ABSTRACT
The progressive failure model developed in Chapter 16 for tensile loading is extended for laminated composites under uniaxial compressive loading. This model is capable of predicting the extent of damage at any load level, the stiffness loss, the stress-strain behavior and the residual strength of the laminates. Compressive response is one of the key parameters used in the design of composite structures. Since most structures contain fastener holes, the compressive response of composite structures with a cutout requires attention and study to predict the extent of damage and damage progression in composites one need to use progressive failure models. More experimental work has been devoted to the damage mechanisms around the hole under compressive loading than tensile loading. In-plane failure can globally be classified into matrix cracking and fiber breakage. A matrix cracking caused by compressive loading may have different mechanism microscopically than that caused by tensile loading.
