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STP486
Damage Tolerance in Aircraft Structures

Rosenfeld MS
Pages: 260
Published: 1971

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The Symposium on Damage Tolerance in Aircraft Structures was conducted in two sessions at the Seventy-third Annual Meeting of the American Society for Testing and Materials, held in Toronto, Ontario, Canada, 21-26 June 1970. The symposium was sponsored by ASTM Committee E09 on Fatigue. M. S. Rosenfeld, of the Naval Air Development Center, served as symposium chairman, with P. C. Paris, Del Research Corp., Hellertown, Pa., and R. J. Hebert, Canadair, Ltd., Montreal, Ontario, presiding as chairmen of the first and second sessions, respectively.



Table of Contents

The Dependence of Fatigue Crack Propagation on Strain Energy Release Rate and Crack Opening Displacement
Barsom J.

Effect of Thickness on the Fracture Toughness of 7075 Aluminum in the T6 and T73 Conditions
Allen F.

The Influence of Curvature on Stress Intensity at the Tip of a Circumferential Crack in a Cylindrical Shell
Adams N.

Evaluation and Prediction of the Residual Strength of Center Cracked Tension Panels
Feddersen C.

Fatigue Crack Propagation in Stiffened Panels
Poe C.

Material Toughness and Residual Strength of Damage Tolerant Aircraft Structures
Ekvall J., Liu A.

An Approach to Predicting the Growth to Failure of Fatigue Cracks Subjected to Arbitrary Uniaxial Cyclic Loading
Brussat T.

Initiation and Growth of Fatigue Cracks in and Residual Strength of the F-100 Wing
Fitch G., Graziano W.

Development of the Fail-safe Design Features of the DC-10
Swift T.

The Ballistic Damage Characteristics and Damage Tolerance of Wing Structural Elements
Jensen J.

The Significance of Fatigue Crack Closure
Elber W.

Crack Propagation in Helicopter Rotor Blades
Rich M.

Committee: E08
Paper ID: STP486-EB
DOI: 10.1520/STP486-EB
ISBN-EB: 978-0-8031-4595-5

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STP486-EB