STP787

    Initiation and Accumulation of Damage in Composite Laminates

    Published: Jan 1982


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    Abstract

    A progressive-ply-failure finite element program for predicting damage initiation and progression in composite structures with stress concentrators is described. The program was used to predict the damage accumulation process in double-edge notched graphite-epoxy specimens subjected to tensile loading. The predictions were found to be in good agreement with experimental data.

    Keywords:

    finite element analysis, progressive ply failure, failure analysis, double-edge notched specimens, graphite-epoxy laminates


    Author Information:

    Sandhu, RS
    Aerospace Engineer, Air Force Wright Aeronautical Laboratories/FIBC, Wright-Patterson Air Force Base, Ohio

    Gallo, RL
    General Dynamics Corporation, Fort Worth, Tex.

    Sendeckyj, GP
    Aerospace Engineer, Air Force Wright Aeronautical Laboratories/FIBE, Wright-Patterson Air Force Base, Ohio


    Paper ID: STP28480S

    Committee/Subcommittee: D30.05

    DOI: 10.1520/STP28480S


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