Abstract
Failure envelopes for unidirectional composites and multi-layered composite laminates have been predicted by linear laminate theory. The ply-by-ply discount method with parallel spring stiffness reduction model was used in the prediction. The stress/strain behavior of four laminates under uniaxial or biaxial loading were predicted by considering both material non-linearity and progressive matrix cracking. Material non-linearity was considered by using a one-parameter plasticity model for fiber-reinforced composites. Progressive matrix cracking and the corresponding stiffness reduction were predicted by use of a simplified shear-lag analysis and finite element analysis.
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