STP580

    A Computational Procedure to Analyze Metal Matrix Laminates with Nonlinear Lamination Residual Strains

    Published: Jan 1975


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    Abstract

    An approximate computational procedure is described for the analysis of angleplied laminates with residual nonlinear strains. The procedure consists of a combination of linear composite mechanics and incremental linear laminate theory. The procedure accounts for initial nonlinear strains, unloading, and in-situ matrix orthrotropic nonlinear behavior. The results obtained in applying the procedure to boron-aluminum angleplied laminates show that this is a convenient means to accurately predict the initial tangent properties of angleplied laminates in which the matrix has been strained nonlinearly by the lamination residual stresses. The procedure predicted initial tangent properties results which were in good agreement with measured data obtained from boron-aluminum angleplied laminates.

    Keywords:

    composite materials, fiber composites, boron-aluminum composites, nonlinear analysis, computational procedure, residual strains, initial properties, computer programs


    Author Information:

    Chamis, CC
    Aerospace research engineer, NASA-Lewis Research Center, Cleveland, Ohio

    Sullivan, TL
    Aerospace research engineer, NASA-Lewis Research Center, Cleveland, Ohio


    Paper ID: STP32317S

    Committee/Subcommittee: D30.07

    DOI: 10.1520/STP32317S


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