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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.
finite element analysis, progressive ply failure, failure analysis, double-edge notched specimens, graphite-epoxy laminates
Aerospace Engineer, Air Force Wright Aeronautical Laboratories/FIBC, Wright-Patterson Air Force Base, Ohio
General Dynamics Corporation, Fort Worth, Tex.
Aerospace Engineer, Air Force Wright Aeronautical Laboratories/FIBE, Wright-Patterson Air Force Base, Ohio