STP864

    First-Ply Failure of Graphite/Epoxy Laminates

    Published: Jan 1985


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    Abstract

    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.

    Keywords:

    composites, laminates, first-ply failure, transverse cracking, free-edge effects


    Author Information:

    Kistner, MD
    Materials research engineers, Materials Laboratory, Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, OH

    Whitney, JM
    Materials research engineers, Materials Laboratory, Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, OH

    Browning, CE
    Materials research engineers, Materials Laboratory, Air Force Wright Aeronautical Laboratories, Wright-Patterson Air Force Base, OH


    Paper ID: STP32782S

    Committee/Subcommittee: D30.04

    DOI: 10.1520/STP32782S


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