223
=100  1\$aYuanming, L., $eauthor.
=245  13$aAn Exact Method for Dynamic Analysis of Rectangular Laminated Orthotropic Plates Under Heating Load / $cL Yuanming, W Yaping.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aBy means of the three-dimensional (3D) elastic theory, a state equation is deduced for the exact analysis of laminated orthotropic plates under a harmonic temperature variation T = T' (x,y,z). The exact solution for the response of simply supported rectangular laminated orthotropic plates to applied heating is given by solving the state equation. Finally, the numeric results of boundary surface stresses of every ply of laminated orthotropic plates are given by two numeric examples.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDynamic analysis.
=650  \0$aExact method.
=650  \0$aHeating load.
=650  \0$aLaminates.
=650  \0$aOrthotropic plates.
=650  \0$aDynamic method.
=650  \0$aStructural analysis (Engineering)
=650  \0$aDynamic testing.
=653  10$aExact method.
=653  20$aDynamic analysis.
=653  20$aOrthotropic plates.
=653  20$aLaminates.
=653  20$aHeating load.
=700  1\$aYaping, W., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10525J.htm

=LDR  03805nam  2200649 i 4500
=001  CTR10528J
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=024  7\$a10.1520/CTR10528J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10528J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aSolti, JP., $eauthor.
=245  12$aA Simplified Approach for Modeling Fatigue of Unidirectional Ceramic Matrix Composites / $cJP Solti, S Mall, DD Robertson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 3 (July 1996)
=504  \\$aIncludes bibliographical references$b40.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn analytical methodology is developed to model the response of unidirectional ceramic matrix composites (CMCs) under monotonic and fatigue loadings at room temperature. The analysis is presented as a first step toward analyzing the fatigue behavior of CMCs at elevated temperatures. The laminate is modeled using a modified shear-lag analyses in which the microstructural damage is estimated using simple damage criteria. Moreover, the damage mechanisms considered in this study are matrix cracking, fiber/matrix interfacial debonding and slip, fiber fracture, and fiber pullout. A simple criterion for estimating the average matrix crack density is developed and compared with classical fracture mechanics techniques. Additionally, a formulation for modeling the fatigue response of ceramic composites including stress-strain hysteresis and strain ratchetting is presented. The stress-strain response under monotonic tensile loading, and the fatigue life (S-N relationship) and stress-strain hysteresis under cyclic loading obtained from the present analytical methodology are compared with their experimental counterparts. They are in good agreement with one another.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCeramic matrix composite.
=650  \0$aFatigue.
=650  \0$aModeling.
=650  \0$aShear-lag.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aCeramic matrix composite.
=653  20$aFatigue.
=653  20$aShear-lag.
=653  20$aModeling.
=700  1\$aMall, S., $eauthor.
=700  1\$aRobertson, DD., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10528J.htm

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=001  CTR10529J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10529J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10529J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aSubramanian, S., $eauthor.
=245  10$aEffect of Loading Frequency and Interleaf on the Delamination Characteristics of Laminated Composites / $cS Subramanian, WS Chan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (15 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b30.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this study, the effect of loading frequency on delamination onset and growth characteristics of (30/−302/30/90)s IM6/3501-6 laminates, with and without an interleaf was studied. FM 300 adhesive layers, manufactured by American Cynamid, were placed at the 30/90 interface to study the influence of interleaf on the delamination characteristics of laminates. Quasi 3-D finite element analysis results indicate that the maximum interlaminar normal stress is lower in the laminate with the interleaf compared to the baseline laminate. Results also indicate that the presence of an interleaf reduces the Mode I component of strain energy release rate at the critical interface.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDamage tolerance.
=650  \0$aDelamination.
=650  \0$aDurability.
=650  \0$aFatigue.
=650  \0$aFractography.
=650  \0$aFrequency effects.
=650  \0$aInterleaf.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDelamination.
=653  20$aFatigue.
=653  20$aFrequency effects.
=653  20$aInterleaf.
=653  20$aDamage tolerance.
=653  20$aDurability.
=653  20$aFractography.
=700  1\$aChan, WS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10529J.htm

=LDR  03889nam  2200685 i 4500
=001  CTR10530J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10530J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10530J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGoethe, JE., $eauthor.
=245  13$aAn Experimental Investigation of the Failure Modes in Hybrid Ceramic Matrix Composites / $cJE Goethe, LR Dharani, DR Carroll.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 3 (July 1996)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA material system has been developed that employs the benefits of both fiber and whisker reinforcement in the strengthening and toughening of ceramics. Testing was performed on this hybrid material system in three-point flexure using a combination of acoustic emissions analysis and microscopy techniques for damage analysis. It is shown that the hybrid material system will withstand a higher stress before microcracking occurs in the matrix and has improved transverse strength. In the longitudinal direction, microcracking occurred at 121 MPa for the hybrid composite, compared to 47 MPa for composites reinforced solely with fibers. The transverse flexure strength was 62 MPa for the hybrid, compared with 24 MPa for fiber-reinforced composites. The hybrid composite also had higher stiffness and better damage tolerance in both the longitudinal and transverse directions. Material properties are presented for three material systems: a whisker-reinforced cordierite composite, a fiber-reinforced cordierite composite, and a fiber/whisker hybrid-reinforced cordierite composite.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCeramic matrix.
=650  \0$aComposites.
=650  \0$aFailure mechanisms.
=650  \0$aHybrid composites.
=650  \0$aMicrocracking.
=650  \0$aTransverse properties.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aCeramic matrix.
=653  20$aHybrid composites.
=653  20$aMicrocracking.
=653  20$aFailure mechanisms.
=653  20$aTransverse properties.
=700  1\$aDharani, LR., $eauthor.
=700  1\$aCarroll, DR., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10530J.htm

=LDR  03203nam  2200601 i 4500
=001  CTR10531J
=003  IN-ChSCO
=005  20161219163000.0
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10531J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10531J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aRoy, AK., $eauthor.
=245  10$aTensile Fatigue Behavior of a Coated Two-Dimensional Carbon-Carbon Composite Laminate / $cAK Roy.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 3 (July 1996)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe room-temperature tensile static and fatigue properties of a coated two-dimensional carbon-carbon composite laminate are reported. The cross-ply laminate is made of 8HS balanced weave of T300 heat treated carbon fibers with a CVI densified inhibited carbon matrix. The fatigue properties are obtained for four different stress levels. The in-plane stiffness and strength degradation due to fatigue and fatigue life are obtained at these four stress levels. The effect of the fatigue loading on the matrix properties is determined by measuring the interlaminar tensile strength for two different fatigue stress levels. The coating interface tensile strength degradation due to the fatigue loading is also reported.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon-carbon.
=650  \0$aFatigue life.
=650  \0$aStrength degradation.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aCarbon-carbon.
=653  20$aFatigue life.
=653  20$aStrength degradation.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10531J.htm

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=001  CTR10532J
=003  IN-ChSCO
=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10532J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10532J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA460
=082  04$a620.1617$223
=100  1\$aO'Connor, MJ., $eauthor.
=245  10$aStress-Free Temperature of the Macro-Interface in Selectively Reinforced Aluminum Castings / $cMJ O'Connor, FE Wawner, CC Jones.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new method was used to investigate the effect of thermal cycling on the stress-free temperature of the macro-interface in castings consisting of an Al-12%Si alloy (A339) with a 16% v/o discontinuous Saffil [1] fiber reinforced region. Thin bimaterial strips, containing both the unreinforced alloy and composite, were sectioned from castings after being thermally cycled between 50°C and 275°C. Because these strips curl in response to thermal stress, like bimetal thermostats, it was possible to measure their deflection at different temperatures and thereby determine the temperature at which the thermal stress is nonexistent. It was found that this stress-free temperature increased with increasing numbers of thermal cycles and approached the maximum thermal cycle temperature. It is suggested that this is a result of dimensional changes experienced by the composite region during thermal cycling.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aMacro-interface.
=650  \0$aReinforced aluminum castings.
=650  \0$aStress-free temperature.
=650  \0$aTemperature.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aStress-free temperature.
=653  20$aMacro-interface.
=653  20$aReinforced aluminum castings.
=700  1\$aWawner, FE., $eauthor.
=700  1\$aJones, CC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10532J.htm

=LDR  03649nam  2200649 i 4500
=001  CTR10533J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10533J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10533J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aKujawski, D., $eauthor.
=245  13$aAn Effective Stress Parameter for Long-Term Fatigue Strength of Fiber-Reinforced Plastic Pipes / $cD Kujawski, AS Chiu, F Ellyin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe currently used American Society for Testing and Materials (ASTM) procedure and a modified American Petroleum Institute (API) method for cyclic pressure strength of fibre reinforced plastic (FRP) pipes are critically discussed together with the test results generated by Battelle. In addition, two new damage parameters, recently proposed by the authors, are examined using the Battelle tests as a database. An equivalent stress range damage parameter, Δ¯σ, is recommended which combined the loading condition, hoop stress range and normalized mean stress, and FRP pipe material properties. The proposed damage parameter, Δ¯σ, can be used in the engineering evaluation of fatigue performance of pressured fiberglass pipes. The Δ¯σ provides substantial improvement over the ASTM recommended parameter, hoop stress range. Using the Δ¯σ, the fatigue data for different mean pressures are consolidated into a narrow scatter band.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiberglass/epoxy pipes.
=650  \0$aLong-term fatigue strength.
=650  \0$aMean stress effect.
=650  \0$aTesting procedure.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aFiberglass/epoxy pipes.
=653  20$aLong-term fatigue strength.
=653  20$aMean stress effect.
=653  20$aTesting procedure.
=700  1\$aChiu, AS., $eauthor.
=700  1\$aEllyin, F., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10533J.htm

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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC321
=082  04$a536/.2012$223
=100  1\$aTai, H., $eauthor.
=245  10$aEquivalent Thermal Conductivity of Two- and Three-Dimensional Orthogonally Fiber-Reinforced Composites in One-Dimensional Heat Flow / $cH Tai.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aBy applying the fundamental definition of thermal conductivity to a unit cell of an orthogonal fiber-reinforced composite material in a one-dimensional heat flow, one can readily deduce simple mathematical expressions for the equivalent thermal conductivity for the composite material. Such expressions can serve as useful guides for materials development.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber-reinforced composites.
=650  \0$aHeat flow.
=650  \0$aThermal conductivity.
=650  \0$aHeat $xConduction.
=650  \0$aMaterials $xThermal properties.
=650  \7$aSCIENCE $xMechanics $xThermodynamics.
=653  10$aThermal conductivity.
=653  20$aHeat flow.
=653  20$aFiber-reinforced composites.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10534J.htm

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=024  7\$a10.1520/CTR10535J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10535J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aJohnson, WS., $eauthor.
=245  10$aConcise Encyclopedia of Composite Materials Revised Edition / $cWS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (1 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 18, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10535J.htm

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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aBakis, CE., $eauthor.
=245  10$aPreamble to the Collection of Papers Based on Presentations Given at the Symposium on Durability of Composites, Dedicated in Honor of Professor Kenneth L. Reifsnider of Virginia Tech / $cCE Bakis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10538J.htm

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=001  CTR10539J
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=005  20161219163000.0
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10539J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10539J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aSpearing, SM., $eauthor.
=245  14$aThe Durability of Fiber Composites-The Case for Mechanism-Based Models / $cSM Spearing.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b32.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aLong-duration durability (particularly fatigue) testing of composites is time consuming and expensive. There is, therefore, a stronger incentive to reduce reliance on such testing than in other areas of design. Mechanism-based models offer the potential to reduce the reliance on test programs. Such models have been derived for several fatigue damage mechanisms, notably: delamination, fiber-bridged cracking, and off-axis ply cracking. There has been less success at modeling fatigue processes at higher levels, such as at notches. Examples of existing models are presented from the literature, and their capabilities and deficiencies are discussed in the context of improving the processes of materials selection and design for durability. Key principles are advocated, including modeling damage propagation utilizing Paris-type expressions, the importance of length scales in modeling fatigue processes, and the need to improve the capability to model multiple, interacting, damage processes.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite damage.
=650  \0$aComposites fatigue.
=650  \0$aFatigue crack growth.
=650  \0$aMechanism-based models.
=650  \0$aNotch tip damage.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites fatigue.
=653  20$aComposite damage.
=653  20$aFatigue crack growth.
=653  20$aMechanism-based models.
=653  20$aNotch tip damage.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10539J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10540J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10540J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aHalverson, HG., $eauthor.
=245  10$aResidual Strength-Based Life Predictions of Composite Materials Under Combined Damage Mechanisms / $cHG Halverson, SW Case.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWe seek a method by which the residual strengths of composites subjected to combined degradation mechanisms may be calculated. Three different approaches are considered. First, the inputs to the residual strength analysis are purely phenomenological. Second, we make use of a micromechanics-based simulation to combine the effects of two specified damage mechanisms. Finally, we develop a hybrid approach in which the results from the micromechanics simulations for individual mechanisms are used as inputs to the residual strength model as if they had been obtained from experimental data. The residual strength model is then used to predict the combined behavior, and the results are compared with those obtained directly from the simulations. For the two mechanisms considered (slow crack growth and asperity creep), the results for the detailed micromechanical simulations were accurately represented by the residual strength-based model.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aLife prediction.
=650  \0$aMicromechanics.
=650  \0$aResidual strength.
=650  \0$aSimulation.
=650  \0$aStress rupture.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aResidual strength.
=653  20$aLife prediction.
=653  20$aMicromechanics.
=653  20$aSimulation.
=653  20$aStress rupture.
=700  1\$aCase, SW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10540J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10541J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10541J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aCarrier, CR., $eauthor.
=245  12$aA Simple Discrete-Tow Model for Analysis of Textile Composites / $cCR Carrier, RC Averill.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b26.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA simplified discrete-tow model is presented for analysis of textile composite materials. This model discretely represents the fiber tows and resin independently as beam and shell finite elements, respectively. The approach is simple and very computationally efficient, making it especially well suited for modeling sections of a textile composite material much larger than a unit cell. In the present study, the discrete-tow model is formulated in detail and its utility is demonstrated for the prediction of effective properties for a variety of plain weave and triaxial braid materials.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDiscrete tow model.
=650  \0$aFiber tows.
=650  \0$aTextile composite materials.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aTextile composite materials.
=653  20$aDiscrete tow model.
=653  20$aFiber tows.
=653  20$aResin.
=700  1\$aAverill, RC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10541J.htm

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=024  7\$a10.1520/CTR10542J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10542J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aZaffaroni, G., $eauthor.
=245  10$aFatigue Behavior of Glass-Reinforced Epoxy Resin Submitted to Hot-Wet Aging / $cG Zaffaroni, C Cappelletti.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aTo assess the effect of hot-wet aging on the properties of a glass-reinforced epoxy resin, three kinds of specimens were subjected to static and dynamic (fatigue) tests, in both dry and moisture-saturated conditions. Although a reduction of both elastic properties and strengths was found, it seems that hygrothermal aging has no effect on the S-N fatigue behavior when the part at low loads is considered. It is proposed that there is a balance between the damage generated by micro-effects (such as fiber damaging, resin micro-cracking or micro-crazing) and the increased energy dissipation capability of the resin generated by the absorbed moisture. The first kind of behavior is dominant at high loads (low number of cycles: i.e., the static situation), while the second is more important where a high number of cycles is concerned.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEnvironmental effect.
=650  \0$aFatigue behavior.
=650  \0$aGlass fiber composites.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aGlass fiber composites.
=653  20$aEnvironmental effect.
=653  20$aFatigue behavior.
=700  1\$aCappelletti, C., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10542J.htm

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=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aShirey, CL., $eauthor.
=245  10$aTensile Behavior of Filament-Wound Composites in Medium Vacuum / $cCL Shirey, CE Bakis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 4 (October 2000)
=504  \\$aIncludes bibliographical references$b25.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn order to design the most efficient flywheel energy systems using fiber-reinforced polymer composite rotors, design allowables for the rotor material in a realistic environment and under realistic stresses must first be established. As a first step, this investigation characterizes the 0-deg tensile behavior of unidirectional T700 carbon and E-glass reinforced epoxy composites both as received and after conditioning at a pressure of 15 mtorr and a temperature of 20 to 25°C. Constant-amplitude tension-tension cyclic fatigue tests were carried out on half the specimens in a similar medium vacuum environment. Weights of specimens were tracked with immeasurable changes noted due to vacuum conditioning for up to 300 days' duration. E-glass/epoxy specimens had a higher quasi-static strength following conditioning, but this difference was not evident on an absolute stress basis in the fatigue tests. At the baseline comparison point of 105 cycles to failure, there was little difference in fatigue strength of as-received and conditioned E-glass/epoxy specimens. In the case of T700/epoxy, little difference between conditionings was noted in quasi-static tests, but as-received specimens had slightly higher fatigue strength at a lifetime of 105 cycles. Microscopic inspection of fracture surfaces following quasi-static and fatigue failures revealed no significant differences due to the type of loading or conditioning.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon.
=650  \0$aFatigue.
=650  \0$aFlywheel.
=650  \0$aGlass.
=650  \0$aVacuum.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aFatigue.
=653  20$aVacuum.
=653  20$aFlywheel.
=653  20$aCarbon.
=653  20$aGlass.
=700  1\$aBakis, CE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10543J.htm

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=001  CTR10544J
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=024  7\$a10.1520/CTR10544J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10544J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aDavalos, JF., $eauthor.
=245  10$aFiber-Reinforced Composite and Wood Bonded Interfaces : $bPart 1. Durability and Shear Strength / $cJF Davalos, P Qiao, BS Trimble.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFiber-reinforced plastic (FRP) composites have shown the potential for reinforcement of wood structures (e.g., bonding of FRP strips or fabrics to wood members). Although significant increases in stiffness and strength are achieved by this reinforcing technique, there is a concern about the reliable performance of the FRP-wood adhesive bond, which is susceptible to delamination. The overall objective of this two-part paper is to develop a qualification program to evaluate the service performance and fracture of composite/wood bonded interfaces. Two types of FRP-wood interfaces are studied: phenolic FRP-wood and epoxy FRP-wood bonds. In the present paper, Part 1, the durability and shear strength of FRP-wood bonds are evaluated by modified ASTM tests. First, the service performance and durability of FRP-wood interface bond is evaluated using a modified ASTM delamination test. Then, the apparent shear strengths of bonded interfaces under both dry and wet conditions are obtained from modified ASTM block-shear tests. It is shown that the modified ASTM D 2559 standard test can be successfully used to study the effect of several parameters (e.g., bonding pressure, assembling time, and coupling agents) on bondline performance under wet-dry exposure cycles. Then for the best combination of parameters, the average interface shear strengths can be obtained from block-shear tests of ASTM D 905, modified for hybrid laminates. Mode I fracture of FRP-wood bonded interfaces and guidelines for FRP-wood bond performance evaluation are presented in the companion Part 2 paper.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBonded interface.
=650  \0$aCoupling agents.
=650  \0$aDelamination.
=650  \0$aDurability.
=650  \0$aFiber-reinforced plastics.
=650  \0$aShear strength.
=650  \0$aWood.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFiber-reinforced plastics.
=653  20$aWood.
=653  20$aDurability.
=653  20$aDelamination.
=653  20$aShear strength.
=653  20$aBonded interface.
=653  20$aCoupling agents.
=700  1\$aQiao, P., $eauthor.
=700  1\$aTrimble, BS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10544J.htm

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=001  CTR10545J
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=024  7\$a10.1520/CTR10545J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10545J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aDavalos, JF., $eauthor.
=245  10$aFiber-Reinforced Composite and Wood Bonded Interfaces : $bPart 2. Fracture / $cJF Davalos, P Qiao, BS Trimble.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe evaluation of durability and shear strength of FRP-wood bonded interfaces is presented in Part 1 of this two-part study (see Davalos et al. [1]); here, in Part 2, an innovative contoured double-cantilever beam (CDCB) specimen is used to evaluate Mode I fracture of bonded interfaces, and interface fracture toughness data are experimentally obtained for dry and wet conditions. The specimens are designed by the Rayleigh-Ritz method to achieve a linear rate of compliance with respect to crack length. The proposed CDCB specimen is an efficient tool to evaluate Mode I fracture of hybrid interfaces, and the fracture toughness data obtained can be used to predict whether or not a bonded interface will delaminate under general service conditions. Based on the results of this two-part study, recommendations and guidelines are given for evaluation and qualification of FRP-wood bonded interfaces; the methods presented are useful for designing bonded joints, evaluating in-service durability of interfaces, and obtaining fracture toughness data for FRP-wood material combinations.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDelamination.
=650  \0$aFiber-reinforced plastics.
=650  \0$aFracture toughness.
=650  \0$aHybrid bonded interface.
=650  \0$aWood.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFiber-reinforced plastics.
=653  20$aWood.
=653  20$aDelamination.
=653  20$aHybrid bonded interface.
=653  20$aMode I fracture.
=653  20$aFracture toughness.
=700  1\$aQiao, P., $eauthor.
=700  1\$aTrimble, BS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10545J.htm

=LDR  03879nam  2200685 i 4500
=001  CTR10546J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10546J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10546J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aSenne, J., $eauthor.
=245  12$aA Life Prediction Methodology for Thick Section Composites Used in Civil Infrastructure / $cJ Senne, JJ Lesko, SW Case.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 4 (October 2006)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAs fiber-reinforced polymer (FRP) composites find application in highway bridge structures, methodologies for describing their long-term performance under service loading will be a necessity for designers. The designer of FRP bridge structures will be faced with out-of-plane damage and delamination at ply interfaces. The damage most often occurs between hybrid plys and dominates the lifetime response of a thick-section FRP structure. In this paper a model is developed to address these issues. The methodology employs the quadratic delamination initiation failure criteria, in conjunction with a delamination growth law to describe the out-of-plane damage under bending. These phenomena are combined with the critical element residual strength life prediction tool to determine remaining bending stiffness and moment capacity of a pultruded and hybrid FRP 20.3-cm-deep structural shape. The model successfully describes the onset of delamination prior to fiber failure and suggests that out-of-plane failure controls the life of the structure.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDelamination.
=650  \0$aFatigue.
=650  \0$aFiber-reinforced polymer composites.
=650  \0$aHybrid.
=650  \0$aLife prediction.
=650  \0$aOut-of-plane failure.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDelamination.
=653  20$aOut-of-plane failure.
=653  20$aFatigue.
=653  20$aLife prediction.
=653  20$aHybrid.
=653  20$aFiber-reinforced polymer composites.
=700  1\$aLesko, JJ., $eauthor.
=700  1\$aCase, SW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10546J.htm

=LDR  04068nam  2200757 i 4500
=001  CTR10551J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10551J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10551J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aPoursartip, A., $eauthor.
=245  12$aA Technique for Measuring Delamination Crack Tip Behavior in Composite Materials Inside a Scanning Electron Microscope / $cI Paris, R Bennett, M Mager, A Poursartip.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b23.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper presents a technique for measuring the crack opening displacement (COD) and crack shear displacement (CSD) profiles at a delamination crack tip, and using them to evaluate the effective 'local' Mode I and Mode II strain energy release rates. These values can then be compared to the 'global' strain energy release rates calculated in the usual manner from the globally applied conditions using Linear Elastic Fracture Mechanics (LEFM). The fixture that has been developed can accommodate full size standard delamination specimens, which can be loaded to failure in Mode I, Mode II, and mixed mode inside a Scanning Electron Microscope (SEM). The globally applied conditions (loads and displacements) and the local crack tip displacements can be simultaneously recorded and compared. The specimen preparation, the data acquisition and test control system, and the image acquisition and analysis system are described in detail.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCrack opening displacement.
=650  \0$aCrack shear displacements.
=650  \0$aCrack tip behavior.
=650  \0$aDelamination.
=650  \0$aFracture mechanics.
=650  \0$aMixed mode.
=650  \0$aScanning electron microscopy.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFracture mechanics.
=653  20$aDelamination.
=653  20$aIn situ.
=653  20$aCrack tip behavior.
=653  20$aCrack opening displacement.
=653  20$aCrack shear displacements.
=653  20$aScanning electron microscope (SEM).
=653  20$aMode I.
=653  20$aMode II.
=653  20$aMixed mode.
=700  1\$aBennett, R., $eauthor.
=700  1\$aMager, M., $eauthor.
=700  1\$aPoursartip, A., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10551J.htm

=LDR  05186nam  2200625 i 4500
=001  CTR10552J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10552J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10552J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMollenhauer, DH., $eauthor.
=245  10$aInterlaminar Deformation Along the Cylindrical Surface of a Hole in Laminated Composites-Experimental Analysis by Moiré Interferometry / $cDH Mollenhauer, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 3 (July 2001)
=504  \\$aIncludes bibliographical references$b36.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe deformation along cylindrical surfaces of holes in tensile-loaded specimens was measured using new moiré interferometry techniques. The techniques were developed and validated using an isotropic, homogeneous aluminum specimen. Two composite tensile specimens, fabricated from IM7/5250-4 pre-preg with ply lay-ups of [0°4?90°4]3s and [+30°2??30°2?90°4]3s, were then examined using the new techniques. Circumferential and thickness direction displacement fringe patterns (each 3° wide) were assembled into 90°-wide mosaics around the hole periphery for both composite specimens. Distributions of strain were calculated with high confidence on a sub-ply basis at selected angular locations. The measured strain behavior was complex. Ply-by-ply trends were revealed. Large ply-related variations in the circumferential strain were observed at certain angular locations around the periphery of the holes in both composites. Extremely large ply-by-ply variations of the shear strain were also documented in both composites. Peak values of shear strain approached 30 times the applied far-field axial strain. Residual  viscoelastic shearing strains were recorded in regions of large load-induced shearing strains. Large ply-group related variations in the thickness direction strain were observed in the [+30°, were then examined using the new techniques. Circumferential and thickness direction displacement fringe patterns (each 3° wide) were assembled into 90°-wide mosaics around the hole periphery for both composite specimens. Distributions of strain were calculated with high confidence on a sub-ply basis at selected angular locations. The measured strain behavior was complex. Ply-by-ply trends were revealed. Large ply-related variations in the circumferential strain were observed at certain angular locations around the periphery of the holes in both composites. Extremely large ply-by-ply variations of the shear strain were also documented in both composites. Peak values of shear strain approached 30 times the applied far-field axial strain. Residual viscoelastic shearing strains were recorded in regions of large load-induced shearing strains. Large ply-group related variations in the thickness direction strain were observed in the [+30°2??30°2?90°4]3s specimen. An important large-scale trend was observed in which the thickness direction strain tended to be more tensile near the outside faces of the laminate than near the mid-ply region.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aInterlaminar deformation.
=650  \0$aOpen holes.
=650  \0$aPolymer matrix composites.
=650  \0$aComposite material.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aPolymer matrix composites.
=653  20$aMoiré interferometry.
=653  20$aInterlaminar deformation.
=653  20$aOpen holes.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10552J.htm

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=001  CTR10553J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10553J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10553J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSouth, JT., $eauthor.
=245  10$aStrain Rate and Temperature Effects on the Mechanical Properties of an E-Glass/Vinyl Ester Composite System / $cJT South, KL Reifsnider, SW Case.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe need exists for a failure time schema to predict composite component lifetimes from quasi-static to dynamic strain rates. Models need to incorporate temperature, loading rate, and the time to failure of the composite components. An approach to describe the effects of strain rate and temperature on the mechanical properties of an E-glass/vinyl ester composite system is presented and verified with experimental data. A representation of the time to failure of the composite was constructed using the Monkmann-Grant equation, relating the applied steady state strain rate and the time to failure. Strain rates of 10−6 to 1.6 s−1 were achieved and experiments were conducted at room temperature, 80 and 120°C. It was found that the composite system exhibited nearly a constant strain to failure over the applied rates and temperatures. The test data verified an approach to a failure time estimation scheme for steady state strain rate utilizing the Monkmann-Grant approach.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aE-glass.
=650  \0$aStrain rate.
=650  \0$aTemperature.
=650  \0$aVinyl ester.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aE-glass.
=653  20$aVinyl ester.
=653  20$aStrain rate.
=653  20$aTemperature.
=653  20$aMonkmann-Grant.
=700  1\$aReifsnider, KL., $eauthor.
=700  1\$aCase, SW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10553J.htm

=LDR  03423nam  2200637 i 4500
=001  CTR10554J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10554J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10554J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.58
=082  04$a620.1123$223
=100  1\$aPonter, ARS, $eauthor.
=245  10$aShakedown Limits for a Metal Matrix Composite / $cARS Ponter, KF Carter, JM Duggan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe paper discusses a method for the evaluation of the yield values of a metal matrix composite material when subjected to a variation in temperature. A direct shakedown analysis method is described which produces a shakedown stress value as a result of a sequence of incompressible linear solutions with a spatially varying modulus. The process converges to the minimum upper bound associated with the class of displacement fields when implemented in a finite element method (Ponter and Carter [1,2]). The solutions for an Aluminum/alumina system loaded in a direction perpendicular to the direction of the fibers demonstrate the high sensitivity of this material to fluctuations in temperature. Simple approximate equations for strength values are presented in terms of nondimensional variables.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComputational methods.
=650  \0$aMetal matrix composites.
=650  \0$aShakedown.
=650  \0$aThermal stresses.
=650  \0$aThermal-expansion stresses.
=650  \0$aStructural dynamics.
=653  10$aMetal matrix composites.
=653  20$aThermal stresses.
=653  20$aShakedown.
=653  20$aComputational methods.
=700  1\$aCarter, KF., $eauthor.
=700  1\$aDuggan, JM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10554J.htm

=LDR  04015nam  2200673 i 4500
=001  CTR10555J
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10555J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10555J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aOdegard, G., $eauthor.
=245  10$aFailure Analysis of ±45° Off-Axis Woven Fabric Composite Specimens / $cG Odegard, D Armentrout, K Searles, L Kumosa, JK Sutter, M Kumosa.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (20 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe purpose of this research is to evaluate the mechanical response of eight harness satin woven graphite/polyimide composite specimens using the ±45° test. A series of tensile tests have been conducted at room temperature to evaluate the effect of specimen width as well as monotonic, progressive, and multiple loadings on the response of the composite specimens. Acoustic emission techniques have been employed to monitor damage initiation and progression in the specimens at different stages of loading. In addition, nonlinear finite element computations have been conducted to determine stress distributions in the ±45° fabric specimens. It has been shown that the specimen width effect is strong and should not be ignored in a failure analysis of the fabric composite using the ±45° test. The shear strength of the composite determined from the maximum loads increases substantially with the width of the specimen. It has also been shown in this research that the initiation of intralaminar damage in the graphite/polyimide composite can be monitored using acoustic emission. The initiation of interlaminar damage can be determined either from the characteristic knees on the load/displacement diagrams or from the acoustic emission data.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aGraphite/PMR-15.
=650  \0$aOff-axis testing.
=650  \0$aWoven fabric composites.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=653  10$aWoven fabric composites.
=653  20$aOff-axis testing.
=653  20$aFEM.
=653  20$aGraphite/PMR-15.
=700  1\$aArmentrout, D., $eauthor.
=700  1\$aSearles, K., $eauthor.
=700  1\$aKumosa, L., $eauthor.
=700  1\$aSutter, JK., $eauthor.
=700  1\$aKumosa, M., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10555J.htm

=LDR  04192nam  2200793 i 4500
=001  CTR10556J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10556J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10556J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aNaik, NK., $eauthor.
=245  10$aEffect of Twisting on Tensile Failure of Impregnated Yarns with Broken Filaments / $cNK Naik, I Mudzingwa, MN Singh.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 3 (July 2001)
=504  \\$aIncludes bibliographical references$b33.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe tensile strength of impregnated strand/unidirectional composite depends on many factors including the strength of the interface. Recent efforts in trying to increase the strength of composites have been directed towards increasing the strength of the interface through fiber surface treatment and better resin systems that give better interfacial shear strength. However, the role of frictional forces and analysis of twisted impregnated yarns have largely been ignored. Twisted geometry gives rise to lateral pressure that contributes to the frictional shear stress; therefore, for a twisted yarn, interfacial shear strength would be higher than that of a impregnated strand/unidirectional composite. Twisted yarns have the obvious disadvantage that their unidirectional strength suffers because of fiber obliquity. This work examines the effect of the lateral pressure on the tensile strength of twisted yarns with broken filaments. Studies have been carried out on both the helical wound impregnated yarns and helical twisted impregnated yarns.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBroken filament.
=650  \0$aFrictional shear strength.
=650  \0$aIneffective length.
=650  \0$aInterface efficiency.
=650  \0$aInterfacial shear strength.
=650  \0$aLateral pressure.
=650  \0$aStress concentration.
=650  \0$aTwisted yarn.
=650  \0$aWound yarn.
=650  \0$aYarn tensile strength.
=650  \0$aShear (Mechanics)
=650  \0$aDeformations (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aYarn tensile strength.
=653  20$aTwisted yarn.
=653  20$aWound yarn.
=653  20$aLateral pressure.
=653  20$aStress concentration.
=653  20$aIneffective length.
=653  20$aInterfacial shear strength.
=653  20$aFrictional shear strength.
=653  20$aInterface efficiency.
=653  20$aBroken filament.
=700  1\$aMudzingwa, I., $eauthor.
=700  1\$aSingh, MN., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10556J.htm

=LDR  03534nam  2200613 i 4500
=001  CTR10560J
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10560J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10560J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aKim, H., $eauthor.
=245  14$aThe Design of In-Plane Shear and Tension-Loaded Bonded Composite Lap Joints / $cH Kim, KT Kedward.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 2 (April 2002)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe stress analysis of a bonded joint carrying combined in-plane shear and tension load is presented. A general equation is derived that governs the transfer of shear load through a joint. For the case of uniform in-plane shear loading, a closed-form solution exists that is directly analogous to the well-known tension-loaded case. When shear and tension loads are simultaneously applied to a joint, the results of stress analyses treating each loading case separately are superimposed to calculate a combined biaxial shear stress state in the adhesive. Predicting the elastic limit of the adhesive for a lap joint under combined loading is then accomplished by using the von Mises yield criterion. This approach allows the calculation of a limit load envelope that maps the range of combined loading conditions within which the joint is expected to behave elastically. An example design case study of a bonded I-beam shear web is included.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCombined loading.
=650  \0$aComposite bonded lap joint.
=650  \0$aIn-plane shear loading.
=650  \0$aShear (Mechanics)
=650  \0$aDeformations (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aComposite bonded lap joint.
=653  20$aIn-plane shear loading.
=653  20$aCombined loading.
=700  1\$aKedward, KT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10560J.htm

=LDR  04849nam  2200709 i 4500
=001  CTR10561J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10561J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10561J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aKrueger, R., $eauthor.
=245  10$aFatigue Life Methodology for Bonded Composite Skin/Stringer Configurations / $cR Krueger, IL Paris, TK O'Brien, PJ Minguet.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (24 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 2 (April 2002)
=504  \\$aIncludes bibliographical references$b25.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA methodology is presented for determining the fatigue life of composite structures based on fatigue characterization data and geometric nonlinear finite element analyses. To demonstrate the approach, predicted results were compared to fatigue tests performed on specimens which consisted of a tapered composite flange, representing a stringer or frame, bonded onto a composite skin. In a first step, quasi-static tension and fatigue tests were performed to evaluate the debonding mechanisms between the skin and the bonded stringer. Specimen edges were examined under the microscope to document the damage occurrence. In a second step, a two-dimensional finite element model was developed to analyze the tests. To predict matrix cracking onset, the relationship between the externally applied tension load and the maximum principal stresses transverse to the fiber direction was determined through geometrically nonlinear analysis. Transverse tension fatigue life data were used to generate an onset fatigue life P-N curve for matrix cracking. The resulting prediction was in good agreement with measured data from the fatigue tests. In a third step, a fracture mechanics approach based on geometrically nonlinear analysis was used to determine the relationship between the externally applied tension load and the critical energy release rate. Mixed mode energy release rate fatigue life data from DCB, 4ENF, and MMB tests were used to create a fatigue life onset G-N curve for delamination. The resulting prediction was in good agreement with data from the fatigue tests. Additionally, the prediction curve for cumulative life to failure was generated from the matrix onset and delamination onset fatigue life curves. The results were in good agreement with data from the fatigue tests, which demonstrated that the methodology offers a significant potential to predict cumulative fatigue life of composite structures.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFatigue life prediction.
=650  \0$aFinite element analysis.
=650  \0$aFracture mechanics.
=650  \0$aSkin/flange interface.
=650  \0$aTesting.
=650  \0$aFinite element method.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aComposite materials.
=653  20$aTesting.
=653  20$aFinite element analysis.
=653  20$aFatigue life prediction.
=653  20$aFracture mechanics.
=653  20$aSkin/flange interface.
=700  1\$aParis, IL., $eauthor.
=700  1\$aO'Brien, TK., $eauthor.
=700  1\$aMinguet, PJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10561J.htm

=LDR  04100nam  2200661 i 4500
=001  CTR10562J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10562J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10562J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.A3
=082  04$a668/.3$223
=100  1\$aTomblin, J., $eauthor.
=245  10$aCharacterization of Bondline Thickness Effects in Adhesive Joints / $cJ Tomblin, P Harter, W Seneviratne, C Yang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b27.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aGrowing application of composite materials in airframe structures tends to make significant use of bonded constructions. Despite the large work that has been done on adhesive characterization over previous years, various certification-related issues arise in these applications. The available test methods for determining the in situ properties of an adhesive joint for use in the design must be clarified for thick bondlines, where there is a lack of readily available data. Results from three test methods indicated a decrease in the apparent shear strength as the bondline thickness was increased. The apparent shear strength given by the test methods investigated was found to be highly dependent on the adherend bending stiffness, which directly effects the peel stress distributions in the adhesive layer. In the adhesive strength comparisons as a function of test method, it was found that the thin-adherend tests gave different comparative results than the thick-adherend tests, which were primarily a function of the high peel stresses in the thin-adherend joints. This combined state of stress does not give a true view of the apparent shear stress of the adhesive, but rather an indication of the adhesive behavior under this type of combined loading. It is recommended that thick adherends be used when comparing different adhesive systems for apparent shear strength, and that thin adherends should be used for qualitative tests only.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive.
=650  \0$aBondline thickness.
=650  \0$aJoint.
=650  \0$aLap shear.
=650  \0$aAdhesive bonding.
=650  \0$aAdhesive joints.
=650  \0$aGlued joints.
=653  10$aAdhesive.
=653  20$aJoint.
=653  20$aLap shear.
=653  20$aBondline thickness.
=700  1\$aHarter, P., $eauthor.
=700  1\$aSeneviratne, W., $eauthor.
=700  1\$aYang, C., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10562J.htm

=LDR  04455nam  2200649 i 4500
=001  CTR10563J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10563J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10563J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHuang, H., $eauthor.
=245  10$aStress and Failure Analyses of Adhesive-Bonded Composite Joints Using ASTM D3165 Specimens / $cH Huang, C Yang, JS Tomblin, P Harter.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b33.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn analytical model was developed to determine the stress and strain distributions of single-lap adhesive-bonded composite joints under tension. Both the adherend and the adhesive were assumed linear elastic in the derivations. The Laminated Plate Theory was used in defining the mechanical behavior of the composite adherends, whereas the linear elasticity theory was applied to describe the material response of the adhesive. By doing so, the stresses in the adhesive can vary through the bondline thickness. After the overall system of governing equations was determined by energy method, it was solved by using a symbolic solver-Maple with appropriate boundary conditions. Results from the analytical model were verified with finite element analysis using commercial software ABAQUS. Single-lap composite joint experiments were conducted following ASTM D3165, Strength Properties of Adhesives in Shear by Tension Loading of Single-Lap-Joint Laminated Assemblies. Although all three failure modes of bonded joints, substrate, cohesive, and adhesive failure, were present as the experimental results, the substrate failure mode was the major failure mode observed. Therefore, only substrate failure mode was analyzed using the developed model in the present paper. Four failure criteria, Tsai-Hill failure criterion, von Mises failure criterion, maximum interlaminar tensile stress criterion, and maximum normal stress criterion, were used to correlate the stresses and failure load. Nonlinear regression was conducted to determine the necessary parameters in the failure criteria. Based on the experimental results, thicker bondlines result in weaker joints. The variation of failure load for joints with various bondline thicknesses was consistent with the predicted results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive.
=650  \0$aBonded joints.
=650  \0$aComposites.
=650  \0$aLap joints.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aAdhesive.
=653  20$aBonded joints.
=653  20$aLap joints.
=700  1\$aYang, C., $eauthor.
=700  1\$aTomblin, JS., $eauthor.
=700  1\$aHarter, P., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10563J.htm

=LDR  04885nam  2200649 i 4500
=001  CTR10566J
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=024  7\$a10.1520/CTR10566J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10566J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.A3
=082  04$a668/.3$223
=100  1\$aHart-Smith, LJ., $eauthor.
=245  10$aAdhesive Bonding of Composite Structures-Progress to Date and Some Remaining Challenges / $cLJ Hart-Smith.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (19 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe purpose of this paper is to describe and explain some highlights in the history of adhesive bonding of fibrous composite structures. Successes are described, along with opportunities to do better in future. The importance of making simple details is stressed, in the context of making high-strength composite parts free from wrinkles in the fibers. A case is made that secondary bonding is frequently less expensive than co-curing of complex "single-step" parts, despite the consistent projections that the opposite should be true. Some explanations are presented to explain how this misconception arises, based mainly on the issue that the estimates used for comparison are traditionally based on the costs of making only the first articles, whereas what should have been compared was the cost of making possibly very differently designed lower-cost parts and structures for series production. Some common misunderstandings about variable-thickness adhesives layers are put to rest by explaining how intense load transfer occurs only in small areas, where the adhesive layer is thinnest, with the rest of the bond area inevitably lightly stressed. The problem created by variable thickness bonds is not that of weak bonds. The thicker, and often porous, bond lines usually shed most of the load they were intended to transmit to nearby thin and stiffer areas. Indeed, the loss of load caused by softening can exceed the loss of strength caused by the porosity. No, the problem caused by variable thickness adhesive layers is that it increases the local stresses in the skin whenever the glue layer is thinnest. Traditional problems with release-agent-coated peel plies that prevent adhesion of the glue to the substrate are recounted. This issue is now fairly well known. What is far less understood is the adverse influence of pre-bond moisture that is unable to escape during the bond cycle. This prevents adhesion perhaps even more effectively than a layer of silicone. The importance of bonding only dry parts is explained. This is far easier to do at the time of original manufacture and less easy for in-service repairs and repainting. The paper concludes with a discussion of the important factors to be considered during design and analysis of bonded composite joints.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive bonding.
=650  \0$aJoints.
=650  \0$aProcessing.
=650  \0$aSurface preparation.
=650  \0$aVolatiles.
=650  \0$aAdhesive joints.
=650  \0$aGlued joints.
=650  \0$aJoints.
=653  10$aAdhesive bonding.
=653  20$aJoints.
=653  20$aProcessing.
=653  20$aSurface preparation.
=653  20$aVolatiles.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10566J.htm

=LDR  03611nam  2200673 i 4500
=001  CTR10567J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10567J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10567J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.A3
=082  04$a668/.3$223
=100  1\$aTessler, A., $eauthor.
=245  10$aEfficient Adaptive Mesh Refinement Modeling of Adhesive Joints / $cA Tessler, ML Dambach, DW Oplinger.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (28 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 3 (July 2002)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe smoothing element analysis for stress recovery and error estimation is applied to facilitate adaptive finite element solutions of adhesively bonded structures. The formulation is based on the minimization of a penalized discrete least-squares variational principle leading up to the recovery of C1-continuous stress fields from discrete, Gauss-point finite element stresses. The smoothed distributions are then used as reference solutions in a posteriori error estimators. Adaptive mesh refinements are performed to predict the linearly elastic response of uniformed and tapered double splice adhesively bonded joints. Key aspects pertaining to specific smoothing strategies, adaptive refinement solutions, and detailed stress distributions are discussed. Consistent comparisons are also presented with Oplinger's one-dimensional adhesive lap joint analysis.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdaptive mesh refinement.
=650  \0$aAdhesive joints.
=650  \0$aError estimation.
=650  \0$aPenalty method.
=650  \0$aSmoothing finite element.
=650  \0$aAdhesive bonding.
=650  \0$aAdhesive joints.
=650  \0$aGlued joints.
=653  10$aAdhesive joints.
=653  20$aError estimation.
=653  20$aAdaptive mesh refinement.
=653  20$aSmoothing finite element.
=653  20$aPenalty method.
=700  1\$aDambach, ML., $eauthor.
=700  1\$aOplinger, DW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10567J.htm

=LDR  04434nam  2200661 i 4500
=001  CTR10568J
=003  IN-ChSCO
=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10568J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10568J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aLi, J., $eauthor.
=245  10$aThree-Dimensional Effect in the Prediction of Flange Delamination in Composite Skin-Stringer Pull-off Specimens / $cJ Li.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThree-dimensional finite element modeling was used to analyze the delamination between the stiffener flange and the skin of a typical pull-off specimen representing a section of a stiffened skin panel. The finite element analysis results were used to calculate the total strain energy release rate and its Mode I, Mode II, and Mode III components along the delamination front through the width of the pull-off specimen. Three-dimensional modeling makes it possible to represent ply-by-ply lamina properties in the model. However, the ply-by-ply approach should not be used for highly angle ply laminates because of the strong transverse effect from adjacent plies. A smeared properties approach is more robust for the strain energy release rate analysis of delamination between ±45-degree angle ply laminates. The three-dimensional analysis indicates that delamination failure between the stiffener flange and the skin is dominated by Mode I and Mode II delamination modes. The three-dimensional analysis predicts delamination growth from the interior of the pull-off specimen width, and higher pull-off load is required to grow the delamination close to the free edges. The delamination initiation load along the interior of the pull-off specimen width does not change with the change of the width of the pull-off specimen. However, the wider specimen has stronger free edge effects than the narrower specimen. The lay-up of the skin and the flange can have significant effect on the delamination initiation load. Stiffening the skin and maintaining the compliant flange will increase the delamination initiation load.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDelamination.
=650  \0$aFailure criteria.
=650  \0$aFracture mechanics.
=650  \0$aPull-off test.
=650  \0$aStrain energy release rate.
=650  \0$aThree-dimensional finite element analysis.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDelamination.
=653  20$aFracture mechanics.
=653  20$aFailure criteria.
=653  20$aPull-off test.
=653  20$aThree-dimensional finite element analysis.
=653  20$aStrain energy release rate.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10568J.htm

=LDR  04003nam  2200685 i 4500
=001  CTR10569J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10569J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10569J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aHoyt, DM., $eauthor.
=245  10$aStrength and Fatigue Life Modeling of Bonded Joints in Composite Structure / $cDM Hoyt, SH Ward, PJ Minguet.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (21 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe aerospace industry lacks a validated, practical analysis method for the strength, durability, and damage tolerance evaluation of composite bonded joints. This paper presents the results of a combined strength and fracture analysis approach applied to typical bonded joint configurations found in rotorcraft composite structures. The analysis uses detailed 2-D non-linear finite element models of the local bondline. Strength-of-materials failure criteria are used to predict critical damage initiation loads and locations. A fracture mechanics approach is used to predict damage growth and failure under static and cyclic loads based on test data for static fracture toughness (GIc, GIIc) and crack growth rate (da/dN). Results are presented from the application of the analysis approach to two joint configurations: 1) a skin-stiffener T-joint and; 2) a bonded repair lap joint. The results show that the proposed approach can be used to predict critical failure modes, damage initiation loads and locations, crack and/or delamination stability, static strength, residual strength, and fatigue life. Discussion is also included on how this approach can be applied in damage tolerance evaluations of composite bonded joints.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive.
=650  \0$aBonded joints.
=650  \0$aComposites.
=650  \0$aDamage growth.
=650  \0$aDamage tolerance.
=650  \0$aDelamination.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aAdhesive.
=653  20$aComposites.
=653  20$aBonded joints.
=653  20$aDamage growth.
=653  20$aDamage tolerance.
=653  20$aDelamination.
=700  1\$aWard, SH., $eauthor.
=700  1\$aMinguet, PJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10569J.htm

=LDR  04142nam  2200745 i 4500
=001  CTR10589J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10589J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10589J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRaju, IS., $eauthor.
=245  10$aClassical Laminate Theory Models for Woven Fabric Composites / $cIS Raju, JT Wang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (15 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 4 (October 1994)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aImproved classical laminate theory (CLT) models are developed for plain weave, 5-, and 8-harness satin weave composites. These models retain the simplicity of the fiber undulation model and the bridging model developed by Chou and Ishikawa but do not have the assumptions made to simplify the analysis. Closed-form expressions are derived for the CLT matrices for the woven fabric composites. These expressions are then used to predict moduli, Poisson's ratios, and the coefficients of thermal expansion (CTE) using the properties of the constituents. The results from the present CLT model are compared to the results from the fabric analysis method, three-dimensional (3D) finite element mosaic models, and other CLT models. The present model results for moduli and Poisson's ratio are, in general, in good agreement with those of other models and the very limited experimental results available in the literature. However, the comparisons for the thermal coefficients of expansion are not satisfactory. The models presented in this paper can be used to predict and rank the performance of woven fabric composites starting from the properties of the constituents.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aClassical laminate theory.
=650  \0$aElastic moduli.
=650  \0$aFabric and woven composites.
=650  \0$aPlain weave.
=650  \0$aPoisson's ratios.
=650  \0$aRepeating cells.
=650  \0$aSatin weaves.
=650  \0$aThermal coefficients of expansion.
=650  \0$aUnit cells.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFabric and woven composites.
=653  20$aPlain weave.
=653  20$aSatin weaves.
=653  20$aClassical laminate theory (CLT).
=653  20$aUnit cells.
=653  20$aRepeating cells.
=653  20$aElastic moduli.
=653  20$aPoisson's ratios.
=653  20$aThermal coefficients of expansion.
=700  1\$aWang, JT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10589J.htm

=LDR  04014nam  2200685 i 4500
=001  CTR10590J
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=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10590J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10590J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aMall, S., $eauthor.
=245  10$aLongitudinal Fatigue Response of a Metal Matrix Composite Under Strain Controlled Mode at Elevated Temperature / $cBP Sanders, S Mall.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 4 (October 1994)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe fatigue characteristics of a unidirectional titanium-based metal matrix composite (MMC) (SCS-6/Ti-15-3) were investigated at elevated temperature (427°C). A hybrid strain controlled loading mode was employed for this purpose. This hybrid control mode did not allow the specimen to experience compressive stress in order to prevent any possible buckling effects. To fully understand the fatigue behavior of the MMC under this control mode, fatigue tests, microscopic evaluation, and micromechanical analysis were performed. Based on this combination of activities, the damage and deformation mechanisms were systematically identified. It was found that the fatigue behavior was initially dominated by creep deformation of the matrix. This was accompanied by plastic deformation in those specimens that were subjected to a maximum strain level of 0.55% or higher. Depending on the maximum strain level, the specimen failure was a result of either fiber fracture or matrix cracking. Using the combined approach involving experiments, microscopy, and analysis, the interrelationships among applied strain levels, fatigue life, damage mechanisms, and macroscopic response were established to characterize the longitudinal fatigue characteristics of the tested MMC.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFatigue.
=650  \0$aFiber cracks.
=650  \0$aLongitudinal.
=650  \0$aMatrix cracks.
=650  \0$aMetal matrix composite.
=650  \0$aStrain control.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aMetal matrix composites (MMCs).
=653  20$aLongitudinal.
=653  20$aFatigue.
=653  20$aFiber cracks.
=653  20$aMatrix cracks.
=653  20$aStrain control.
=700  1\$aMall, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10590J.htm

=LDR  05034nam  2200721 i 4500
=001  CTR10591J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10591J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10591J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aTamin, MN., $eauthor.
=245  10$aTime-Dependent Behavior of Continuous-Fiber-Reinforced Metal Matrix Composites : $bModeling and Applications / $cMN Tamin, D Zheng, H Ghonem.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 4 (October 1994)
=504  \\$aIncludes bibliographical references$b37.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA time-dependent approach employing a four-phase concentric cylinder model has been developed to predict the response of metal matrix composites (MMCs) subjected to thermomechanical loadings in which both plastic and creep responses of the composites are considered. The progressive development of plasticity in the matrix phase is determined using the deformation theory of plasticity while the creep deformation of this phase is estimated using the Bailey-Norton equation with an Arrhenius-type expression for the time-dependent creep coefficient. The model is applied to SCS-6/Ti-β21S composite to study the evolution of the stress and strain states in the constituents of the composite during initial cool-down and subsequent thermal cycles. The model is then employed to examine the influence of several critical parameters on the composite internal stress and strain states. These parameters include the thickness of the equivalent composite media, the type of fiber coating material, the thickness of the reaction zone, cooling rate during initial cool-down, and the kinetics of creep process during thermal cyclic loading. Results of these applications indicated that the process-induced thermal stresses in the matrix phase can be relaxed due to creep following initial cool-down from fabrication. This stress reduction is enhanced at a slower cooling rate. Comparison of different fiber coating materials shows that the use of carbon coating induces compressive stress state in the brittle interfacial region. TiB2-coated fibers, however, are found to be less affected by the growing interphase thickness in preserving the compressive radial stress component in the matrix and the interphase zone. Furthermore, it is found that the matrix activation energy for creep, Q, is history-dependent and can be correlated with the level of creep strain accumulated in the matrix phase. In addition, the residual thermal stresses induced in the matrix phase during initial cool-down can be relaxed by the application of subsequent thermal cycles.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aActivation energy.
=650  \0$aCoefficient of thermal expansion (CTE).
=650  \0$aCreep.
=650  \0$aInterfacial region.
=650  \0$aMetal matrix composite.
=650  \0$aPlastic deformation.
=650  \0$aResidual stress.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aResidual stress.
=653  20$aMetal matrix composite (MMC).
=653  20$aInterfacial region.
=653  20$aCoefficient of thermal expansion (CTE).
=653  20$aActivation energy.
=653  20$aCreep.
=653  20$aPlastic deformation.
=700  1\$aZheng, D., $eauthor.
=700  1\$aGhonem, H., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10591J.htm

=LDR  04082nam  2200661 i 4500
=001  CTR10592J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10592J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10592J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aCastelli, MG., $eauthor.
=245  13$aAn Advanced Test Technique to Quantify Thermomechanical Fatigue Damage Accumulation in Composite Materials / $cMG Castelli.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 4 (October 1994)
=504  \\$aIncludes bibliographical references$b25.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA mechanical test technique was developed to assist in quantifying the accumulation of damage in composite materials during thermomechanical fatigue (TMF) cycling. This was accomplished by incorporating explicit mechanical property measurements into an ongoing load-controlled TMF test without disturbing the test specimen or significantly altering the test conditions. The technique allows two fundamental composite properties consisting of the isothermal elastic static moduli and the macroscopic coefficient of thermal expansion (CTE) to be measured and collected as functions of the TMF cycles. The specific implementation was incorporated into the commonly employed idealized in-phase and out-of-phase TMF cycles. However, the techniques discussed could be easily implemented into any form of loadcontrolled TMF mission cycle. By quantifying the degradations of these properties, tremendous insights are gained concerning the progression of macroscopic composite damage and often times the progression of damage within a given constituent. This information should also be useful for the characterization and is essential for the verification of analytical damage modeling methodologies. Several examples using this test technique are given for three titanium metal matrix composite (MMC) laminates.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCoefficient of thermal expansion (CTE).
=650  \0$aComposites.
=650  \0$aDamage progression.
=650  \0$aStiffness.
=650  \0$aTest techniques.
=650  \0$aThermomechanical fatigue.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aThermomechanical fatigue (TMF).
=653  20$aComposites.
=653  20$aDamage progression.
=653  20$aTest techniques.
=653  20$aStiffness.
=653  20$aCoefficient of thermal expansion (CTE).
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10592J.htm

=LDR  03767nam  2200661 i 4500
=001  CTR10593J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10593J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10593J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aCui, W., $eauthor.
=245  10$aEffect of Through Thickness Tensile and Compressive Stresses on Delamination Propagation Fracture Energy / $cW Cui, MR Wisnom, MI Jones.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 4 (October 1994)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aStrain energy release rate criteria are often used for predicting delamination. However, the fracture energy for delamination propagation is not a material constant, but varies depending on the through thickness normal stress. For tensile normal stresses this problem is usually overcome by using a mixed mode fracture criterion. However, the mixed mode approach fails to take into account compressive through thickness normal stresses. These can greatly increase the delamination stress and therefore cannot be simply ignored. A new approach is proposed in which it is assumed that the fracture energy for delamination propagation is a linear function of the average through thickness normal stress. Comparison with experimental results for unidirectional specimens with discontinuous plies shows excellent correlation, and accounts for a number of experimental observations that cannot be explained using the standard fracture mechanics approach.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDelamination.
=650  \0$aFracture energy.
=650  \0$aMixed mode fracture.
=650  \0$aStrain energy release rate.
=650  \0$aThrough thickness stresses.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFracture energy.
=653  20$aStrain energy release rate.
=653  20$aDelamination.
=653  20$aMixed mode fracture.
=653  20$aThrough thickness stresses.
=700  1\$aWisnom, MR., $eauthor.
=700  1\$aJones, MI., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10593J.htm

=LDR  03399nam  2200649 i 4500
=001  CTR10594J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10594J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10594J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aWang, JZ., $eauthor.
=245  12$aA Biaxial Tension-Compression Test Method for Composite Laminates / $cJZ Wang, DF Socie.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 4 (October 1994)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDevelopment of a test system and associated experimental procedure for evaluating the strength of composite laminates under an in-plane biaxial tension-compression (BTC) stress state is presented. A description of the BTC test system and specimen is given. Flexible end reinforcements which do not transfer transverse external loads were used to eliminate stress concentrations caused by tensile grips and prevented the edges of the laminates from being crushed in compression. A relatively homogeneous statically determinant biaxial tension-compression stress field can be achieved in the gage section and the effects of a range of biaxial tension or compression stresses on the shear failure behavior can be easily studied.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBiaxial testing.
=650  \0$aComposite laminates.
=650  \0$aFailure mechanisms.
=650  \0$aFailure strength.
=650  \0$aWoven laminates.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite laminates.
=653  20$aBiaxial testing.
=653  20$aFailure strength.
=653  20$aFailure mechanisms.
=653  20$aWoven laminates.
=700  1\$aSocie, DF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10594J.htm

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=001  CTR10595J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19949999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10595J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10595J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aYuen, JL., $eauthor.
=245  10$aElevated Temperature Fatigue Behavior of Tungsten Fiber Reinforced Superalloy Composites / $cJL Yuen, DW Petrasek.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1994.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 16, Issue 4 (October 1994)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe low-and high-cycle fatigue behavior of three different fiber-reinforced superalloy (FRS) composite materials were evaluated. Each composite material contained 40 vol% unidirectionally aligned continuous length tungsten-1.5 wt% ThO2 fibers. The metal matrices were Waspaloy, Type 316L stainless steel, and Incology 907. Fatigue tests were conducted at 871°C in a helium atmosphere under load control with a load ratio (minimum stress/maximum stress) of 0.2. The composites were found to have excellent elevated temperature fatigue strength. The fibers played a major role in controlling the fatigue strength of the composites. Fatigue crack fronts were found to be retarded by the fibers. The cracks tended to branch at the fiber/matrix interface and grew by a sliding mode along the interface. Matrix surface cracks induced by thermal shock damage had little influence on the fatigue strength of the FRS composites.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1994. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aElevated temperatures.
=650  \0$aFatigue.
=650  \0$aFractography.
=650  \0$aInert gas.
=650  \0$aMetal matrix.
=650  \0$aSuperalloys.
=650  \0$aThermal shock.
=650  \0$aTungsten fiber.
=650  \0$aWaspaloy.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aComposites.
=653  20$aTungsten fiber.
=653  20$aMetal matrix.
=653  20$aSuperalloys.
=653  20$aType 316 stainless steel.
=653  20$aIncology 907.
=653  20$aWaspaloy.
=653  20$aFatigue.
=653  20$aElevated temperatures.
=653  20$aFractography.
=653  20$aInert gas.
=653  20$aThermal shock.
=700  1\$aPetrasek, DW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10595J.htm

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=001  CTR10608J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10608J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10608J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aCalcaterra, JR., $eauthor.
=245  10$aResidual Strength Degradation of Cross-Ply Titanium Matrix Composite Due to Elevated Temperature / $cJR Calcaterra, S Mall, A Ruiz.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 1 (January 1999)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis study investigates the residual strength degradation of cross-ply, SCS-6/Ti-15-3 titanium matrix composite (TMC) due to elevated temperature fatigue. To accomplish this, several specimens were cycled at 427°C to certain fractions of their expected fatigue lives, then monotonically loaded to failure. Fatigue tests were conducted in both load-control mode with a load ratio (Rσ) of 0.05 and strain-control mode with a strain ratio (Rε) of − 1. Maximum stresses in the load-controlled tests were 300 and 450 MPa with frequencies of 5 and 10 Hz, respectively. The strain amplitudes ranged from 0.25 to 0.4% in the strain-controlled tests. Rather than being conducted at a constant frequency, these tests were performed at a strain rate of 0.1% per s. Various mechanical responses during cycling are discussed and compared for the load-controlled and strain-controlled tests. After failure, specimens were sectioned and studied using both optical and scanning electron microscopy. Residual strength data were then correlated to the amount and type of each damage mechanism. It was found that the residual strength degradation in cross-ply laminate, when exposed to different fatigue conditions, correlates together with the fraction of the cyclic life left in the composite.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aElevated temperature.
=650  \0$aFatigue.
=650  \0$aMetal matrix composite.
=650  \0$aSilicon carbide.
=650  \0$aTitanium.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aTitanium.
=653  20$aComposite.
=653  20$aMetal matrix composite.
=653  20$aElevated temperature.
=653  20$aFatigue.
=653  20$aSilicon carbide.
=700  1\$aMall, S., $eauthor.
=700  1\$aRuiz, A., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10608J.htm

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=001  CTR10609J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10609J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10609J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTG300
=082  04$a624/.25$223
=100  1\$aKhong, PW., $eauthor.
=245  10$aOptimal Design of Laminates for Maximum Buckling Resistance and Minimum Weight / $cPW Khong.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 1 (January 1999)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this paper, a multi-objective optimal design for uniaxially loaded laminated composite panels is presented. Three design variables are adopted, namely number of layers, ply-thickness, and ply orientation angle. The two design objectives are to maximize buckling resistance and to minimize weight of the composite laminates. These two design objectives are assigned with different design level requirements, owing to different relative importance in practice. The fuzzy-optimization approach is engaged in such a case. Hence, a set of compromise solutions for the fuzzy-controlled multi-objective optimization can be obtained. The designer can thus select the preferred design level and obtain the optimal solution. In the complete design scheme, the composite laminates are analyzed by the refined finite strip analysis. This approach can deal with the instability of slender composite laminates effectively.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFinite strip analysis.
=650  \0$aFuzzy multi-optimization.
=650  \0$aLaminates.
=650  \0$aFinite strip method.
=650  \0$aStructural analysis (Engineering)
=653  10$aLaminates.
=653  20$aFuzzy multi-optimization.
=653  20$aFinite strip analysis.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10609J.htm

=LDR  03326nam  2200637 i 4500
=001  CTR10610J
=003  IN-ChSCO
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10610J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10610J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aYan, Y., $eauthor.
=245  10$aComparison of Static Properties of 2-D and 3-D Woven Fabric Reinforced Composites / $cY Yan, YQ Ding.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 1 (January 1999)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper investigates the relationship between fabric structure and composite properties for 2-D and 3-D carbon fiber reinforced composites that contain the same fiber volume fraction. The investigation involved determining the tensile strength and modulus, flexural, and interlaminar shear strengths of each specimen type. The 2-D composite shows better in-plane tensile properties than the 3-D composite due to the lower yarn crimp and consequently higher length of yarn orientated in the stress direction. Through-the-thickness reinforcement in the 3-D fabric was found to increase the apparent short beam shear and flexure strengths due to suppression of delamination.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFlexure strength.
=650  \0$aShort beam shear strength.
=650  \0$aTensile strength.
=650  \0$aWoven composites.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aWoven composites.
=653  20$a2-D and 3-D woven structures.
=653  20$aTensile strength.
=653  20$aFlexure strength.
=653  20$aShort beam shear strength.
=700  1\$aDing, YQ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10610J.htm

=LDR  03838nam  2200709 i 4500
=001  CTR10611J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10611J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10611J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aJuntti, M., $eauthor.
=245  10$aAssessment of Evaluation Methods for the Mixed-Mode Bending Test / $cM Juntti, LE Asp, R Olsson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 1 (January 1999)
=504  \\$aIncludes bibliographical references$b34.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe evaluation procedure for the mixed mode bend (MMB) delamination test is assessed with focus on analytically equivalent evaluation models, expressed in load-displacement or load-only parameters. In particular, the assessment concerns the sensitivity of the interlaminar toughness to the test rig forces as well as material and geometrical properties of the specimen. For a typical example, neglect of test rig forces causes a 10% relative error in the calculated mixed mode ratio when using methods based on load only. When all additional forces were considered, both evaluation methods produced almost identical results. However, evaluation based on load only is sensitive to variations in specimen flexural modulus and dimensions and had a larger scatter. The application of crack length corrections for calculating the Mode I component is discussed in detail. The findings of the study are summarized in recommendations for the MMB test procedure and its subsequent evaluation.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBeam theory.
=650  \0$aComposite materials.
=650  \0$aDelamination tests.
=650  \0$aFracture mechanics.
=650  \0$aMixed-mode bend test.
=650  \0$aStrain energy release rate.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aMixed-mode bend test.
=653  20$aStrain energy release rate.
=653  20$aMode I.
=653  20$aMode II.
=653  20$aDelamination tests.
=653  20$aFracture mechanics.
=653  20$aBeam theory>.
=700  1\$aAsp, LE., $eauthor.
=700  1\$aOlsson, R., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10611J.htm

=LDR  03532nam  2200661 i 4500
=001  CTR10612J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10612J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10612J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aBowles, KJ., $eauthor.
=245  10$aDurability of Graphite-Fiber-Reinforced PMR-15 Composites Aged at Elevated Temperatures / $cKJ Bowles.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 3 (July 1999)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aEarlier work that reported relationships between compression properties and elevated-temperature aging duration and weight losses also pointed out the apparent influence of surface layer formation and growth on the retention of compression properties during extended aging times. Since that time, further studies have focused on evaluating the growth of the surface layer. The composition and features of this layer were found to change as the aging temperature changed. Microcracks and small voids initiated and advanced inward at all temperatures. Visible oxidation at the surface occurred only at temperatures above 260°C. Relationships between layer thickness, aging time, and temperature were evaluated and empirically formulated. Then, the compression properties were graphically related to the surface layer thickness with excellent correlation.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon fiber.
=650  \0$aComposites.
=650  \0$aCompression properties.
=650  \0$aDurability.
=650  \0$aPolymer matrix.
=650  \0$aThermal aging.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aPolymer matrix.
=653  20$aCarbon fiber.
=653  20$aDurability.
=653  20$aCompression properties.
=653  20$aThermal aging.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10612J.htm

=LDR  03681nam  2200625 i 4500
=001  CTR10613J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10613J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10613J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNayeb-Hashemi, H., $eauthor.
=245  10$aThermal Residual Stress Analyses of Nextel 440/Aluminum Composite / $cH Nayeb-Hashemi, Y Yang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 3 (July 1999)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFinite element analyses were performed to evaluate the residual stresses developed during the fabrication process of the Nextel 440/A1-6061 composite. The purpose of the analyses was to find the effect of fiber orientation and fiber spacing on processing-induced thermal residual stresses in the metal matrix composite with noncircular fibers' cross section. It was found that high compressive stresses developed between two fibers that increased as the two fibers approached each other. However, significant tensile stresses developed between fibers once the two fibers touched each other. The transition from compression to tension is explained by considering the force balance between contacting fibers. The normal stress on the fiber/matrix interface was higher when the major axis of two noncircular fibers' cross section was oriented at 45° to each other, than it was when the major axis was oriented at 0° to each other. The normal residual stress at the fiber/matrix interface for noncircular fiber geometry was higher compared to what would have developed using round fibers.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aFiber/matrix interface.
=650  \0$aResidual stress.
=650  \0$aStresses.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aStresses.
=653  20$aResidual stress.
=653  20$aFiber/matrix interface.
=700  1\$aYang, Y., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10613J.htm

=LDR  03754nam  2200625 i 4500
=001  CTR10614J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10614J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10614J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC457
=082  04$a621.36/2$223
=100  1\$aBrady, RP., $eauthor.
=245  10$aThermal Image Analysis for the In-Situ NDE of Composites / $cRP Brady, MR Kulkarni, TCP Chu, S Russell.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 3 (July 1999)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThermal image analysis is an emerging nondestructive evaluation (NDE) technique that shows promise as a potential on-line monitoring and inspection method for composites. The method is rapid, user-friendly, and can determine two-dimensional material property distributions as well as quantitatively characterize delaminations. In this paper, the theoretical background of the method and fundamental apparatus are described. Results of the analysis applied to defect-free and delaminated carbon-carbon composite plates are discussed. Two-dimensional distributions of thermal diffusivity were obtained and verified with values obtained by the ASTM standard laser flash diffusivity method. Global specific heat and thermal conductivities were also found and compared to baseline values. In all cases the thermal image analysis results were found to provide reasonable engineering accuracy. Additionally, delaminated plates were tested in order to quantitatively characterize defect location and size. The thermal image analysis results for the delaminated plates were comparable, if not more precise, than observations using ultrasonic C-scan.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aNondestructive evaluation.
=650  \0$aThermoanalysis.
=650  \0$aThermography.
=650  \0$aInfrared radiation.
=650  \7$aTECHNOLOGY & ENGINEERING $xOptics.
=653  10$aNondestructive evaluation.
=653  20$aThermography.
=653  20$aThermoanalysis.
=700  1\$aKulkarni, MR., $eauthor.
=700  1\$aChu, TCP, $eauthor.
=700  1\$aRussell, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10614J.htm

=LDR  04003nam  2200781 i 4500
=001  CTR10615J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10615J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10615J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aLawson, LR., $eauthor.
=245  10$aFatigue Crack Coalescence in Discontinuously Reinforced Metal Matrix Composites : $bImplications for Reliability Prediction / $cLR Lawson, EY Chen.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 3 (July 1999)
=504  \\$aIncludes bibliographical references$b26.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper examines aspects of the distribution of the longest possible microcracks in specimens of a fatigued aluminum-matrix silicon carbide whisker composite and the probability of coalescence in general. The length of the longest microcracks in this material is determined largely by coalescence and making reasonable assumptions is bounded and an upper bound can be calculated. This upper bound is used to fit sample data to an asymptotic extreme value distribution from which reliabilities based on an arbitrarily chosen critical length are calculated. It is shown that for reliabilities corresponding to failure probabilities less than even 10−10 the mere presence of an upper bound on microcrack length can determine the extreme value distribution independent of the actual value of that bound provided that the experimental data supporting the extreme value distribution are entirely characteristic of actual service and that a loading criterion is met.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aCrack coalescence.
=650  \0$aDimensional analysis.
=650  \0$aExtreme value distribution.
=650  \0$aFatigue.
=650  \0$aGumbel distribution.
=650  \0$aMetal matrix.
=650  \0$aMicrocracks.
=650  \0$aReliability.
=650  \0$aStochastic process.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aComposite.
=653  20$aReliability.
=653  20$aCrack coalescence.
=653  20$aExtreme value distribution.
=653  20$aGumbel distribution.
=653  20$aMetal matrix.
=653  20$aDimensional analysis.
=653  20$aStochastic process.
=653  20$aFatigue.
=653  20$aMicrocracks.
=700  1\$aChen, EY., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10615J.htm

=LDR  03801nam  2200685 i 4500
=001  CTR10616J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10616J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10616J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNaik, NK., $eauthor.
=245  10$aBehavior of 3-D Orthogonally Woven Composites Under Tensile Loading / $cNK Naik, BJ Thuruthimattam.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 3 (July 1999)
=504  \\$aIncludes bibliographical references$b29.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA three-dimensional woven fabric composite strength model is presented for predicting the failure behavior of three-dimensional orthogonally woven composites under on-axis, uniaxial, static tensile loading. The representative unit cell is discretized into sections and elements. The method predicts the stress levels at which secondary failures take place at element level. The effect of secondary failure is considered for further analysis, and the ultimate tensile-failure strength and failure strain are predicted. It is observed that for the same fiber volume fractions, 3-D orthogonally woven composites show a significant increase in through-the-thickness properties without a comparable reduction in in-plane properties. It is found that the assumed cross-sectional geometry of the strand with the same overall fiber volume fraction does not make a significant difference to the elastic and strength properties, and hence a square cross-section can be considered.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aElastic properties.
=650  \0$aFailure strength.
=650  \0$aOrthogonally woven.
=650  \0$aPrediction.
=650  \0$aThree-dimensional composite.
=650  \0$aVolume averaging.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aThree-dimensional composite.
=653  20$aOrthogonally woven.
=653  20$a3-D woven fabric-composite strength model.
=653  20$aVolume averaging.
=653  20$aElastic properties.
=653  20$aFailure strength.
=653  20$aPrediction.
=700  1\$aThuruthimattam, BJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10616J.htm

=LDR  04176nam  2200649 i 4500
=001  CTR10617J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10617J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10617J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a624.1/8$223
=100  1\$aRosenberger, AH., $eauthor.
=245  10$aPreliminary Mechanical Property Assessment of an Ultra SCS®/Ti-22A1-23Nb Composite / $cAH Rosenberger, PR Smith, SM Russ.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 3 (July 1999)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe mechanical performance of an orthorhombic-based titanium aluminide matrix composite (OTMC) reinforced with Ultra SCS® silicon carbide continuous monofilament (i.e., Ultra SCS®/Ti-22Al-23Nb) was investigated. Tensile properties, creep resistance, isothermal fatigue, and thermomechanical fatigue were examined over the temperature range from 20 to 760°C, with the bulk of the testing conducted at the upper end of this range to more fully characterize the high-temperature performance of this new composite system. A comparison was made with two similar OTMCs consisting of SCS-6 and Trimarc 1® silicon carbide fiber reinforcement of a Ti-22Al-23Nb matrix. In general, the longitudinal properties benefited significantly as a result of the higher-strength Ultra SCS® fiber. Both the cyclic behavior, isothermal fatigue, and in-phase thermomechanical fatigue, as well as static properties, tension, and creep were improved. However, matrix-dominated performance, including out-of-phase thermomechanical fatigue and transverse properties, was similar or exhibited a slight debit in the Ultra SCS®/Ti-22Al-23 composite. The demonstrated improvement in longitudinal properties makes the Ultra SCS® composite system an excellent choice for rotating components in advanced gas turbine engine applications. However, improvements in transverse properties may still be required for those applications subjected to appreciable off-axis loads.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aMechanical performance.
=650  \0$aMetal matrix composite.
=650  \0$aOrthorhombic titanium aluminide.
=650  \0$aSilicon carbide fibers.
=650  \0$aMechanical.
=650  \0$aMatrix composite.
=653  10$aMetal matrix composite.
=653  20$aSilicon carbide fibers.
=653  20$aMechanical performance.
=653  20$aOrthorhombic titanium aluminide.
=653  20$aUltra SCS®.
=700  1\$aSmith, PR., $eauthor.
=700  1\$aRuss, SM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10617J.htm

=LDR  04254nam  2200757 i 4500
=001  CTR10618J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10618J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10618J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSeferis, JC., $eauthor.
=245  10$aAging Analyses of Polymer Composites Through Time-Temperature Equivalence / $cJC Seferis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 3 (July 1999)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA fundamental problem of advanced airplane composite systems is the lack of understanding of the aging process and how it affects the material properties associated with degradation. The concept of Equivalent Property Time (EPT) was established and can be used to understand degradation of polymers and composites in a uniform manner, both for isothermal and dynamic elevated temperature exposures. In this work, bismaleimide neat resin and composite degradation was analyzed with isothermal and dynamic thermogravimetric analysis adapting a descriptive time-temperature concept originally developed for the curing of thermosets. The concept, defined as EPT, described the experimental data accurately for the experimental conditions tested. Thus, this methodology was demonstrated to be a useful tool in designing aging experiments and assessing the lifetime of composite systems. An extension of this concept was developed to include Equivalent Cycle Time (ECT), which involves the effects of cycling-heating, cooling, and holding, which can be used to understand degradation aging phenomena from repeated exposure. Collectively, this work focused on providing an understanding of cycling phenomena for polymers and composites as they relate to environmental influences and their accelerated aging behavior.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAccelerated aging.
=650  \0$aAging.
=650  \0$aComposites.
=650  \0$aCycling.
=650  \0$aDegradation.
=650  \0$aEnvironmental influence.
=650  \0$aEquivalent cycle time (ECT).
=650  \0$aEquivalent property time (EPT).
=650  \0$aPolymer.
=650  \0$aThermosets.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aPolymer.
=653  20$aComposites.
=653  20$aDegradation.
=653  20$aAccelerated aging.
=653  20$aThermosets.
=653  20$aEquivalent property time (EPT).
=653  20$aAging.
=653  20$aEquivalent cycle time (ECT).
=653  20$aCycling.
=653  20$aEnvironmental influence.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10618J.htm

=LDR  03224nam  2200649 i 4500
=001  CTR10619J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10619J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10619J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aOkoli, OI., $eauthor.
=245  10$aHigh Strain Rate Characterization of a Glass/Epoxy Composite / $cOI Okoli, GF Smith.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 1 (October 2006)
=504  \\$aIncludes bibliographical references$b27.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aHigh strain rate characterization of polymer composite materials has been limited due to difficulties in the measuring equipment. In particular, jigs and fixtures can be subject to inertial disturbances present at speeds up to and above 2 m/s. These disturbances are due to the phenomena of mechanical resonance and control problems that the test equipment acquires at high speeds. The amplitudes of the resulting oscillations increase with test speed and change the test sample response, making results difficult to analyze. These inertial problems may be avoided if the extrapolation of low to high strain data is applicable.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aHigh speed.
=650  \0$aInertia.
=650  \0$aStrain rate.
=650  \0$aTesting.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aInertia.
=653  20$aHigh speed.
=653  20$aStrain rate.
=653  20$aTesting.
=653  20$aComposite.
=700  1\$aSmith, GF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10619J.htm

=LDR  04065nam  2200673 i 4500
=001  CTR10620J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10620J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10620J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aPeters, PWM, $eauthor.
=245  10$aStress Transfer in the Fiber/Matrix Interface of Titanium Matrix Composites Due to Thermal Mismatch and Reaction Layer Development / $cPWM Peters, J Hemptenmacher, A Werner.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 1 (October 2006)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIt is well known that the difference in the coefficient of thermal expansion of the components of titanium matrix composites with the SCS-6 SiC-fiber gives rise to substantial residual stresses. Due to the fact that the fiber/matrix bond strength is low (as long as there is still a substantial thick carbon protection layer) fiber/matrix stress transfer is realized partly through interfacial friction enabled by the residual radial compressive stress at the fiber/matrix interface. Fiber matrix reactions usually lead to a volume change. In the present investigation this volume change is investigated analytically as well as experimentally on the SCS-6/IMI834 system. It was determined analytically with the aid of a two-dimensional stress analysis that fiber/matrix reaction leads to a reduction of the residual stresses. Experimental results on composite specimen diameter change indicate an increase of the residual stress caused by an unexpected shrinkage of the matrix. Another source for residual stress is an unequal (inwards and outwards) radial growth of the reaction layer if the diffusion rate of the reacting species through the reaction layer differs from the stoichiometric relation for the reaction.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFrictional shear stress.
=650  \0$aInterface.
=650  \0$aReaction.
=650  \0$aResidual stresses.
=650  \0$aTitanium matrix composites.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aTitanium matrix composites.
=653  20$aInterface.
=653  20$aFrictional shear stress.
=653  20$aResidual stresses.
=653  20$aReaction.
=700  1\$aHemptenmacher, J., $eauthor.
=700  1\$aWerner, A., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10620J.htm

=LDR  03676nam  2200613 i 4500
=001  CTR10621J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10621J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10621J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aDickinson, LC., $eauthor.
=245  10$aFailure Initiation in Translaminar Reinforced Composites / $cLC Dickinson, GL Farley, MK Hinders.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 1 (October 2006)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA translaminar-reinforced (TLR) composite is an otherwise two-dimensional laminate with through-thickness or Z-direction fibrous reinforcement across the lamina. Only small amounts (less than 5% volume) of TLR are necessary to substantially improve compression-after-impact response, increase fracture toughness, and severely restrict the size and growth of delamination. These improvements have been documented repeatedly in the literature, and it is generally accepted that TLR restricts the size and growth of delamination. In this paper we report a detailed investigation of whether TLR delays the initiation of delamination via finite-element analysis and a strength-of-materials approach. The various parameters investigated include TLR material, diameter, spacing, volume fraction, and through-thickness angle. In addition, the unavoidable microstructural features of curved in-plane fibers and resin pockets were examined. Our conclusion is that TLR does not delay damage initiation, even though it has been shown experimentally to restrict damage progression.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDelamination.
=650  \0$aReinforced composites.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aReinforced composites.
=653  20$aDelamination.
=700  1\$aFarley, GL., $eauthor.
=700  1\$aHinders, MK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10621J.htm

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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10622J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10622J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aWright, RJ., $eauthor.
=245  10$aBolt Bearing Behavior of Highly Loaded Polymer Matrix Composite Joints at Elevated Temperatures With and Without Clamp-Up / $cRJ Wright, WS Johnson, S Sacks, H Ahmad.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 1 (October 2000)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aData are presented on time-dependent behavior of bolted joints made from 64-ply IM7 carbon fiber/K3B thermoplastic polyimide quasi-isotropic lay-up tested in pure bolt bearing and in bearing bypass. Composite panels were aged at temperatures of 177 and 204°C for 5 000 and 10 000 (h) to simulate cumulative effects of supersonic flight conditions on a bolted composite joint. Changes in joint-bearing capacity and determination of time-dependent behavior have been covered in this study. Test coupons sized and drilled to correspond to the ratios found in actual joints were loaded over a wide range at both with and without clamp-up forces. Testing at 177°C simulated supersonic cruise temperature. Bearing creep testing revealed time-dependent behavior only in a very narrow loading region, above which bearing failure occurred almost instantaneously and below which no damage occurred. Testing of aged material showed degradation in material aged at 177°C for 5000 h; however, material aged at 177°C for 10 000 h demonstrated a recovery in bearing capacity, while material aged at temperatures of 177 and 204°C for 5000 and 10 000 h showed neither increased nor equivalent performance degradation. Testing with neat resin demonstrated that the matrix material becomes more brittle both with temperature and with aging. It was concluded that this material experiences no significant time-dependent deformation for temperatures at or below 204°C.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAging.
=650  \0$aBolt bearing.
=650  \0$aBypass.
=650  \0$aCreep.
=650  \0$aJoints.
=650  \0$aBolted joints.
=650  \0$aJoints (Engineering)
=650  \0$aBolts and nuts.
=653  10$aBolt bearing.
=653  20$aJoints.
=653  20$aCreep.
=653  20$aAging.
=653  20$aBypass.
=700  1\$aJohnson, WS., $eauthor.
=700  1\$aSacks, S., $eauthor.
=700  1\$aAhmad, H., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10622J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10623J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10623J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aThomas, R., $eauthor.
=245  10$aEffect of High-Frequency Low-Amplitude Impact Loads on Polymeric Composites / $cR Thomas, R Krishnamurthy.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 1 (October 2006)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aComposites are used abundantly in aerospace applications. A major issue facing the aerospace industry is the effect of service exposure on the performance of graphite/epoxy structural components. Detailed studies were performed on the structural integrity of graphite epoxy laminations subjected to high-frequency, low-amplitude impact loads. The material response was evaluated by change in stiffness, residual work, and by permanent set and damping coefficient and other related features. The objective of the study was to evaluate the performance, and thereby assess the suitability of polymeric composites as materials for aerospace models for high-speed wind tunnel testing by simulated trials. The observations indicated that high-frequency, low-load impact improves the stiffness of the graphite-epoxy composite; however, it was associated with a reduction in the damping characteristics. The improvement can be attributed to a change in the modulus of the reinforcement due to strain stiffening.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aGraphite-epoxy composite.
=650  \0$aHigh-frequency impact.
=650  \0$aHysteresis work.
=650  \0$aPermanent set.
=650  \0$aStiffness.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aGraphite-epoxy composite.
=653  20$aHigh-frequency impact.
=653  20$aStiffness.
=653  20$aPermanent set.
=653  20$aHysteresis work.
=700  1\$aKrishnamurthy, R., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10623J.htm

=LDR  03673nam  2200697 i 4500
=001  CTR10624J
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=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10624J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10624J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aRC78.7.T6
=082  04$a616.07 54 05$223
=100  1\$aGonzalez, M., $eauthor.
=245  10$aSome Results from X-Ray Computed Tomography Applied to Metal Matrix Composites / $cM Gonzalez, G Dominguez, C Bathias.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 1 (October 2006)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis study presents computed tomography (CT) results from a medical scanner carried out on metal matrix composite materials obtained by a casting process. In order to test the capabilities of the CT technique to study the flaws in the sample, few precautions have been taken during the manufacturing process, resulting in composite ingots with many flaws (porosity, segregation, etc.). The mold was modified to obtain a concentration of particles at the bottom of the ingot. CT images and scanning electronic microscopy images were taken at the same slice surface and show good agreement in the distribution of particles and porosity. The spatial resolution of the medical scanner (12 pairs of lines/cm) lets us distinguish between, at the mesoscopic scale, heterogeneous distribution of particles and porosity, but not individual flaws.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAluminum matrix.
=650  \0$aCharacterization.
=650  \0$aComputed tomography.
=650  \0$aMedical scanner.
=650  \0$aMetal matrix composites.
=650  \0$aNondestructive.
=650  \0$aTomography.
=650  \0$aTomographic imaging.
=650  \0$aRadiological stratigraphy.
=653  10$aMetal matrix composites.
=653  20$aComputed tomography.
=653  20$aAluminum matrix.
=653  20$aNondestructive.
=653  20$aMedical scanner.
=653  20$aCharacterization.
=700  1\$aDominguez, G., $eauthor.
=700  1\$aBathias, C., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10624J.htm

=LDR  04390nam  2200733 i 4500
=001  CTR10626J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10626J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10626J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aBradford, D., $eauthor.
=245  10$aEvaluation of the Effect of a Custom Fiber Surface Treatment on the Adhesion Level in a Polymer-Based Composite Using the Single Fiber Fragmentation Test / $cD Bradford, K Lease, PMA Sherwood.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b29.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDuring the past several years, a number of investigations have focused on improved fiber surface treatments as well as the development of micromechanical experimental techniques to accurately evaluate the fiber/matrix adhesion level. The aim of this study was to evaluate the effect of a custom fiber surface treatment on the fiber/matrix adhesion level of a carbon fiber reinforced, polymer matrix composite material. Single fiber fragmentation tests were performed on specimens produced using EPON 828 resin and AU-4 fibers, AS-4 fibers, and AU-4 fibers that were treated with a custom fiber surface treatment known to lead to direct chemical reaction with the EPON 828 resin. Qualitative inspection of the birefringent stress patterns produced by the custom treated fiber indicate a high level of fiber/matrix adhesion, greater than the adhesion exhibited by either of the two as received fiber types. In addition, the custom treated fibers produced an average fiber fragment length approximately 23% shorter than the AS-4 specimens, indicating a rather significant increase in adhesion level for the custom treated fibers over the commercially treated fibers. Calculated interfacial shear strength values follow the same trend as was seen during the evaluation of the average fragment length values.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon fibers.
=650  \0$aComposite failure.
=650  \0$aComposite strength.
=650  \0$aFiber/matrix adhesion.
=650  \0$aInterfacial shear strength.
=650  \0$aPolymer matrix composites.
=650  \0$aSingle fiber fragmentation.
=650  \0$aSurface treatment.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFiber/matrix adhesion.
=653  20$aSingle fiber fragmentation.
=653  20$aInterfacial shear strength.
=653  20$aCarbon fibers.
=653  20$aSurface treatment.
=653  20$aPolymer matrix composites.
=653  20$aComposite strength.
=653  20$aComposite failure.
=700  1\$aLease, K., $eauthor.
=700  1\$aSherwood, PMA, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10626J.htm

=LDR  03964nam  2200721 i 4500
=001  CTR10627J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10627J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10627J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aGao, X-L, $eauthor.
=245  12$aA Two Dimensional Rule-of-Mixtures Micromechanics Model for Woven Fabric Composites / $cX-L Gao, S Mall.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA two-dimensional rule-of-mixtures micromechanics model is presented for planar woven fabric-reinforced composites subjected to in-plane biaxial normal loads. The impregnated warp/fill yarns are treated as orthotropic materials and the interyarn matrix as an isotropic material. The undulations of both warp and fill yarns in two orthogonal directions are considered, and the temperature effects are included. A set of iso-strain conditions, together with the symmetry and periodicity requirements, are employed. The resulting formulation of the present model is simple and more explicit than those of several existing analytical models. This model can deal with different weave patterns, undulation shapes and constituent materials and hence may be viewed as a generic approach. Sample calculations are provided for plain weave, 5-harness and 8-harness satin weave woven composites to demonstrate applications of the present model and to compare with other known results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnalytical modeling.
=650  \0$aClassical laminate theory.
=650  \0$aEffective elastic and thermal properties.
=650  \0$aFabric-reinforced woven composites.
=650  \0$aMicromechanics.
=650  \0$aPlain weave.
=650  \0$aRule of mixtures.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFabric-reinforced woven composites.
=653  20$aMicromechanics.
=653  20$aClassical laminate theory.
=653  20$aRule of mixtures.
=653  20$aAnalytical modeling.
=653  20$aPlain weave.
=653  20$a5- and 8-harness satin weaves.
=653  20$aEffective elastic and thermal properties.
=700  1\$aMall, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10627J.htm

=LDR  03590nam  2200613 i 4500
=001  CTR10628J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10628J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10628J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aO'Driscoll, D., $eauthor.
=245  10$aLightning Strike of Perforated Carbon Fiber Epoxy Laminar Flow Panels / $cD O'Driscoll, J Hardwick, T Young, J Ryan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effect of lightning on a perforated carbon fiber composite is examined in this technical note. This perforated material has been considered for use on an aircraft engine nacelle to achieve hybrid laminar flow. The work was carried out under a European Commission program HYLDA (Hybrid Laminar Flow Demonstration on Aircraft). Hybrid laminar flow is a combination of natural laminar flow achieved by aerodynamic profiling and leading edge suction through the perforated surface. The carbon fiber panels were perforated using an Nd-YAG laser. The specimens were subjected to simulated zone 2A and 1C lightning strikes and the results are compared to similar tests on non-perforated and painted specimens. It was found that the visible damage was less on the perforated specimens compared to the other two. This is presumed to be due to the lightning arc attaching to the fiber ends in the holes, and thus being spread over a larger area.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon fiber epoxy composites.
=650  \0$aLightning strike.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aLightning strike.
=653  20$aCarbon fiber epoxy composites.
=653  20$aPerforated laminar flow panels.
=700  1\$aHardwick, J., $eauthor.
=700  1\$aYoung, T., $eauthor.
=700  1\$aRyan, J., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10628J.htm

=LDR  04246nam  2200697 i 4500
=001  CTR10629J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10629J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10629J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aWolfenden, A., $eauthor.
=245  10$aDynamic Elastic Modulus and Vibrational Damping in Nicalon SiCxOy Fiber/Borosilicate Glass Composites : $bEffects of Thermal Cycling / $cA Wolfenden, DL Anthony, KK Chawla, AR Boccaccini.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aMeasurements of dynamic elastic modulus and vibrational damping were made at room temperature for DURAN (a borosilicate glass) and SiCxOy Nicalon™/DURAN (a glass matrix composite). Both sets of materials had been thermal cycled to 500 and 700°C which are below and above the glass transition temperature (Tg = 530°C), respectively. The piezoelectric ultrasonic composite oscillator technique (PUCOT) was used to determine the values of the Young's modulus and damping. Archimedes' method was used to find the density of the specimens, and the impulse excitation technique was used to find the flexural modulus. Microstructural examinations were made on selected specimens. The experimental results showed that thermal cycling of the composites below Tg had no distinguishable effect on the density, dynamic Young's modulus or flexural modulus values; however, an increase in damping of 56% was observed. For thermal cycling above Tg, the density decreased by about 0.5%, the Young's modulus decreased by 8%, the flexural modulus decreased by 15% and the damping increased by 608%. The simultaneous decrease of elastic modulus and density, and increase of damping in the composites with increasing thermal cycling temperature were analyzed in terms of microstructural degradation due to thermal effects on the matrix, fibers and interfaces.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBorosilicate glass.
=650  \0$aDamping.
=650  \0$aElastic modulus.
=650  \0$aGlass matrix composites.
=650  \0$aNicalon fibers.
=650  \0$aThermal cycling.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aElastic modulus.
=653  20$aDamping.
=653  20$aGlass matrix composites.
=653  20$aBorosilicate glass.
=653  20$aNicalon™ fibers.
=653  20$aThermal cycling.
=700  1\$aAnthony, DL., $eauthor.
=700  1\$aChawla, KK., $eauthor.
=700  1\$aBoccaccini, AR., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10629J.htm

=LDR  04322nam  2200697 i 4500
=001  CTR10630J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10630J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10630J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aWood, JD., $eauthor.
=245  10$aAssessment of Residual Composite Properties as Influenced by Thermal Mechanical Aging / $cJD Wood, RB Plunkett, PH Tsang, KNE Verghese, JJ Lesko.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 2 (April 2000)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this study two quasi-isotropic carbon fiber-reinforced polyimide material systems, IM7/K3B and IM7/PETI-5, were thermally aged at 163°C (325°F) for up to 10 000 hours under a static compressive load (controlled at 2000 μɛ). The compressive load was applied using steel fixtures supplied by The Boeing Company. Back-to-back gages on the aging panels monitored compressive strain as well as bending strain. Following aging at 1500, 3000, and 10 000 hours, ambient residual compression properties were assessed using the IITRI compression test method. Unexposed specimens were also tested to obtain baseline properties for comparison. These results showed that 10 000 hours of stressed isothermal aging did not significantly affect the compressive properties of the two composite systems. However, there was one exception. A slight increase in scatter of the residual strength was observed. Statistical evaluation of the results provided guidelines for the development of A-basis and B-basis values and assessing significant property changes following aging. Differential scanning calorimetry (DSC) found the glass transition temperatures for the two material systems to be unaffected by 3000 and 10 000 hours of aging. The combined results of these experiments provide valuable information on the effects of physical and chemical aging on the long-term thermal mechanical behavior of these materials.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite material.
=650  \0$aCompression properties.
=650  \0$aMechanical aging.
=650  \0$aPhysical and chemical aging.
=650  \0$aThermal aging.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aHigh Speed Civil Transport (HSCT).
=653  20$aComposite material.
=653  20$aMechanical aging.
=653  20$aThermal aging.
=653  20$aPhysical and chemical aging.
=653  20$aCompression properties.
=700  1\$aPlunkett, RB., $eauthor.
=700  1\$aTsang, PH., $eauthor.
=700  1\$aVerghese, KNE, $eauthor.
=700  1\$aLesko, JJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10630J.htm

=LDR  03468nam  2200613 i 4500
=001  CTR10631J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10631J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10631J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aYotte, S.., $eauthor.
=245  10$aNumerically Based Compliance Calibration for Steel Frame Assisted Tension Specimen / $cS. Yotte, JM Quenisset.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 2 (April 2006)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aRecently, a new procedure has been proposed for testing the toughness of thin materials. The test procedure consists of glueing a metal frame onto each specimen face and applying load to the metal frame. This procedure is designed to avoid a Brinel effect on the specimen. Since the characterization of the material toughness requires a compliance function, a finite element calculation is performed in order to evaluate the influence of various material parameters. The deviation of the compliance with the Young's moduli of the frame and tested materials, and also with the shear modulus, G, is studied. The resulting relationships are used to obtain a definition of the compliance function which takes into account the notch length and a stiffness representative of the tested materials and the glued frame. Comparison between calculated compliances and experimental data exhibits a good agreement.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompliance.
=650  \0$aComposite.
=650  \0$aToughness testing.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aSFAT specimen.
=653  20$aComposite.
=653  20$aCompliance.
=653  20$aToughness testing.
=700  1\$aQuenisset, JM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10631J.htm

=LDR  03692nam  2200625 i 4500
=001  CTR10632J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10632J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10632J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA645
=082  04$a624.1/7$223
=100  1\$aChen, C-F, $eauthor.
=245  10$aCylindrical Indentation of Orthotropic Laminates on Elastic Foundations / $cC-F Chen.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aProblems of cylindrical indentation of orthotropic laminated beams on an elastic foundation are studied. Exact solution methods are developed to assess the displacement field for both the simply supported and clamped-ended cases. A numerical iteration algorithm is established to detect the contact length and the associated contact stresses for a prescribed contact load. The induced interlaminar shear stresses through the thickness and the amount of indentation are evaluated subsequently. The objective is to investigate the effects of span, indentor size, end support conditions, and foundation stiffness on the local field responses and load-indentation relationships. The results show that the effects of indentor size and foundation stiffness are significant. A sharp indentor or stiff foundation tends to localize the contact phenomenon, regardless of the span and the end support conditions. On the other hand, the effects of both the boundary condition and span may be prominent if a blunt indentor and a relatively soft foundation are employed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCylindrical indentation.
=650  \0$aInterlaminar stresses.
=650  \0$aIteration algorithm.
=650  \0$aNon-Hertzian behavior.
=650  \0$aStrains and stresses.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aCylindrical indentation.
=653  20$aIteration algorithm.
=653  20$aInterlaminar stresses.
=653  20$aNon-Hertzian behavior.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10632J.htm

=LDR  03425nam  2200673 i 4500
=001  CTR10633J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10633J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10633J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aBardis, JD., $eauthor.
=245  12$aA New Compression Test Fixture for Unnotched or Notched Thin Composite Laminates / $cJD Bardis, KT Kedward, JO Bish, TK Tsotsis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new compression fixture suitable for testing relatively thin composite laminates with or without holes or notches is described and evaluated. This UCSB fixture comprises several features of detail that are different from those of the existing fixtures, such as the large, well-established Supplies of Advanced Composite Materials Association (SACMA) fixture. Both a description and a rationale for such features are included together with compressive strength data for notched and unnotched carbon fiber reinforced polymer matrix composite (PMC) laminates obtained using the UCSB fixture.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression strength.
=650  \0$aOpen hole compression.
=650  \0$aPolymer matrix composite laminates.
=650  \0$aSpecimen geometry.
=650  \0$aTest fixture.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aPolymer matrix composite laminates.
=653  20$aOpen hole compression.
=653  20$aCompression strength.
=653  20$aTest fixture.
=653  20$aSpecimen geometry.
=700  1\$aKedward, KT., $eauthor.
=700  1\$aBish, JO., $eauthor.
=700  1\$aTsotsis, TK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10633J.htm

=LDR  03580nam  2200625 i 4500
=001  CTR10634J
=003  IN-ChSCO
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=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10634J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10634J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aMcManus, HL., $eauthor.
=245  10$aMechanism-Based Modeling of Long-Term Degradation / $cHL McManus, BJ Foch, RA Cunningham.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b22.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe use of composites in high-temperature, long-lifetime applications requires a basic understanding of composite degradation mechanisms, advances in analytical capabilities, and accurate accelerated and scaled tests. To advance all of these goals, models are proposed based on a variety of fundamental material mechanisms. Thermal, oxygen, and moisture diffusion, chemical reactions, composite micromechanics, modified laminated plate theory, and fracture mechanics based damage models are used. All models are designed to stay as simple and fundamental as possible. All are coupled, so that interactions between various effects are modeled implicitly. Ongoing efforts at MIT are reviewed here, with some reference to other work, but no attempt is made to do a comprehensive review. Mechanism-based models are yielding an understanding of the mechanisms behind observed degradation phenomena, helping to design accelerated tests, and are the first steps toward a predictive capability.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDegradation.
=650  \0$aLong-term degradation.
=650  \0$aModeling.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDegradation.
=653  20$aLong-term degradation.
=653  20$aModeling.
=700  1\$aFoch, BJ., $eauthor.
=700  1\$aCunningham, RA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10634J.htm

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=001  CTR10635J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10635J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10635J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aLavoie, JA., $eauthor.
=245  10$aScaling of First-Ply Failure and Strength in [+ϑn/−ϑ/−ϑn/90/902n]s Laminates : $bExperiments and Predictions / $cJA Lavoie, J Morton.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn experimental investigation of first-ply failure and strength was conducted on ply-level scaled carbon/epoxy composite laminates having a stacking sequence of [+ϑn/−ϑ/−ϑn/90/902n]s where the constraint ply angle, ϑ, was varied from 0 to 75°, and where the constraint ply angle, ϑ, was varied from 0 to 75°, and n varied from 1 to 4. First-ply failure was shown to depend on the level of constraint and the scale factor, n. The strain energy release rate for matrix microcracking was computed from first-ply failure data of the [02/902]s laminate. Then, first-ply failure for all other layups was predicted using a numerical model that accounted for both constraint and size. Tensile strength was predicted using a strain energy release rate model for delamination of surface angle plies. A delamination energy value for each ply angle was calculated from the thinnest (n = 1) laminates to predict strength of the other sizes.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite laminate.
=650  \0$aDelamination.
=650  \0$aFirst-ply failure.
=650  \0$aMatrix cracking.
=650  \0$aStrength scaling.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMatrix cracking.
=653  20$aFirst-ply failure.
=653  20$aDelamination.
=653  20$aStrength scaling.
=653  20$aComposite laminate.
=700  1\$aMorton, J., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10635J.htm

=LDR  04581nam  2200817 i 4500
=001  CTR10636J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10636J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10636J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aMelin, LG., $eauthor.
=245  10$aEvaluation of Four Composite Shear Test Methods by Digital Speckle Strain Mapping and Fractographic Analysis / $cLG Melin, JM Neumeister, KB Pettersson, H Johansson, LE Asp.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 22, Issue 3 (July 2006)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFour methods to determine composite interlaminar shear strength (ILSS) are evaluated. In particular, the recently devised inclined double-notch shear test (IDNS) is compared with three existing and more established methods: the Iosipescu test, the short three-point bending test (S3PB) and the double-notch compression test (DNC). The uniformity of strain field in the test region in a real test situation-which is the crucial test method quality parameter-is investigated by strain mapping using digital speckle photography. The measured strain fields are compared with FE-calculated strains representing ideal conditions and both known advantages and drawbacks of the different methods are confirmed. The IDNS test produces the most uniform strain fields and also consistently high ILSS values. A fractographic analysis indicates shear separation over a major part of the fracture surfaces of all specimen types; typical shear cusps were found over about 80% of the IDNS fracture surface and in about 50% to 70% in the other specimens. For the Iosipescu tests, failure initiation could be ascribed to initiation in tension at defects. Experimentally determined stress-strain responses in shear exhibit a distinct variation among the different methods. For the best methods, a notable material softening was observed prior to failure. Observed formation of shear cusps is believed to be the primary cause for this softening of the composite material studied here.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComparison.
=650  \0$aComposite.
=650  \0$aDouble notch.
=650  \0$aEvaluation.
=650  \0$aExperiment.
=650  \0$aFractography.
=650  \0$aInclined.
=650  \0$aShear test.
=650  \0$aShort beam.
=650  \0$aStrain mapping.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aComposite.
=653  20$aShear test.
=653  20$aIosipescu.
=653  20$aShort beam.
=653  20$aDouble notch.
=653  20$aInclined.
=653  20$aExperiment.
=653  20$aComparison.
=653  20$aEvaluation.
=653  20$aFractography.
=653  20$aStrain mapping.
=700  1\$aNeumeister, JM., $eauthor.
=700  1\$aPettersson, KB., $eauthor.
=700  1\$aJohansson, H., $eauthor.
=700  1\$aAsp, LE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10636J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10648J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10648J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aGV54.M32
=082  04$a306/.48$223
=100  1\$aReifsnider, KL., $eauthor.
=245  10$aIn the Spirit of the Times, A Comment / $cKL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1978.
=300  \\$a1 online resource (1 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 1 (October 1978)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1978. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAmusements.
=650  \0$aAmusements $xSocial aspects.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10648J.htm

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=006  m\\\\\\\\\\\\\\\\\
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=008  161219c19789999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10650J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10650J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTS283
=082  04$a681/.760410288$223
=100  1\$aD'Andrea, G., $eauthor.
=245  10$aFilament Wound Pressure Vessels / $cG D'Andrea.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1978.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 1 (October 1978)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFilament winding is a well developed technology for simple composite pressure vessels, such as rocket motor cases or tanks. However, the winding of vessels that contain reversed curvatures or variable diameters requires an advanced technology. At the Benet Weapons Laboratory (BWL), we have designed, fabricated, and tested several unusual filament wound pressure vessels. The vessel geometries vary (1) from a closed-end to an open-end configuration, (2) from a nonlined vessel to a lined vessel with a composite jacket, (3) from a similar to a dissimilar end dome or closure, and (4) from an axisymmetric to a nonaxisymmetric configuration.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1978. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aPressure Vessels.
=650  \0$aFilament winding.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10650J.htm

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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aGY, Ohgi., $eauthor.
=245  10$aThermal Expansion Compensating Linkage-A Metal/Composite Joint Design / $cOhgi GY.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1978.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 1 (October 1978)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe graphite/epoxy 737 horizontal stabilizer shown in Fig. 1 features a metal elevator side-load reacting hinge at the inboard end and aerodynamic balance panels at the mid-span. Under the temperature extremes of airplane operation, the metal elevator expands and contracts about the side load reacting hinge. Because of the difference in thermal expansion between the aluminum elevator and the graphite/epoxy stabilizer, a large thermal displacement builds up along the span of the elevator. The magnitude of the displacement is such that the balance panel seals would become ineffective and friction would be excessive. Also, the clevis of the outer hinges would have to be widened considerably to accommodate the hinge displacements. Widening the hinges could result in excessive hinge-pin bending stresses.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1978. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10651J.htm

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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aCouch, WP., $eauthor.
=245  10$aEvaluating a Hybrid Composite/Steel Tapered Box Beam for Advanced Ship Structures / $cWP Couch, AB Macander, L Greszczuk.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1978.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 1 (October 1978)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFiber composite materials have been widely accepted for applications as secondary structural elements. Recently however, they are also being considered seriously for many primary load-bearing structures. The David W. Taylor Naval Ship Research and Development Center has been conducting a program to evaluate the potential of fiber composites for advanced naval ship structures. As a result of feasibility studies performed by the McDonnell Douglas Astronautics Company and the Grumman Aerospace Corporation, and a review of high payoff areas for structural application of advanced composites, the hydrofoil strut/foil system was selected as the primary structural element with which to assess the current technology status of advanced composites for marine application.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1978. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aMacander, AB., $eauthor.
=700  1\$aGreszczuk, L., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10652J.htm

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=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.P6
=082  04$a668.4/225$223
=100  1\$aMinor, LH., $eauthor.
=245  10$aAramid/Polyester Composite Armor / $cLH Minor.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1978.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 1 (October 1978)
=504  \\$aIncludes bibliographical references$b1.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aLightweight and toughness are key considerations for protective armor. Composite armor of Kevlar 29 aramid fabric and polyester resin was prepared using techniques developed for fiberglass/polyester armor. Commercial preimpregnated fabric was press-molded to prepare the target samples. The samples of the preimpregnated fabric were cured in a Pasadena press for 1 h at 165°C and 690 kPa.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1978. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aPolyester.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10653J.htm

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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTJ1185
=082  04$a671.5/3$223
=100  1\$aMarks, W., $eauthor.
=245  10$aCutting, Machining, and Drilling of Composites / $cW Marks.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1978.
=300  \\$a1 online resource (1 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 1 (October 1978)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe inherent structural efficiency of boron and graphite fibers in epoxy matrices has led to selective application of advanced composites in current aircraft designs and promises even greater use in future advanced technology vehicles. However, these new material forms do not necessarily adapt to the same processing methods used for their predecessor metallic structures. As such, new cost factors must be considered in the fabrication of advanced composites.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1978. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aMachining.
=650  \0$aCutting.
=650  \0$aManufacturing processes.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10654J.htm

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=007  cr\\\\\\\\\\\\
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10655J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10655J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKulkarni, SV., $eauthor.
=245  10$aDeveloping a Tapered Thickness Composite Flywheel Rotor / $cSV Kulkarni.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1978.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 1 (October 1978)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFiber composite flywheels are being seriously evaluated as energy storage devices, to be used in combination with advanced batteries, for automobile power systems. The key attraction for composites in this application is their high strength-to-density ratio that yields high energy storage.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1978. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10655J.htm

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=007  cr\\\\\\\\\\\\
=008  161219c19799999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10660J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10660J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA352
=082  04$a620.1/04$223
=100  1\$aWeisinger, MD., $eauthor.
=245  10$aBoron Aluminum Tube Struts for the NASA Space Shuttle / $cMD Weisinger.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 2 (January 1979)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aBoron/aluminum is specified for tube truss members for the mid-fuselage of the Space Shuttle Orbiter being produced by General Dynamics under contract to Rockwell International. In all, 243 tubes have been installed on each of the first three Orbiters to serve as main frame and rib truss struts, frame stabilizing braces, and nose landing gear drag brace support struts.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDynamics.
=650  \0$aApplied dynamics.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10660J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10661J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10661J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.E6
=082  04$a668/.374$223
=100  1\$aRinde, JA., $eauthor.
=245  12$aA Room Temperature Stable "B" Staging Epoxy Resin System / $cJA Rinde, HA Newey.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 2 (January 1979)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWe have discovered a new curing agent for epoxy resins that has both interesting and useful properties. The compound, 2,5-dimethyl-2,5-hexane diamine (DMHDA) is a sterically hindered, primary aliphatic amine. As a curing agent for DGEBA epoxy resins, it has the following desirable characteristics: (1) at room temperature, it forms a stable "B" stage resin; (2) it is a good wet-filament-winding resin having both a low viscosity (0.5 Pa...s) and a long gel time (21 h for a 30-g mass); and (3) the cured resin properties are good, e.g., the tensile strength is 86 MPa (12,500 psi) and the glass transition temperature is greater than 140°C when cured at 130°C.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy resins.
=650  \7$aTECHNOLOGY & ENGINEERING / Chemical & Biochemical.
=700  1\$aNewey, HA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10661J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10662J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10662J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.E6
=082  04$a668/.374$223
=100  1\$aEdelman, R., $eauthor.
=245  12$aA New DAP-Polyester Resin for Carbon Fibers / $cR Edelman, PE McMahon.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 2 (January 1979)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aEpoxy resins are the primary matrix materials used in carbon fiber composites, and prepreg systems made with these epoxies offer good handling characteristics and good ambient and elevated temperature properties. However, epoxy resins do have certain deficiencies in that the prepreg materials must be kept refrigerated, cost is higher than other available thermoset materials, and cure time is often long.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy resins.
=650  \7$aTECHNOLOGY & ENGINEERING / Chemical & Biochemical.
=700  1\$aMcMahon, PE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10662J.htm

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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHenneke, EG., $eauthor.
=245  10$aUltrasonic Testing Methods for Composite Materials / $cEG Henneke, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 2 (January 1979)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aUltrasonic testing methods that are well established for application to metals and alloys can not be identically applied to composite materials. Because composites are both heterogeneous and anisotropic, complications arise in the mechanics of the interaction of the stress waves with the material. This leads to a variety of new R&D problems that are both difficult and interesting. Attempts to characterize material strength, material (tensor) stiffness, and defect distributions are currently being conducted.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10663J.htm

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=041  \\$aeng
=050  \4$aTS283
=082  04$a681/.760410288$223
=100  1\$aHahn, HT., $eauthor.
=245  10$aLife Prediction of Composite Pressure Vessels / $cHT Hahn.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 2 (January 1979)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAquisition of data on the long-term behavior of composite pressure vessels is costly, not only for materials but also for fabrication and testing. If proven accurate, one way to minimize cost is to extrapolate the vessel performance from the strand data. We at the Lawrence Livermore Laboratory (under joint contract with NASA-Lewis Research Center) have been conducting stress-rupture tests on epoxy-impregnated strands and composite pressure vessels. We have accumulated 7 y of lifetime data on strand specimens and vessels have been held under constant pressure for over 1 y.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aPressure vessels $xMaintenance and repair.
=650  \7$aTECHNOLOGY & ENGINEERING $vTechnical & Manufacturing Industries & Trades.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10664J.htm

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=041  \\$aeng
=050  \4$aRD99
=082  04$a610$223
=100  1\$aReifsnider, KL., $eauthor.
=245  10$aEducational Opportunities / $cKL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
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=338  \\$aonline resource$2rdacarrier
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=362  0\$aVolume 1, Issue 2 (January 1979)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aEducational Opportunities.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEducation.
=650  \0$aEducation $vPeriodicals.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10666J.htm

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=037  \\$aCTR10671J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aWeingart, O., $eauthor.
=245  10$aFilament Wound Large E-Glass/Epoxy Spars and Blades / $cO Weingart.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 3 (April 1979)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA national wind energy program has been established to develop the technology required to make wind energy systems cost-competitive with conventional power generation systems and suitable for rapid commercial expansion to produce significant quantities of electrical power. The nominal 1500-kW Mod-2 Wind Turbine Generator being developed will require a rotor diameter of 300 ft (Fig. 1). Because of the considerable extension of technology that is required to produce the 150-ft blades, Structural Composites Industries and Kaman Aerospace Corporation have been awarded a contract by the Department of Energy through NASA-Lewis Research Center to design, fabricate, test, and evaluate a 150-ft composite blade. The primary structural element of the blade is a one-piece 20,000-lb spar fabricated using a new filament winding process, low-cost materials, and minimum labor.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10671J.htm

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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aHarvill, WE., $eauthor.
=245  10$aCo-Cured Graphite/Epoxy Vertical Fin Spar / $cWE Harvill.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 3 (April 1979)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe Lockheed-Georgia Company has recently constructed a one-piece molded front spar for the vertical fin of the L-1011 airplane (Fig. 1). The 26-ft-long graphite-epoxy spar contains integrally molded caps, webs, stiffeners, and rib attachments. This spar was fabricated as part of a contract sponsored by NASA-Langley Research Center with Lockheed-California Company to demonstrate production readiness and provide confidence in the use of composite primary structures. The spar is molded of T300/5208 graphite/epoxy. It replaces 39 metal parts, eliminates almost 1000 fasteners, and weighs about half as much as the metallic counterpart. The caps and webs vary in thickness and ply orientation along the length of the spar. These variations are achieved by build-up and deletion of the plies, all the while maintaining a balanced laminate to avoid warpage in the finished spar. Selected areas of this spar were fabricated separately and tested before the full-size 26-ft-long spar was fabricated. These tests demonstrated that the static strength, fatigue endurance, and damage resistance of the spar exceed all requirements.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10672J.htm

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=024  7\$a10.1520/CTR10673J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aHeitkamp, RR., $eauthor.
=245  10$aFilament Wound Kevlar 49/Epoxy Rocket Motor Cases / $cRR Heitkamp, RE Landes, BJ West.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 3 (April 1979)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aTwo high-performance rocket motor cases were recently fabricated at SCI by filament winding with Kevlar-49. The work was done under the validation phase of the Air Force's IUS (Inertial Upper Stage) and IPSM (Improved Performance Space Motor) Programs.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy.
=650  \0$aKevlar fiber.
=650  \0$aPlasma treatment.
=700  1\$aLandes, RE., $eauthor.
=700  1\$aWest, BJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10673J.htm

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=024  7\$a10.1520/CTR10674J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.2
=082  04$a620.1/1232$223
=100  1\$aCrossman, FW., $eauthor.
=245  10$aADV*LAM-An Advanced Laminate Code for Viscoelastic Analysis / $cFW Crossman.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 3 (April 1979)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAdvanced polymeric composite material systems are viscoelastic. Because of this, their response to mechanical and/or hygrothermal loading is dependent on time, temperature, environmental conditions, and their prior stress (strain) history. In turn, this dependence causes composite materials to experience a "shift" in their real-time behavior under hygrothermal conditions that accelerates stress relaxation and creep.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aViscoelasticity.
=650  \0$aElasticity.
=650  \7$aSCIENCE $xNanoscience.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10674J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10675J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10675J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aDuggan, MF., $eauthor.
=245  14$aThe Slotted Tension Shear Test for Composite Laminates / $cMF Duggan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 3 (April 1979)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe mechanical behavior of a composite laminate can be predicted by lamination theory if the properties of individual lamina are known. The in-plane shear stiffness and strength of lamina and of multidirectionally reinforced laminates have often proved to be most difficult to measure. In this article, we present an experimental technique that is used at Lockheed Missiles & Space Company, Inc., to measure the inplane shear properties of advanced composite laminates with plies of arbitrary fiber orientation.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10675J.htm

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=024  7\$a10.1520/CTR10676J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10676J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aHamstad, MA., $eauthor.
=245  10$aAging Data for Kevlar 49/Epoxy Pressure Vessels / $cMA Hamstad.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 3 (April 1979)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA study of aging degradation of filament wound cylindrical pressure vessels Kevlar 49/epoxy is being conducted at LLL. After over 5.5 years of aging in a laboratory environment, no significant change in the average failure pressure has been observed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy.
=650  \0$aKevlar fiber.
=650  \0$aPlasma treatment.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10676J.htm

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=024  7\$a10.1520/CTR10681J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10681J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA413.5
=082  04$a620.1/123/028$223
=100  1\$aKevin O'Brien, T., $eauthor.
=245  10$aEffect of Gage-Section Size on Composite Stiffness Measurements / $cT Kevin O'Brien.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 4 (July 1979)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe stiffness of engineering materials is typically calculated using a strain value recorded from a gage mounted on test coupons of the material. In heterogeneous materials, such as fiber reinforced composites, the measured strain used to calculate stiffness may depend on the size of the gage section, i.e., the area over which the strain is measured.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aStrain gage.
=650  \0$aExtensometer.
=650  \0$aGages.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10681J.htm

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=024  7\$a10.1520/CTR10682J$2doi
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=037  \\$aCTR10682J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aQD96.I5
=082  04$a543/.57$223
=100  1\$aHinrichs, R., $eauthor.
=245  10$aAdvanced Characterization Techniques for Composite and Adhesive Manufacturing Process Control / $cR Hinrichs, J Thuen.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 4 (July 1979)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe application of advanced chemical characterization techniques to polymer manufacturing control systems has been developed to control composite/adhesive resin formulations. High-pressure liquid chromatography (HPLC), viscoelastic rheological equipment, thermal analysis, and infrared spectroscopy are all used to evaluate the starting materials, the formulation process, and the final product. By developing the central system around these three manufacturing stages, chemical control of a system is possible. This control will, in turn, reduce our reliance on mechanical tests, which depend heavily on fabrication and handling techniques, to ensure quality control and consistency.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aInfrared spectroscopy.
=650  \0$aLiquid chromatography.
=650  \7$aSCIENCE $vSpectroscopy & Spectrum Analysis.
=700  1\$aThuen, J., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10682J.htm

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=024  7\$a10.1520/CTR10683J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aTheodore Sumsion, H., $eauthor.
=245  10$aSimple Torsion Test for Determining the Shear Moduli of Orthotropic Composites / $cH Theodore Sumsion, YDS Rajapakse.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 4 (July 1979)
=504  \\$aIncludes bibliographical references$b1.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe shear properties of a composite must be known for the design and use of the composite material. Although many methods are available for measuring in-plane shear, no simple test technique has been offered for determining out-of-plane shear. We, however, have developed a simple method for determining both in-plane and out-of-plane shear moduli of a homogeneous, orthotropic material. From torsion tests performed on specimens in the shape of a rectangular parallelepiped (a prism whose bases are parallelograms) of at least two different cross sections, the effective in-plane (G13) and out-of-plane (G23) moduli (Fig. 1) can be determined. (Please note that fiber direction is three-directional.) Additionally, we have determined these moduli for two different graphite-epoxy composites (AS/3501 and T300/5209), composites that have both uniaxial and cross-ply fiber orientations.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aRajapakse, YDS, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10683J.htm

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=024  7\$a10.1520/CTR10684J$2doi
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=037  \\$aCTR10684J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aThomas Hahn, H., $eauthor.
=245  10$aEffect of Storage Time on the Tensile Strength of Kevlar 49/Epoxy Strands / $cH Thomas Hahn, TL Gates.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1979.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 1, Issue 4 (July 1979)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn an effort to delineate the effect of storage time on strength, we have tested three types of Kevlar 49/epoxy strands up to 3.5 y after fabrication. The same fiber, Kevlar 49 (380 denier), was used with three different epoxy systems. The epoxy composition and cure cycles are listed in Table 1, and details of the test results are given in Table 2. Specimen preparation and test procedures have been reported elsewhere (for example, see Ref. 1). Note that in Table 2, failure loads were converted into fiber strengths using the fiber cross-sectional area.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1979. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aGates, TL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10684J.htm

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=024  7\$a10.1520/CTR10689J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10689J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTL1530
=082  04$a629.477$223
=100  1\$aWolff, EG., $eauthor.
=245  10$aSpacecraft Requirements for Dimensionally Stable Composites / $cEG Wolff.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 1 (January 1980)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aComposite materials are attractive for spacecraft use because of their high stiffness-to-weight ratios and significant improvements in dimensional stability over structural metals and alloys. A recent review of this topic (Ref. 1) discusses the state of the art of dimensional stability of composites. It also introduces the potential range of spacecraft applications for various composite systems, principally pseudo-isotropic graphite-fiber-reinforced resin matrix laminates. The range of factors which must be considered when evaluating the stability of spacecraft materials is illustrated by considering the sum of the allowable engineering strains: ε = Sσ + αΔT + βΔM + γΔT + ϑΔt + ρΔR.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aSpacecraft.
=650  \7$aTECHNOLOGY & ENGINEERING $xAeronautics & Astronautics.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10689J.htm

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=024  7\$a10.1520/CTR10690J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10690J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aErratt, RL., $eauthor.
=245  10$aFatigue Performance of High Strength Molding Compounds / $cRL Erratt, NL Lindley, RE Thomas.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 1 (January 1980)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe use of composite parts made from sheet molding compound (SMC), less than 35 wt% glass fiber, is well known in the automotive and transportation industry. Although the long term performance of these parts is important, most applications are primarily appearance parts with only minimal structural requirements. In these applications, the dynamic, load-bearing, performance of the SMC is not a major concern of the design engineer.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=700  1\$aLindley, NL., $eauthor.
=700  1\$aThomas, RE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10690J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10691J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10691J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aDjiauw, LK., $eauthor.
=245  10$aPrediction of Fatigue Life in Fiberglass-Reinforced Plastic Structures by Acoustic Emission Analysis / $cLK Djiauw, DG Fesko.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 1 (January 1980)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aComputer-linked acoustic emission (AE) monitoring instrumentation can record noises associated with crack growth in a fiberglass-reinforced plastic (FRP) component when it is proof tested, locate the source, and measure a number of parameters describing the wave form of the acoustic events. The use of AE to characterize the integrity of FRP structural components and then predict the performance of a part can be a valuable quality control tool. Having such a mechanism of quality assurance would be of tremendous value to the automotive industry by generating confidence in using this "new" material in place of steel in structural components.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=700  1\$aFesko, DG., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10691J.htm

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=024  7\$a10.1520/CTR10692J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10692J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aSendeckyj, GP., $eauthor.
=245  14$aThe Effect of Tetrabromoethane-Enhanced X-Ray Inspection on Fatigue Life of Resin-Matrix Composites / $cGP Sendeckyj.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 1 (January 1980)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aTetrabromoethane (TBE)-enhanced x-ray radiography is probably the most powerful tool available for documenting the damage accumulation process in resin-matrix composite materials. It can easily find individual matrix cracks, delaminations, and fiber bundle fractures. When used in the stereo mode, it can provide a detailed spatial description of the damage. With these obvious advantages, it is surprising that TBE (or some other x-ray opaque penetrant) enhanced x-ray radiography is not more widely used.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10692J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10693J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10693J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTR750
=082  04$a778.3$223
=100  1\$aRatwani, MM., $eauthor.
=245  10$aInfluence of Penetrants Used in X-Ray Radiography on Compression Fatigue Life of Graphite/Epoxy Laminates / $cMM Ratwani.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 1 (January 1980)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aCompression fatigue of composites has attracted considerable interest in recent years. It has been established that, unlike metallic structures, compression fatigue of composites is an important design consideration. There is significant life reduction for both tension-compression and compression-compression loading when compared to tension-tension loading. The fatigue failures are generally accompanied by progressive delaminations, fiber splitting, and fiber buckling.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aRadiography.
=650  \0$aX-ray photography.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10693J.htm

=LDR  03531nam  2200517 i 4500
=001  CTR10694J
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=030  \\$aJCTRER
=037  \\$aCTR10694J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aQC173.59.G44
=082  04$a530.11$223
=100  1\$aKulkarni, SV., $eauthor.
=245  10$aQuasi-Isotropic, Thick Composite Laminates Fabricated by the Matched Metal Die Compression Molding Process / $cSV Kulkarni.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 1 (January 1980)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aOne of the designs currently being explored under the DOE/LLL composite flywheel rotor development effort is the tapered thickness laminated disk "Stodola" rotor concept. The goal of this effort is to develop a prototype high-energy-density, economical composite laminate rotor for utilization in hybrid flywheel/electric/ICE vehicles and in stationary applications. In terms of energy density, the objective is to obtain 88 Wh/kg at failure with an operational range of 44-55 Wh/kg and an energy storage capacity of approximately 1 kWh. To that end, a high-strength graphite/epoxy (Celion 6000/5213) (0/±45/90) composite laminate tapered disk was fabricated and spin tested. Table 1 presents the test results. It appears from Table 1 that the governing failure criterion is the off-axis failure strength, which is typically lower than the strength along the fiber direction in most quasi-isotropic laminates. This strength anisotropy results in the under-utilization of the laminate strength and in lower energy densities. This suggests that there are two avenues open to improve the performance of laminated disk rotors: (1) increase the basic strength of the composite, and (2) reduce the strength anisotropy of the laminate.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnisotropic crystals.
=650  \0$aAnisotropy.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10694J.htm

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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA455.A34
=082  04$a620.1/99$223
=100  1\$aMorgan, RJ., $eauthor.
=245  10$aEnvironmental Sensitivity of Epoxies / $cRJ Morgan, ET Mones.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 1 (January 1980)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA number of laboratory and field studies have indicated that the combined effects of sorbed moisture and thermal environment can cause significant changes in the mechanical response of epoxy composites and adhesives. The increasing use of these materials in extreme environments requires a greater understanding of their durability. However, the long-term, in-service durability of epoxy adhesives and composites is uncertain primarily because (1) long-term, in-service aging conditions are difficult to simulate by short-term laboratory or field tests, and (2) the basic phenomena responsible for changes in the mechanical response of the epoxies themselves in laboratory-simulated service environments have not all been identified or understood.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesives.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aMones, ET., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10695J.htm

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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aMorgan, RJ., $eauthor.
=245  14$aThe Microscopic Failure Processes of Kevlar/Epoxy Composites / $cRJ Morgan, ET Mones, WJ Steele.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 3 (July 1980)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aKevlar 49† fibers, E.I. duPont, are increasingly being used in high performance, fibrous epoxy composites. To predict the durability of these composites with confidence requires identification of the microscopic deformation and failure processes and the structural parameters that control these processes. In this paper we review our present understanding of these processes in Kevlar/epoxy strands and multilayer composite pressure vessels.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aMones, ET., $eauthor.
=700  1\$aSteele, WJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10701J.htm

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=024  7\$a10.1520/CTR10702J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10702J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHahn, HT., $eauthor.
=245  10$aSimplified Formulas for Elastic Moduli of Unidirectional Continuous Fiber Composites / $cHT Hahn.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 3 (July 1980)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe elastic moduli of composites reinforced with continuous fibers depend on the elastic moduli of the constituent materials and on the geometry and spatial arrangement of fibers. The determination of the relationship between the composite properties and the constituent properties has been an area of extensive research. As a result, a large number of formulas are available for various combinations of geometry and distribution of fibers.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10702J.htm

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=007  cr\\\\\\\\\\\\
=008  161219c19809999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10703J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10703J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aCrews, JH., $eauthor.
=245  10$aWidth Effects on Stresses in Graphite/Epoxy Laminates with Loaded Holes / $cJH Crews, IS Raju.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 3 (July 1980)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAt present, mechanical fastening is a common joining method for graphite/epoxy laminates, despite the considerable loss of laminate strength due to the fastener holes. To date, most research on graphite/epoxy laminates has involved the testing of laminates with unloaded holes; very little research has been done with loaded holes, especially on the stress analysis of such holes. The purpose of this paper is to present some analytical results for stresses near loaded holes in finitewidth laminates.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=700  1\$aRaju, IS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10703J.htm

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=001  CTR10704J
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=008  161219c19809999pau||#p|s||||||||||0eng|d
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=024  7\$a10.1520/CTR10704J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10704J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.P5
=082  04$a668.4$223
=100  1\$aHyer, MW., $eauthor.
=245  10$aIsotropic Character of Quasi-Isotropic Lay-ups / $cMW Hyer.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 3 (July 1980)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDespite the tailorability of laminated fiber composites, the tendency has been to use lay-ups that more closely approximate an isotropic material. These so-called quasi-isotropic lay-ups are used so the structure or component fabricated from them can withstand loads oriented in many directions or perhaps accommodate an unexpected loading. Since there is so much literature associated with predicting the static and dynamic response of isotropic beams, plates, and shells, particularly in table look-up format, the question arises as to the applicability of these tabulated results to members made from quasi-isotropic composite materials. The purposes of this paper are: (1) to indicate the degree of isotropy exhibited by a certain quasi-isotropic sandwich construction, (2) to verify that standard isotropic strength-of-materials formulas can be used to predict the response of these quasi-isotropic components for certain loadings, and (3) to present numerical data for a particular material system. It is felt that even though the results are presented for a sandwich construction, they can be extended to quasi-isotropic lay-ups in general.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aPlastics.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10704J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10705J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10705J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHinrichs, RJ., $eauthor.
=245  10$aCharacterizing Rheological Cure Behavior of Epoxy Composite Materials / $cRJ Hinrichs, JM Thuen.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 3 (July 1980)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aComposite structures are now being fabricated into primary aircraft components. These laminates are critical to the structural integrity of the aircraft and represent significant material-labor costs to produce. Unfortunately, most fabrication facilities experience random, apparently unexplained, part rejections due to variations in cure ply thickness, porosity, and voids. This study deals with the application of rheological characterization techniques to elucidate the unpredictable process behavior of composite structures. The rheological properties of epoxy polymers are directly related to the reaction cure dynamics, flow, gas-liquid transport, and consolidation of the laminate.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aThuen, JM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10705J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10706J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10706J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.E6
=082  04$a668/.374$223
=100  1\$aKolb, JR., $eauthor.
=245  10$aPreliminary Development of an Epoxy Resin System for Flywheel Applications / $cJR Kolb, IL Chiu, HA Newey.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 3 (July 1980)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWe at Lawrence Livermore National Laboratory (LLNL) have a very active Flywheel program, one component of which is the development of new resin systems to serve as matrix materials for fiber-reinforced composites. A resin matrix for filament-wound flywheels must have a combination of characteristics that is normally difficult to achieve and, at times, may be almost mutually exclusive. The needs most prominent are low viscosity for fiber penetration, a long pot life for handling ease, low toxicity, and low cost. Very few resin systems satisfactorily meet each of these necessary criteria. An additional constraint lies within the service temperatures where the flywheel must operate. Three distinct temperature regimes have been defined. The first is where the flywheel reaches a maximum temperature of 65°C. In the second region, a maximum temperature of 100°C has been defined. In the third region, the temperature may reach 120°C or higher. For the low temperature use, a room temperature curable resin system with a glass transition temperature (Tg) of approximately 65°C seems satisfactory. For intermediate temperature uses, a rubberized epoxy resin cured with an aromatic amine (Tg = 104°C) looks promising.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy resins.
=650  \7$aTECHNOLOGY & ENGINEERING / Chemical & Biochemical.
=700  1\$aChiu, IL., $eauthor.
=700  1\$aNewey, HA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10706J.htm

=LDR  02982nam  2200541 i 4500
=001  CTR10707J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19809999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10707J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10707J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.A3
=082  04$a668/.3$223
=100  1\$aHinrichs, RJ., $eauthor.
=245  10$aStructural Adhesives Rheological Behavior Response to Process-Environmental Variation / $cRJ Hinrichs, JM Thuen.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 3 (July 1980)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAdhesive bonding operations have been randomly plagued with mechanical and physical (flow, bond line thickness, slick-off, etc.) problems. In an effort to define some of the sources for such problems, we investigated the relationship between environmental (humidity, aging) and cure cycle variations on the adhesive processing characteristics (flow, rheological behavior) as well as mechanical properties. Six adhesives, including some from competitive manufacturing origins, were used for general comparison to ensure that the observed trends were not generic to specific formulations. In this paper, we present a summary of the results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive bonding.
=650  \0$aAdhesive joints.
=650  \0$aGlued joints.
=700  1\$aThuen, JM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10707J.htm

=LDR  02242nam  2200505 i 4500
=001  CTR10711J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19819999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10711J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10711J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aReifsnider, KL., $eauthor.
=245  10$aLove, Lollipops, and Composite Materials / $cKL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (1 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 1 (April 1981)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10711J.htm

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=001  CTR10713J
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=007  cr\\\\\\\\\\\\
=008  161219c19819999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10713J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10713J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSandorff, PE., $eauthor.
=245  10$aExperimental Evaluation of Column Compression Properties of Graphite/Epoxy Composites / $cPE Sandorff, JT Ryder, KN Lauraitis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 1 (April 1981)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aExperimental procedures for evaluating the column compression properties of graphite/epoxy laminated composites are described. The test procedure allows the determination of a buckling curve up to and including the inelastic, fully supported, zero-length column. Verification of the test procedure is provided by using flat aluminum test specimens. Application to specific graphite/epoxy laminated composites is described. Inelastic compression properties are shown to be highly sensitive to environmental conditions and laminate lay-up. Prediction of the elastic compression properties of graphite/epoxy laminates by the Euler relation is shown to be significantly nonconservative.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aComposite materials.
=650  \0$aCompressing.
=650  \0$aGraphite composites.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aCompressing.
=653  20$aBuckling.
=653  20$aGraphite composites.
=700  1\$aRyder, JT., $eauthor.
=700  1\$aLauraitis, KN., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10713J.htm

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=001  CTR10714J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19819999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10714J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10714J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aReifsnider, KL., $eauthor.
=245  14$aThe Effect of Lamination-Induced Stresses on Fatigue Damage Development at Internal Flaws / $cKL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 1 (April 1981)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFor the purposes of our discussion here, we define an "unconstrained" case to be a unidirectional lamina. "Constraint stresses," then, will be those stresses that owe their existence to the constraints exerted by off-axis plies, which are laminated to 0° laminae on the response of those 0° laminae. In the next few paragraphs we will discuss the development of damage during fatigue loading in 0° plies and attempt to extend the discussion to the response of those plies when embedded in a laminate under the influence of these constraint stresses.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10714J.htm

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=001  CTR10715J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19819999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10715J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10715J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC173.59.G44
=082  04$a530.11$223
=100  1\$aNeiderstadt, G., $eauthor.
=245  10$aElastic Constants of Mat-Reinforced Laminates / $cG Neiderstadt, B Geier.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 1 (April 1981)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aChopped-strand mats are often used as reinforcements for plastics. These chopped-strand mats consist of short glass fibers aligned parallel to the plane of layering but randomly oriented in the remaining directions. The gross mechanical behavior of a mat laminate may be characterized as transversely isotropic, that is, isotropic in its own plane but anisotropic with respect to an axis normal to it. This contrasts strongly with the gross orthotropic behavior of unidirectional laminates.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnisotropic crystals.
=650  \0$aAnisotropy.
=700  1\$aGeier, B., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10715J.htm

=LDR  03078nam  2200517 i 4500
=001  CTR10716J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19819999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10716J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10716J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aZweben, C., $eauthor.
=245  14$aThe Effect of Stress Nonuniformity and Size on the Strength of Composite Materials / $cC Zweben.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 1 (April 1981)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIt has long been known that the strength of brittle materials like ceramics depends on the volume of stressed material and the nature of the stress distribution. Both of these effects arise because brittle materials are flaw-sensitive, and flaw severity is generally statistical in nature. As the probability of finding a serious flaw increases with increasing material volume, large brittle bodies tend to fail at lower stress levels than do smaller ones when both are subjected to the same kind of uniform stress field, such as pure tension. The dependence of strength on stress distribution arises because the stress in the region of at least one flaw must equal its critical value for failure to occur. In this paper, we refer to this phenomenon as a "nonuniformity effect."
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10716J.htm

=LDR  02339nam  2200517 i 4500
=001  CTR10717J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19819999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10717J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10717J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aHahn, HT., $eauthor.
=245  14$aThe Effect of Vacuum and Temperature on the Mechanical Properties of an Aramid/Epoxy Composite / $cHT Hahn, WK Chin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 1 (April 1981)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aChin, WK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10717J.htm

=LDR  03447nam  2200553 i 4500
=001  CTR10718J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19819999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10718J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10718J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA648.3
=082  04$a624.1/7$223
=100  1\$aHighsmith, A., $eauthor.
=245  10$aStress Redistribution in Composite Laminates / $cA Highsmith, KL Reifsnider, WW Stinchcomb.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 1 (April 1981)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWe have prepared this brief report to stimulate interest in and draw attention to a general concept we believe to be of considerable practical use in the determination of the strength, stiffness, and life (what we collectively call the material's response) of composite laminates. The general concept is the determination of stress redistribution during damage development. While the idea of stress redistribution is certainly not new, the suggestion that a general rational approach to the understanding and analysis of damage states and their effect on the materials response of composite laminates is both new and incompletely developed at this point. It is appropriate, then, that the generality and utility of this scheme be brought to the attention of the composites community by this communication so that a greater number of investigators can participate in the development of the concept if they wish. Less general but more specific and precise treatments of this subject will appear in the formal literature in the coming months.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aStrains and stresses.
=650  \0$aStructural dynamics.
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=700  1\$aReifsnider, KL., $eauthor.
=700  1\$aStinchcomb, WW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10718J.htm

=LDR  02854nam  2200517 i 4500
=001  CTR10719J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19819999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10719J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10719J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQH212.E4
=082  04$a570/.28/25$223
=100  1\$aMasters, JE., $eauthor.
=245  10$aSurface Replication : $bA Reliable Method of Detecting Matrix Cracks in Composite Laminates / $cJE Masters.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 1 (April 1981)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe purpose of this brief report is to bring to the attention of the composites community an experimental technique that was introduced by Masters, Stalnaker, et al [1-3]. The technique is surface replication, a scheme that is well established as a metallographic method applied to optical and electron microscopy. Application of this method to composite materials requires that somewhat different procedures be used compared to the common metallographic practices. A description of these procedures for a specific case and an illustrative example are provided below.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aElectron microscopy.
=650  \0$aSurface replication.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10719J.htm

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=001  CTR10724J
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=024  7\$a10.1520/CTR10724J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10724J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKuroda, T., $eauthor.
=245  10$aEquations for Estimating the Bending Modulus of Elasticity of Rigid Plastics by Extrapolation / $cT Kuroda.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 2 (July 1981)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new method to estimate a reliable value of the bending modulus of elasticity E from apparent moduli E' calculated from gradients of crosshead travel versus load for three-point bend tests on specimens at different support spans L is presented. The equation 1/E' = 1/E + C/L, where C is a constant, is proposed for this estimation. Flexure tests were run at various support spans on specimens of various widths and made of three kinds of materials (a type of polyvinyl chloride and two types of fiber-reinforced materials). Then the values of E' obtained from the tests at the longest spans were compared with the extrapolated moduli E" at those same spans, calculated by the equation from values of E' at various shorter spans. Moduli at infinite span E∞" were also calculated by extrapolation from E' at various spans, and the E∞" of a width and of a material were compared with one another. The results show that the equation is a convenient and adequate means of estimating the characteristic modulus of elasticity of the specimen.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBend tests.
=650  \0$aComposite materials.
=650  \0$aModulus of elasticity.
=650  \0$aPlastics.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aBend tests.
=653  20$aModulus of elasticity.
=653  20$aPlastics.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10724J.htm

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=001  CTR10725J
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=024  7\$a10.1520/CTR10725J$2doi
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=037  \\$aCTR10725J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKnauss, JF., $eauthor.
=245  14$aThe Compressive Failure of Graphite/Epoxy Plates with Circular Holes / $cJF Knauss, EG Henneke.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 2 (July 1981)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe results of an experimental investigation of the compressive behavior of T300/5208 graphite/epoxy laminated plates measuring 127.0 by 254.0 mm and containing circular holes ranging to 38.1 mm are reported. Two thicknesses, 24-ply and 48-ply, were chosen to differentiate between stability failures resulting from buckling and strength failures caused by the hole. Both quasi-isotropic and orthotropic stacking arrangements were used. The critical buckling load of the 24-ply panels was independent of hole size. Bifurcation occurred in the two half-wave mode longitudinally and one half-wave mode laterally in the quasi-isotropic panels. For the orthotropic 24-ply panels, bifurcation began in the one half-wave mode shape in each direction but changed to the two half-wave mode before failure. Consistent post-buckling strength was exhibited by both laminate configurations. The 48-ply quasi-isotropic specimens displayed decreasing strength with increasing hole diameter to approximately 50% of the ultimate strength of the panel without holes for a diameter-to-width ratio of 0.30. The 48-ply orthotropic panels displayed a strength/stability threshold between hole diameters of 3.175 and 6.35 mm. Panels with hole diameters below 3.175 mm displayed buckling before failure; those with holes larger than 6.35 mm experienced material failure around the hole before panel collapse. The 48-ply quasi-isotropic panels showed no comparable behavior; failure was induced by the stress concentration in these panels for all hole sizes.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBifurcation.
=650  \0$aBuckling.
=650  \0$aComposite materials.
=650  \0$aCompressive properties.
=650  \0$aGraphite composites.
=650  \0$aHoles.
=650  \0$aLaminates.
=650  \0$aPostbuckling.
=650  \0$aStability.
=650  \0$aStress concentration.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aLaminates.
=653  20$aGraphite composites.
=653  20$aCompressive properties.
=653  20$aStress concentration.
=653  20$aHoles.
=653  20$aBuckling.
=653  20$aStability.
=653  20$aBifurcation.
=653  20$aPostbuckling.
=700  1\$aHenneke, EG., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10725J.htm

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=024  7\$a10.1520/CTR10726J$2doi
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=037  \\$aCTR10726J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aStrife, JR., $eauthor.
=245  10$aEvaluation of Metal Ribbon Reinforced/Resin Matrix Composites / $cJR Strife, KM Prewo.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 2 (July 1981)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aRibbon-reinforced composites possess a unique set of properties which can offer specific advantages when compared to fiber-reinforced composites. The potential for this class of composites has been demonstrated in several investigations utilizing ribbon-reinforced metal matrix systems [1-8] and ribbon-reinforced resin matrix systems [9-15]. However, the development and practical application of ribbon-reinforced composites has progressed very slowly due to the absence of a low-cost, high-performance ribbon material.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aPrewo, KM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10726J.htm

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=024  7\$a10.1520/CTR10727J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10727J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aHahn, HT., $eauthor.
=245  10$aEngineering Properties of a Filament-Wound Kevlar 49/Epoxy Composite / $cHT Hahn, WK Chin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 2 (July 1981)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe effect of a simulated flywheel service environment on the longitudinal tensile properties, both static and in fatigue, of a filament-wound Kelvar 49/epoxy composite was presented in a recent paper. The epoxy, formulated at the Lawrence Livermore National Laboratory, was DER 332/Kelpoxy G293/Helox 68/Tonox 60-40 (77/23/65/37.3), and the composite was cured first at 60°C for 4.5 h and then at 130° C for 3 h. The effect of the same environment (vacuum and temperature) on the remaining properties, that is, longitudinal compression, transverse tension, transverse compression, and longitudinal shear, are described here.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aChin, WK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10727J.htm

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=024  7\$a10.1520/CTR10728J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10728J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aLockwood, PA., $eauthor.
=245  10$aResults of the ASTM Round-Robin on the Rail Shear Test for Composites / $cPA Lockwood.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 2 (July 1981)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aASTM Committee D-30 on High Modulus Fibers and Their Composites proposed a new standard to measure in-plane shear properties of high modulus fiber composites. The new method would use a two-rail or three-rail shear test system, both of which are being used in industry at this time. During the Subcommittee D-30.04 review, several suggested modifications were offered which indicated a lack of uniformity between the methods in current use. Another problem was that one laboratory had tested material with both methods and obtained different values with the two-rail versus the three-rail shear test systems. It was decided to run a round-robin using both test systems.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10728J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10732J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10732J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMandell, JF., $eauthor.
=245  10$aTensile Fatigue Performance of Glass Fiber Dominated Composites / $cJF Mandell, DD Huang, FJ McGarry.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 3 (October 1981)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe fatigue data curves of a variety of glass fiber composites ranging from injection-molded thermoplastics and sheet molding compounds to unidirectional laminates are shown to have the same fatigue degradation rate, losing approximately 10% of their initial tensile strength per decade of fatigue cycles. This degradation rate is derived from the reinforcement: unimpregnated strands have the same fatigue performance as do composites. The matrix and interface contribute nothing to the resistance to fatigue failure. The underlying mechanisms responsible for this behavior are discussed. Exceptions occur in some materials because of specimen size effects and in others because of more severe degradation mechanisms such as those that occur with woven fabric reinforcement. The behavior at very low stresses and long lifetimes requires further investigation.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aDegradation.
=650  \0$aFatigue (materials)
=650  \0$aStresses.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFatigue (materials).
=653  20$aComposite materials.
=653  20$aDegradation.
=653  20$aStresses.
=700  1\$aHuang, DD., $eauthor.
=700  1\$aMcGarry, FJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10732J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10733J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10733J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.P55
=082  04$a624.1892$223
=100  1\$aPruneda, CO., $eauthor.
=245  14$aThe Relation Between Physical Structure and Deformation and Failure Processes of Kevlar 49 Fibers / $cCO Pruneda, WJ Steele, RP Kershaw, RJ Morgan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 3 (October 1981)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aTo conserve energy, high-performance fiber composites are increasingly used by the transportation industry as lightweight, strong structural materials. In the past, graphite, glass, or boron fibers were predominantly used in these composites. However, since their introduction ten years ago, poly(p-phenylene terephthalamide) (PPTA) fibers (Kevlar 49, E. I. du Pont) have found increasing use in such composites. The chemical structure of PPTA is illustrated in Fig. 1. The PPTA macromolecule has the physical shape of a rod and an average length of ∼200 nm.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber-reinforced plastics.
=650  \0$aFibrous composites.
=700  1\$aSteele, WJ., $eauthor.
=700  1\$aKershaw, RP., $eauthor.
=700  1\$aMorgan, RJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10733J.htm

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=024  7\$a10.1520/CTR10734J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10734J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSW, Tsai, $eauthor.
=245  10$aGeneralized Stress-Strain Relations of Laminated Composite Materials / $cTsai SW.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 3 (October 1981)
=504  \\$aIncludes bibliographical references$b1.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe stress-strain relations for the conventional homogeneous isotropic and anisotropic material under plane stress are: σ=Qε, ε=Sσ where σ and ε are stress and strains, respectively, and Q and S are the modulus and compliance, respectively. In the theory of plates and shells, it is customary to use variables other than σ and ε, such as: N=Aε0, ε0=aNM = Dk, k=dM where N: stress resultant = ∫dz, M = moment : ∫zdz, ε0 : in-plane strain : mid-plane strain, k = curvature, where ε = zk, A = in-plane modulus = ∫Qdz, D = flexural modulus = ∫Qz2dz, a = A-1 = in-plane compliance, and d = D-1 = flexural compliance.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10734J.htm

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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA648.3
=082  04$a624.1/7$223
=100  1\$aCT, Sun, $eauthor.
=245  10$aImprovement of the First-Ply-Failure Strength in Laminates by Using Softening Strips / $cSun CT, Voit PM.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 3 (October 1981)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn an aircraft structure with fastener holes, stress concentrations that occur near the holes may dominate the design consideration. Softening strips have been tested to reduce these stress concentrations in laminated composites [1, 2]. In the region containing the hole, the high-modulus composite material is replaced with low-modulus, high-failure-strain composite. For example, in a [0, ± 45, 90] graphite/epoxy laminate, a softening strip can be made by replacing the 0° plies with 0° glass/epoxy composite plies. Experiments have shown that a softening strip can increase the static strength over the plain laminate by as much as 20% [2]. This paper reports an analytical study of softening strips in various laminates. The maximum stress criterion was used to predict the first ply failure. We present the calculated results first for the plain, baseline laminates, then for laminates with softening strips.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aStrains and stresses.
=650  \0$aStructural dynamics.
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=700  1\$aPM, Voit, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10735J.htm

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=024  7\$a10.1520/CTR10736J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA648.3
=082  04$a620.1/123$223
=100  1\$aHT, Hahn, $eauthor.
=245  10$aWarping of Unsymmetric Cross-Ply Graphite/Epoxy Laminates / $cHahn HT.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 3 (October 1981)
=504  \\$aIncludes bibliographical references$b1.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aResidual stresses in composite laminates are induced by the anisotropic expansional properties of the constituent unidirectional plies. Immediately after fabrication, laminates are subjected to curing stresses because of the thermal expansion mismatch between plies with different fiber orientations. Furthermore, as the laminates are left in a moist environment, they absorb moisture and swell. The swelling strains can offset the curing strains with the net result of reduced residual stresses.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aStrains and stresses.
=650  \0$aMechanical prestressing.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10736J.htm

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=024  7\$a10.1520/CTR10737J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10737J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRM, Jones, $eauthor.
=245  10$aComposite Materials Education in the United States / $cJones RM.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 3 (October 1981)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe modern revolution of composite materials began in the 1950s with the development of the filament winding technique for glass fibers to make rocket motor cases. The usefulness of composites expanded dramatically in the 1960s and 1970s with the advent of first boron and then graphite fibers. Now, with the composite technology that is increasingly attractive to an ever-broadening group of industries, it is necessary to educate a larger number of engineers in analysis. design, and fabrication of composite structures. Engineering curricula have not been revised by all institutions to respond to the need for engineers with knowledge of composites. However, some institutions have developed strong, innovative programs at both the undergraduate and graduate level. Moreover, postgraduate learning in the form of short courses and seminars has played an important role in the development of composites technology. Current programs at undergraduate, graduate, and postgraduate levels are reviewed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite material.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10737J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10742J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10742J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aYaniv, G., $eauthor.
=245  10$aResidual Thermal Stresses in Bonded Metal and Fiber-Reinforced Plastic Systems / $cG Yaniv, O Ishai.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 4 (December 1981)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA model of a nonsymmetrical bonded fiber-reinforced plastic (FRP) metal system was investigated, both theoretically and experimentally, to study the effects of curing, thermal history, and material characteristics on its thermoelastic behavior. It was found that a simplified closed form solution is sufficient for the prediction of the adherends' residual thermal stresses, while a numerical finite element solution is the best approach for determining the interlaminar stresses present in the boundary zones of the adhesive layer. In these zones the shear and lateral tensile stresses (peel) reach their respective maximum values, which are eventually the cause of the interlaminar failure mode of the adhesive layer under subsequent thermomechanical loading.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aResidual stress.
=650  \0$aThermal stresses.
=650  \0$aThermoelasticity.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aResidual stress.
=653  20$aThermal stresses.
=653  20$aThermoelasticity.
=700  1\$aIshai, O., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10742J.htm

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=024  7\$a10.1520/CTR10743J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10743J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aWang, TK., $eauthor.
=245  12$aA Loading Rate and Environmental Effects Study of Adhesive Bonded Sheet Molding Compound Joints / $cTK Wang, BA Sanders, US Lindholm.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 4 (December 1981)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAs sheet molding compound (SMC) materials become more widely used in today's automobiles, the need for economical and reliable methods of joining them increases. In this paper, the static and dynamic behavior of SMC-R25® and SMC-R50® single lap shear joints, bonded with a two-part urethane adhesive under various loading and environmental soaking conditions, are determined and analyzed. Engineering properties of the adherends (substrates) and adhesive are also presented.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesives.
=650  \0$aAutomobiles.
=650  \0$aComposite materials.
=650  \0$aLap joints.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aAdhesives.
=653  20$aLap joints.
=653  20$aAutomobiles.
=700  1\$aSanders, BA., $eauthor.
=700  1\$aLindholm, US., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10743J.htm

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=024  7\$a10.1520/CTR10744J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10744J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC173.59.G44
=082  04$a530.11$223
=100  1\$aEvans, WD., $eauthor.
=245  10$aEffect of a Resin Interlayer on Composites with Free Edges / $cWD Evans, NJ Salamon.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 4 (December 1981)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe interlaminar stress problem in laminated composites requires precise definition to predict failure reliably as well as to characterize laminates. An assessment and review of the problem has been reported by Salamon [1]. The majority of investigations treat an idealized laminate model composed of anisotropic, homogeneous sheets bonded together along a planar surface; the interface between sheets has no thickness. Numerical solutions do not accurately capture the mechanical behavior of the laminate in regions of apparent singularities; that is, boundary or interface continuity conditions are not satisfied. Furthermore, magnitudes of the predicted stresses are sensitive to the order of the approximation and vary from one solution to another. One exception is a work by Wang and Choi [2] which, for angle-ply laminates, defines the singularity and takes it into account using a numerical collocation technique.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnisotropic.
=650  \0$aCrystallography.
=700  1\$aSalamon, NJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10744J.htm

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=024  7\$a10.1520/CTR10745J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTL1530
=082  04$a629.477$223
=100  1\$aPrewo, KM., $eauthor.
=245  10$aGraphite-Fiber-Reinforced Glass for Spacecraft Applications / $cKM Prewo.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 4 (December 1981)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA recent report [1] describes a program performed under National Aeronautics Space Administration (NASA) Langley sponsorship to establish the fabrication procedures and properties of a new graphite-fiber-reinforced composite for applications requiring exceptional stability over a wide range of temperatures and environments. The system, based on the use of a wide variety of graphite fibers to reinforce glass matrices, will help meet the increasing need for high-temperature, stable, low-density composites. It is a direct outgrowth of the well-developed technology of resin-matrix composites in that the matrix can be caused to flow and encapsulate the reinforcing fibers without damaging them. Also, as in the case of resin- and metal-matrix composites, the elastic modulus of the fibers exceeds that of the matrix enough to provide effective reinforcement. The development of the fabrication procedures and technology that led to these recent data can be traced through three interim technical reports [2-4] and several publications [5-7]. The current report summarizes the most important aspects of the work and describes the most recently developed composites and their properties.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aSpacecraft.
=650  \0$aAstronautics.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10745J.htm

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=024  7\$a10.1520/CTR10746J$2doi
=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aQC173.59.G44
=082  04$a530.11$223
=100  1\$aKriz, RD., $eauthor.
=245  10$aAbsorbed Moisture and Stress-Wave Propagation in Graphite/Epoxy / $cRD Kriz.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 4 (December 1981)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aEnergy flux of stress waves propagating through anisotropic crystals has been shown by previous investigators [1,2] to deviate from the direction of the normal to the plane wave. Fiber-reinforced materials, which are also anisotropic, exhibit the same phenomena [3].
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnisotropic crystals.
=650  \0$aAnisotropy.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10746J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10747J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10747J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aAlper, JM., $eauthor.
=245  10$aCompressive Strength of a Unidirectional Graphite/Epoxy Composite Following a Tensile Proof-Load / $cJM Alper, ASD Wang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 4 (December 1981)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe "equal rank" assumption is commonly used to statistically relate the tensile strength and fatigue life of specimens made from fibrous composite materials [1-4]. It implies that a specimen in a given population has the same rank in the static-strength distribution as it does in the fatigue-life distribution. This assumption has been shown to be generally valid for unidirectional graphite/epoxy composites subjected to static tension and tensile fatigue loadings [5].
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aWang, ASD, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10747J.htm

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=024  7\$a10.1520/CTR10748J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10748J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aQC367.3.I58
=082  04$a522/.6$223
=100  1\$aJamison, RD., $eauthor.
=245  10$aStrain Field Response of 0° Glass/Epoxy Composites Under Tension / $cRD Jamison, AL Highsmith, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1981.
=300  \\$a1 online resource (1 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 3, Issue 4 (December 1981)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAs part of a general effort to study the development of damage in fiber-reinforced composite materials, the method of moiré interferometry is being applied to specimens under tensile load to examine the strain field on one face of the specimen and thereby reduce displacements in underlying plies. A 600-line/mm silicone rubber diffraction grating is bonded directly to the surface of the specimen. A virtual reference grating is formed in space parallel to this active grating and a pattern of interference fringes representing lines of constant displacement is observed. The required optical elements shown in Fig. 1 are attached to a rigid plate which is in turn attached to the support columns of an MTS testing machine.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1981. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aInterferometry.
=650  \0$aOptical measurements.
=700  1\$aHighsmith, AL., $eauthor.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10748J.htm

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=001  CTR10754J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19829999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10754J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10754J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aAgarwal, BD., $eauthor.
=245  10$aStrain-Controlled Flexural Fatigue of Unidirectional Composites / $cBD Agarwal, SK Joneja.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 1 (April 1982)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aStrain-controlled flexural fatigue of a unidirectionally reinforced glass fiber epoxy composite has been studied for four fiber orientations: 0, 10, 45, and 90°. Progressive damage has been investigated through measurements during fatigue tests and through static tests on precycled specimens. Variations in residual stiffness and strength have been explained through observed damage mechanisms at different fiber orientations. Two empirical relations have been evolved to predict fatigue strength of fibrous composites from their static properties alone. These predictions are in good agreement with the present experimental results as well as with the limited results available in the literature.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aEpoxy resin.
=650  \0$aFatigue (materials)
=650  \0$aFatigue damage.
=650  \0$aFlexural fatigue.
=650  \0$aGlass fibers.
=650  \0$aOff-axis fatigue.
=650  \0$aPrediction of fatigue life.
=650  \0$aStrain-controlled fatigue.
=650  \0$aStrains.
=650  \0$aUnidirectional composites.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aFatigue (materials).
=653  20$aUnidirectional composites.
=653  20$aStrains.
=653  20$aGlass fibers.
=653  20$aEpoxy resin.
=653  20$aFlexural fatigue.
=653  20$aFatigue damage.
=653  20$aOff-axis fatigue.
=653  20$aStrain-controlled fatigue.
=653  20$aPrediction of fatigue life.
=700  1\$aJoneja, SK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10754J.htm

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=001  CTR10755J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10755J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10755J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aLifshitz, JM., $eauthor.
=245  10$aStrain Rate, Temperature, and Humidity Influences on Strength and Moduli of a Graphite/Epoxy Composite / $cJM Lifshitz.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 1 (April 1982)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aResults of an experimental study of the influence of strain rate, temperature, and humidity on the mechanical behavior of a graphite/epoxy fiber composite are presented. Three principal strengths (longitudinal, transverse, and shear) and four basic moduli (longitudinal, transverse, axial shear, and major Poisson's ratio) of a unidirectional graphite/epoxy (T300/5208) composite were studied as functions of strain rate, temperature, and humidity. Each test was performed at a constant tensile strain rate in an environmental chamber providing simultaneous temperature and humidity control. Before being tested, specimens were given a moisture preconditioning treatment at 60°C. Values for the matrix-dominated moduli and strength were significantly influenced by both environmental and rate parameters, whereas the fiber-dominated moduli were not. However, the longitudinal strength was significantly influenced by temperature and moisture content. A qualitative explanation for these observations is presented.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aEpoxy laminates.
=650  \0$aGraphite composites.
=650  \0$aHumidity.
=650  \0$aModuli.
=650  \0$aStrain rate.
=650  \0$aStrains.
=650  \0$aStrength.
=650  \0$aTemperature.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aGraphite composites.
=653  20$aEpoxy laminates.
=653  20$aStrains.
=653  20$aTemperature.
=653  20$aHumidity.
=653  20$aStrain rate.
=653  20$aStrength.
=653  20$aModuli.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10755J.htm

=LDR  02789nam  2200529 i 4500
=001  CTR10756J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19829999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10756J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10756J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHighsmith, A., $eauthor.
=245  10$aMeasurement of Nonuniform Microstrain in Composite Laminates / $cA Highsmith, KL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 1 (April 1982)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn a previous communication [1] we described a new technique for measuring nonuniform microstrain in a composite laminate during loading using a very high resolution optical scheme originated by Daniel Post [2]. Here we present one example of how that technique can be applied to obtain basic information that is critical to more complete understanding of the deformation processes that control the strength, stiffness, and life of composite materials.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aReifsnider, KL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10756J.htm

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=001  CTR10757J
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=007  cr\\\\\\\\\\\\
=008  161219c19829999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10757J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10757J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.12
=082  04$a620.1129$223
=100  1\$aChaturvedi, SK., $eauthor.
=245  10$aIsotropic and Singular Points in Photoelasticity of Composites / $cSK Chaturvedi.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 1 (April 1982)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe motivation behind this report is the need for a thorough understanding of the photoelastic effect observed in birefringent anisotropic composite materials. Basically, there are two main sources of difficulties in anisotropic photoelasticity. The first is due to the inherent mechanical and optical heterogeneities caused by the different constituents of model materials. The second is interpreting the isochromatic and isoclinic fringes that are obtained as integrated effects along a light-path.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aPhotoelasticity.
=650  \0$aPhotoelastic method.
=650  \0$aElasticity.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10757J.htm

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=001  CTR10762J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19829999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10762J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10762J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aTakeda, N., $eauthor.
=245  10$aMicroscopic Observations of Cross Sections of Impacted Composite Laminates / $cN Takeda, RL Sierakowski, LE Malvern.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 2 (July 1982)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aMicroscopic observations of cross sections of impacted [(0°)5/(90°)5/(0°)5] glass/epoxy composite laminates have been made using a scanning electron microscope. The microphotos obtained have confirmed macroscopic observations such as the initiation and propagation of the transverse cracks and delamination cracks and also given some details that cannot be obtained macroscopically. The transverse cracks are perpendicular to lamina interfaces when there is no delamination nearby, while transverse cracks grow obliquely to interfaces when they are accompanied by a delamination crack. Delamination cracking appears to interact with the observed transverse cracks.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aCracks.
=650  \0$aDelamination.
=650  \0$aGlass/epoxy composite laminates.
=650  \0$aImpact.
=650  \0$aMicrophotographs.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aMicrophotographs.
=653  20$aImpact.
=653  20$aCracks.
=653  20$aGlass/epoxy composite laminates.
=653  20$aDelamination.
=700  1\$aSierakowski, RL., $eauthor.
=700  1\$aMalvern, LE., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10762J.htm

=LDR  03581nam  2200733 i 4500
=001  CTR10763J
=003  IN-ChSCO
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10763J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10763J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aAdams, DF., $eauthor.
=245  10$aAnalytical/Experimental Correlations of Stiffness Properties of Unidirectional Composites / $cDF Adams, BG Schaffer.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 2 (July 1982)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA finite element micromechanics analysis is used to predict the longitudinal and transverse moduli of both graphite/epoxy and glass/epoxy unidirectional composites, as a function of temperature, for various moisture preconditionings. These predictions are then correlated with corresponding experimental data. The micromechanics analysis includes temperature- and moisture-dependent matrix material properties, inelastic matrix stress-strain response, and anisotropic fibers. Thermal residual stresses caused by cooldown from the cure temperature and moisture-induced swelling stresses are included in the analysis. Good correlation is obtained between theory and experiment.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aComposite moduli.
=650  \0$aGlass/epoxy.
=650  \0$aGraphite composites.
=650  \0$aGraphite/epoxy.
=650  \0$aMicromechanics analysis.
=650  \0$aStiffness.
=650  \0$aUnidirectional composites.
=650  \0$aEpoxy.
=650  \0$aKevlar fiber.
=650  \0$aPlasma treatment.
=653  10$aComposite materials.
=653  20$aGraphite composites.
=653  20$aStiffness.
=653  20$aGraphite/epoxy.
=653  20$aGlass/epoxy.
=653  20$aUnidirectional composites.
=653  20$aMicromechanics analysis.
=653  20$aComposite moduli.
=700  1\$aSchaffer, BG., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10763J.htm

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=001  CTR10764J
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=008  161219c19829999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10764J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10764J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aDubel, JF., $eauthor.
=245  10$aReinforced Aluminum Composites for Underwater Systems / $cJF Dubel, BG Leonard.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (1 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 2 (July 1982)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aRecent advances in the technology of reinforced-aluminum composites have led to increased government and commercial interest, but very few data are available on their design, development, and manufacturing. Our challenge was to select, design, fabricate, and test a component that would demonstrate the advantages of reinforced-aluminum composites and then project these advantages into underwater systems to show improvements in performance, a reduction in system life-cycle cost, or both.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aLeonard, BG., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10764J.htm

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=024  7\$a10.1520/CTR10765J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10765J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.P55
=082  04$a668.4$223
=100  1\$aAl-Qureshi, HA., $eauthor.
=245  13$aAn Approximate Method of Sizing Soluble Plaster Mandrels in Filament Winding / $cHA Al-Qureshi, FL Kerber.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 2 (July 1982)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe mandrel is one of the most important components of the filament-winding process. Careful attention must be paid to the mandrel design, material selection, and all other relevant manufacturing and processing parameters involved in fabricating a vessel. The material selected for the mandrel should have a substantial strength and be capable of retaining dimensional accuracy of the required wound wessel. The stiffness of the mandrel material plays an important role in governing the residual filament stresses in the wound products.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFilament winding.
=650  \0$aMaterial selection.
=700  1\$aKerber, FL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10765J.htm

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=001  CTR10766J
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=008  161219c19829999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10766J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10766J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC793.5.E627
=082  04$a620.1/67$223
=100  1\$aGovada, A., $eauthor.
=245  10$aFailure Analysis of Composites Using Auger Electron Spectroscopy / $cA Govada, JC Duke.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 2 (July 1982)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAs composite materials are used more in critical design applications, it becomes more important to understand how they respond under load and, in particular, to identify precisely the outcome of any failure process. In most instances, optical or scanning electron microscopy provides the basis for this interpretation, but sometimes the information obtained may be ambiguous. To supplement conventional microscopy, Auger electron spectroscopy (AES) may be used. We describe an example in which depth profiling by the use of AES made possible a more complete analysis of the failure surface of a composite with a titanium metal matrix reinforced with boron-carbide-coated boron fibers.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAuger electron spectroscopy.
=650  \0$aScanning.
=650  \0$aMicroscopy, Scanning auger.
=700  1\$aDuke, JC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10766J.htm

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=001  CTR10767J
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=008  161219c19829999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10767J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10767J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aSun, CT., $eauthor.
=245  10$aOn the Measurement of Lamina In-Plane Shear Strength / $cCT Sun, S Yamada.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 2 (July 1982)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aMany current strength theories for laminated composites depend on knowledge of the basic lamina strengths, namely, the longitudinal, transverse, and in-plane shear strengths. Usually, these are determined from the unidirectional composite. Whether the in-situ lamina strengths, that is, the actual strengths of a lamina in a laminate, are the same as those of the unidirectional composite remains a subject for study.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=700  1\$aYamada, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10767J.htm

=LDR  03806nam  2200697 i 4500
=001  CTR10772J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19829999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10772J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10772J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKay, JF., $eauthor.
=245  10$aAdvances in a Structural Sheet Molding Compound / $cJF Kay.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 4 (December 1982)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aRecent work on a structural sheet molding compound with more than 60% by weight reinforcements of E-glass and S-2 Glass® in a low-profile polyester resin system demonstrates high-performance capability and versatility that permit tailoring of the composite properties to a specific application. A full range of room-temperature mechanical properties was developed for various combinations of randomly oriented chopped glass to continuous glass fiber reinforcement, as well as chopped glass core-continuous glass skin laminates. Test panels were molded as flat symmetric laminates, and both ply-reinforcement configuration and laminate lay-up sequence were varied. Mechanical properties investigated included tensile strength, compressive strength, flexural strength, shear strength, impact strength, specific gravity, and Poisson's ratio. It was determined that some mechanical properties can be significantly increased by the use of continuous fibers and S-2 Glass reinforcement.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite fabrication.
=650  \0$aComposite materials.
=650  \0$aComposite structures.
=650  \0$aE-glass.
=650  \0$aFiber reinforced polyester.
=650  \0$aMechanical properties.
=650  \0$aStructural sheet molding compound.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aComposite structures.
=653  20$aComposite fabrication.
=653  20$aMechanical properties.
=653  20$aStructural sheet molding compound.
=653  20$aFiber reinforced polyester.
=653  20$aE-glass.
=653  20$aS-2 Glass®.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10772J.htm

=LDR  03950nam  2200697 i 4500
=001  CTR10773J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19829999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10773J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10773J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRaju, IS., $eauthor.
=245  10$aThree-Dimensional Analysis of [0/90]s and [90/0]s Laminates with a Central Circular Hole / $cIS Raju, JH Crews.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 4 (December 1982)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aStress distributions were calculated near a circular hole in [0/90]s and [90/0]s laminates, using a three-dimensional finite-element analysis. These stress distributions were presented in three ways: through the thickness at the hole boundary, along radial lines at the 0/90 and 90/0 interfaces, and around the hole at these interfaces. The interlaminar normal stress σz and the shear stress σzϑ distributions had very steep gradients near the hole boundary, which suggested interlaminar stress singularities. The largest compressive σz stress occurred at about 60° from the load axis; the largest σzϑ occurred at about 75°. A simple procedure was introduced to calculate interlaminar stresses near the hole boundary. It used strains calculated by an exact two-dimensional analysis of a laminate with a hole as input to a quasi-three-dimensional model. It produced stresses that closely agreed with those from the three-dimensional finite-element model. For laminates with holes, this simple procedure may become a viable alternative to three-dimensional finite-element analyses.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCircular hole.
=650  \0$aComposite materials.
=650  \0$aEdge stresses.
=650  \0$aInterlaminar stresses.
=650  \0$aStress concentration.
=650  \0$aStresses.
=650  \0$aThree-dimensional finite-element analysis.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aStress concentration.
=653  20$aStresses.
=653  20$aCircular hole.
=653  20$aThree-dimensional finite-element analysis.
=653  20$aInterlaminar stresses.
=653  20$aEdge stresses.
=700  1\$aCrews, JH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10773J.htm

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=001  CTR10774J
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=008  161219c19829999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10774J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10774J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aYamasaki, RS., $eauthor.
=245  10$aSurface Weatherability of Glass-Fiber Reinforced Polyester Sheeting. II. Effect of Constituents / $cRS Yamasaki.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 4 (December 1982)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn accelerated weathering test (2 to 0.67 cycle) has been applied to glass-fiber reinforced polyester (GRP) to evaluate the effect of constituents on the surface durability of GRP. The nature and rate of induced surface degradation was assessed by scanning electron microscopy. For general-purpose GRP (GRP (GP)), replacement of chopped glass roving reinforcement with chopped glass mat reinforcement did not change the nature and rate of surface degradation. Incorporation of a glass surfacing veil, to provide a resin-rich surface layer, however, improved the durability of GRP (GP) to fiber pop out by 100%. Moreover, replacement of styrene with a styrene-methyl methacrylate cross-linking agent enhanced the resistance of GRP (GP) to fiber pop out, erosion, and surface microcracking an average of 70%. Substitution of an ultraviolet absorber Tinuvin P with Tinuvin 327 did not alter the durability of ethylene glycol-based GRP, while replacement of Tinuvin P with Tinuvin P/Tinuvin 144 in neopentyl glycol-based GRP improved the resistance to fiber pop out by 17% but decreased the durability to erosion and surface microcracking by 19 and 12%, respectively.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAccelerated weathering test.
=650  \0$aComposite materials.
=650  \0$aComposite structures.
=650  \0$aCross-linking agent.
=650  \0$aGlass fiber reinforced polyester.
=650  \0$aGlass fiber reinforcement.
=650  \0$aGlass fibers.
=650  \0$aGlass surfacing veil.
=650  \0$aPolyester fibers.
=650  \0$aScanning electron microscopy.
=650  \0$aSurface weatherability.
=650  \0$aUltraviolet absorbers.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aComposite structures.
=653  20$aGlass fibers.
=653  20$aPolyester fibers.
=653  20$aUltraviolet absorbers.
=653  20$aGlass fiber reinforcement.
=653  20$aGlass surfacing veil.
=653  20$aCross-linking agent.
=653  20$aGlass fiber reinforced polyester.
=653  20$aSurface weatherability.
=653  20$aAccelerated weathering test.
=653  20$aScanning electron microscopy.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10774J.htm

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=024  7\$a10.1520/CTR10775J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10775J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aSendeckyj, GP., $eauthor.
=245  10$aWithin-Panel Variability and Scaling Effects in Composite Materials / $cGP Sendeckyj, HD Stalnaker, LG Bates, RA Kleismit, JV Smith.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 4 (December 1982)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn the process of fabricating specimens for a fatigue investigation, we found that the panels had a systematic thickness and density variation. Because this could bias test results, we conducted an experimental study to assess the consequences of the observed variability within the panels. Moreover, we obtained data on the effect of specimen width on the static strength.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aStalnaker, HD., $eauthor.
=700  1\$aBates, LG., $eauthor.
=700  1\$aKleismit, RA., $eauthor.
=700  1\$aSmith, JV., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10775J.htm

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=024  7\$a10.1520/CTR10776J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10776J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.2
=082  04$a620.1/1232$223
=100  1\$aShivakumar, KN., $eauthor.
=245  13$aAn Equation for Bolt Clampup Relaxation in Transient Environments / $cKN Shivakumar, JH Crews.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 4 (December 1982)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe viscoelasticity of resin-based laminates allows the clampup force on bolts to relax, with a corresponding degradation in joint strength. We have studied clampup relaxation for steady temperature and moisture (T-M) conditions [1], but in typical applications laminate temperature and moisture both vary with time. These transient conditions influence clampup in two ways: first, the laminate thermal expansion (contraction) and moisture swelling (shrinkage) cause elastic changes in the clampup, and second, the T-M conditions influence the rate of clampup relaxation.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aViscoelasticity.
=650  \0$aElasticity.
=650  \7$aSCIENCE $xNanoscience.
=700  1\$aCrews, JH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10776J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10777J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10777J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA641
=082  04$a651.26$223
=100  1\$aGriffin, OH., $eauthor.
=245  10$aEvaluation of Finite-Element Software Packages for Stress Analysis of Laminated Composites / $cOH Griffin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 4 (December 1982)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aCurrent mechanical design and analysis requirements are such that advanced techniques, and the finite-element method in particular, are used routinely, often by people with little or no theoretical background or training. Selecting a software package for dissemination to a user community is a significant task, especially given the initial cost, the cost of user training, and the impact that use or abuse of the package will have on future products and manpower requirements.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \7$aSTRESS.
=650  \0$aStress Analysis.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10777J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10778J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10778J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMasters, JE., $eauthor.
=245  10$aRecent Work in the Fractography of Composite Materials / $cJE Masters.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 4 (December 1982)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFractographic techniques have been increasingly applied to failed specimens in attempts to define micromechanical failure mechanisms in composite materials. This effort can provide useful information relevant to all phases of studies of composite materials. For example, fractographic data obtained from laboratory control specimens can be used in material selection and optimization. Similarly, efficient structural design requires a detailed understanding of the fracture behavior of the material and the modes of failure of the component. Finally, as a production tool, microscopy can be applied to assess the quality of incoming material once key accept/reject features have been identified.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10778J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10784J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10784J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aWardle, MW., $eauthor.
=245  10$aDrop Weight Impact Testing of Laminates Reinforced with Kevlar® Aramid Fibers, E-Glass, and Graphite / $cMW Wardle, EW Tokarsky.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 1 (April 1983)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe instrumented drop weight impact test has been used to study the relative impact damage tolerance of Kevlar®-49 and Kevlar-29 aramid fibers, Thornel®-300 graphite fiber, and E-glass as reinforcements in epoxy-matrix composite materials. Under the conditions of the test, the energy absorbed to failure, defined as the first through crack or the maximum of the load-displacement trace, is proportional to the tensile strain energy to failure of the reinforcing fiber. Thus, the Kevlar fibers, and in particular Kevlar 29, absorb significantly more energy than Thornel 300, while E-glass is intermediate between the two Kevlar fibers. Hybrids with Kevlar 49 and Thornel 300 also absorb more total energy than do all graphite.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEnergy absorption.
=650  \0$aFiber reinforced composites.
=650  \0$aFibers.
=650  \0$aGlass.
=650  \0$aGraphite.
=650  \0$aImpact.
=650  \0$aModulus.
=650  \0$aTensile strength.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=653  10$aImpact.
=653  20$aFibers.
=653  20$aFiber reinforced composites.
=653  20$aKevlar®.
=653  20$aGlass.
=653  20$aGraphite.
=653  20$aEnergy absorption.
=653  20$aTensile strength.
=653  20$aModulus.
=700  1\$aTokarsky, EW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10784J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10785J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10785J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKural, MH., $eauthor.
=245  12$aA Finite Element Analysis of Composite Tension Specimens / $cMH Kural, DL Flaggs.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 1 (April 1983)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe stress state in graphite epoxy tension specimens subjected to pure tension, to combined tension, and to out-of-plane bending is analyzed. A finite element solution technique is used that includes full representation of the wedge-action grip mechanism of the testing machine as well as end tabs bonded to the test laminate with a finite thickness adhesive layer. Results of the study indicate that stresses are generally lower for the tension specimens with tapered tab geometry. Peak stresses in the specimens are found to be sensitive to tab length. thickness, and layer orientation, as well as test laminate stiffness. Out-of-plane specimen bending resulting from grip misalignment also resulted in significant increases in the specimen stresses.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aEccentric loading.
=650  \0$aFinite element analysis.
=650  \0$aGraphite composites.
=650  \0$aTensile stress.
=650  \0$aTension specimens.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aTensile stress.
=653  20$aGraphite composites.
=653  20$aTension specimens.
=653  20$aFinite element analysis.
=653  20$aEccentric loading.
=700  1\$aFlaggs, DL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10785J.htm

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=008  161219c19839999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10786J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10786J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.E6
=082  04$a668/.374$223
=100  1\$aChiu, IL., $eauthor.
=245  13$aAn Epoxy Resin System for Composite Flywheels / $cIL Chiu, JR Kolb, HA Newey.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 1 (April 1983)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aOne component of Lawrence Livermore National Laboratory's (LLNL) flywheel program is the development of new resin systems to serve as matrix materials for fiber-reinforced composites. A resin matrix for filament-wound flywheels must have a combination of characteristics that is normally difficult to achieve and, at times, may be almost mutually exclusive. The needs most prominent are low viscosity for fiber penetration, a long pot life for handling ease, low toxicity, and low cost. Very few resin systems satisfactorily meet each of these criteria. An additional constraint lies within the service temperatures where the flywheel must operate. Three distinct temperature regimes have been defined at 65, 100, and 120°C or higher. For the low-temperature use, a room-temperature-curable resin system with a glass transition temperature (Tg) of approximately 65°C seems satisfactory [1]. For intermediate-temperature uses, a rubberized epoxy resin cured with an aromatic amine (Tg = 104°C) looks promising [2].
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy resins.
=650  \7$aTECHNOLOGY & ENGINEERING / Chemical & Biochemical.
=700  1\$aKolb, JR., $eauthor.
=700  1\$aNewey, HA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10786J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10787J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10787J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aGlaser, RE., $eauthor.
=245  10$aLife Estimation of an S-Glass®/Epoxy Composite Under Sustained Tensile Loading / $cRE Glaser, RL Moore, TT Chiao.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 1 (April 1983)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aLife estimation is crucial in designing fiber composite structures for long-term applications. To study this subject, in 1969 we started an experimental program using simple epoxy composites from S-Glass®, aramid (1971), and some graphite fibers. These impregnated fiber strands were tested for lifetimes (also called stress-rupture or static fatigue) under tension. We selected the strand specimens because they truly represented the basic building blocks of composite structures. As data became available, they were analyzed by different schemes and published during the last decade. In January 1980, a major earthquake in northern California destroyed most of our test specimens. For all practical purposes, this ended our approximately 10-year experiment. The purpose of this article is to review and analyze the available data on the S-Glass/epoxy composite and to make some final comments with regard to the long-term performance of this composite. Plots for life estimation and reliability assessment will be provided for engineering use.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aMoore, RL., $eauthor.
=700  1\$aChiao, TT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10787J.htm

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=001  CTR10788J
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=024  7\$a10.1520/CTR10788J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10788J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHahn, HT., $eauthor.
=245  12$aA Mixed-Mode Fracture Criterion for Composite Materials / $cHT Hahn.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 1 (April 1983)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe failure of composite laminates is invariably preceded by the cracking of matrix and interface, which appears as the cracking of unidirectional plies along the fibers and as delamination between plies. Since the ply cracking and delamination appear as macroscopically self-similar crack extension at least within each ply, they are amenable to the linear elastic fracture analysis.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10788J.htm

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=001  CTR10793J
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=024  7\$a10.1520/CTR10793J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10793J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNunes, J., $eauthor.
=245  10$aTensile Property Evaluation of Polycrystalline Alumina Filaments and Their Composites / $cJ Nunes.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 2 (July 1983)
=504  \\$aIncludes bibliographical references$b25.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe tensile failure stresses of polycrystalline alumina filaments (DuPont Fiber FP) were experimentally measured and statistically evaluated for several different gage lengths 1.27, 2.54, 5.0, 7.6, 12.7, and 25.4 cm. Static and dynamic tensile elastic moduli results also are reported, and a method for determining the true fiber gage length is described.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAluminum oxide.
=650  \0$aComposites.
=650  \0$aFiber composites.
=650  \0$aStresses.
=650  \0$aTensile strength.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aStresses.
=653  20$aTensile strength.
=653  20$aFiber composites.
=653  20$aAluminum oxide.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10793J.htm

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=001  CTR10794J
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=024  7\$a10.1520/CTR10794J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10794J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNemeth, MP., $eauthor.
=245  10$aOn the Off-Axis Tension Test for Unidirectional Composites / $cMP Nemeth, CT Herakovich, D Post.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 2 (July 1983)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe off-axis tension test was examined experimentally to obtain actual displacement fields over the surface of graphite-polyimide coupon specimens; the experimental results were compared with the approximate analytical solution of Pagano and Halpin and newly generated finite-element results. A new optical method of high-sensitivity moiré interferometry was used to determine the actual displacements to high precision. It is shown that the approximate analytical solution and the finite-element results compare very favorably with the measured centerline displacements in the test section, and the finite-element displacement fields provide excellent agreement with the moiré displacements throughout the specimen. Results are presented for a 15° fiber orientation and coupon aspect ratios of 5 and 15.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDisplacement.
=650  \0$aExperimentation.
=650  \0$aFinite elements.
=650  \0$aMoiré effects.
=650  \0$aOff axis.
=650  \0$aStresses.
=650  \0$aTheories.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aMoiré effects.
=653  20$aDisplacement.
=653  20$aStresses.
=653  20$aTheories.
=653  20$aExperimentation.
=653  20$aOff axis.
=653  20$aFinite elements.
=700  1\$aHerakovich, CT., $eauthor.
=700  1\$aPost, D., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10794J.htm

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=001  CTR10795J
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=008  161219c19839999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10795J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10795J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/4$223
=100  1\$aPrewo, KM., $eauthor.
=245  10$aSilicon Carbide Yarn Stimulates Development of New Composites / $cKM Prewo.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 2 (July 1983)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe creation of new types of fibers has, in the past, stimulated the development of equally new composites. Besides the most commonly used glass and graphite fiber types, a number of newer ceramic fibers have been introduced: Fiber FP® by DuPont and 3M Company's Nextel® are two recent examples. In addition, a silicon carbide yarn is currently available from the Nippon Carbon Company of Japan. This last fiber, called Nicalon®, has created a great deal of interest because of its unique suitability for reinforcement of resin, metal, and ceramic matrix composites. I will briefly describe some of the characteristics of this ceramic yarn and the composites that have been fabricated with it. While these data are of interest, it is probably more important that this fiber has stimulated wide enthusiasm for fibers and ceramics created from organometallic precursors.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCeramic-matrix composites.
=650  \0$aPolymeric composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10795J.htm

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=024  7\$a10.1520/CTR10796J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10796J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aReifsnider, KL., $eauthor.
=245  10$aGeneric Aspects of Three-Dimensional Internal-Damage Development in Fatigue-Loaded Composite Laminates / $cKL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 2 (July 1983)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFatigue loading is a common and important engineering problem in applications involving loads that vary in amplitude with time. Cyclic loads, a common type of variable load, can be characterized as cyclic stress amplitudes superimposed on "steady" stresses. It is well known that fatigue-load amplitudes of roughly half the ultimate strength of a given material can cause the material to fail after a large number (on the order of 106) of load cycles. The weakness of such a loaded material indicates a corresponding degree of damage development. The amount of damage and its consequences must be great to reduce the strength of long-life specimens to the low level of applied stress corresponding to most engineering applications.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10796J.htm

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=001  CTR10801J
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=024  7\$a10.1520/CTR10801J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10801J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.12
=082  04$a620.1129$223
=100  1\$aAgarwal, BD., $eauthor.
=245  12$aA Stress Separation Technique for Photo-Orthotropic Elasticity / $cBD Agarwal, PK Jha.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 3 (October 1983)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA stress separation technique using an approximate strain-optic law has been developed for photo orthotropic elasticity. The technique is similar to the shear difference method of stress separation used in photoelasticity of isotropic materials and involves stepwise numerical integration. The technique has been illustrated through its application to the analysis of a circular disk of orthotropic material under diametral compression.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompressing.
=650  \0$aFiber composites.
=650  \0$aPhotoelasticity.
=650  \0$aStrains.
=650  \0$aStress analysis.
=650  \0$aPhotoelastic method.
=650  \0$aElasticity.
=653  10$aPhotoelasticity.
=653  20$aStress analysis.
=653  20$aStrains.
=653  20$aFiber composites.
=653  20$aCompressing.
=700  1\$aJha, PK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10801J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10802J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10802J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aXing-Hua, P., $eauthor.
=245  10$aShear Characteristics of Glass Fiber/Epoxy Laminates / $cP Xing-Hua, Y Zhen-Min, W Shuo.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 3 (October 1983)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis article reports the shear characteristics within 1% strain of three typical glass fiber/epoxy laminates commonly used in engineering. By using acoustic-emission and microstructure analysis, correlation of the stress-strain curve with the microstructure of interface cracks and fiber fractures can provide experimental data for the determination of design allowables.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=700  1\$aZhen-Min, Y., $eauthor.
=700  1\$aShuo, W., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10802J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10803J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10803J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aKong, F-M, $eauthor.
=245  10$aStress-Optical Microscopy Studies of the Microscopic Deformation and Failure Modes of Kevlar 49/Epoxy Composites / $cF-M Kong, CO Pruneda, RJ Morgan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 3 (October 1983)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe increasing use of Kevlar 49/epoxy composites in critical structural applications has led to a concern for their ability to maintain structural integrity over long periods. In order to predict their durability with confidence, we must understand their microscopic deformation and failure modes as well as the roles played by the fiber, epoxy matrix, and fiber-matrix interface in composite performance.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aPruneda, CO., $eauthor.
=700  1\$aMorgan, RJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10803J.htm

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=024  7\$a10.1520/CTR10804J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10804J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aChiao, TT., $eauthor.
=245  10$aNo-Stress Aging of Aramid/Epoxy Composites / $cTT Chiao, RL Moore, HT Hahn.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 3 (October 1983)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aEnvironmental degradation of composite materials is of serious concern for many long-term applications. This is particularly true in the case of aramid/epoxy composites because both the reinforcing fiber and the matrix are organic materials. Over the past decade, we have collected limited data on no-stress aging of these materials, which we summarize here. We aged the test specimens in three environments: (1) 20 to 23°C, 20 to 55% relative humidity (RH), no fluorescent lighting; (2) 20 to 28°C, 24 to 37% RH, with fluorescent lighting; and (3) outdoor weathering in San Ramon, CA. When the composite strands and vessels were stored in the dark (indoors), we found no noticeable strength degradation in ambient environment for up to ten years.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \0$aAramid/epoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aMoore, RL., $eauthor.
=700  1\$aHahn, HT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10804J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10808J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10808J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTP261.G7
=082  04$a662/.92$223
=100  1\$aHurwitz, FI., $eauthor.
=245  14$aThe Effect of a Coating on the Thermo-Oxidative Stability of Celion 6000 Graphite Fiber/PMR 15 Polyimide Composites / $cFI Hurwitz, JD Whittenberger.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 4 (December 1983)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe thermo-oxidative stability in air at 316°C of unidirectional uncoated and aluminum coated Celion 6000 graphite fiber/PMR 15 polyimide composites has been determined for exposure times up to nominally 2000 h. Comparison of the weight loss data and microstructural integrity reveals that a thin aluminum-foil coating can provide significant protection from oxidation. A quantitative description of the average depth of the reaction zone and the maximum length of cracks produced during oxidation as a function of time in uncoated Celion 6000/PMR 15 are given.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAluminum foil.
=650  \0$aCarbon fibers.
=650  \0$aComposite materials.
=650  \0$aGraphite composites.
=650  \0$aOxidizing atmospheres.
=650  \0$aGraphene.
=650  \0$aGraphitization.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aComposite materials.
=653  20$aAluminum foil.
=653  20$aGraphite composites.
=653  20$aCarbon fibers.
=653  20$aOxidizing atmospheres.
=700  1\$aWhittenberger, JD., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10808J.htm

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=024  7\$a10.1520/CTR10809J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10809J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aHodson, J., $eauthor.
=245  14$aThe Deformation and Failure Processes of Kevlar 49 Single Filaments / $cJ Hodson, CO Pruneda, RP Kershaw, RJ Morgan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 4 (December 1983)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aKevlar 49 fibers [poly (p-phenylene terephthalamide), or PPTA] are increasingly utilized in high-performance fibrous epoxy composites in critical structural applications in which they are expected to maintain their structural integrity over long time periods. To predict the fiber durability with confidence requires a detailed understanding of the deformation and failure processes of the fiber and the structural and environmental factors that affect such processes.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aPruneda, CO., $eauthor.
=700  1\$aKershaw, RP., $eauthor.
=700  1\$aMorgan, RJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10809J.htm

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=024  7\$a10.1520/CTR10810J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10810J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aHunston, DL., $eauthor.
=245  10$aEffects of Lay-Up, Temperature, and Loading Rate in Double Cantilever Beam Tests of Interlaminar Crack Growth / $cDL Hunston, WD Bascom.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 4 (December 1983)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe increasing interest in the problem of delamination in composites has led to many experiments designed to help characterize and evaluate interlaminar crack growth. For the particular area of predominantly Mode-I type loading, most studies have focused on various versions of the double cantilever beam (DCB) geometry [1-6]. In order to establish this test as a general quantitative method, however, it is necessary to examine in a complete and systematic way all of the parameters that may affect the results. These parameters include fiber orientation, specimen size and shape, fiber volume fraction, matrix and fiber type, temperature and loading rate, environmental effects, and data analysis methods. Although some of these parameters have been examined, the results are often incomplete or not reported in the open literature. As a result, a cooperative program involving the National Bureau of Standards, NASA Langley Research Center, the University of Illinois, Hercules Inc., and other industrial suppliers was initiated to examine the DCB specimen in a comprehensive way. This note reports some preliminary results with respect to the effects of fiber lay-up pattern, test temperature, and loading rate on interlaminar fracture as measured by this specimen.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aBascom, WD., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10810J.htm

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=024  7\$a10.1520/CTR10811J$2doi
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=037  \\$aCTR10811J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA660.T34
=082  04$a681/.76041$223
=100  1\$aHamstad, MA., $eauthor.
=245  10$aAging Results for PRD 49 III/Epoxy and Kevlar 49/Epoxy Composite Pressure Vessels / $cMA Hamstad.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1983.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 5, Issue 4 (December 1983)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aKevlar 49/epoxy composite is growing in use as a structural material because of its high strength-to-weight ratio. Currently, it is used for the Trident rocket motor case and for various pressure vessels on the Space Shuttle. In 1979, we published the initial results for aging of filament-wound cylindrical pressure vessels which were manufactured with preproduction Kevlar 49 [1]. This preproduction fiber was called PRD 49 III. This report updates the continuing study to 10-year data and also presents 7.5-year data for spherical pressure vessels wound with production Kevlar 49. For completeness, this report will again describe the specimens of the original study with PRD 49 as well as specimens for the new study with Kevlar 49.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1983. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aPressure vessels.
=650  \0$aStructural engineering.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10811J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10817J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10817J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aWang, ASD, $eauthor.
=245  10$aFracture Mechanics of Sublaminate Cracks in Composite Materials / $cASD Wang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (18 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 2 (July 1984)
=504  \\$aIncludes bibliographical references$b58.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper presents an overview of a fracture-mechanics approach to some of the most frequently encountered matrix-dominated sublaminate cracks in epoxy-based composite laminates. By "sublaminate," it is meant that the cracks are internal to the laminate, generally invisible macroscopically, but are much larger in size than those microcracks considered in the realm of micromechanics. The origin of sublaminate cracks is assumed to stem from the coalesence of natural material flaws (also microcracks), which occur under a certain favorable laminate stress condition. Thus, the modeling of the mechanisms of sublaminate crack initiation and propagation is essentially mechanistic and probabilistic in nature. Some specific results from several analytical/experimental investigations using graphite-epoxy laminates are presented and discussed in this paper.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCracks.
=650  \0$aDelamination.
=650  \0$aFailure modes sequence.
=650  \0$aFinal failure mechanisms.
=650  \0$aFracture mechanics.
=650  \0$aMacroscopic analysis.
=650  \0$aMechanistic modeling.
=650  \0$aStochastic processes.
=650  \0$aStochastic simulations.
=650  \0$aSublaminate cracks interaction.
=650  \0$aTransverse cracks.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCracks.
=653  20$aStochastic processes.
=653  20$aDelamination.
=653  20$aMacroscopic analysis.
=653  20$aFracture mechanics.
=653  20$aTransverse cracks.
=653  20$aMechanistic modeling.
=653  20$aStochastic simulations.
=653  20$aSublaminate cracks interaction.
=653  20$aFinal failure mechanisms.
=653  20$aFailure modes sequence.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10817J.htm

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=024  7\$a10.1520/CTR10818J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10818J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aYaniv, G., $eauthor.
=245  10$aHygrothermal Effects on Stresses and Deformations in a Bonded Fiber-Reinforced Plastic/Aluminum System / $cG Yaniv, O Ishai.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 2 (July 1984)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe hygrothermal effect on time dependent mechanical behavior of a model of nonsymmetrical bonded fiber-reinforced plastic (FRP)/aluminum system was investigated analytically. It was found that a linear viscoelastic closed form solution is sufficient for the prediction of model deformations for short periods of time and small strains, while a numerical finite-element solution is preferable for determining adhesive stresses and deformational behavior of the model at any time. The thermoelastic numerical solution shows a certain decrease with time of adhesive stresses, which does not seem to affect significantly the global deformations of the model. On the other hand, it was found that the presence of moisture within the polymeric adhesive layer causes significant decrease in adhesive stresses, which affects deformational changes with time, far beyond the level predicted by the static solution.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBonded systems.
=650  \0$aFinite-element method.
=650  \0$aHygrothermal effects.
=650  \0$aInterlaminar stresses.
=650  \0$aStress relaxation.
=650  \0$aThermoelasticity.
=650  \0$aViscoelasticity.
=650  \0$aFinite element analaysis.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aViscoelasticity.
=653  20$aThermoelasticity.
=653  20$aHygrothermal effects.
=653  20$aInterlaminar stresses.
=653  20$aStress relaxation.
=653  20$aBonded systems.
=653  20$aFinite-element method.
=700  1\$aIshai, O., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10818J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10819J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10819J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aTsiang, T-H, $eauthor.
=245  10$aSurvey of Bolted-Joint Technology in Composite Laminates / $cT-H Tsiang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 2 (July 1984)
=504  \\$aIncludes bibliographical references$b64.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aMechanically fastened joints in composites with variations in both laminate properties and joint configurations have been tested and evaluated in numerous works. Indications are that bolted joints for multiorientation laminates can be structurally efficient and cost effective. The specific static strength of joints in fiber composites can be significantly better than those in metals. As described in the following review, there are several dominant aspects of the bolt-bearing problem in composites, including stress analysis as complicated by anisotropy, heterogeneity and bolt-hole interaction, stable damage development and associated local failure criteria, reduction of stress concentration factors by damage development, and final failure modes and criteria.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBolted joints.
=650  \7$aTECHNOLOGY & ENGINEERING $xMachinery.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10819J.htm

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=030  \\$aJCTRER
=037  \\$aCTR10820J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHappe, JA., $eauthor.
=245  10$aNMR Characterization of Boron Trifluoride-Amine Catalysts Used in the Cure of Carbon Fiber/Epoxy Prepregs / $cJA Happe, RJ Morgan, CM Walkup.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 2 (July 1984)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDiaminodiphenyl sulfone (DDS) cured tetraglycidyl 4,4' diaminodiphenyl methane (TGDDM) epoxies are the most common composite matrices utilized in high-performance fibrous composites.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFibrous composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aMorgan, RJ., $eauthor.
=700  1\$aWalkup, CM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10820J.htm

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=024  7\$a10.1520/CTR10821J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10821J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aHartung, W., $eauthor.
=245  10$aInfluence of a Simulated Space Environment on the Behavior of Carbon-Fiber-Reinforced Plastics with ±45° Ply Orientations-Part 1 / $cW Hartung, HW Bergmann.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 2 (July 1984)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe growing dimensions of spacecraft foreseen for the future pose new challenges concerning mass, dynamic behavior, dimensional stability, and reliability. Because of their attractive structural properties, graphite/epoxy or graphite/polymide composites are the prime material candidates for such applications. Besides their specific strength and stiffness properties, they offer low coefficients of thermal expansion so that deformations of the structures under temperature exposure can be held to a minimum. However, on the microscopic level, the large differences in thermal-expansion coefficients between the resins and the fibers lead to thermally induced stresses of substantial magnitude when the material undergoes thermal cycling as a consequence of sun and shadow phases in an earth orbit. The corresponding upper and lower temperature limits depend on the surface coating of the structure and on the attitude angle relative to the sun. They may range from −160°C in deep shadow to +100°C and even more when exposed to the sun. Depending on orbit height, inclination, and service time, 3000 to 5000 thermal cycles may occur during the life of a typical vehicle and thereby introduce thermal fatigue problems in the material. Additionally, electromagnetic and particle irradiation may degrade the properties of the organic matrix.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=700  1\$aBergmann, HW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10821J.htm

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=001  CTR10826J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10826J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10826J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aLal, KM., $eauthor.
=245  10$aRelationship Between Phase Difference and Coefficient of Restitution During Low Velocity Foreign Object Transverse Damage of Composite Plates / $cKM Lal.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 3 (October 1984)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis work discusses a model to correlate the coefficient of restitution of low velocity transverse impacts of graphite-epoxy laminates with the residual deformation or central deflection at the end of the impact event. It is assumed that the energy absorbed by the target can be calibrated in terms of residual deflection, and thereby in terms of phase difference between the occurrence of impact force and central deflection to their maximas. Analysis was modeled on the basis of the experience from impact tests. Predictions are compared with the test results of impacted circular and flat plates. Experimentally measured values of coefficient of restitution and phase difference agreed well with the predicted relationship between them.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy laminates.
=650  \0$aGraphite composites.
=650  \0$aImpact.
=650  \0$aPlates.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aImpact.
=653  20$aPlates.
=653  20$aEpoxy laminates.
=653  20$aGraphite composites.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10826J.htm

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=024  7\$a10.1520/CTR10827J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10827J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aLal, KM., $eauthor.
=245  10$aCoefficient of Restitution for Low Velocity Transverse Impact of Thin Graphite-Epoxy Laminates / $cKM Lal.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 3 (October 1984)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper discusses a simple model to study low velocity transverse impact of thin plates made of fiber-reinforced composite material, in particular, T300/5208 graphite-epoxy. This model predicts the coefficient of restitution, which is a measure of the energy absorbed by the target during an impact event. The model is constructed on the assumption that the plate is inextensible in the fiber direction and that the material is incompressible in the z direction. Such a plate essentially deforms by shear, hence, this model neglects bending deformations of the plate. The coefficient of restitution is predicted to increase with large interlaminar shear strength and low transverse shear modulus of the laminate.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCoefficients.
=650  \0$aGraphite composites.
=650  \0$aImpact strength testing.
=650  \0$aLaminates.
=650  \0$aShear strength.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aImpact strength testing.
=653  20$aShear strength.
=653  20$aLaminates.
=653  20$aGraphite composites.
=653  20$aCoefficients.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10827J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10828J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10828J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aBlake, RA., $eauthor.
=245  10$aComputer-Aided Ultrasonic Evaluation of Fiber FP Metal Matrix Composites / $cRA Blake, HS Hartmann.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 3 (October 1984)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA computer based digital analyzer was used to evaluate the time domain ultrasonic waveforms of Fiber FP reinforced magnesium and aluminum composites. Digital amplitude signature evaluation was correlated with photomicrographic examination to provide a quantitative base for transducer selection and implementation of advanced signal and image processing techniques.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aComputers.
=650  \0$aDigital computers.
=650  \0$aTransducers.
=650  \0$aUltrasonic tests.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComputers.
=653  20$aDigital computers.
=653  20$aUltrasonic tests.
=653  20$aComposites.
=653  20$aTransducers.
=700  1\$aHartmann, HS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10828J.htm

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=001  CTR10829J
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=024  7\$a10.1520/CTR10829J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10829J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aReifsnider, KL., $eauthor.
=245  10$aEngineering Life Prediction of Composite Materials : $bElements of a Mechanistic Model / $cKL Reifsnider.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 3 (October 1984)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIt is the practice in engineering to attempt to avoid problems that we do not understand; such is frequently the case for damage development in composite materials. The prudent designer prescribes design strain levels low enough so that damage development is thought to be precluded. However, something should be known of damage development if it is to be avoided, and the basic question of how long a particular structure will last cannot be answered without some understanding of damage development in composite materials. As new material systems and applications are developed and as old ones are further exploited, a more and more precise understanding of damage development will be required. What is needed is a rational analysis that can be used to describe and explain damage development in composite laminates so that we can anticipate their residual strength, stiffness, and life under engineering conditions. In general, this requires a replacement for the single-crack problem (and fracture mechanics) in homogeneous isotropic materials.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10829J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10830J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10830J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aHartung, W., $eauthor.
=245  10$aInfluence of Simulated Space Environment on the Behavior of Carbon-Fiber-Reinforced Plastics with ±45° Ply Orientations-Part 2 / $cW Hartung, HW Bergmann.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 3 (October 1984)
=504  \\$aIncludes bibliographical references$b1.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe first part of this paper [1] described the nondestructive evaluation of ±45° carbon-fiber-reinforced plastic (CFRP) laminates before and after exposure to thermal cycling or electron irradiation. In contrast to predictions based on computational analyses, only minor matrix cracking could be observed in the graphite/epoxy laminates. The effects of different types of fibers in the prepregs and of different curing temperatures of the epoxy resins were negligible. The polyimide-based laminate, however, suffered both severe cracking and delaminations due to thermal cycling.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aBergmann, HW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10830J.htm

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=001  CTR10831J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19849999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10831J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10831J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aPenn, LS., $eauthor.
=245  10$aStudies on Bonding at the Aramid-Epoxy Interface / $cLS Penn, TK Liao.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 3 (October 1984)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn fiber composites, several micromechanical processes can contribute to damage accumulation and final failure. One of these processes is debonding at the fiber-matrix interface. Interfacial debonding has been identified as a distinct event in high-performance composites such as aramid/epoxy and graphite/epoxy [1-4].
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \0$aAramid/epoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aLiao, TK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10831J.htm

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=024  7\$a10.1520/CTR10836J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10836J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aRotem, A., $eauthor.
=245  10$aFracture Modes Identification of Composite Materials by Acoustic Emission Analysis / $cA Rotem.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (14 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 4 (December 1984)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAcoustic emission technique was used to monitor the failure modes of multidirectional composite laminates when loaded to 30% of their ultimate. It is shown that each failure mode, that is, fiber fracture, in-plane cracking, and interlaminar cracking, has a different amplitude function when it is presented by normalized parameters. But the discrimination between in-plane matrix cracking and interlaminar matrix cracking is not clear, and another tool is used to discriminate between them, the variation of ring-down period with pulse length. Penny shape artificial delamination also produces unique amplitude distribution that has a smaller slope than the amplitude distribution from free-edge delamination.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAcoustic emission.
=650  \0$aComposite materials.
=650  \0$aComposites.
=650  \0$aFracture modes.
=650  \0$aFractures (materials)
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFractures (materials).
=653  20$aComposite materials.
=653  20$aComposites.
=653  20$aAcoustic emission.
=653  20$aFracture modes.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10836J.htm

=LDR  03798nam  2200721 i 4500
=001  CTR10837J
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=008  161219c19849999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10837J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10837J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMahishi, JM., $eauthor.
=245  10$aAnalysis of Neat Resin Cracking Induced by Rapid Moisture Loss / $cJM Mahishi, DF Adams.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 4 (December 1984)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDuring routine moisture conditioning of neat (unreinforced) resin test specimens of two different types of epoxy polymers, the active humidity control of the chamber failed, causing a rapid drop in the humidity level. Approximately half of the specimens of one material cracked while none of the specimens of the other material were damaged. The accident was later recreated, monitoring the cracking as a function of time using acoustic emission sensors mounted on individual specimens, while also recording the relative humidity decrease as a function of time. An analytical study was also performed, using a finite-element finite-difference technique to predict the moisture gradients in the specimens and a finite-element analysis to predict the initiation and propagation of cracking as a function of time. The results presented here demonstrate the ability to predict cracking and indicate the material parameters that dominate the process.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAcoustic emission.
=650  \0$aComposites.
=650  \0$aCrack propagation.
=650  \0$aEpoxy matrix.
=650  \0$aEpoxy resins.
=650  \0$aFinite-element analysis.
=650  \0$aMoisture effects.
=650  \0$aNeat resin.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aEpoxy resins.
=653  20$aCrack propagation.
=653  20$aNeat resin.
=653  20$aEpoxy matrix.
=653  20$aMoisture effects.
=653  20$aAcoustic emission.
=653  20$aFinite-element analysis.
=700  1\$aAdams, DF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10837J.htm

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=001  CTR10838J
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=008  161219c19849999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10838J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10838J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aGlaser, RE., $eauthor.
=245  10$aTheoretical Relations Between Static Strength and Lifetime Distributions of Composites : $bAn Evaluation / $cRE Glaser, RM Christensen, TT Chiao.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 4 (December 1984)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe present work is concerned with the stress rupture behavior of S-Glass® fiber/epoxy matrix composites. The prime objective is to relate static strength behavior to the lifetime characteristics under the constant load conditions of stress rupture. A specific theoretical model is used to interrelate a large experimental data base on S-Glass composites.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \0$aEpoxy matrix composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aChristensen, RM., $eauthor.
=700  1\$aChiao, TT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10838J.htm

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=001  CTR10839J
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=007  cr\\\\\\\\\\\\
=008  161219c19849999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10839J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10839J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA409
=082  04$a620.1/126$223
=100  1\$aClements, LL., $eauthor.
=245  10$aFractography Used to Identify Defective 0° Graphite/Epoxy Specimens / $cLL Clements.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 4 (December 1984)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aTest results on composite materials are frequently plagued by a few inexplicably low or otherwise anomalous results. Even though the researcher may suspect that there was some type of undetected flaw, scientific honesty dictates that, without further evidence, the data remain in the statistical results. This problem is particularly common for 0° and 90° unidirectional laminates, where the statistical deviations introduced by these "anomalies" may overwhelm any changes introduced by the variables of actual interest.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFractography.
=650  \0$aComposite materials.
=650  \0$aMaterials.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10839J.htm

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=001  CTR10840J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19849999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10840J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10840J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA450
=082  04$a620.1/4492$223
=100  1\$aKong, ES-W, $eauthor.
=245  10$aMoisture Diffusion and Solid-State NMR Investigations on the Physical Aging Processes in Network Epoxy Glasses / $cES-W Kong, M Adamson, L Meuller.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 4 (December 1984)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA polymer does not, in general, reach thermodynamic equilibrium when quenched through its glass-transition temperature Tg because the motion of the polymer chains is impaired owing to the increase in viscosity. Thus, the polymer cannot reach its equilibrium conformation or degree of packing. One characteristic of the quenched glassy state is an excess of trapped free volume, and a consequence is a lowering of the bulk polymer density. This change in free volume also alters the molecular mobility and hence influences the segmental relaxation times.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aPhysical Aging.
=650  \0$aGlasses.
=700  1\$aAdamson, M., $eauthor.
=700  1\$aMeuller, L., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10840J.htm

=LDR  03673nam  2200553 i 4500
=001  CTR10841J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19849999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10841J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10841J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA409
=082  04$a620.1/26$223
=100  1\$aAgarwal, BD., $eauthor.
=245  10$aPrediction of Instability Point During Fracture of Composite Materials / $cBD Agarwal, BS Patro, P Kumar.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 4 (December 1984)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe crack growth resistance (R curve) approach [1,2] has been widely used to analyze fracture test results on composite materials [3-6]. The method requires measurement of instantaneous crack length with increasing load in a fracture test. In homogeneous materials, the crack is well defined and can be easily measured at any instant. However, fractures in composite materials proceed not by a simple enlargement of the original crack but by formation of a large number of microcracks due to debonding, matrix cracking, and fiber breaks. An instantaneous crack length is difficult to define or measure. Consequently, instantaneous crack length is estimated through a compliance matching procedure [7]. By applying this procedure, point by point, the complete load-crack opening displacement (COD) curve is transformed to an R curve. Fracture toughness of the composite is then obtained by locating the point of instability on the R curve. The process is tedious and time consuming and may reduce accuracy. This technical note mathematically establishes the point of instability on the load-COD curve, which eliminates the necessity of transforming the entire load-COD curve and thus saves time and increases accuracy in obtaining the fracture toughness.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFracture mechanics.
=650  \0$aFracture of materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aPatro, BS., $eauthor.
=700  1\$aKumar, P., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10841J.htm

=LDR  03139nam  2200517 i 4500
=001  CTR10842J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19849999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10842J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10842J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aHunston, DL., $eauthor.
=245  10$aComposite Interlaminar Fracture : $bEffect of Matrix Fracture Energy / $cDL Hunston.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 4 (December 1984)
=504  \\$aIncludes bibliographical references$b26.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aNumerous recent studies of composite delamination behavior have used the double cantilever beam test to provide a measure of the interlaminar fracture energy of a composite subjected to simple Mode-1 type loading. A major result from these tests has been the observation that increasing the toughness of the matrix resin by a large amount, say twenty-fold, produced a major (approximately fourfold) benefit in this interlaminar fracture energy [1-7]. At present, however, the detailed relationship between resin and composite interlaminar behaviors has not been clearly established because no single study has examined resins with a wide enough range of toughnesses. The purpose of this note is to combine the data from three recent papers [6,8,9] in an effort to make such a comparison for simple Mode-I type loading.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10842J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10848J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10848J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aAbedian, A., $eauthor.
=245  10$aResidual Thermal Stresses in Metallic and Intermetallic Matrix Composites After Cooling from Processing Temperature / $cA Abedian, W Szyszkowski, S Yannacopoulos.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1998.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 3 (July 1998)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThermal stresses induced during cooling from the fabrication to ambient temperatures of SCS-6/Ti-6Al-4V and SCS-6/Ti-24Al-4Nb composites are analyzed applying the finite element method. The matrix is modeled as a bilinear elasto-plastic material with work and kinematic hardening. Thermo-mechanical properties of both the fiber and the matrix are temperature dependent. Effects of the free surface of the composite are included in the analysis. It is shown that during cooling the matrix behavior may switch from elastic to elastoplastic and back to elastic. In particular, for the Ti-6Al-4V matrix, the stresses remain below the yield limit and the cooling process is elastic at the beginning (at high temperature) and also when approaching room temperature.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1998. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite material.
=650  \0$aFinite element method.
=650  \0$aMicromechanics.
=650  \0$aPlastic deformation.
=650  \0$aThermal residual stress.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aFinite element method (FEM).
=653  20$aComposite material.
=653  20$aThermal residual stress.
=653  20$aPlastic deformation.
=653  20$aMicromechanics.
=700  1\$aSzyszkowski, W., $eauthor.
=700  1\$aYannacopoulos, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10848J.htm

=LDR  04178nam  2200661 i 4500
=001  CTR10849J
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=024  7\$a10.1520/CTR10849J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10849J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQA403
=082  04$a515.2433$223
=100  1\$aPieracci, A., $eauthor.
=245  10$aNonlinear Analyses of Homogeneous, Symmetrically Delaminated Single Leg Bending Specimens / $cA Pieracci, BD Davidson, V Sundararaman.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1998.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 3 (July 1998)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aEnergy release rates obtained by geometrically linear and geometrically nonlinear finite element analyses of homogeneous, symmetrically delaminated single leg bending specimens are presented for a variety of materials, specimen geometries and fixture dimensions. It is shown that certain test geometries will exhibit strong nonlinear effects; thus, critical energy release rates obtained from tests of these geometries, using data reduction procedures that are based on linear theory, may contain significant errors. The nonlinear finite element results are used to develop empirical relationships between energy release rate as predicted by the nonlinear analyses and those predicted by linear analyses. These empirical relationships are shown to be valid over a wide range of specimen material properties, material property ratios (e.g., Young's modulus to shear modulus) and geometric properties of both the specimen and fixture, including fixture roller diameters. Thus, the empirical relationships may be used in a quantitative manner to design tests in order that significant nonlinear effects do not occur prior to fracture, and hence linear data reduction procedures remain valid. Alternatively, the empirical relationships may be used to interpret test results where nonlinear behavior occurs. Both uses are illustrated by example for typical laminated composite materials.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1998. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDelamination.
=650  \0$aEnergy release rate.
=650  \0$aNonlinear finite element analysis.
=650  \0$aSingle leg bending specimen.
=650  \0$aTesting design procedure.
=650  \0$aHomogeneous Analyses.
=650  \0$aHomogeneous.
=653  10$aSingle leg bending specimen.
=653  20$aNonlinear finite element analysis.
=653  20$aTesting design procedure.
=653  20$aEnergy release rate.
=653  20$aDelamination.
=700  1\$aDavidson, BD., $eauthor.
=700  1\$aSundararaman, V., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10849J.htm

=LDR  03789nam  2200709 i 4500
=001  CTR10850J
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=024  7\$a10.1520/CTR10850J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10850J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aNicholas, T., $eauthor.
=245  10$aFatigue Life Prediction of Titanium Matrix Composites Under Mission Spectrum Loading / $cT Nicholas, AH Rosenberger.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1998.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 3 (July 1998)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFatigue life predictions are conducted for a high temperature composite for hypersonic vehicle structural applications. A SCS-6/Timetal® 21S [0/90]s composite is evaluated under thermomechanical fatigue (TMF) as well as under typical hypersonic mission profiles and segments of those missions. The fatigue life analysis is based on micromechanical stresses which, in turn, are input into a damage summation model. Spectrum loading is decomposed into a series of in-phase and out-of-phase TMF segments whose lives are predicted from a life fraction model which was developed for isothermal and TMF data. Analytical predictions for the mission spectrum and the simple mission profiles are compared with experimental data obtained here as well as in a previous study. The model is demonstrated to be able to predict fatigue life under mission spectrum loading based solely on calibration under simple isothermal fatigue and TMF conditions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1998. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aElevated temperature.
=650  \0$aFatigue.
=650  \0$aLife prediction.
=650  \0$aMicromechanics.
=650  \0$aSpectrum loading.
=650  \0$aThermomechanical fatigue.
=650  \0$aTitanium matrix composites.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aTitanium matrix composites.
=653  20$aThermomechanical fatigue.
=653  20$aLife prediction.
=653  20$aMicromechanics.
=653  20$aSpectrum loading.
=653  20$aFatigue.
=653  20$aElevated temperature.
=700  1\$aRosenberger, AH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10850J.htm

=LDR  03988nam  2200685 i 4500
=001  CTR10851J
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=024  7\$a10.1520/CTR10851J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10851J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.A3
=082  04$a668/.3$223
=100  1\$aVintilescu, I., $eauthor.
=245  10$aFracture Load Predictions for Adhesive Joints Under Mixed Mode I-II-III Loading / $cI Vintilescu, JK Spelt.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1998.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 20, Issue 3 (July 1998)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aApplication of a method for predicting the fracture strength of adhesive joints under mixed mode I-II-III conditions is presented. The expressions used for the average energy release rate in Mode I, Mode II and Mode III along the idealized straight crack front of a cracked, generalized adhesive sandwich are based on a beam-on-elastic foundation model. Fracture experiments were performed with obliquely loaded unequal-adherend split-cantilever-beam (SCB) specimens of different widths and loading angles, using two different epoxy adhesives. The fracture strengths agreed reasonably well with predictions based on the previously measured fracture envelopes (Gc vs. mode ratio) obtained for these epoxies using equal-adherend obliquely loaded SCB specimens. It was seen that the fracture surface had an arrowhead shape for small loading angles (similar to that of SCB-type specimens), and a thumbnail shape for larger loading angles (similar to that of double-cantilever-beam (DCB)-type specimens). Moreover, a sharp step was observed in the thickness of the residual adhesive half-way across the specimen width. As in the case of equal-adherend specimens, the addition of Mode I greatly reduced GC, and caused the effect on GC of Mode II to be similar to that of Mode III.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1998. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive joints.
=650  \0$aEnergy release rate.
=650  \0$aFracture.
=650  \0$aMixed-mode.
=650  \0$aSplit cantilever beam.
=650  \0$aAdhesive bonding.
=650  \0$aGlued joints.
=653  10$aFracture.
=653  20$aAdhesive joints.
=653  20$aMixed-mode.
=653  20$aMode I.
=653  20$aMode II.
=653  20$aMode III.
=653  20$aEnergy release rate.
=653  20$aSplit cantilever beam.
=700  1\$aSpelt, JK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10851J.htm

=LDR  02687nam  2200517 i 4500
=001  CTR10855J
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=008  161219c19809999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10855J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10855J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aPing, XH., $eauthor.
=245  10$aMeasuring In-Plane Shear Properties of Glass-Fiber/Epoxy Laminates / $cXH Ping.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 2 (April 1980)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFor design analysis of the fiber composite propeller blade, the moduli and strengths of two commonly used typical laminates consisting of a 50-vol % glass fiber in an epoxy were determined. Three basic test methods for determining in-plane shear properties of glass/epoxy laminates were evaluated: twist, shear, and off-axis tensile. The advantages and disadvantages of these methods are explained from the experimental viewpoint.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10855J.htm

=LDR  02779nam  2200541 i 4500
=001  CTR10856J
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=007  cr\\\\\\\\\\\\
=008  161219c19809999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10856J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10856J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aJamison, RD., $eauthor.
=245  10$aPredicting the Critical Buckling Load for a Graphite/Epoxy Laminate / $cRD Jamison, NF Black.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 2 (April 1980)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe critical buckling load for a slender specimen of an isotropic, homogeneous material can usually be predicted adequately from fundamental strength-of-materials considerations. The extension of this approach to specimens of composite materials can be accomplished formally by using appropriate anisotropic elastic constants in the Euler buckling formulas, or by performing a more rigorous and substantially more complicated analysis based on plate theory.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=700  1\$aBlack, NF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10856J.htm

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=001  CTR10857J
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=008  161219c19809999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10857J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10857J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTN693.M4
=082  04$a669.94$223
=100  1\$aYeow, YT., $eauthor.
=245  10$aFundamental Aspects of Composites Reinforced with Glassy Metal Ribbons / $cYT Yeow.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 2 (April 1980)
=504  \\$aIncludes bibliographical references$b3.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe utilization of continuous rectangular shaped reinforcing materials (known here as ribbons) in advanced composites has been studied on a feasibility basis for more than a decade. The main difficulty discerned by these studies was the absence of ribbons possessing mechanical properties similar to contemporary filament reinforcements. Recently in the research and development of metallic glasses, glassy metal ribbons have been manufactured in a continuous manner with aspect ratios (width to thickness) up to 500; these ribbons are available commercially. Depending on the alloy used, some metallic glasses possess high strength, good magnetic properties, and chemical resistance. Accordingly, the objective of this article is to determine some of the advantages and limitations of advanced composites reinforced with glassy metal ribbons.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aMetallic glasses.
=650  \7$aTECHNOLOGY & ENGINEERING $xMetallurgy.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10857J.htm

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=024  7\$a10.1520/CTR10858J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10858J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aGibbins, M., $eauthor.
=245  10$aResponse of Graphite/Epoxy Composite Laminates with Embedded Notches / $cM Gibbins.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 2 (April 1980)
=504  \\$aIncludes bibliographical references.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFatigue response of composite materials has been extensively studied from many different viewpoints and under many different conditions. The same statement can be made for the response of notched composite materials under quasi-static loading. However, one area which has been studied less extensively and is presently incompletely understood is the response of composite laminates with notches embedded in the interior plies. In the present case, investigations of such response were undertaken for two laminate types. Embedded notches were oriented either transverse or parallel (longitudinal) to the loading axis. Unnotched laminates were also considered.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10858J.htm

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=001  CTR10859J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10859J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10859J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.E6
=082  04$a668/.374$223
=100  1\$aChiu, IL., $eauthor.
=245  12$aA Cycloaliphatic Epoxy Resin/Anhydride System Usable up to 150°C / $cJA Rinde, HA Newey, IL Chiu.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1980.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 2, Issue 2 (April 1980)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aWe determined the physical and mechanical properties of a cyloaliphatic epoxy resin that was cured using a liquid anhydride plus 1-methylimidazole as a catalyst. The resin system has a low viscosity and a long gel time, making it suitable for wet filament winding. The system cures at low temperatures (100-120°C) to yield strong, high modulus resins. High glass transition temperatures (>200°C) can be achieved with curing at 150°C. The cost of the resin system is low compared to other elevated-temperature resins. Data on aging at 150°C in air are presented. Erratum to this paper appears in 3(2)
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1980. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy resins.
=650  \7$aTECHNOLOGY & ENGINEERING / Chemical & Biochemical.
=700  1\$aNewey, HA., $eauthor.
=700  1\$aChiu, IL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10859J.htm

=LDR  03835nam  2200625 i 4500
=001  CTR10864J
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=024  7\$a10.1520/CTR10864J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10864J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aYang, JN., $eauthor.
=245  10$aFatigue of Graphite/Epoxy [0/90/45/−45]s Laminates Under Dual Stress Levels / $cJN Yang, DL Jones.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 3 (October 1982)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA model previously developed by the authors to predict the effect of loading sequence on the statistical distribution of the fatigue life and residual strength of composite materials has been generalized and applied to graphite/epoxy [0/90/45/−45]s laminates. The load sequence effects have been shown to be caused in general by the difference in residual strength when failure occurs (boundary effect) and the effect of previously applied loads (memory effect). The present model permits isolation of the memory effect from the boundary effect and estimations of the magnitude of the memory effect under dual levels of fatigue loadings. The model parameters were evaluated from baseline data, including static strength, fatigue life, and residual strength tests. Predictions of the material response were then made and verified with additional fatigue life and residual strength testing. It was shown that the material memory effect is insignificant for this material and correlations between predictions of the number of early failures agreed quite well with the verification tests. Predictions of the fatigue life and residual strength degradation under dual stress levels were also in good agreement with the test results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFatigue (materials)
=650  \0$aLaminates.
=650  \0$aLoading (structural).
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aFatigue (materials).
=653  20$aLaminates.
=653  20$aLoading (structural).
=700  1\$aJones, DL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10864J.htm

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=024  7\$a10.1520/CTR10865J$2doi
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=037  \\$aCTR10865J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aWhitcomb, JD., $eauthor.
=245  10$aApproximate Analysis of Postbuckled Through-Width Delaminations / $cJD Whitcomb.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 3 (October 1982)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn approximate analysis was developed to investigate the postbuckling behavior of through-width delaminations in a laminated coupon. The analysis contains two parameters that are determined using a finite element analysis. After calculating the parameters for a few configurations, the approximate analysis was used to analyze many other configurations. Lateral deflections and Mode I strain-energy release rates obtained with the approximate analysis were compared with results from the finite element analysis. For the configurations analyzed, the approximate analysis agreed very well with the finite element results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aComposite materials.
=650  \0$aDelaminating.
=650  \0$aLaminates.
=650  \0$aNonlinear stress analysis.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aBuckling.
=653  20$aLaminates.
=653  20$aDelaminating.
=653  20$aNonlinear stress analysis.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10865J.htm

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=024  7\$a10.1520/CTR10866J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aLifshitz, JM., $eauthor.
=245  10$aNonlinear Matrix Failure Criterion for Fiber-Reinforced Composite Materials / $cJM Lifshitz.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 3 (October 1982)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA new failure criterion for fiber-reinforced composite materials is proposed and its predictions agree very well with experimental results obtained from testing of angle ply glass/epoxy specimens in tension. The criterion is based on Hill's failure criterion for orthotropic materials and predicts first ply failure of laminae under plane stress conditions. Fiber stress and strength are not included in the criterion. The matrix stresses are calculated by nonlinear analysis, assuming the nonlinearity to be confined to shear behavior. When very large interlaminar stresses develop [such as near edges of (±15°)s specimens], the correlation between experimental results and prediction is not very good. The new criterion fits the present experimental results better than two other criteria, namely the Azzi-Tsai and the Tsai-Wu criteria.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aCriteria.
=650  \0$aExperimental.
=650  \0$aFailure.
=650  \0$aGlass/epoxy angle ply.
=650  \0$aLaminates.
=650  \0$aMatrix.
=650  \0$aNonlinear analysis.
=650  \0$aStrength.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aFailure.
=653  20$aCriteria.
=653  20$aLaminates.
=653  20$aNonlinear analysis.
=653  20$aExperimental.
=653  20$aGlass/epoxy angle ply.
=653  20$aMatrix.
=653  20$aStrength.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10866J.htm

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=024  7\$a10.1520/CTR10867J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10867J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aYamasaki, RS., $eauthor.
=245  10$aSurface Weatherability of Glass-Fiber-Reinforced Polyester Sheeting. I. Effect of Modification of Resin Chemical Composition / $cRS Yamasaki.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 3 (October 1982)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn accelerated weathering test (2 to 0.67 cycle) has been applied to glass-fiber-reinforced polyester (GRP) to determine the effect on surface durability of modifiying the chemical composition of the resin matrix. The nature and rate of induced surface degradation were monitored by scanning electron microscopy. For GRP based on general purpose polyester resin (o-phthalic anhydride-propylene glycol-maleic anhydride-based) the nature of surface damage was not significantly influenced by chemical modification, although the time of initiation was altered. The average overall durability of GRP improved 60% by substitution of propylene glycol with neopentyl glycol, 30% by incorporation of a greater amount of maleic anhydride, and 20% by replacement of both anhydride and glycol with isophthalic acid and neopentyl glycol, respectively. By inference, replacement of anhydride with isophthalic acid reduced the durability of neopentyl glycol-based GRP by 40%.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAccelerated weathering test.
=650  \0$aComposite materials.
=650  \0$aGlass fibers.
=650  \0$aPolyester laminates.
=650  \0$aResin chemical composition.
=650  \0$aScanning electron microscopy.
=650  \0$aSurface properties.
=650  \0$aComposites.
=653  10$aComposite materials.
=653  20$aSurface properties.
=653  20$aGlass fibers.
=653  20$aPolyester laminates.
=653  20$aResin chemical composition.
=653  20$aAccelerated weathering test.
=653  20$aScanning electron microscopy.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10867J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10868J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10868J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/18$223
=100  1\$aKong, FM., $eauthor.
=245  14$aThe Relation Between the Network Structure, Deformation and Failure Processes, and Mechanical Properties of Epoxies / $cFM Kong, CM Walkup, RJ Morgan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 3 (October 1982)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe increasing use of high-performance fiber composites in critical structural applications has led to a need to predict the lifetimes of these materials in service environments. Such predictions require a basic understanding of (1) the microscopic deformation and failure processes of the composite, (2) the roles played by the fiber, epoxy matrix, and fiber-matrix interface in composite performance, and (3) the relations between the structure, the deformation and failure processes, and the mechanical response of these three elements and how those relations are modified by environmental factors.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber composites.
=650  \0$aMicroscopic deformation.
=700  1\$aWalkup, CM., $eauthor.
=700  1\$aMorgan, RJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10868J.htm

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=024  7\$a10.1520/CTR10869J$2doi
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aHahn, HT., $eauthor.
=245  10$aEnvironmental Stability of Kevlar 49 Fiber for Flywheel Applications / $cHT Hahn, WK Chin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 3 (October 1982)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn two earlier papers [1,2], we reported that the simulated flywheel service environment (vacuum and 75°C) had negligible effect on the mechanical properties of a Kevlar 49/epoxy composite except for the cracking of plies in cross-ply laminates resulting from high curing stresses and low transverse strength. To ascertain this excellent property retention, we further tested individual fibers in similar environments. The results on strength and failure mode of these individual fibers are presented in this paper.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aChin, WK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10869J.htm

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=001  CTR10870J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10870J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10870J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aKong, ESW, $eauthor.
=245  14$aThe Effect of Physical Aging on the Time-Dependent Properties of Carbon-Fiber-Reinforced Epoxy Composites / $cESW Kong.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 3 (October 1982)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aMatrix-dominated physical properties of a carbon-fiber-reinforced epoxy composite and a neat epoxy resin have been found to be affected by annealing in nitrogen below the glass transition temperature Tg. Postcured (±45)2s specimens of Thornel 300 carbon-fiber/Fiberite 934 epoxy as well as neat Fiberite 934 epoxy resin were quenched from above Tg and given a sub-Tg annealing at 140°C for times up to 105 min. The damping behavior, stress-relaxation rate, and the enthalpic state of the matrix material were found to decrease as functions of annealing time. No weight loss was observed during annealing. The time-dependent change in physical properties is explained on the basis of free-volume collapse that is related to the physical aging of the nonequilibrium glassy network of epoxy. Physical aging in network epoxy has been demonstrated to be a thermoreversible process. The kinetics of this aging process were monitored by differential scanning calorimetry, stress-relaxation tests, and dynamic mechanical analysis.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10870J.htm

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=024  7\$a10.1520/CTR10871J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10871J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC173.59.G44
=082  04$a530.11$223
=100  1\$aReddy, JN., $eauthor.
=245  10$aSurvey of Recent Research in the Analysis of Composite Plates / $cJN Reddy.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 3 (October 1982)
=504  \\$aIncludes bibliographical references$b80.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis note surveys papers published in the open literature on the static bending and free vibration of layered, anisotropic, composite plates. Papers published through early 1982 are reviewed.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnisotropic crystals.
=650  \0$aAnisotropy.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10871J.htm

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=024  7\$a10.1520/CTR10872J$2doi
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=037  \\$aCTR10872J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMallick, PK., $eauthor.
=245  10$aFlexural Creep of a High-Fiber-Content Sheet Molding Compound Composite / $cPK Mallick.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1982.
=300  \\$a1 online resource (2 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 4, Issue 3 (October 1982)
=504  \\$aIncludes bibliographical references$b2.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis brief report describes the flexural creep behavior of a high-fiber-content sheet molding compound, known as HSMC. Such data are particularly useful when HSMC is being considered for automotive applications, for example in wheels or transmission crossmembers, where it is not uncommon to experience continuous temperatures as high as 100 to 150°C under normal operating conditions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1982. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite material.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10872J.htm

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=001  CTR10876J
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=024  7\$a10.1520/CTR10876J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10876J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQH212.S3
=082  04$a502/.8$223
=100  1\$aSchulte, K., $eauthor.
=245  10$aDamage Development Near the Edges of a Composite Specimen During Quasi-static and Fatigue Loading / $cK Schulte, WW Stinchcomb.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 1 (April 1984)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe replication technique is a method of following the damage development at the edge of a specimen during a load history. The observation of the edge replica in the scanning electron microscope makes it possible to observe micro-details during the damage development. Fracture of 0° fibers could be observed at the edge surface of [0, ± 45, 0]2s and [0, 90, 0, 90]2s laminates after monotonic and cyclic loading. A documentation and explanation of the formation and development of the 0° fiber fracture is given.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aDamage development.
=650  \0$aEpoxy laminates.
=650  \0$aFatigue loading.
=650  \0$aFiber failure.
=650  \0$aGraphite composites.
=650  \0$aReplication technique.
=650  \0$aScanning electron microscopy.
=650  \0$aStatic loads.
=650  \0$aScanning electron microscopy.
=650  \0$aElectron microscopy.
=653  10$aComposite materials.
=653  20$aGraphite composites.
=653  20$aEpoxy laminates.
=653  20$aFatigue loading.
=653  20$aStatic loads.
=653  20$aDamage development.
=653  20$aFiber failure.
=653  20$aReplication technique.
=653  20$aScanning electron microscopy.
=700  1\$aStinchcomb, WW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10876J.htm

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=024  7\$a10.1520/CTR10877J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10877J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA640.2
=082  04$a624.1/71$223
=100  1\$aGuess, TR., $eauthor.
=245  10$aSpherical Kevlar 49/Epoxy Vessels with 430-MPa (62-ksi) Burst Pressures / $cTR Guess.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 1 (April 1984)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA development program for spherical composite pressure vessels with burst pressures as high as 430 MPa (62.5 ksi) is described. Vessels were fabricated by filament-winding Kevlar 49/epoxy over thin seamless copper liners. Two configurations of stainless steel fill stems were evaluated both experimentally and analytically. Finite-element techniques were used to compute stress concentrations produced in the liner and composite shell as a result of the fill-stem geometry. An analytical model was used to estimate vessel pressure-strain response and predict burst pressure as a function of composite and liner properties, composite fiber volume fraction vf, and the composite shell's outer to inner radius ratio β. This model predicts a nonlinear relationship between the burst pressure and β, and at a given β a strong dependence of burst pressure on vf. Experimental data confirmed the predicted dependence of burst pressure on fiber volume fraction. In addition, predicted values of surface strain and burst pressures were in fair agreement with experimental data.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aElectroforming.
=650  \0$aFiber volume fraction.
=650  \0$aFilament winding.
=650  \0$aFinite element analysis.
=650  \0$aPressure vessels.
=650  \0$aStress concentration.
=650  \0$aThick-walled vessels.
=650  \0$aFinite element method.
=650  \0$aStructural analysis (Engineering)
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aPressure vessels.
=653  20$aComposite materials.
=653  20$aFilament winding.
=653  20$aElectroforming.
=653  20$aFinite element analysis.
=653  20$aKevlar 49 composites.
=653  20$aStress concentration.
=653  20$aFiber volume fraction.
=653  20$aThick-walled vessels.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10877J.htm

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=008  161219c19849999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10878J$2doi
=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aQC173.59.G44
=082  04$a530.11$223
=100  1\$aFeng, WW., $eauthor.
=245  10$aGeneral and Specific Quadratic Yield Functions / $cWW Feng, WH Yang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 1 (April 1984)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis report describes a general yield function for anisotropic elastoplastic materials written in a quadratic form in terms of the stress components. The function contains 28 independent coefficients that must be determined experimentally. A set of inequality constraint conditions imposed on these coefficients is derived from the convexity requirement for all yield functions. A number of previously derived yield functions are recognized here as special cases of the general quadratic yield function, and the convexity condition for each of them is also provided. These inequality conditions should aid experimental projects for material identification.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnisotropic.
=650  \0$aElastoplastic materials.
=650  \0$aAnisotropy.
=700  1\$aYang, WH., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10878J.htm

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=008  161219c19849999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10879J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10879J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aGriffin, OH., $eauthor.
=245  14$aThe Use of Proper Shear Moduli in the Analysis of Laminated Composites / $cOH Griffin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 1 (April 1984)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this report, a fully three-dimensional finite-element analysis of residual curing stresses in cross-ply graphite/epoxy composite laminates is performed, and the error introduced by the common assumption of equality of all shear moduli and certain Poisson's ratios is examined. In particular, interlaminar stresses near the laminate midplane are presented. The error introduced by the assumption of coefficient equality will be shown to be significant only in the interlaminar shear stresses and insignificant in other stress components.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10879J.htm

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=024  7\$a10.1520/CTR10880J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10880J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTD893.6.T7
=082  04$a625.7/08 s$223
=100  1\$aAl-Qureshi, HA., $eauthor.
=245  10$aNomograph for Thicknesses Calculation in a Filament-Wound Pressure Vessel / $cHA Al-Qureshi, R Corrêa.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (3 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 1 (April 1984)
=504  \\$aIncludes bibliographical references$b6.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe use of nomographs in engineering has been in decline for some years; however, there are still engineering applications where charting the equations is a useful aid in understanding the problem at hand. The nomograph, a representation of a large number of equations, possesses a number of advantages; it consists of very few lines and is easy to construct, requires little skill to use, and permits immediate visualization of the changes in one parameter due to changes in other parameters. The fundamental principle in constructing the chart is simply representing the equations by means of scales along certain straight lines.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aNomographs.
=650  \0$aEngineering.
=650  \0$aNomography.
=700  1\$aCorrêa, R., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10880J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10881J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10881J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aGlaser, RE., $eauthor.
=245  10$aLife Estimation of Aramid/Epoxy Composites Under Sustained Tension / $cRE Glaser, RL Moore, TT Chiao.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1984.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 6, Issue 1 (April 1984)
=504  \\$aIncludes bibliographical references$b23.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFor long-term applications, the life of fiber composites is a key concern for engineers. Over the last decade, we have been studying this subject by measuring the stress-rupture behavior of several composites under sustained tensile loads [1-19]. Stress rupture (also called lifetime, static fatigue, creep rupture, or time-dependent strength) is the failure time of a composite material or structure under a sustained load. Recently, we summarized our 10-y study in stress rupture on a simple S-Glass/epoxy composite [20]. In the case of aramid/epoxy composites, we gathered lifetime data from 1971 until early 1980, when a major earthquake interrupted part of our experiment. Our effort on this class of composite has been quite extensive with tests that use large numbers of composite strands and pressure vessels. For the strand testing, several temperatures also were involved. Different analytical methods were used for the treatment of data. Because of the large scope of this work, long experimental time span, and the number of people involved, some data inconsistency and different interpretations of results have been unavoidable. In this article, we review all of our stress-rupture data on aramid/epoxy composites from 1971 to early 1980, analyze them with an up-to-date statistical method, provide plots for life estimation and reliability assessment, and offer comments on some issues of particular interest.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1984. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEpoxy composites.
=650  \0$aAramid/epoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=700  1\$aMoore, RL., $eauthor.
=700  1\$aChiao, TT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10881J.htm

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=024  7\$a10.1520/CTR10892J$2doi
=030  \\$aJCTRER
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKumosa, M., $eauthor.
=245  10$aComparison of the ±45° Tensile and Iosipescu Shear Tests for Woven Fabric Composite Materials / $cM Kumosa, G Odegard, D Armentrout, L Kumosa, K Searles, JK Sutter.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (14 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 1 (January 2002)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe mechanical response of a woven eight-harness satin graphite/polyimide composite has been investigated by performing ±45° tensile and Iosipescu shear tests at room temperature. Nonlinear finite element simulations of the tests have been conducted to determine internal stress distributions in the ±45° tensile and Iosipescu fabric specimens as a function of load. In the experimental part of this study, a series of tensile and Iosipescu shear tests have been performed. Acoustic emission techniques have been employed to monitor damage initiation and progression in the composite. The finite element computations have shown that the internal stress distributions in the Iosipescu and tensile fabric specimens are significantly different. In the gage sections of Iosipescu specimens, the state of stress is essentially pure shear, whereas the tensile tests generate biaxial stress conditions. It has been shown in this research that the shear strength of the composite determined from the maximum loads obtained from the Iosipescu shear tests is significantly higher than the shear strength obtained from the ±45° tensile tests. Moreover, the initiation of intralaminar damage in the tensile specimens occurs at much lower loads than in the Iosipescu specimens. It appears that the ±45° tensile test significantly underestimates the shear strength of the composite evaluated from the onset of intralaminar damage and the maximum loads.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=700  1\$aOdegard, G., $eauthor.
=700  1\$aArmentrout, D., $eauthor.
=700  1\$aKumosa, L., $eauthor.
=700  1\$aSearles, K., $eauthor.
=700  1\$aSutter, JK., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10892J.htm

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=001  CTR10893J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10893J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10893J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aJohnson, WS., $eauthor.
=245  10$aTemperature Effects on Ultimate Bearing Strength of Polymeric Composite Joints / $cWA Counts, WS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 1 (January 2002)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe ultimate bearing strength (UBS) of IM7/PETI-5 composite materials in a quasi-isotropic lay-up, 64 plies thick, was determined using a compressive bearing test setup. Testing was performed at room temperature, 177°C (350°F) and −50°C (−58°F). Some specimens were thermally aged at 177°C (350°F) for up to 10000 h. It was found that the IM7/PETI-5 composite material's UBS was essentially unaffected by the thermal aging. At elevated temperature, the UBS of IM7/PETI-5 decreased, while at low temperature, the UBS increased slightly. Despite the increase in UBS at low temperature, the bearing failure was catastrophic, resulting in widespread delamination due to the brittleness of the matrix.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBearing strength.
=650  \0$aCompression.
=650  \0$aDurability.
=650  \0$aPly buckling.
=650  \0$aThermal aging.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aPly buckling.
=653  20$aThermal aging.
=653  20$aDurability.
=653  20$aCompression.
=653  20$aBearing strength.
=700  1\$aJohnson, WS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10893J.htm

=LDR  03306nam  2200649 i 4500
=001  CTR10894J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10894J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10894J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGowayed, Y., $eauthor.
=245  12$aA Design Procedure for Textile Composite Materials / $cY Gowayed, L Barowski.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 1 (January 2002)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA design procedure for textile composite materials that is able to satisfy a set of target mechanical and thermal properties is presented. First the search space, within which a feasible solution may exist, is divided into discrete sections. These sections are sufficiently small so that material properties show little variation. In each section, the composite is defined as a set of yarn segments that possess certain relative volume fractions, initial elliptical cross-section shape, and spatial direction cosines. A unique solution is calculated using a stiffness averaging routine. Solutions are then compared and ranked based on a chosen selection criterion.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDesign.
=650  \0$aGraphic $xGeometric modeling.
=650  \0$aNumerical modeling.
=650  \0$aTextiles.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aTextiles.
=653  20$aComposites.
=653  20$aDesign.
=653  20$aNumerical modeling.
=653  20$aGraphic and geometric modeling.
=700  1\$aBarowski, L., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10894J.htm

=LDR  03430nam  2200709 i 4500
=001  CTR10895J
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=006  m\\\\\\\\\\\\\\\\\
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=008  161219c20029999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10895J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10895J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP968
=082  04$a620.199$223
=100  1\$aBardis, JD., $eauthor.
=245  10$aSurface Preparation Effects on Mode I Testing of Adhesively Bonded Composite Joints / $cJD Bardis, KT Kedward.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 1 (January 2002)
=504  \\$aIncludes bibliographical references$b25.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe determination and significance of surface preparation on the long-term durability of bonded composite joints is addressed. Several potential factors are evaluated, including the effects of release fabric (sometimes incorrectly referred to as a peel ply) usage and grit blasting on the fracture toughness and failure modes of bonded assemblies. The double cantilever beam (DCB) test is adapted with the intent of developing a quantitative interpretation of a composite version of the wedge test. This well-established wedge test is used for quality and durability assessments of metal bonded systems.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBonded joint durability.
=650  \0$aGrit blast.
=650  \0$aJoint failure.
=650  \0$aPeel ply.
=650  \0$aRelease fabric.
=650  \0$aStructural adhesive.
=650  \0$aSurface preparation.
=650  \0$aStructural engineering.
=650  \0$aAdhesive bonding.
=653  10$aStructural adhesive.
=653  20$aBonded joint durability.
=653  20$aSurface preparation.
=653  20$aMode I failure tests.
=653  20$aJoint failure.
=653  20$aPeel ply.
=653  20$aRelease fabric.
=653  20$aGrit blast.
=700  1\$aKedward, KT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10895J.htm

=LDR  03550nam  2200721 i 4500
=001  CTR10907J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10907J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10907J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.2
=082  04$a620.1/1232$223
=100  1\$aAkshantala, NV., $eauthor.
=245  12$aA Damage Evolution Model for Viscoelastic Composite Laminates / $cNV Akshantala, LC Brinson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 1 (January 2001)
=504  \\$aIncludes bibliographical references$b36.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA damage model for polymeric composite laminates operating at elevated temperatures is proposed. Viscoelastic behavior of the material is accounted for via the correspondence principle, and a variational approach is adopted to compute the temporal stresses within the laminate. Also, the effect of physical aging on ply level stress and on overall laminate behavior is included. An important feature of the model is that damage evolution predictions for viscoelastic laminates can be made. This allows us to track the mechanical response of the laminate up to large load levels, though within the confines of linear viscoelastic constitutive behavior.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite laminate.
=650  \0$aCorrespondence principle.
=650  \0$aDamage evolution.
=650  \0$aLinear viscoelastic constitutive behavior.
=650  \0$aPhysical aging.
=650  \0$aPolymeric.
=650  \0$aTemporal stress.
=650  \0$aViscoelastic.
=650  \0$aViscoelasticity.
=650  \0$aContinuum mechanics.
=653  10$aDamage evolution.
=653  20$aViscoelastic.
=653  20$aPolymeric.
=653  20$aComposite laminate.
=653  20$aCorrespondence principle.
=653  20$aTemporal stress.
=653  20$aLinear viscoelastic constitutive behavior.
=653  20$aPhysical aging.
=700  1\$aBrinson, LC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10907J.htm

=LDR  03242nam  2200601 i 4500
=001  CTR10908J
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=006  m\\\\\\\\\\\\\\\\\
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=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10908J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10908J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aLiao, K., $eauthor.
=245  10$aEvaluation of Film-Substrate Interface Durability Using a Shaft-Loaded Blister Test / $cK Liao, KT Wan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 1 (January 2001)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this paper, an analytical solution is presented for a shaft-loaded blister test for a thin film-substrate system. Both bending and stretching modes of deformation of the film are considered in the model. It is suggested that film-substrate delamination behavior under a Mode I separation load is governed by a parameter that relates the membrane stress to the rigidity of the film. The delamination behavior of several model thin film-substrate systems under repeated mechanical loads is studied. It is suggested from the results that film-substrate delamination under cyclic load depends on film rigidity, loading frequency, and film-substrate interfacial characteristics.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBlister test.
=650  \0$aDeformation.
=650  \0$aFilm-substrate system.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aBlister test.
=653  20$aFilm-substrate system.
=653  20$aDeformation.
=700  1\$aWan, KT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10908J.htm

=LDR  03171nam  2200589 i 4500
=001  CTR10909J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10909J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10909J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.2
=082  04$a620.1/1232$223
=100  1\$aTzeng, JT., $eauthor.
=245  10$aViscoelastic Modeling of Press-Fitted Composite Cylinders / $cJT Tzeng.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 1 (January 2001)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aInterference stress is an important design factor for press-fitted cylinder applications such as flywheels and pressure vessels, which may decrease over a period of time. Stress relaxation and creep in press-fitted composite cylinders are investigated based on anisotropic viscoelasticity. The analysis accounts for ply-by-ply variation of material properties and fiber orientations through the thickness of cylinders. Viscoelastic characteristics of press-fit composite assemblies are quite different from those of isotropic cylinders, due to the extreme anisotropy of composite materials. Results show a significant change of interference stresses over a period of time, which is critical to structural performance and durability.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnisotropy.
=650  \0$aInterference stress.
=650  \0$aViscoelasticity.
=650  \0$aViscoelastic.
=650  \0$aContinuum mechanics.
=653  10$aInterference stress.
=653  20$aAnisotropy.
=653  20$aViscoelasticity.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10909J.htm

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=001  CTR10910J
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=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10910J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10910J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aVeazie, DR., $eauthor.
=245  10$aEffects of Resin Consolidation on the Durability of IM7/PETI-5 Composites / $cDR Veazie, JS Lindsay, EJ Siochi.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 1 (January 2001)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn experimental study was undertaken to investigate the mechanical response of the graphite fiber reinforced thermoplastic polyimide composite IM7/LaRC™-PETI-5 for use in long term durability tests. Composite panels were prepared using unidirectional prepreg and regions of different resin consolidation were identified using a nondestructive ultrasonic technique. Specimens representing four different degrees of resin consolidation were tested at room temperature in tension, compression, and flexure in the as-received state, as well as isothermally exposed for 1500 h at 177°C, and isothermally exposed to a "hot/wet" environment (80°C, 90%+ relative humidity). Results showed that specimens tested in tension and compression had a higher dependence on resin consolidation than those tested in flexure. However, specimens tested in flexure showed a greater property degradation from environmental exposure due to a lack of resin consolidation.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression.
=650  \0$aEnvironmental exposure.
=650  \0$aFlexure.
=650  \0$aMoisture conditioning.
=650  \0$aNondestructive evaluation.
=650  \0$aPolymer matrix composites.
=650  \0$aResin consolidation.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aPolymer matrix composites.
=653  20$aFlexure.
=653  20$aEnvironmental exposure.
=653  20$aResin consolidation.
=653  20$aCompression.
=653  20$aMoisture conditioning.
=653  20$aNondestructive evaluation.
=700  1\$aLindsay, JS., $eauthor.
=700  1\$aSiochi, EJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10910J.htm

=LDR  04347nam  2200697 i 4500
=001  CTR10911J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10911J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10911J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aWalther, MB., $eauthor.
=245  10$aSingle-Fiber Fragmentations of AS-4 Carbon Fiber Embedded in Epon 828 Under the Effect of Elevated Temperatures / $cMB Walther, KL Reifsnider, M Madhukar, MS Genidy.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 1 (January 2001)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSingle fiber fragmentation tests were performed over a range of elevated temperatures (ambient to 160°C) to study the effect of temperature on the fiber-matrix interface. In order to understand the mechanical performance of a polymer/carbon fiber composite system, the micromechanical performance must be understood. The mechanical performance of a composite material is dependent on the fiber-matrix interface region. The nature of the fiber-matrix interface controls the interfacial shear strength and this is an important parameter in the formulation of shear-lag and other micromechanical models. Micromechanical shear-lag models are used to estimate macromechanical properties of composite materials. Environmental conditions that affect the macromechanical properties of polymer composites need to be understood at the micromechanical level. Temperature is one example of an environmental condition that influences the mechanical response of some composite systems. The study presented in this paper uses the measurement of broken fiber lengths resulting from the multiple fracture of a single fiber that is embedded in resin with applied load. The material system used in this study was an AS4-carbon-fiber/Epon-828/mPDA-epoxy-resin-system. The critical fragmentation lengths were measured with the aid of a microscope, and the critical lengths were found to increase 70% from ambient temperature to 160°C.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCritical fragmentation length.
=650  \0$aElasticity model.
=650  \0$aFiber/matrix interface.
=650  \0$aInterfacial shear strength.
=650  \0$aTemperature.
=650  \0$aThermodynamic model.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aFiber/matrix interface.
=653  20$aCritical fragmentation length.
=653  20$aTemperature.
=653  20$aInterfacial shear strength.
=653  20$aElasticity model.
=653  20$aThermodynamic model.
=700  1\$aReifsnider, KL., $eauthor.
=700  1\$aMadhukar, M., $eauthor.
=700  1\$aGenidy, MS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10911J.htm

=LDR  03765nam  2200649 i 4500
=001  CTR10912J
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=005  20161219163000.0
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=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10912J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10912J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.B63
=082  04$a621.8/82$223
=100  1\$aLubke, KA., $eauthor.
=245  10$aEffect of Environment on Fracture Toughness and Debond Growth of Aluminum/FM®73/Boron-Epoxy Adhesively Bonded Joints / $cKA Lubke, LM Butkus, WS Johnson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 1 (January 2001)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aTests were conducted to determine the fracture toughness of aluminum/FM®73/boron-epoxy adhesively bonded joints. Double cantilever beam (DCB) specimens and end-notched flexure (ENF) specimens were exposed to one of the following environments: hot/wet (71° C(160° F) and >90% RH) conditions for 5000 h, thermal cycles between 71° C (160° F) and −54° C (−65° F), or an outdoor "rooftop" environment for 10 000 h. The environmentally exposed specimens were tested along with as-received (or unexposed specimens). The different adherend materials had different coefficients of thermal expansion (CTE). The mismatch of CTE between adherends caused residual thermal stresses in the adhesive joints at every temperature other than the elevated cure temperature. The residual stresses could not be accounted for with closed form solutions. Finite element analysis (FEA) of the specimens was required. Using FEA solutions, it was determined that the fracture toughness of the environmentally exposed specimens was lower than the as-received specimens for every environment tested for both DCB and ENF specimens.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDurability.
=650  \0$aFatigue.
=650  \0$aJoints.
=650  \0$aBolted joints.
=650  \0$aJoints (Engineering)
=650  \0$aBolts and nuts.
=653  10$aDurability.
=653  20$aFatigue.
=653  20$aComposites.
=653  20$aJoints.
=700  1\$aButkus, LM., $eauthor.
=700  1\$aJohnson, WS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10912J.htm

=LDR  03688nam  2200757 i 4500
=001  CTR10914J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10914J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10914J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aAsp, LE., $eauthor.
=245  10$aDelamination Growth and Thresholds in a Carbon/Epoxy Composite Under Fatigue Loading / $cLE Asp, A Sjögren, ES Greenhalgh.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (14 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 2 (April 2001)
=504  \\$aIncludes bibliographical references$b38.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper presents a study on delamination growth in Mode I, Mode II and mixed mode under fatigue loading in an HTA/6376C composite. The computed slopes of the modified Paris plots were high. Therefore, threshold values of the strain energy release rate for delamination growth were determined. Low fatigue threshold values revealed a significant effect of fatigue loading. The largest effect was found for the ENF test (Mode II) for which the fatigue threshold value was only 10% of the critical strain energy release rate in static tests. Threshold values for MMB (mixed mode) and DCB (Mode I) tests were 15% and 23% of the static values, respectively.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aDelamination.
=650  \0$aFailure mechanisms.
=650  \0$aFatigue.
=650  \0$aFractography.
=650  \0$aInterlaminar fracture toughness.
=650  \0$aMixed-mode bend test.
=650  \0$aShear cusps.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aInterlaminar fracture toughness.
=653  20$aFatigue.
=653  20$aMode I.
=653  20$aMode II.
=653  20$aMixed-mode bend test.
=653  20$aDelamination.
=653  20$aFractography.
=653  20$aFailure mechanisms.
=653  20$aShear cusps.
=700  1\$aSjögren, A., $eauthor.
=700  1\$aGreenhalgh, ES., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10914J.htm

=LDR  03953nam  2200733 i 4500
=001  CTR10915J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10915J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10915J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aJohn, R., $eauthor.
=245  10$aBridging Stress Distributions During Fatigue Crack Growth in Continuously Reinforced [0] Metal Matrix Composites / $cR John, DJ Buchanan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 2 (April 2001)
=504  \\$aIncludes bibliographical references$b36.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn optimization procedure was developed to deduce the fiber bridging stresses from crack opening displacements measured in situ during crack growth. This procedure was used to determine the bridging stress distribution during fatigue crack growth in a unidirectionally reinforced metal matrix composite (SCS-6/TIMETAL®21S). The bridging stress is non-zero at the crack tip contrary to predictions from conventionally used shear lag models. The bridging stress at the crack tip is proportional to the applied far-field stress. The deduced bridging law is similar to the new shear lag models with non-zero bridging stresses at the crack tip. Any bridging model can be used to predict the crack growth behavior by choosing appropriate values of the frictional shear stress (τ). Consequently, the magnitude of the stresses in the fibers bridging the crack will depend on the fiber bridging model. Hence, the fiber tensile strength required to predict the onset of fiber failure will also depend on the fiber bridging model.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBridging stress intensity factor.
=650  \0$aBridging stress.
=650  \0$aCrack growth.
=650  \0$aFatigue.
=650  \0$aFiber bridging.
=650  \0$aMetal matrix composite.
=650  \0$aShear lag.
=650  \0$aTitanium matrix composite.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aBridging stress.
=653  20$aBridging stress intensity factor.
=653  20$aCrack growth.
=653  20$aFatigue.
=653  20$aFiber bridging.
=653  20$aMetal matrix composite.
=653  20$aShear lag.
=653  20$aTitanium matrix composite.
=700  1\$aBuchanan, DJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10915J.htm

=LDR  03932nam  2200745 i 4500
=001  CTR10916J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10916J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10916J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aRamulu, M., $eauthor.
=245  10$aAbrasive Water Jet Machining Mechanisms in Continuous-Fiber Ceramic Composites / $cM Ramulu, MG Jenkins, Z Guo.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 2 (April 2001)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAdvanced continuous fiber-reinforced ceramic composite (CFCC) materials have been machined with abrasive water jet (AWJ) drilling and cutting processes. Cutting forces, surface microstructure, and retained tensile behaviors were evaluated using dynamometry, surface profilometry, scanning electron microscopy, and tensile testing, respectively. The AWJ surface characteristics, i.e., roughness and the micromechanisms of material removal of CFCCs, were compared with those of a conventional diamond saw cut surface. Material removal mechanisms for AWJ cutting of CFCC consist of a combination of bending, shearing, micromachining, and erosion. The micromechanisms associated with AWJ hole drilling, or piercing on the other hand, are microfracture of fibers and matrix, delamination, and fragmentation of fiber bundles. The tensile mechanical behavior is negligibly different between the AWJ machined and diamond grit ground CFCC materials.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBending fracture.
=650  \0$aContinuous-fiber ceramic composites.
=650  \0$aDelamination.
=650  \0$aEdge finishing.
=650  \0$aErosion.
=650  \0$aFiber direction.
=650  \0$aMachining.
=650  \0$aSurface roughness.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aContinuous-fiber ceramic composites.
=653  20$aAbrasive water jet.
=653  20$aMachining.
=653  20$aEdge finishing.
=653  20$aFiber direction.
=653  20$aSurface roughness.
=653  20$aBending fracture.
=653  20$aErosion.
=653  20$aDelamination.
=700  1\$aJenkins, MG., $eauthor.
=700  1\$aGuo, Z., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10916J.htm

=LDR  03315nam  2200697 i 4500
=001  CTR10917J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10917J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10917J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.P6
=082  04$a668.4/225$223
=100  1\$aVan de Velde, K., $eauthor.
=245  10$aEffects of Chemical Environments on Pultruded E-Glass Reinforced Polyesters / $cK Van de Velde, P Kiekens.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 2 (April 2001)
=504  \\$aIncludes bibliographical references$b28.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this work, the chemical resistance of six kinds of pultruded E-glass fiber reinforced isophthalic polyesters are studied. They contain 50 w% or 60 w% glass. The composites were either unfilled or filled with calcium carbonate or kaolin clay. The mechanical, physical, optical, and structural properties of the pultruded flat profiles before and after immersion in seawater, demineralized water, sodium hydroxide (5%), and sulfuric acid (10%) were analyzed over the period of one year.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAlkaline solutions.
=650  \0$aChemical degradation.
=650  \0$aDemineralized water.
=650  \0$aGlass/polyester.
=650  \0$aPultruded composites.
=650  \0$aSeawater.
=650  \0$aSulfuric acid.
=650  \0$aPolyester.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aPultruded composites.
=653  20$aChemical degradation.
=653  20$aAlkaline solutions.
=653  20$aDemineralized water.
=653  20$aSeawater.
=653  20$aSulfuric acid.
=653  20$aGlass/polyester.
=700  1\$aKiekens, P., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10917J.htm

=LDR  03580nam  2200673 i 4500
=001  CTR10918J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10918J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10918J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.82
=082  04$a551.9$223
=100  1\$aDavidson, DL., $eauthor.
=245  10$aMatrix Properties of Textile Reinforced Ceramic Matrix Composites Measured by Nanoindentation / $cDL Davidson, GM Pharr.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 2 (April 2001)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aNanoindentation was used to measure the elastic modulus (E) and hardness (H) of the matrix materials of three ceramic composites reinforced with woven Nicalon fiber fabrics. The matrices included: (1) alumina produced by the Dimox process; (2) silicon carbide synthesized by chemical vapor infiltration; and (3) a SiC/BN material produced by polymer infiltration pyrolysis. The elastic moduli and hardnesses of the matrices of all three materials were found to be significantly lower than bulk ceramics of similar composition, probably due to porosity in the matrix and/or incomplete conversion of the infiltration materials to ceramic. Each of the composites was exposed to air at 750°C for 64 h, and measurements of E and H were made. The silicon carbide matrix was essentially unaffected, but two other materials exhibited significant reductions in both E and H caused by thermal exposure.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCeramic composite.
=650  \0$aElastic modulus.
=650  \0$aHardness.
=650  \0$aMatrix material.
=650  \0$aNanoindentation.
=650  \0$aPorosity.
=650  \0$aAdsorption.
=650  \0$aMaterials.
=653  10$aNanoindentation.
=653  20$aElastic modulus.
=653  20$aHardness.
=653  20$aMatrix material.
=653  20$aCeramic composite.
=653  20$aPorosity.
=700  1\$aPharr, GM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10918J.htm

=LDR  03646nam  2200649 i 4500
=001  CTR10919J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10919J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10919J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC173.59.G44
=082  04$a530.11$223
=100  1\$aWelsh, JS., $eauthor.
=245  10$aBiaxial and Triaxial Failure Strengths of 6061-T6 Aluminum and AS4/3501-6 Carbon/Epoxy Laminates Obtained by Testing Thickness-Tapered Cruciform Specimens / $cJS Welsh, DF Adams.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 2 (April 2001)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aUsing a thickness-tapered cruciform specimen, uniaxial and biaxial tests were performed on 6061-T6 aluminum as well as biaxial and triaxial tests on an AS4/3501-6 carbon/epoxy cross-ply laminate. Designed in conjunction with a new triaxial test facility, the performance of the cruciform specimen was analyzed using an anisotropic, linear-elastic, finite element analysis. The results of this analysis, as well as the experimental data generated for both the aluminum and AS4/3501-6 carbon/epoxy material systems, are presented. An undesirable failure mode was observed in several biaxial tension tests, and the triaxial tension tests were not performed successfully. This study represents the initial effort using this specimen design and test facility, and several recommendations to improve the performance of the thickness-tapered cruciform specimen in future studies are presented. The potential of the triaxial testing facility and the thickness-tapered cruciform specimen has been demonstrated.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBiaxial.
=650  \0$aCruciform.
=650  \0$aTesting.
=650  \0$aTriaxial.
=650  \0$aUniaxial.
=650  \0$aAnisotropic crystals.
=650  \0$aAnisotropy.
=653  10$aCruciform.
=653  20$aUniaxial.
=653  20$aBiaxial.
=653  20$aTriaxial.
=653  20$aTesting.
=700  1\$aAdams, DF., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10919J.htm

=LDR  03810nam  2200625 i 4500
=001  CTR10920J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10920J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10920J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aCapello, E., $eauthor.
=245  10$aDrilling Damage of GFRP and Residual Mechanical Behavior-Part I : $bDrilling Damage Generation / $cE Capello, V Tagliaferri.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 2 (April 2001)
=504  \\$aIncludes bibliographical references$b14.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe drilling of composite laminates generates several kinds of damage that can be detrimental to the mechanical behavior around the hole. The present work is the first part of a study that investigates the effect of the drilling on the residual mechanical behavior of glass fiber reinforced plastic (GFRP) laminates when the hole is subjected to bearing load. In the first part, the influence of drilling parameters on the type and extension of the damage is analyzed. The damage is described at the macro level (delaminated area) and at the micro level (cracks, fiber-matrix debonding, etc.). The Design of Experiments and Analysis of Variance techniques are used in order to determine the statistical influence of the drilling parameters on the delamination area. Moreover, the effects of drilling with or without a support beneath the specimens are analyzed and discussed. Results indicate that the degree of peel-up delamination depends on the feed rate and on the helix angle of the twist drill. Push-down delamination is mainly affected by the feed rate, by the presence of support beneath the specimen, and by the twist drill temperature.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDamage generation mechanism.
=650  \0$aDelamination.
=650  \0$aDrilling.
=650  \0$aGFRP laminate.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDelamination.
=653  20$aDrilling.
=653  20$aGFRP laminate.
=653  20$aDamage generation mechanism.
=700  1\$aTagliaferri, V., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10920J.htm

=LDR  03704nam  2200637 i 4500
=001  CTR10921J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10921J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10921J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aCapello, E., $eauthor.
=245  10$aDrilling Damage of GFRP and Residual Mechanical Behavior-Part II : $bStatic and Cyclic Bearing Loads / $cE Capello, V Tagliaferri.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 2 (April 2001)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe damage generated during the drilling of Glass Fiber Reinforced Plastics (GFRP) laminates can be detrimental for the mechanical behavior of the material around the hole, especially when the hole surface is subjected to a bearing load. The present work is the second part of a study aiming to investigate the effect of drilling conditions on the residual mechanical behavior of GFRP laminates subjected to a bearing load. To address this aim, holes drilled in different conditions were tested with static and cyclic bearing loads. The results of these tests were characterized through quantitative parameters and through microscopic observations of hole sections. Results indicate that for the range of the experimental conditions investigated, the main cause of mechanical failure is the micro damage generated at the inner part of the hole surface, while delamination plays a minor role. Therefore, despite the general attention paid during drilling to reduce delamination, the optimal drilling conditions should avoid the onset of microcracks distributed in the inner part of the hole.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDrilling damage.
=650  \0$aFatigue.
=650  \0$aGFRP laminate.
=650  \0$aStatic strength.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aDrilling damage.
=653  20$aGFRP laminate.
=653  20$aStatic strength.
=653  20$aFatigue.
=700  1\$aTagliaferri, V., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10921J.htm

=LDR  03778nam  2200757 i 4500
=001  CTR10927J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20029999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10927J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10927J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC367.3.I58
=082  04$a522/.6$223
=100  1\$aGolda, D., $eauthor.
=245  10$aDeflection Measurements of Laminated Thin Plates Using Electronic Speckle Pattern Interferometry / $cD Golda, D Kedlaya, AA Pelegri.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 4 (December 2002)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn adaptive Electronic speckle Pattern Interferometry (ESPI) system has been developed to measure out-of-plane deformation of laminates subjected to quasi-static loads. The system was installed and setup for calibration with aluminum specimens mounted to an optical breadboard. Several parameters of the test fixture and system's geometry needed to be adjusted before usable fringe patterns were obtained, and the system's resolution and range were determined. The ESPI system was then reconfigured for use with composite specimens subjected to quasi-static loading. Results of fringe patterns, calibration curves and deformation patterns are presented for A1 and graphite/epoxy specimens. The ESPI resolution was estimated at 25 μm per fringe for the A1 surface, and 11 μm per fringe for the composite laminate. From the results, it can be concluded that the usable deflection range is limited at high system resolutions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aCrack.
=650  \0$aExperiments.
=650  \0$aFailure.
=650  \0$aFringe.
=650  \0$aInterferometry.
=650  \0$aLaminate.
=650  \0$aLaser.
=650  \0$aSpeckle.
=650  \0$aInterferometry.
=650  \0$aOptical measurements.
=653  10$aComposite.
=653  20$aCrack.
=653  20$aExperiments.
=653  20$aFailure.
=653  20$aFringe.
=653  20$aInterferometry.
=653  20$aLaminate.
=653  20$aLaser.
=653  20$aSpeckle.
=700  1\$aKedlaya, D., $eauthor.
=700  1\$aPelegri, AA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10927J.htm

=LDR  04400nam  2200685 i 4500
=001  CTR10928J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c20029999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10928J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10928J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA409
=082  04$a620.1/26$223
=100  1\$aTekkam, A., $eauthor.
=245  12$aA Statistical Approach for Optimizing the Fracture Toughness of a Composite Laminate / $cA Tekkam, AA Pelegri.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 4 (December 2002)
=504  \\$aIncludes bibliographical references$b15.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aDelamination is one of the most critical failure modes in laminated composite structures due to its abrupt and damaging character. In the present investigation a methodology is developed using Designed Experiments and Taguchi concepts to analyze the contribution and significance of several factors to the mode I delamination fracture toughness of a composite structure. The factors tested were selected based on their degree of influence on the fracture toughness and their tailoring adjustability. Considering these two criteria, the most important factors in optimizing a laminate's strength include crack (delamination) length, stacking sequence, width, thickness, and length of the structure. Most importantly, the effect of their first order interactions, i.e., concurrent effect, on a damaged laminate is investigated. All the factors are regarded at two levels and a Fractional Factorial experiment is conducted. Taguchi arrays are used to select the combination of factors that will maximize the amount of information from the minimum number of experiments. The idea of significant factors and their interactions is then used to obtain a response surface equation. Estimation of the structure's interlaminar fracture toughness follows once the response surface equation is identified. The developed methodology significantly reduces the required number of experiments and qualitatively describes the effect of various factors, and their interactions, on the fracture toughness. Experimental and analytical results, employing the optimal combination of factors as determined by the presented method, are in good agreement.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDesign of experiments.
=650  \0$aFracture toughness.
=650  \0$aLaminates.
=650  \0$aOptimization.
=650  \0$aResponse surface.
=650  \0$aTaguchi.
=650  \0$aFracture mechanics.
=650  \0$aFracture of materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aLaminates.
=653  20$aFracture toughness.
=653  20$aOptimization.
=653  20$aTaguchi.
=653  20$aDesign of experiments.
=653  20$aResponse surface.
=700  1\$aPelegri, AA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10928J.htm

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=001  CTR10929J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10929J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10929J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQH541.15.E24
=082  04$a577$223
=100  1\$aChandra, N., $eauthor.
=245  14$aThe Effect of Material Heterogeneity on the Shock Response of Layered Systems in Plate Impact Tests / $cN Chandra, X Chen, AM Rajendran.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 4 (December 2002)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn the study of shock wave propagation in solids, scattering, dispersion, and attenuation play a critical role in determining the thermomechanical response of the media. These phenomena can be attributed to a number of nonlinearities arising from the wave characteristics, loading conditions, material heterogeneity (measured at various spatial scales ranging from nanometers to a few millimeters). The nonlinear effects in general can be ascribed to impedance (and geometric) mismatch present at various length scales as often encountered in composite material systems, apart from material nonlinearities arising from inelastic effects, void nucleation and growth, cracking, and delamination. However, in nearly brittle material systems, elastic effects dominate and is the only effect considered here. Uniaxial strain experiments on the S-2 glass/polymer composite system display markedly different behavior than that observed in monolithic metallic systems [6] and this motivated the present work. Stress profiles measured at various locations along the direction of wave propagation in the plate impact experiments showed that the shock wave rise time increased with propagation in addition to the reduction of peak stress. In this work, we specifically address the issue of shock wave rise time in a simplified multi-layered system. A careful analysis of wave propagation in heterogeneous medium is performed by considering the elastic/acoustic properties of individual lamina in a layered system. An analytical model has been developed to describe the scattering process (reflection/transmission) at various layer interfaces of multilayer composite system. FEM results are then used to compare with the analytical predictions. These results show that the rise time can be a consequence of multiple internal reflections and transmissions occurring at the heterogeneous interfaces, it is further shown that the rise time depends on the magnitude of impedance mismatch and the number of layers.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aHigh velocity impact response.
=650  \0$aLayered heterogeneous materials.
=650  \0$aPlate impact.
=650  \0$aRise characteristics.
=650  \0$aScattering.
=650  \0$aEcological heterogeneity.
=650  \7$aNATURE $xEcology.
=653  10$aHigh velocity impact response.
=653  20$aLayered heterogeneous materials.
=653  20$aScattering.
=653  20$aRise characteristics.
=653  20$aPlate impact.
=700  1\$aChen, X., $eauthor.
=700  1\$aRajendran, AM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10929J.htm

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=024  7\$a10.1520/CTR10930J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10930J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aHoriguchi, K., $eauthor.
=245  10$aEnd-Notched Flexure Testing and Analysis of Mode II Interlaminar Fracture Behavior of Glass-Cloth/Epoxy Laminates at Cryogenic Temperatures / $cK Horiguchi, Y Shindo, H Kudo, S Kumagai.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 4 (December 2002)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper presents results from an analytical and experimental study of the effect of temperature and geometrical variations on the Mode II interlaminar fracture toughness in glass-cloth/epoxy laminates. The end-notched flexure (ENF) test geometry was used for Mode II experiments, which were performed at room temperature (R.T.), liquid nitrogen temperature (77 K), and liquid helium temperature (4 K). The fracture surfaces were also examined by scanning electron microscopy to verify the fracture mechanisms. A finite element model was further used to perform the delamination crack analysis. Critical load levels, and the geometric and material properties of the test specimens were input data for the analysis, which evaluated the Mode II energy release rate at onset of delamination crack propagation. The results of the finite element analysis are used to supplement the experimental data.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCryomechanics.
=650  \0$aEnd-notched flexure testing.
=650  \0$aFinite element analysis.
=650  \0$aGlass-cloth/epoxy laminates.
=650  \0$aInterlaminar fracture toughness.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aCryomechanics.
=653  20$aEnd-notched flexure testing.
=653  20$aFinite element analysis.
=653  20$aGlass-cloth/epoxy laminates.
=653  20$aInterlaminar fracture toughness.
=700  1\$aShindo, Y., $eauthor.
=700  1\$aKudo, H., $eauthor.
=700  1\$aKumagai, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10930J.htm

=LDR  04307nam  2200757 i 4500
=001  CTR10931J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10931J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10931J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aPeters, PWM, $eauthor.
=245  10$aFiber Dominant Tensile and Creep Strength at 600°C of SCS-6 Fiber Reinforced Titanium Alloys / $cPWM Peters, J Hemptenmacher, K Weber, H Assler.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 4 (December 2002)
=504  \\$aIncludes bibliographical references$b16.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe influence of the fiber strength on the unidirectional tensile and creep strength at 600°C has been investigated. Single fiber tensile tests are performed at 600°C and the resulting Weibull strength distribution is compared with the room temperature distribution. The 600°C characteristic strength is found to be only 7.6% smaller than that at room temperature. Fibers extracted from loaded-unloaded specimens at 600°C show more failures than expected on the basis of the 600°C Weibull strength distribution determined as manufactured fibers. From this and other experiments it is concluded, that the in-situ tensile strength of fibers at 600°C (embedded in the titanium) is smaller than that of manufactured fibers. Relaxation behavior of the unreinforced titanium alloys was investigated and described with the aid of Bailey-Norton creep law. This enables description of the stress redistribution during creep of the unidirectional composites performed in short time creep experiments up to ∼100 h. The creep strength has been described considering stress relaxation in the matrix and slow defect growth in the fibers. From the shape of the creep strength-life curve it is concluded that three different ranges of defect growth contribute to the creep strength.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCreep.
=650  \0$aDefects.
=650  \0$aFiber strength.
=650  \0$aHigh temperature.
=650  \0$aRelaxation.
=650  \0$aSlow crack growth.
=650  \0$aTitanium matrix composites.
=650  \0$aWeibull strength distribution.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aTitanium matrix composites.
=653  20$aSiC-fiber.
=653  20$aFiber strength.
=653  20$aDefects.
=653  20$aWeibull strength distribution.
=653  20$aSlow crack growth.
=653  20$aHigh temperature.
=653  20$aCreep.
=653  20$aRelaxation.
=700  1\$aHemptenmacher, J., $eauthor.
=700  1\$aWeber, K., $eauthor.
=700  1\$aAssler, H., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10931J.htm

=LDR  03663nam  2200697 i 4500
=001  CTR10932J
=003  IN-ChSCO
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=008  161219c20029999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10932J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10932J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC183
=082  04$a541/.33$223
=100  1\$aMelograna, JD., $eauthor.
=245  10$aAdhesion of Stainless Steel to Fiber Reinforced Vinyl Ester Composite / $cJD Melograna, JL Grenestedt.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 4 (December 2002)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aJoints between stainless steel and composites have many applications. For example, marine vessels may be composed of a steel hull joined to a composite bow, stern, and/or topside structure. Joining these components adhesively is a major structural challenge, and overcoming this challenge necessitates the development of strong adhesion between steel and composites. The present study investigates AL-6XN stainless steel and glass fiber reinforced vinyl ester. Several specimens were manufactured with different surface preparations, adhesives, and/or additives. Short-term transverse tensile strength in dry conditions was used as the measure by which the different strategies were compared. All specimens were manufactured using a vacuum infusion technique, with the steel embedded within the fiber reinforcements before the molding. No secondary bonding was done.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesion.
=650  \0$aFiber reinforced composite.
=650  \0$aStainless steel.
=650  \0$aSurface preparation.
=650  \0$aTransverse tensile strength.
=650  \0$aVacuum infusion.
=650  \0$aVinyl ester.
=650  \0$aAdhesives.
=650  \0$aCohesion.
=653  10$aAdhesion.
=653  20$aSurface preparation.
=653  20$aFiber reinforced composite.
=653  20$aStainless steel.
=653  20$aVinyl ester.
=653  20$aTransverse tensile strength.
=653  20$aVacuum infusion.
=700  1\$aGrenestedt, JL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10932J.htm

=LDR  03474nam  2200661 i 4500
=001  CTR10947J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10947J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10947J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHosur, MV., $eauthor.
=245  10$aCompression After Impact Testing of Carbon Fiber Reinforced Plastic Laminates / $cMV Hosur, CRL Murthy, TS Ramurthy.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (14 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 2 (April 1999)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aCarbon fiber reinforced plastic (CFRP) composite laminates are susceptible for multiple delaminations, which reduce the compressive strength significantly even when the impact load is insufficient to cause visible damage. The post-impact compression test is used widely to assess the relative performance of different composite laminates with different fiber matrix combinations. In the present work, CFRP (T300/924) laminates were subjected to low-velocity impact loading simulating tool drops and runway debris. Compression after impact (CAI) tests were performed using fixtures as per NASA specifications. Results obtained indicate definite correlation between impact energy, failure strain, and residual compressive strength.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aCompression-after-impact.
=650  \0$aFailure strain.
=650  \0$aLow-velocity impact.
=650  \0$aResidual strength.
=650  \0$aComposite material.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aLow-velocity impact.
=653  20$aCompression-after-impact.
=653  20$aResidual strength.
=653  20$aFailure strain.
=700  1\$aMurthy, CRL, $eauthor.
=700  1\$aRamurthy, TS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10947J.htm

=LDR  03733nam  2200661 i 4500
=001  CTR10948J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10948J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10948J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aLiu, H-K, $eauthor.
=245  10$aCompressive Strength of Hybrid Composite Tubes After Low-Energy Impact / $cH-K Liu, N-H Tai, S-Y Lin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 2 (April 1999)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aHybrid composite tubes were wound with Kevlar fibers under three winding angles and sandwiched by either hoop carbon or glass fibers. The tubes subjected to low-energy impact using a drop-weight impact apparatus with a round-ended impactor have been investigated. Compression after impact (CAI) strengths were measured, and the damage tolerances of hybrid tubes were assessed by the residual strengths. Compared to compressive strengths of the tubes without low-energy impact, CAI strengths of hybrid tubes decreased significantly due to delamination generation and propagation from the impact site. The microstructure of CAI hybrid tubes were examined, and explanations for their damage modes through the thickness were proposed. We also studied the damage mechanisms that were induced by impact and compression, and their interaction, which was related to winding angle and hybrid fibers. In addition, the correlation among damage mechanisms, failure modes, and CAI strengths was also investigated.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCompression after impact.
=650  \0$aDelamination.
=650  \0$aFilament winding.
=650  \0$aHybrid.
=650  \0$aLow-energy impact.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aHybrid.
=653  20$aLow-energy impact.
=653  20$aFilament winding.
=653  20$aCompression after impact.
=653  20$aDelamination.
=700  1\$aTai, N-H, $eauthor.
=700  1\$aLin, S-Y, $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10948J.htm

=LDR  03728nam  2200661 i 4500
=001  CTR10949J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10949J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10949J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aNeu, RW., $eauthor.
=245  10$aDamage Modeling of a Transversely Loaded Titanium Matrix Composite Under Cyclic Conditions / $cRW Neu, AM Patel.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 2 (April 1999)
=504  \\$aIncludes bibliographical references$b24.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe life-limiting loading configuration of weakly bonded unidirectional titanium matrix composites is often transverse cyclic loading. Most fatigue tests under this loading configuration have been conducted at maximum stress levels above the monotonic proportional limit. However, the fatigue behavior at maximum stress levels below the monotonic proportional limit is often of interest, yet little work has been performed to identify this region on the fatigue life diagram. This investigation examined the behavior of a 16-ply SCS-9/Timetal 21S composite loaded transversely under generally low amplitude fatigue conditions. The fatigue limit under this loading configuration was found to be about one half the proportional limit. Residual strength tests were then conducted to determine the state of damage through measuring the change in stiffness using a number of unloading and reloading events. A damage mechanics methodology was demonstrated as a means to quantify the effects of the fatigue damage on the mechanical performance.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDamage mechanics.
=650  \0$aFatigue.
=650  \0$aResidual strength.
=650  \0$aTitanium matrix composites.
=650  \0$aTransverse loading.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aTitanium matrix composites.
=653  20$aTransverse loading.
=653  20$aFatigue.
=653  20$aResidual strength.
=653  20$aDamage mechanics.
=700  1\$aPatel, AM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10949J.htm

=LDR  04628nam  2200721 i 4500
=001  CTR10950J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10950J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10950J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.S3
=082  04$a624.1/779$223
=100  1\$aVaidya, UK., $eauthor.
=245  10$aLow-Velocity Impact Response of Cross-Ply Laminated Sandwich Composites with Hollow and Foam-Filled Z-Pin Reinforced Core / $cUK Vaidya, MV Kamath, MV Hosur, H Mahfuz, S Jeelani.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (14 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 2 (April 1999)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSandwich composites offer unique lightweight and high bending stiffness advantages for a wide variety of engineered structures. Traditional foam core sandwich constructions exhibit low transverse stiffness and catastrophic compression failure of the core, besides being inaccessible in terms of space. In this study, two configurations including a hollow truss/Z-pin core comprising a three-dimensional (3-D) open network of titanium pins and a foam core reinforced with a 3-D arrangement of titanium pins have been considered in conjunction with traditional foam core sandwich composites. These innovative core designs have the potential to enhance the impact damage resistance, and provide damage containment mechanisms and space/core accessibility advantages. The top and bottom facesheets in all three types of sandwich constructions are made from 16 layers of E-glass/epoxy prepregs stacked in crossly orientation. The low-velocity impact response of the composites is studied at five energy levels, ranging from 11 to 40 J, with an intention of investigating the damage initiation, damage propagation, and failure mechanisms. The influence of spacing the Z-pins in a foam core has also been studied at the same five energy levels. Detailed microscopic inspection has been conducted to determine the impact failure characteristics of the three types of sandwich composites. For the energy levels considered, the results demonstrate that by reinforcing the foam cells with Z-pins, low-velocity impact damage is contained effectively and is limited to the localized dimensions of the core and facesheet that lie within a pain cluster dimension.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFoam core.
=650  \0$aFoam reinforced pins.
=650  \0$aLow-velocity impact damage.
=650  \0$aSandwich composites.
=650  \0$aTruss core.
=650  \0$aZ-pin reinforcement.
=650  \0$aSandwich construction.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xStructural.
=653  10$aSandwich composites.
=653  20$aZ-pin reinforcement.
=653  20$aFoam core.
=653  20$aFoam reinforced pins.
=653  20$aTruss core.
=653  20$aLow-velocity impact damage.
=700  1\$aKamath, MV., $eauthor.
=700  1\$aHosur, MV., $eauthor.
=700  1\$aMahfuz, H., $eauthor.
=700  1\$aJeelani, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10950J.htm

=LDR  03943nam  2200613 i 4500
=001  CTR10951J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10951J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10951J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.54
=082  04$a620.1/1296$223
=100  1\$aZalameda, JN., $eauthor.
=245  10$aMeasured Through-the-Thickness Thermal Diffusivity of Carbon Fiber Reinforced Composite Materials / $cJN Zalameda.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 2 (April 1999)
=504  \\$aIncludes bibliographical references$b18.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe thermal diffusivity of carbon fiber reinforced composite materials is dependent on fiber, matrix, and porosity volume fractions. Since the carbon fiber thermal conductivity is much greater than the epoxy resin matrix thermal conductivity, thermal diffusivity is a good indicator of the fiber volume fraction. In this study, through-the-thickness thermal diffusivity images were obtained nondestructively on carbon fiber reinforced composite plates, and the values varied from 0.0035 to 0.0062 cm2/s. The fiber and porosity volume fractions were measured destructively, and their values varied from 56.0 to 70.5% and from 0.9 to 7.2%, respectively. The destructive test data were used as a standard for comparison of three commonly used transverse equivalent thermal conductivity models: the Stacked Plate, the mixed flow Cylindrical Fiber model, and the Composite Circular Assemblage model. In these models, a porosity correction is also studied. There was very good agreement between the Composite Circular Assemblage and Cylindrical Fiber model when porosity levels were less than 2%. The porosity correction helped to reduce the chi-squared value by 24% in the Cylindrical Filament model. Finally, the potential is discussed to image fiber volume fraction nondestructively using the described thermal measurement system.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDestructive testing.
=650  \0$aFiber fraction and porosity.
=650  \0$aGraphite fiber composite.
=650  \0$aThermal diffusivity.
=650  \0$aDensity currents.
=650  \7$aSCIENCE $xNanoscience.
=653  10$aGraphite fiber composite.
=653  20$aThermal diffusivity.
=653  20$aDestructive testing.
=653  20$aFiber fraction and porosity.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10951J.htm

=LDR  03359nam  2200709 i 4500
=001  CTR10952J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20039999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10952J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10952J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA347.F5
=082  04$a620.00151825$223
=100  1\$aChandra, R., $eauthor.
=245  10$aExperimental Evaluation of Damping of Fiber-Reinforced Composites / $cR Chandra, SP Singh, K Gupta.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 2 (April 2003)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAnisotropic behavior of damping in fiber-reinforced composites is well established. An attempt is made to measure all the six loss factors for glass fiber-reinforced epoxy (three in normal and three in shear) experimentally using free decay method. Different types of specimen such as beam, tubular and cuboidal in shape made from glass fiber-reinforced epoxy are tested under different loading conditions. The six loss factors (η11, η22, η33, η12, η13 and η23) so determined are compared with the analytical results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnd cuboidal specimen.
=650  \0$aBeam.
=650  \0$aDamping.
=650  \0$aFiber-reinforced composite.
=650  \0$aFinite-element analysis.
=650  \0$aLoss factor.
=650  \0$aTubular.
=650  \0$aFinite element method.
=650  \7$aTECHNOLOGY & ENGINEERING $xEngineering (General.
=653  10$aDamping.
=653  20$aLoss factor.
=653  20$aFiber-reinforced composite.
=653  20$aBeam.
=653  20$aTubular.
=653  20$aAnd cuboidal specimen.
=653  20$aFinite-element analysis.
=700  1\$aSingh, SP., $eauthor.
=700  1\$aGupta, K., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10952J.htm

=LDR  03404nam  2200649 i 4500
=001  CTR10953J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20039999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10953J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10953J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aTaheri, F., $eauthor.
=245  12$aA Rational Procedure for Development of Hybrid Composite Masts / $cF Taheri, M Hassan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 2 (April 2003)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis study was carried out with the aim of developing a rational and effective design procedure for the development of cost-effective composite masts that can be manufactured by automated manufacturing procedure. This was in response to the lack of availability of systematic design and analytical procedure for such structural components, and the relatively high cost of the currently available composite masts in market. To achieve this objective, a systematic evaluation of the loads on the mast was performed, followed by a relatively accurate design procedure that considered structural design of an actual mast for a commonly used YD-40 boat. It will be shown that the proposed mast will be less expensive than the commercially available all carbon-epoxy masts.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAnalytical solution.
=650  \0$aBuckling.
=650  \0$aComposites.
=650  \0$aFinite element method.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aMasts.
=653  20$aBuckling.
=653  20$aFinite element method.
=653  20$aMast loads.
=653  20$aAnalytical solution.
=700  1\$aHassan, M., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10953J.htm

=LDR  03662nam  2200637 i 4500
=001  CTR10954J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20039999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10954J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10954J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA347.F5
=082  04$a620.00151825$223
=100  1\$aChiewanichakorn, M., $eauthor.
=245  10$aFailure Analysis of Fiber-Reinforced Polymer Bridge Deck System / $cM Chiewanichakorn, AJ Aref, S Alampalli.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 2 (April 2003)
=504  \\$aIncludes bibliographical references$b13.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThroughout the United States including New York, many reinforced concrete bridges on county and state highway systems have deteriorated to the certain degree that structural strengthening is necessary to extend their service life. Fiber reinforced polymer (FRP) composite systems appeared to be one of the options to address the issues of cost-effective load-rating improvement. Recently, an FRP deck has been installed on a state highway, located in New York State, as an experimental project. This paper describes multi-step linear static analyses that were conducted using the finite element method to study the possible failure mechanisms of the deck-superstructure system. Finite element model was verified using the load tests of the bridge deck. Furthermore, the thermal behavior of the FRP deck was investigated and presented in this paper. Analytical results reveal several potential failure mechanisms for the FRP deck and truss bridge system.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBridge deck.
=650  \0$aFiber-reinforced polymer (FRP).
=650  \0$aFinite element analysis.
=650  \0$aThermal analysis.
=650  \0$aFinite element method.
=650  \7$aTECHNOLOGY & ENGINEERING $xEngineering (General.
=653  10$aFiber-reinforced polymer (FRP).
=653  20$aFinite element analysis.
=653  20$aBridge deck.
=653  20$aThermal analysis.
=700  1\$aAref, AJ., $eauthor.
=700  1\$aAlampalli, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10954J.htm

=LDR  04384nam  2200637 i 4500
=001  CTR10955J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20039999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10955J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10955J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNayeb-Hashemi, H., $eauthor.
=245  10$aAnalytical Determination of Localized Heat Damage in Fiberglass Reinforced Resin Beams Using the Frequency Response Shifting / $cH Nayeb-Hashemi, A Harrison, A Vaziri.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 2 (April 2003)
=504  \\$aIncludes bibliographical references$b20.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe dynamic response of a localized, heat-damaged, fiberglass-reinforced epoxy cantilever beam is obtained as a function of damaged length and damage severity. A heat-damaged area causes a reduction in the local stiffness of the beam and introduces a complex damping in the damaged zone. These variations in the local mechanical properties could result in changing vibration characteristics of the beam. The variations in the system characteristic could then be used to assess the structural integrity of the composite beam. A cantilever beam made of a glass fiber-resin composite material and damaged by a hot tip contact element and a laser beam is evaluated for its dynamic response using numerical methods. The laser beam caused local melting of many fibers in the damaged area and thus reducing the stiffness of the beam in the damaged area. The beam is analyzed by modeling it as a lumped system and a continuous system and by a finite element. The goal of the research is to find out whether the changes in the frequency response of the damaged beam can be used as a diagnostic tool for estimating the severity of the damage. The results show that the size and location of damage are equally as important as the local stiffness and damping of the damaged region in terms of their effects on the beam resonant frequencies. The results indicate that the resonance frequencies may not be suitable parameters for estimating the residual tensile strength of the composite. A 50% reduction in the local bending rigidity produced relatively little change in the system first resonance frequency. In contrast, it significantly reduced the residual tensile strength of the composite.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aDynamic response.
=650  \0$aHeat damage.
=650  \0$aNatural frequency.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite.
=653  20$aHeat damage.
=653  20$aNatural frequency.
=653  20$aDynamic response.
=700  1\$aHarrison, A., $eauthor.
=700  1\$aVaziri, A., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10955J.htm

=LDR  02994nam  2200541 i 4500
=001  CTR10956J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20039999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10956J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10956J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aUleck, KR., $eauthor.
=245  10$aInfluence of Temperature on the Fatigue Life of a Quasi-isotropic Gr/Ep Laminate / $cKR Uleck, AJ Vizzini.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 3 (July 2003)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper describes the development and results of a tension-tension fatigue life test program. The fatigue life of a quasi-isotropic graphite/epoxy laminate was experimentally measured at three temperatures: −195°C, 22°C, and 121°C. To perform testing at these temperatures a supplemental gripping fixture and a cold cell were designed and manufactured. Issues addressed during the test program include failure of the gripping system, grip-induced failure of the test laminate, and temperature stability. The test results showed that the test laminate's nominal fatigue life improved when tested at −195°C, and decreased when tested at 121°C.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=700  1\$aVizzini, AJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10956J.htm

=LDR  03910nam  2200649 i 4500
=001  CTR10957J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20039999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10957J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10957J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aNoh, J., $eauthor.
=245  10$aEffect of Laminate Design and Loads on Crack Opening Volume in Laminates Used in Cryogenic Tanks / $cJ Noh, J Whitcomb.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 3 (July 2003)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe use of advanced composite materials for cryogenic fuel tanks reduces the mass of the structure but the leakage of fuel can become a problem. Since the amount of leakage will increase with crack opening volume, it is essential that we understand the factors that affect the crack opening. In a previous study by the authors, the degradation behavior of lamina properties due to cracking was studied extensively. The study examined the effects of a variety of parameters such as adjacent ply orientation, material properties of adjacent plies, initial properties of the cracked ply, and cracks in adjacent plies on the effective properties of the cracked ply. It was shown that the rate of degradation is not very sensitive to these parameters. In the current paper, it will be shown that the crack opening volume can be directly related to changes in effective moduli. A simple calculation of the crack opening volume for a laminate based on the degradation of the E22 of a cracked lamina is presented. The effect of various parameters on the crack opening volume shows a similar pattern as the E22 degradation of a cracked ply. This suggests that the opening volume is expected to also be quite insensitive to the laminate design parameters listed above.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aCrack opening.
=650  \0$aCryogenic tanks.
=650  \0$aLaminates.
=650  \0$aMatrix crack.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite.
=653  20$aLaminates.
=653  20$aMatrix crack.
=653  20$aCrack opening.
=653  20$aCryogenic tanks.
=700  1\$aWhitcomb, J., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10957J.htm

=LDR  03849nam  2200637 i 4500
=001  CTR10958J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
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=008  161219c20039999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10958J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10958J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.56
=082  04$a620.1/1296$223
=100  1\$aWang, YL., $eauthor.
=245  10$aEffect of Interfacial Bonding Strength on Thermal Expansion Behavior of Carbon-Fiber-Reinforced Copper-Matrix Composites / $cYL Wang, FG Zhou, YZ Wan.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 3 (July 2003)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAlloying elements were added to the copper matrix to produce unidirectional carbon-fiber-reinforced copper-matrix composites with different interfacial bonding strengths (IBS). The thermal expansion coefficients of these composites were determined to investigate the influence of the IBS on the thermal expansion behavior at a low temperature range. The results showed that the thermal expansion coefficient (CTE) at low temperatures (elastic region) of the composites was controlled by the IBS. Furthermore, the IBS of the composites was observed to control the thermal stresses in the matrix and, therefore, to affect the temperature of the onset of matrix yielding. However, the relationship between IBS and expansion behavior at a high temperature range (beyond elastic region) for the present carbon-fiber copper composite system cannot be determined because of the influence of matrix strength. Further work is underway to develop a model so as to correlate the IBS with the CTE of the composites under elastic stage, and a suitable composite system is needed to correlate the IBS to the CTE at high temperatures.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCarbon fiber.
=650  \0$aCopper matrix composite.
=650  \0$aInterfacial bonding strength.
=650  \0$aThermal expansion behavior.
=650  \0$aThermal expansion.
=650  \0$aMaterials $xThermal properties.
=653  10$aCopper matrix composite.
=653  20$aCarbon fiber.
=653  20$aInterfacial bonding strength.
=653  20$aThermal expansion behavior.
=700  1\$aZhou, FG., $eauthor.
=700  1\$aWan, YZ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10958J.htm

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=024  7\$a10.1520/CTR10959J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10959J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.84
=082  04$a620.1/127$223
=100  1\$aKumosa, M., $eauthor.
=245  10$aStress Corrosion Cracking in a Unidirectional E-Glass/Polyester Composite Subjected to Static and Cyclic Loading Conditions / $cD Armentrout, M Gentz, L Kumosa, B Benedikt, M Kumosa.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (17 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 4 (October 2003)
=504  \\$aIncludes bibliographical references$b33.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis work evaluates the effects of static and cyclic loading conditions on the stress corrosion process in unidirectional glass/modified polyester composite in the presence of a nitric acid solution. The composites were investigated under static, cyclic, and static with overload conditions using a rectangular specimen with centrally positioned grooves. The stress corrosion process was monitored using acoustic emission (AE). It was found that the time-to-failure of the composite specimens were only slightly affected by loading conditions. However, the large scatter in the time-to-failure of the specimens did not allow for the proper evaluation of the effect of the cyclic loads on the stress corrosion fracture process. It seemed that the time-to-failure were more influenced by the specimen variations than by the type of loading. By using an AE digital set-up based on four transducers, not only can the fiber fracture by stress corrosion be very accurately monitored, but also the location of AE sources can be precisely determined.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAcoustic emission.
=650  \0$aAcoustical engineering.
=700  1\$aGentz, M., $eauthor.
=700  1\$aKumosa, L., $eauthor.
=700  1\$aBenedikt, B., $eauthor.
=700  1\$aKumosa, M., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10959J.htm

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=001  CTR10960J
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=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20039999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10960J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10960J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA347.F5
=082  04$a620.00151825$223
=100  1\$aBekisli, B., $eauthor.
=245  10$aWrinkling of Zebra Skin Sandwich Panels / $cB Bekisli, JL Grenestedt.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 4 (October 2003)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe wrinkling, or skin buckling, behavior of sandwich panels with skins consisting of equally spaced strips was investigated. These so-called zebra skin sandwiches proved to be superior to full skin sandwiches in terms of weight and wrinkling strength. Two and three-dimensional finite element analyses were performed and the full skin sandwich results were compared to various results in the open literature. An approximate analytical estimate, using Euler-Bernoulli kinematics in the skin and a simple exponentially decaying field in the core, was derived and compared with finite element results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFinite element method.
=650  \0$aGrid skins.
=650  \0$aSandwich.
=650  \0$aSkin strips.
=650  \0$aWrinkling.
=650  \0$aFinite element method.
=650  \7$aTECHNOLOGY & ENGINEERING $xEngineering (General.
=653  10$aSandwich.
=653  20$aSkin strips.
=653  20$aGrid skins.
=653  20$aWrinkling.
=653  20$aFinite element method.
=700  1\$aGrenestedt, JL., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10960J.htm

=LDR  03602nam  2200649 i 4500
=001  CTR10961J
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=008  161219c20039999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10961J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10961J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/186$223
=100  1\$aReeder, JR., $eauthor.
=245  10$aRefinements to the Mixed-Mode Bending Test for Delamination Toughness / $cJR Reeder.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 4 (October 2003)
=504  \\$aIncludes bibliographical references$b11.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe mixed-mode bending (MMB) test for delamination toughness was first introduced in 1988. This simple test is a combination of the standard Mode I (opening) test and a Model II (sliding) test. This MMB test has become widely used in the United States and around the world for mixed-mode toughness measurements. Because of the widespread use of this test method, it has been standardized by ASTM Committee D30 as ASTM Standard Test Method D6671. During the standardization process a round robin test activity was conducted that led to several modifications to the test protocol. These modifications included a new method for calculating toughness from the measured test quantities, a more accurate way of setting the mixed-mode ratio to be tested, and the inclusion of a new alignment criterion for improved consistency in measured values. The rational for these modifications, which were included in the test protocol before standardization, are discussed in this paper.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aDelamination.
=650  \0$aFracture toughness.
=650  \0$aMixed-mode.
=650  \0$aTesting.
=650  \0$aComposite materials $xDelamination $xPrevention.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aDelamination.
=653  20$aComposite.
=653  20$aFracture toughness.
=653  20$aMixed-mode.
=653  20$aMMB.
=653  20$aTesting.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10961J.htm

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=001  CTR10970J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10970J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10970J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA660.P6
=082  04$a624.1/7765$223
=100  1\$aKim, H., $eauthor.
=245  14$aThe Design of In-Plane Shear and Tension-Loaded Bonded Composite Lap Joints / $cH Kim, KT Kedward.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (11 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 2 (April 2002)
=504  \\$aIncludes bibliographical references$b12.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe stress analysis of a bonded joint carrying combined in-plane shear and tension load is presented. A general equation is derived that governs the transfer of shear load through a joint. For the case of uniform in-plane shear loading, a closed-form solution exists that is directly analogous to the well-known tension-loaded case. When shear and tension loads are simultaneously applied to a joint, the results of stress analyses treating each loading case separately are superimposed to calculate a combined biaxial shear stress state in the adhesive. Predicting the elastic limit of the adhesive for a lap joint under combined loading is then accomplished by using the von Mises yield criterion. This approach allows the calculation of a limit load envelope that maps the range of combined loading conditions within which the joint is expected to behave elastically. An example design case study of a bonded I-beam shear web is included.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCombined loading.
=650  \0$aComposite bonded lap joint.
=650  \0$aIn-plane shear loading.
=650  \0$aShear (Mechanics)
=650  \7$aTECHNOLOGY & ENGINEERING.
=653  10$aComposite bonded lap joint.
=653  20$aIn-plane shear loading.
=653  20$aCombined loading.
=700  1\$aKedward, KT., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10970J.htm

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=001  CTR10971J
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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10971J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10971J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aKrueger, R., $eauthor.
=245  10$aFatigue Life Methodology for Bonded Composite Skin/Stringer Configurations / $cR Krueger, IL Paris, TK O'Brien, PJ Minguet.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (24 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 2 (April 2002)
=504  \\$aIncludes bibliographical references$b25.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA methodology is presented for determining the fatigue life of composite structures based on fatigue characterization data and geometric nonlinear finite element analyses. To demonstrate the approach, predicted results were compared to fatigue tests performed on specimens which consisted of a tapered composite flange, representing a stringer or frame, bonded onto a composite skin. In a first step, quasi-static tension and fatigue tests were performed to evaluate the debonding mechanisms between the skin and the bonded stringer. Specimen edges were examined under the microscope to document the damage occurrence. In a second step, a two-dimensional finite element model was developed to analyze the tests. To predict matrix cracking onset, the relationship between the externally applied tension load and the maximum principal stresses transverse to the fiber direction was determined through geometrically nonlinear analysis. Transverse tension fatigue life data were used to generate an onset fatigue life P-N curve for matrix cracking. The resulting prediction was in good agreement with measured data from the fatigue tests. In a third step, a fracture mechanics approach based on geometrically nonlinear analysis was used to determine the relationship between the externally applied tension load and the critical energy release rate. Mixed mode energy release rate fatigue life data from DCB, 4ENF, and MMB tests were used to create a fatigue life onset G-N curve for delamination. The resulting prediction was in good agreement with data from the fatigue tests. Additionally, the prediction curve for cumulative life to failure was generated from the matrix onset and delamination onset fatigue life curves. The results were in good agreement with data from the fatigue tests, which demonstrated that the methodology offers a significant potential to predict cumulative fatigue life of composite structures.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aFatigue life prediction.
=650  \0$aFinite element analysis.
=650  \0$aFracture mechanics.
=650  \0$aSkin/flange interface.
=650  \0$aTesting.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aTesting.
=653  20$aFinite element analysis.
=653  20$aFatigue life prediction.
=653  20$aFracture mechanics.
=653  20$aSkin/flange interface.
=700  1\$aParis, IL., $eauthor.
=700  1\$aO'Brien, TK., $eauthor.
=700  1\$aMinguet, PJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10971J.htm

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=022  \\$a0884-6804
=024  7\$a10.1520/CTR10972J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10972J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA492.A3
=082  04$a668/.3$223
=100  1\$aTomblin, J., $eauthor.
=245  10$aCharacterization of Bondline Thickness Effects in Adhesive Joints / $cJ Tomblin, P Harter, W Seneviratne, C Yang.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 2 (April 2002)
=504  \\$aIncludes bibliographical references$b27.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aGrowing application of composite materials in airframe structures tends to make significant use of bonded constructions. Despite the large work that has been done on adhesive characterization over previous years, various certification-related issues arise in these applications. The available test methods for determining the in situ properties of an adhesive joint for use in the design must be clarified for thick bondlines, where there is a lack of readily available data. Results from three test methods indicated a decrease in the apparent shear strength as the bondline thickness was increased. The apparent shear strength given by the test methods investigated was found to be highly dependent on the adherend bending stiffness, which directly effects the peel stress distributions in the adhesive layer. In the adhesive strength comparisons as a function of test method, it was found that the thin-adherend tests gave different comparative results than the thick-adherend tests, which were primarily a function of the high peel stresses in the thin-adherend joints. This combined state of stress does not give a true view of the apparent shear stress of the adhesive, but rather an indication of the adhesive behavior under this type of combined loading. It is recommended that thick adherends be used when comparing different adhesive systems for apparent shear strength, and that thin adherends should be used for qualitative tests only.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive.
=650  \0$aBondline thickness.
=650  \0$aJoint.
=650  \0$aLap shear.
=650  \0$aAdhesive bonding.
=650  \0$aAdhesive joints.
=650  \0$aGlued joints.
=653  10$aAdhesive.
=653  20$aJoint.
=653  20$aLap shear.
=653  20$aBondline thickness.
=700  1\$aHarter, P., $eauthor.
=700  1\$aSeneviratne, W., $eauthor.
=700  1\$aYang, C., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10972J.htm

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=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20029999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10973J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10973J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHuang, H., $eauthor.
=245  10$aStress and Failure Analyses of Adhesive-Bonded Composite Joints Using ASTM D3165 Specimens / $cH Huang, C Yang, JS Tomblin, P Harter.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2002.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 24, Issue 2 (April 2002)
=504  \\$aIncludes bibliographical references$b33.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn analytical model was developed to determine the stress and strain distributions of single-lap adhesive-bonded composite joints under tension. Both the adherend and the adhesive were assumed linear elastic in the derivations. The Laminated Plate Theory was used in defining the mechanical behavior of the composite adherends, whereas the linear elasticity theory was applied to describe the material response of the adhesive. By doing so, the stresses in the adhesive can vary through the bondline thickness. After the overall system of governing equations was determined by energy method, it was solved by using a symbolic solver-Maple with appropriate boundary conditions. Results from the analytical model were verified with finite element analysis using commercial software ABAQUS. Single-lap composite joint experiments were conducted following ASTM D3165, Strength Properties of Adhesives in Shear by Tension Loading of Single-Lap-Joint Laminated Assemblies. Although all three failure modes of bonded joints, substrate, cohesive, and adhesive failure, were present as the experimental results, the substrate failure mode was the major failure mode observed. Therefore, only substrate failure mode was analyzed using the developed model in the present paper. Four failure criteria, Tsai-Hill failure criterion, von Mises failure criterion, maximum interlaminar tensile stress criterion, and maximum normal stress criterion, were used to correlate the stresses and failure load. Nonlinear regression was conducted to determine the necessary parameters in the failure criteria. Based on the experimental results, thicker bondlines result in weaker joints. The variation of failure load for joints with various bondline thicknesses was consistent with the predicted results.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2002. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aAdhesive.
=650  \0$aBonded joints.
=650  \0$aComposites.
=650  \0$aLap joints.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposites.
=653  20$aAdhesive.
=653  20$aBonded joints.
=653  20$aLap joints.
=700  1\$aYang, C., $eauthor.
=700  1\$aTomblin, JS., $eauthor.
=700  1\$aHarter, P., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10973J.htm

=LDR  03463nam  2200625 i 4500
=001  CTR10982J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10982J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10982J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aEllenburg, MG., $eauthor.
=245  10$aModeling of Thermal Stresses in Yttrium Aluminum Garnet and Alumina Fibers Coated with β"-Alumina / $cMG Ellenburg, WJ Lackey.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 4 (October 1999)
=504  \\$aIncludes bibliographical references$b17.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aSince layered aluminate coatings such as β"-alumina are being considered for tailoring the interfacial properties of oxidation-resistant fiber-reinforced composites, stresses arising from thermal expansion mismatch were calculated for the substrate fiber and coating. Both isotropic and anisotropic β"-alumina coatings were analyzed for yttrium aluminum garnet and single crystal and polycrystalline alumina fibers. It was possible to rank the various fiber-coating combinations in terms of the magnitude of maximum tensile stresses present in the coating. Polycrystalline alumina + isotropic β"-alumina yielded the lowest tensile stresses with radial stress on the order of 10 MPa, while single crystal alumina + anisotropic β"-alumina yielded the highest tensile stresses with tangential stress on the order of >100 MPa.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCeramic matrix composites.
=650  \0$aFibers.
=650  \0$aInterface coatings.
=650  \0$aStress.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCeramic matrix composites.
=653  20$aInterface coatings.
=653  20$aFibers.
=653  20$aStress.
=700  1\$aLackey, WJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10982J.htm

=LDR  03659nam  2200601 i 4500
=001  CTR10983J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10983J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10983J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aZhang, K., $eauthor.
=245  10$aAnalysis of Mechanical Yield Behavior and Constitutive Response of MMC / $cK Zhang, GM Newaz.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 4 (October 1999)
=504  \\$aIncludes bibliographical references$b50.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn effective stress function utilizing the J2 theory, which includes plasticity and damage, was investigated to predict the monotonic response of metal matrix composite (MMC). The damage considered was in the form of debonding between fiber and matrix and plasticity in the form of slip bands in the matrix. Yield surfaces were generated with consideration of both damage and plasticity in effect. The computational micromechanics analysis involved a unit cell model utilizing the ABAQUS code for analysis. The constitutive response predictions from the J2 model were compared with experimental results from monotonic unidirectional loading for transverse tension, compression, longitudinal tension, and pure shear. The finite element analysis estimated apparent yield points at a variety of combinations of normal stresses. Both σ11 and σ22 were consistent with the results obtained from the effective stress function, providing a strong basis for the use of the J2 theory to account for combined plasticity and damage response of MMCs. Good correlation was obtained between experiments and predictions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aConstitutive response.
=650  \0$aMechanical yield behavior.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aMMC.
=653  20$aMechanical yield behavior.
=653  20$aConstitutive response.
=700  1\$aNewaz, GM., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10983J.htm

=LDR  03304nam  2200589 i 4500
=001  CTR10984J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10984J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10984J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHussain, A., $eauthor.
=245  14$aThe Wyoming-Modified Two-Rail Shear Test Fixture for Composite Materials / $cA Hussain, D Adams.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 4 (October 1999)
=504  \\$aIncludes bibliographical references$b22.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA significantly modified two-rail shear fixture with a new clamping concept and enhanced gripping capability has been designed, fabricated, and evaluated. This new fixture solves some of the major shortcomings associated with the ASTM Standard D 4255 Two-Rail Shear test procedure, including limited specimen gripping ability, the need for specimens with holes, and potential failure by out-of-plane buckling. The in-plane unidirectional ply shear properties of AS4/3501-6 carbon/epoxy were measured using specimens of [0/90]3S cross-ply orientation. Repeatable results and acceptable failure modes were obtained. The excellent gripping capability of the new test fixture was also demonstrated in tests of an AS4/3501-6 carbon/epoxy [±45]4S angle-ply composite, a very high shear strength material.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aShear test fixture.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aShear test fixture.
=653  20$aComposite materials.
=653  20$aTwo-rail test.
=700  1\$aAdams, D., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10984J.htm

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=001  CTR10985J
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=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c19999999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10985J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10985J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQH212.S3
=082  04$a502/.8$223
=100  1\$aShaker, M., $eauthor.
=245  10$aComparison of the Low and High Velocity Impact Response of Kevlar Fiber-Reinforced Epoxy Composites / $cM Shaker, F Ko, J Song.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c1999.
=300  \\$a1 online resource (6 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 21, Issue 4 (October 1999)
=504  \\$aIncludes bibliographical references$b10.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFailure mechanisms of basket weave and 3-D braided Kevlar-fabric reinforced epoxy composites under low and high velocity impacts have been studied. The purpose of this study is to examine the initiation and development of damage under these two widely differing loading conditions on 2-D and 3-D structure fabric composites. The critical evaluation of post-damage composite panels was conducted using a combination of high magnification photography, optical microscopy, and scanning electron microscopy (SEM). The first objective, quantification, has been realized in principle with regards to laminated composites, and it has been demonstrated that dispersive failure occurs in these composites. The second objective in this work established the relationship between kinetic energy absorbed and the damage tolerance of inter-leaved composites as assessed by the impact tests. High velocity impact loading by a small projectile is generally more detrimental to the integrity of a composite structure than low velocity dropweight impact loading.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d1999. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBasket weave.
=650  \0$aHigh velocity.
=650  \0$aImpact test.
=650  \0$aLow velocity.
=650  \0$aMicroscopy, Electron, Scanning.
=650  \0$aElectron microscopy.
=653  10$aKevlar-fabric reinforced epoxy.
=653  20$aImpact test.
=653  20$aLow velocity.
=653  20$aHigh velocity.
=653  20$a3-D braid.
=653  20$aBasket weave.
=700  1\$aKo, F., $eauthor.
=700  1\$aSong, J., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10985J.htm

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=001  CTR10996J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10996J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10996J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aQC793.3.F5
=082  04$a530.1/43$223
=100  1\$aWoo, K., $eauthor.
=245  10$aLow Degree of Homogeneity Due to Phase Shifts for Woven Composites / $cK Woo, YW Suh.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 4 (October 2001)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this study, variation of effective properties due to fiber tow phase shifts was investigated for woven textile composites. Plain weave unit cells were modeled with randomly selected phase shifts. Effective properties were calculated using macro finite elements and the results were assessed statistically. It was found that the effective properties depended strongly on the tow phase shifts for thin plain weave composites. The variation in the effective modulus and Poisson's ratio was large, and it showed skewed distributions. As the number of layers increased, however, the average properties converged and the coefficient of variation decreased.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aEffective properties.
=650  \0$aMacroelement.
=650  \0$aPhase shift.
=650  \0$aWoven composites.
=650  \0$aMonte Carlo method.
=653  10$aWoven composites.
=653  20$aPhase shift.
=653  20$aEffective properties.
=653  20$aMonte Carlo simulation.
=653  20$aMacroelement.
=700  1\$aSuh, YW., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10996J.htm

=LDR  03698nam  2200685 i 4500
=001  CTR10997J
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=005  20161219163000.0
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=007  cr\\\\\\\\\\\\
=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10997J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10997J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTP1180.E6
=082  04$a668.4/226$223
=100  1\$aKnack, JL., $eauthor.
=245  10$aEnergy Absorption of Truncated Kevlar Epoxy Cones Under Off-Axis Loads / $cJL Knack, AJ Vizzini.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 4 (October 2001)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aA total of 27 Kevlar/epoxy truncated cones was manufactured and crushed under off-axis loads. Side loads were introduced by cutting the cones at angles relative to their central axes. The failure modes were observed, and the specific sustained crushing stresses were determined and compared against graphite/epoxy cones of the same lay-up and similar geometry. The Kevlar/epoxy cones exhibited significantly different failure modes than the graphite/epoxy cones. Specifically, the cones did not experience brittle fracture, and thus maintained structural integrity after crushing. The Kevlar/epoxy cones were less sensitive to the angle of the applied load than similar graphite/epoxy cones; however, the energy absorbed per unit mass is significantly lower. The role of specimen taper and load inclination is different than that for graphite/epoxy cones. In particular, 10° tapered cones overall had the best performance even under uniaxial loading conditions.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBuckling.
=650  \0$aCompression.
=650  \0$aCrash worthiness.
=650  \0$aCrushing.
=650  \0$aEnergy absorption.
=650  \0$aTruncated cone.
=650  \0$aEpoxy composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xChemical & Biochemical.
=653  10$aCrash worthiness.
=653  20$aEnergy absorption.
=653  20$aTruncated cone.
=653  20$aKevlar/epoxy.
=653  20$aCrushing.
=653  20$aCompression.
=653  20$aBuckling.
=700  1\$aVizzini, AJ., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10997J.htm

=LDR  03353nam  2200781 i 4500
=001  CTR10998J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20019999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10998J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10998J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMauget, BR., $eauthor.
=245  10$aComputational Tracking of Composite Manufacturing with Fiber Preforms / $cBR Mauget, L Minnetyan, CC Chamis.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (5 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 4 (October 2001)
=504  \\$aIncludes bibliographical references$b4.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe use of braided fiber preforms is a cost-effective process for the manufacturing of composite aircraft structures. For a rational design, it is necessary to predict the fiber orientations in the composite structure after molding.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBraided fiber preforms.
=650  \0$aComposite manufacturing.
=650  \0$aComposites.
=650  \0$aComputational simulation.
=650  \0$aDamage progression.
=650  \0$aFiber angle changes.
=650  \0$aPreform molding.
=650  \0$aProgressive fracture.
=650  \0$aShape fitting.
=650  \0$aStructural durability.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aBraided fiber preforms.
=653  20$aComposites.
=653  20$aComposite manufacturing.
=653  20$aComputational simulation.
=653  20$aDamage progression.
=653  20$aFiber angle changes.
=653  20$aPreform molding.
=653  20$aProgressive fracture.
=653  20$aShape fitting.
=653  20$aStructural durability.
=700  1\$aMinnetyan, L., $eauthor.
=700  1\$aChamis, CC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10998J.htm

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=001  CTR10999J
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=024  7\$a10.1520/CTR10999J$2doi
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=037  \\$aCTR10999J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a677/.4$223
=100  1\$aSeneviratne, WP., $eauthor.
=245  10$aAdaptation of the Iosipescu In-plane Shear Test Method for High Strength Textile Composites / $cWP Seneviratne, JS Tomblin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2001.
=300  \\$a1 online resource (8 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 23, Issue 4 (October 2001)
=504  \\$aIncludes bibliographical references$b5.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn order to use the Iosipescu V-notch beam test for determining the in-plane shear strength of high strength 2D 2 × 2 biaxial braided composites, two modifications were made to the specimen geometry. First, they were tabbed to prevent buckling at the gage section and pinching of the specimen at grip sections. Tabbed specimens having gage sections of 0.50", 0.35", 0.188" were studied. Also, to reduce the load required for failure, the shear area was decreased by deepening the V-notch. Failure modes of specimens having notch widths of 0.425", 0.350", 0.325", and 0.300" were examined. In this investigation, high toughness PR520 epoxy resin was selected to make panels by resin transfer molding (RTM). An initial study was conducted to find the best possible specimen geometry using ±45° braid. Then, both ±45° and ±60° braid angles were studied for the selected geometry. In order to investigate the cut direction effects on the ±60° braid in-plane shear modulus and the strength, the specimens were cut in both 0° and 90° directions of the panel. Tabbed specimens with a gage length of 0.188" demonstrated the highest average shear strength. The notch width of 0.325" produced acceptable failures. Thus, it was selected as the minimum notch width. Then, both ±45° and ±60° specimens having gage section of 0.188" and notch width of 0.325" were tested for shear properties. The tabs minimized the bending loads due to buckling and pinching of the specimens across the gage section. Modifications increased the in-plane shear strength by about 33-55% for ±45°. The 0° cut-direction specimens, which had ±30° fibers with respect to the loading path, had lower strength and modulus values than that of the 90° cut-direction specimens. Modulus results for ±60° specimens were close to analytical predictions regardless of the cut direction.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2001. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBraided composites.
=650  \0$aIn-plane shear.
=650  \0$aTextile composites.
=650  \0$aTextile fabrics.
=650  \0$aFibrous composites.
=650  \7$aTECHNOLOGY & ENGINEERING $xTextiles & Polymers.
=653  10$aTextile composites.
=653  20$aBraided composites.
=653  20$aIn-plane shear.
=653  20$aIosipescu.
=700  1\$aTomblin, JS., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10999J.htm

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=024  7\$a10.1520/CTR11001J$2doi
=030  \\$aJCTRER
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=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aGentz, M., $eauthor.
=245  10$aMechanical Behavior of a Woven Graphite/PMR-15 Composite at Room and Elevated Temperatures Determined from the ±45° Tensile and Iosipescu Shear Tests / $cM Gentz, D Armentrout, P Rupnowski, L Kumosa, JK Sutter, M Kumosa.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 1 (January 2003)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFailure and stiffness properties of a woven 8 harness satin (8HS) graphite/PMR-15 composite have been investigated at room temperature and at 315°C by performing the ±45° tensile and Iosipescu tests. Acoustic emission has been monitored during testing. The critical loads for the initiation of damage in the composite have been determined. In particular, the specimen width effect has been investigated in the case of the ±45° specimens by testing the specimens with their width ranging from 12.7-50.8 mm. The results from the high temperature tests have been compared with the room temperature data presented in Refs. 1 and 2. Similar to the room temperature ±45° tests, the shear stresses at the onset of intralaminar damage in the specimens and the shear stresses at the maximum loads at 315°C are significantly affected by the specimen width effect. The trends in the damage initiation stresses and the maximum stresses as a function of specimen width at 315°C have been found to be very similar to the room temperature data with the stresses increasing almost linearly with the specimen width. It has also been shown in this project that the shear stresses at the onset of intralaminar damage and at the maximum load at 315°C depend very strongly on the specimen type. The shear stresses determined at the onset of damage and maximum loads from the Iosipescu tests at 315°C are noticeably higher than the stresses from the ±45° tests. The ±45° tensile test significantly underestimates the room and elevated temperature shear strength properties of the 8HS graphite/PMR-15 composite in comparison with the Iosipescu shear test.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite.
=650  \0$aHarness satin.
=650  \0$aShear strength.
=650  \0$aTensile test.
=650  \0$aComposite materials.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aLosipescu tests.
=653  20$aHarness satin.
=653  20$aComposite.
=653  20$aShear strength.
=653  20$aTensile test.
=700  1\$aArmentrout, D., $eauthor.
=700  1\$aRupnowski, P., $eauthor.
=700  1\$aKumosa, L., $eauthor.
=700  1\$aSutter, JK., $eauthor.
=700  1\$aKumosa, M., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR11001J.htm

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=024  7\$a10.1520/CTR11002J$2doi
=030  \\$aJCTRER
=037  \\$aCTR11002J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA347.F5
=082  04$a620.00151825$223
=100  1\$aGlaessgen, EH., $eauthor.
=245  13$aAn Efficient Analysis for the Debonding of Stitched Skin-Stiffened Structures / $cEH Glaessgen, IS Raju, CC Poe.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (13 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 1 (January 2003)
=504  \\$aIncludes bibliographical references$b28.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aAn analysis based on plate finite elements, nonlinear spring elements and the virtual crack closure technique has been implemented to study the effect of stitching on strain energy release rates for debond configurations. The stitches were modeled as discrete nonlinear spring elements with a compliance determined by experiment. The axial and shear behavior of the stitches was considered, however, the two compliances and failure loads were assumed to be independent. Both a double cantilever beam (mode I) and a mixed mode skin-stiffener debond configuration were studied. In the double cantilever beam configuration, GI began to decrease once the debond had grown beyond the first row of stitches and was reduced to zero for long debonds. In the mixed-mode skin-stiffener configuration, GI showed a similar behavior as in the double cantilever beam configurations; however, GII remained nonzero over the range of debond lengths considered.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDebonding.
=650  \0$aDelamination.
=650  \0$aFinite element analysis.
=650  \0$aSkin-stiffened structure.
=650  \0$aStitching.
=650  \0$aFinite element method.
=650  \7$aTECHNOLOGY & ENGINEERING $xEngineering (General.
=653  10$aStitching.
=653  20$aDelamination.
=653  20$aDebonding.
=653  20$aSkin-stiffened structure.
=653  20$aFinite element analysis.
=700  1\$aRaju, IS., $eauthor.
=700  1\$aPoe, CC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR11002J.htm

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=024  7\$a10.1520/CTR11003J$2doi
=030  \\$aJCTRER
=037  \\$aCTR11003J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aQA273.6
=082  04$a519/.1$223
=100  1\$aO'Brien, TK., $eauthor.
=245  10$aInfluence of Specimen Configuration and Size On Composite Transverse Tensile Strength and Scatter Measured Through Flexure Testing / $cTK O'Brien, AD Chawan, K DeMarco, I Paris.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (19 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 1 (January 2003)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe influence of specimen configuration and size on the transverse tensile strength of two glass/epoxy materials, and one carbon/epoxy material, loaded in three and four-point bending was evaluated. Transverse tensile strength was typically lower for longer span lengths due to the classical weakest link effect. However, strength was less sensitive to volume changes achieved by increasing specimen width. The Weibull scaling law typically over-predicted changes in transverse tensile strengths in three-point bend tests and under-predicted changes in transverse tensile strengths in four-point bend tests. Furthermore, the Weibull slope varied with specimen configuration, volume, and sample size. Hence, this scaling law was not adequate for predicting transverse tensile strength of heterogeneous, fiber-reinforced, polymer matrix composites.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBending tests.
=650  \0$aCarbon/epoxy.
=650  \0$aGlass/epoxy.
=650  \0$aMatrix cracking.
=650  \0$aScale effects.
=650  \0$aTransverse tensile strength.
=650  \0$aWeibull distribution.
=650  \0$aWeibull method.
=650  \0$aWeibull method.
=653  10$aTransverse tensile strength.
=653  20$aMatrix cracking.
=653  20$aWeibull distribution.
=653  20$aScale effects.
=653  20$aGlass/epoxy.
=653  20$aCarbon/epoxy.
=653  20$aBending tests.
=700  1\$aChawan, AD., $eauthor.
=700  1\$aDeMarco, K., $eauthor.
=700  1\$aParis, I., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR11003J.htm

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=024  7\$a10.1520/CTR11004J$2doi
=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aTA347.F5
=082  04$a620.00151825$223
=100  1\$aO'Brien, TK., $eauthor.
=245  10$aAnalysis of Flexure Tests for Transverse Tensile Strength Characterization of Unidirectional Composites / $cTK O'Brien, R Krueger.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (19 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 1 (January 2003)
=504  \\$aIncludes bibliographical references$b9.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aFinite element (FE) analyses were performed on 3-point and 4-point bending test configurations of glass-epoxy and carbon-epoxy unidirectional tape beams tested at ninety degrees to the fiber direction to identify deviations from beam theory predictions. Both linear and geometric non-linear analyses were performed using the ABAQUS® finite element code. The 3-point and 4-point bending specimens were first modeled with two-dimensional elements. Three-dimensional finite element models were then performed for selected 4-point bending configurations to study the stress distribution across the width of the specimens. For 3-point bend test configurations, both the linear and geometric non-linear 2D plane-strain and plane-stress analyses yielded similar results. The maximum tensile stresses under the center load nose calculated from the FE analysis were slightly lower than stresses predicted by beam theory. The difference (maximum of 4%) was greatest for the shortest span analyzed. For 4-point bend test configurations, both the plane-stress and plane-strain 2D linear analysis results agreed closely with beam theory except right below the load points. However, 2D geometric non-linear analyses deviated slightly from beam theory throughout the inner span as well as below the load points. Plane-stress results deviated from beam theory more than plane-strain results. The maximum tensile stresses between the inner span load points were slightly greater than the beam theory result. This difference was greatest (maximum of 4%) for configurations with the shortest spans between inner and outer load points. A contact analysis was also performed in order to investigate the influence of modeling the roller versus modeling the support as a simple boundary condition at one nodal point. The discrepancy between the FE and beam theory results became smaller (max. 2-3%) when the rollers were modeled in conjunction with contact analysis. Hence, the beam theory yields a reasonably accurate value for the maximum tensile stress in bending compared to 2D FE analysis. The FE results are primarily for guidance in the choice of beam thickness, width, and configuration. For the 3-point bend configuration, longer spans are preferred to minimize the error in beam theory data reduction. Similarly, for the 4-point bend configurations, a longer span between the inner and outer load noses, at least equal to the span between the inner load noses, results in less error compared to beam theory. In addition, these FE results indicate that the span between the inner load noses should not be too long to avoid obtaining a non-uniform maximum stress between the inner load noses. Finally, the 3D analysis indicates that specimens should be sufficiently wide to achieve a fully constrained state of plane-strain at the center of the specimen width.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aBending tests.
=650  \0$aFinite element analysis.
=650  \0$aGlass epoxy.
=650  \0$aGraphite epoxy.
=650  \0$aMatrix cracking.
=650  \0$aTransverse tensile strength.
=650  \0$aFinite element method.
=650  \7$aTECHNOLOGY & ENGINEERING $xEngineering (General.
=653  10$aTransverse tensile strength.
=653  20$aMatrix cracking.
=653  20$aFinite element analysis.
=653  20$aGlass epoxy.
=653  20$aGraphite epoxy.
=653  20$aBending tests.
=700  1\$aKrueger, R., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR11004J.htm

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=024  7\$a10.1520/CTR11005J$2doi
=030  \\$aJCTRER
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=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
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=041  \\$aeng
=050  \4$aQC176.8.M5
=082  04$a620.1/1892$223
=100  1\$aHuang, Z-M, $eauthor.
=245  10$aTensile Stiffness and Strength of Regular Braid Composites : $bCorrelation of Theory with Experiments / $cZ-M Huang, K Fujihara, S Ramakrishna.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2003.
=300  \\$a1 online resource (15 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 25, Issue 1 (January 2003)
=504  \\$aIncludes bibliographical references$b19.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper investigates the tensile behavior of plain regular braided fabric reinforced composites subjected to uniaxial load. An experimental program is performed to characterize the stiffnesses and strengths of a number of braid composites. Two different material systems, i.e., carbon/epoxy and glass/epoxy, were investigated in this study, each with three different braiding angles. A theoretical approach, based on a bridging micromechanics model, is employed to predict the tensile properties of the braid composites only using monolithic fiber and matrix properties and the fabric geometric information as input parameters. These parameters are easily obtainable before or after composite fabrication, and determination of them is described in the paper. Unit cell geometry of the braided fabric in the composite was represented by either elliptic or sinusoidal cross section combined with the same undulation function, and a comparative study has been performed. After the unit cell of the braid composite has been divided into slices and the bridging model has been applied, an assemblage based on iso-stress or iso-strain assumption was adopted to obtain the overall properties of the composite. Although both the assumptions give reasonable predictions for the stiffness of glass/epoxy braid composites, significant differences exist between the predictions from the iso-stress approach and those from the iso-strain approach for the strength of the glass/epoxy composites and for the stiffness and strength of the carbon/epoxy composites. The iso-strain approach combined with the elliptic geometric description exhibits the best accuracy, and the predicted stiffnesses and strengths for the two material systems thus obtained are all within 13% discrepancy with the experimental data.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2003. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aMicromechanics.
=650  \0$aComposite materials.
=650  \0$aSolid state physics.
=650  \0$aBridging model.
=650  \0$aExperimental correlation.
=650  \0$aGeometric description.
=650  \0$aIso-stress/iso-strain approach.
=650  \0$aMechanical property.
=650  \0$aMicromechanics.
=650  \0$aRegular braids.
=650  \0$aStiffness.
=650  \0$aStrength.
=650  \0$aTextile composites.
=653  10$aRegular braids.
=653  20$aTextile composites.
=653  20$aGeometric description.
=653  20$aMechanical property.
=653  20$aStiffness.
=653  20$aStrength.
=653  20$aMicromechanics.
=653  20$aBridging model.
=653  20$aIso-stress/iso-strain approach.
=653  20$aExperimental correlation.
=700  1\$aFujihara, K., $eauthor.
=700  1\$aRamakrishna, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR11005J.htm

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=024  7\$a10.1520/CTR10008J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10008J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA455.G7
=082  04$a662/.92$223
=100  1\$aHarris, CE., $eauthor.
=245  12$aA Progressive Damage Model and Analysis Methodology for Predicting the Residual Strength of Composite Laminates / $cCE Harris, TW Coats, DH Allen, DC Lo.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (7 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 1 (January 1997)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe durability and damage tolerance of laminated composites are critical design considerations for airframe composite structures. Therefore, the ability to model damage initiation and growth and predict the life of laminated composites is necessary to achieve efficient and economical structural designs. The purpose of the research presented in this paper is to experimentally verify the application of the damage model developed by the authors to predict progressive damage development in a toughened material system. Damage growth, stiffness degradation, and residual strength were experimentally determined for cross-ply and quasi-isotropic IM7/5260 graphite/bismaleimide laminates due to monotonic and tension-tension fatigue. The damage model, which has been implemented into a finite element code, was used to predict the stiffness loss and residual strength of unnotched and notched laminates. The model predictions were in good agreement to experimental results for several different fatigue loading histories and several different laminate stacking sequences.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposites.
=650  \0$aDamage.
=650  \0$aDelamination.
=650  \0$aGraphite/epoxy.
=650  \0$aInternal state variables.
=650  \0$aMatrix cracks.
=650  \0$aGraphite.
=650  \0$aBlack-lead.
=650  \0$aMaterials engineering.
=653  10$aComposites.
=653  20$aGraphite/epoxy.
=653  20$aDamage.
=653  20$aMatrix cracks.
=653  20$aDelamination.
=653  20$aInternal state variables.
=700  1\$aCoats, TW., $eauthor.
=700  1\$aAllen, DH., $eauthor.
=700  1\$aLo, DC., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10008J.htm

=LDR  03550nam  2200637 i 4500
=001  CTR10009J
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=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10009J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10009J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aHighsmith, AL., $eauthor.
=245  10$aQuantitative Assessment of Fiber Fracture in Damaged Laminates Using X-Ray Radiography / $cAL Highsmith, S Keshav.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 1 (January 2006)
=504  \\$aIncludes bibliographical references$b38.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this paper, a new technique for extracting quantitative information about fiber fracture from dye penetrant enhanced X-ray radiographs is described. In this new inspection method, the observer marks fiber fracture zones on a digitized version of the radiograph depicting the damage state. Image processing routines are used to isolate the marked fiber fracture zones, and then extract fiber fracture parameters such as the length of the longest fiber fracture zone and the total length of fiber fracture from the marked image. The technique has been used to quantify fiber fracture in graphite epoxy laminates damaged by either quasi-static contact loading or low-velocity impact. The residual strengths of these specimens were found to correlate well with the fiber fracture parameters, with specimens containing more fiber fracture exhibiting lower residual strength.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite laminate.
=650  \0$aComposite material.
=650  \0$aFiber fracture.
=650  \0$aMicrostructural damage.
=650  \0$aComposites.
=650  \0$aComposites (Materials)
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite material.
=653  20$aComposite laminate.
=653  20$aMicrostructural damage.
=653  20$aFiber fracture.
=700  1\$aKeshav, S., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10009J.htm

=LDR  04379nam  2200637 i 4500
=001  CTR10010J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10010J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10010J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.118$223
=100  1\$aMartin, RH., $eauthor.
=245  10$aDelamination Characterization of Woven Glass/Polyester Composites / $cRH Martin.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (9 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 1 (January 1997)
=504  \\$aIncludes bibliographical references$b8.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe test methods to determine interlaminar fracture toughness of composite materials require values to be determined at delamination initiation from the thin insert. In woven composites, the location of the insert relative to the yarns will vary which may effect the toughness values at initiation. This work determined the effect of the location of the insert relative to the yarns on interlaminar fracture toughness using the double cantilever beam (DCB) and endnotched flexure (ENF) specimens under quasi-static and fatigue loads. The specimens were configured so that the insert end was placed at the edge of and in the center of a yarn and in a mixed position where the insert was at the edge in one ply above and in the center of the ply below. Quasi-static and fatigue tests were conducted for each configuration. The static tests on the DCB resulted in "stick-slip" type fracture, where the delamination grew rapidly across a transverse yarn to the beginning of the next transverse yarn and stopped until the load increased sufficiently to cause further stick-slip fracture. As the delamination propagated down the beam, the crack branched either side of the transverse yarns eventually resulting in the complete ply bridging the delamination. This resulted in an increase in G1c values. Delamination growth in the ENF static tests also produced crack branching and ply bridging that resulted in stable delamination growth. For both specimen types, the lowest values of Gc were obtained in the specimens with the insert in the center of the yarn and the highest Gc with the insert at the edge of a yarn. The scatter in the fatigue data prevented a clear indication of which insert position resulted in the lowest number of cycles to delamination onset with applied Gmax.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aComposite materials.
=650  \0$aDelamination.
=650  \0$aFracture toughness.
=650  \0$aWoven composites.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aComposite materials.
=653  20$aWoven composites.
=653  20$aFracture toughness.
=653  20$aMode I.
=653  20$aMode II.
=653  20$aDelamination.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10010J.htm

=LDR  03654nam  2200661 i 4500
=001  CTR10011J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10011J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10011J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA418.9.C6
=082  04$a620.1/4$223
=100  1\$aSolti, JP., $eauthor.
=245  10$aModeling of Matrix Failure in Ceramic Matrix Composites / $cJP Solti, S Mall, DD Robertson.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (12 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 1 (January 2006)
=504  \\$aIncludes bibliographical references$b21.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThis paper investigates failure criteria used in modeling matrix failure in unidirectional and cross-ply laminates of ceramic matrix composites. In particular, the critical matrix strain energy (CMSE) criterion, as recently introduced by the authors, is examined in detail. In principle, a failure criterion, such as CMSE, which does not require many empirical constants, is desired. This CMSE approach provides a simple closed-form estimate for the matrix crack density in ceramic matrix composites when subjected to monotonic tensile loading. The proposed criterion can be easily extended to more complex loading conditions (for example, fatigue) and laminate geometries. Other matrix failure criteria, available in the literature, are also discussed. The CMSE criterion does an adequate job of estimating the evolution of matrix damage in both unidirectional and cross-ply laminates.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aCeramic matrix composites.
=650  \0$aCross-ply laminates.
=650  \0$aFailure and damage mechanisms.
=650  \0$aMatrix cracking.
=650  \0$aUnidirectional laminates.
=650  \0$aComposites.
=650  \7$aTECHNOLOGY & ENGINEERING $xMaterial Science.
=653  10$aCeramic matrix composites.
=653  20$aMatrix cracking.
=653  20$aFailure and damage mechanisms.
=653  20$aUnidirectional laminates.
=653  20$aCross-ply laminates.
=700  1\$aMall, S., $eauthor.
=700  1\$aRobertson, DD., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10011J.htm

=LDR  03409nam  2200685 i 4500
=001  CTR10012J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10012J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10012J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aTA417.4
=082  04$a620.1/12740284$223
=100  1\$aHu, S., $eauthor.
=245  14$aThe Recent Development of an Ultrasonic Nondestructive Evaluation Technique for Metal Matrix Composites / $cS Hu.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (4 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 1 (January 1997)
=504  \\$aIncludes bibliographical references$b7.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aIn this study, the use of an ultrasonic nondestructive evaluation technique and the principle of signal phase alteration are discussed. Combining them together, we can investigate the free edge effect, the transverse fiber/matrix interfacial failure, and the fiber breakage associated with the fiber fragmentation process for a single fiber composite. Using this method, we successfully detected composite fiber/matrix interfacial microscopic failure, which is much smaller in dimension than the ultrasonic wave focal area.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aFiber fragmentation.
=650  \0$aFiber/matrix interfacial debond.
=650  \0$aFree edge effect.
=650  \0$aSignal phase alteration.
=650  \0$aTitanium matrix composites.
=650  \0$aTransverse failure.
=650  \0$aUltrasonic nondestructive evaluation.
=650  \0$aNondestructive testing.
=650  \7$aSCIENCE $xNanoscience.
=653  10$aUltrasonic nondestructive evaluation.
=653  20$aSignal phase alteration.
=653  20$aTitanium matrix composites.
=653  20$aFiber/matrix interfacial debond.
=653  20$aFree edge effect.
=653  20$aTransverse failure.
=653  20$aFiber fragmentation.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10012J.htm

=LDR  03740nam  2200661 i 4500
=001  CTR10015J
=003  IN-ChSCO
=005  20161219163000.0
=006  m\\\\\\\\\\\\\\\\\
=007  cr\\\\\\\\\\\\
=008  161219c20069999pau||#p|s||||||||||0eng|d
=022  \\$a0884-6804
=024  7\$a10.1520/CTR10015J$2doi
=030  \\$aJCTRER
=037  \\$aCTR10015J$bASTM
=037  \\$bASTM International, 100 Barr Harbor Dr., West Conshohocken, PA 19428
=040  \\$aASTM$cSCOPE$beng$erda
=041  \\$aeng
=050  \4$aT59.72
=082  04$a610$223
=100  1\$aMall, S., $eauthor.
=245  10$aFatigue Behavior of a Cross-Ply Titanium Matrix Composite with Tensile and Zero Mean Load at Elevated Temperature / $cS Mall, EA Boyum.
=264  \\$aWest Conshohocken, Pa. : $bASTM International, $c2006.
=300  \\$a1 online resource (10 pages) : $billustrations, figures, tables.
=336  \\$atext$2rdacontent
=337  \\$acomputer$2rdamedia
=338  \\$aonline resource$2rdacarrier
=347  \\$atext file $bPDF $2rda
=362  0\$aVolume 19, Issue 2 (April 1997)
=504  \\$aIncludes bibliographical references$b22.
=506  \\$aSubscription required for access to full text.
=506  \\$aLicense restrictions may limit access.
=520  3\$aThe fatigue response of a cross-ply [0/90]2S titanium (Ti-15-3) matrix composite reinforced with silicon carbide fibers (SCS-6) was investigated at 427°C. Tension-tension (tensile mean stress) and tension-compression (zero mean stress) loadings were applied. For the same stress range, tension-tension loading caused much lower fatigue lives and greater strain ratchetting than those under tension-compression loading. Despite the longer fatigue lives under tension-compression loading, additional plasticity sites and fatigue damage mechanisms were observed. Fatigue damage mechanisms could be classified into two distinct regimes, independent of mean load, fiber-dominated (fibers fracture prior to matrix cracking) at high-stresses and low-cyclic lives, and matrix dominated (matrix fatigue cracks prior to fiber fracture) at longer lives. Comparisons of the 427°C results are made with previously reported results at room temperature. Deformation mechanisms and fatigue lives were influenced by the testing temperature.
=530  \\$aAlso available online via the World Wide Web. Tables of contents and abstracts freely available; full-text articles available by subscription.
=530  \\$aFull text article also available for purchase.
=530  \\$aAlso available in PDF edition.
=533  \\$aElectronic reproduction. $bW. Conshohocken, Pa. : $cASTM International, $d2006. $nMode of access: World Wide Web. $nSystem requirements: Web browser. $nAccess may be restricted to users at subscribing institutions.
=538  \\$aMode of access: World Wide Web.
=541  \\$aASTM International$3PDF$cPurchase price$hUSD25.
=588  \\$aDescription based on publisher's website, viewed December 19, 2016.
=650  \0$aDamage mechanisms.
=650  \0$aFatigue.
=650  \0$aTension-compression.
=650  \0$aTension-tension.
=650  \0$aTitanium matrix composites.
=650  \0$aExhaustion.
=650  \0$aAutomotive medicine.
=650  \0$aHuman engineering.
=653  10$aTitanium matrix composites.
=653  20$aFatigue.
=653  20$aTension-tension.
=653  20$aTension-compression.
=653  20$aDamage mechanisms.
=700  1\$aBoyum, EA., $eauthor.
=710  2\$aAmerican Society for Testing and Materials.
=710  2\$aAmerican Society for Testing and Materials. $tComposites Technology and Research.
=710  2\$aASTM International.
=856  40$uhttp://www.astm.org/DIGITAL_LIBRARY/JOURNALS/COMPTECH/PAGES/CTR10015J.htm