SEDL / STP / STP580-EB / STP32317S

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

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

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

Pages: 13    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.