SYMPOSIA PAPER Published: 01 January 1985
STP32782S

First-Ply Failure of Graphite/Epoxy Laminates

Source

In situ transverse-ply failure in AS-4/3502 graphite/epoxy laminates is investigated by determining crack density as a function of laminate axial strain. These results are then related to laminate stress-strain response. Results show that plateaus in either the longitudinal or transverse stress-strain curve are associated with a significant increase in transverse-ply crack density. Stress analysis reveals a departure of inplane stresses from classical lamination theory near free edges. These stresses are found to be a function of laminate-ply orientations and stacking sequence. Thus, the onset of transverse-ply cracking may be influenced by the free edge in a standard tensile coupon.

Author Information

Kistner, MD
Materials Laboratory, Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, OH
Whitney, JM
Materials Laboratory, Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, OH
Browning, CE
Materials Laboratory, Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, OH
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Details
Developed by Committee: D30
Pages: 44–61
DOI: 10.1520/STP32782S
ISBN-EB: 978-0-8031-4929-8
ISBN-13: 978-0-8031-0436-5