STP1156

    Failure Initiation and Ultimate Strength of Composite Laminates Containing a Center Hole

    Published: Jan 1993


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    Abstract

    A failure analysis method that includes the free edge effect was proposed for failure prediction in composite laminates containing a center hole. The location of onset of failure in the hole was determined by comparing the strengths of off-axis coupon specimens with the hoop stress around the hole. The subsequent failure progression was performed by the ply-by-ply classical laminate failure analysis. Experiments on [0/90/±45]s and [0/90]s laminates and their off-axis specimens were performed to verify the present method.

    Keywords:

    failure, composite, laminate, hole, free edge, hoop stress


    Author Information:

    Chu, GD
    Graduate student and professor, School of Aeronautics and Astronautics, Purdue University, West Lafayette, IN

    Sun, CT
    Graduate student and professor, School of Aeronautics and Astronautics, Purdue University, West Lafayette, IN


    Paper ID: STP24723S

    Committee/Subcommittee: D30.05

    DOI: 10.1520/STP24723S


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