PREDICTION OF FAILURE ENVELOPES AND STRESS STRAIN BEHAVIOR OF COMPOSITE LAMINATES/

Failure envelopes for unidirectional composites and multilayered compo site 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 laminat es under uniaxial or biaxial loading were predicted by considering bot h material non-linearity and progressive matrix cracking. Material non -linearity was considered by using a one-parameter plasticity model fo r fiber-reinforced composites. Progressive matrix cracking and the cor responding stiffness reduction were predicted by use of a simplified s hear-lag analysis and finite element analysis. (C) 1998 Elsevier Scien ce Ltd. All rights reserved.