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A micromechanics based analysis to predict damage initiation in compressively loaded symmetric notched multiply laminates at efevated temperature under remote biaxial loading is described. The finite element method in conjunction with the commercial code ABAQUS® is used to solve the governing system of equations. The results obtained for the predictions are compared against a set of experimental results. A unified model that captures damage initiation and which describes failure mode by tracking the response of each lamina is presented. The prediction of the model is found to compare favorably against the experimental data.

A micromechanics based finite element model for the prediction of compressive failure in notched laminated composites