Ultimate Strength Analysis of Symmetric Laminates
AIR FORCE FLIGHT DYNAMICS LAB WRIGHT-PATTERSON AFB OH WRIGHT-PATTERSON AFB
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A technique is presented for predicting the response to failure of composite laminates. In this technique, cubic spline interpolation functions are used to represent basic stress-strain curves obtained from simple tests. This representation in conjunction with an incremental constitutive law is used to generate response of laminates subjected to incremental loads. The ultimate load- carrying capacity of the laminates is determined by the plywise application of a new failure criterion using strain energy under longitudinal, transverse, and shear loadings as independent parameters. Results obtained by this technique are compared with the available experimental data of boron- epoxy laminates as well as the responses generated by methods of Petit-Waddoups and Hahn. Analytical results determined by the present theory correlate with the experimental data better than those obtained by the other two techniques.