Numerical analysis of the residual ultimate strength of composite laminates under uniaxial compressive load

Abstract

In the current study, the residual ultimate strength of a composite laminate with delamination is determined under in-plane compressive loading numerically. The delamination growth is predicted and modelled using the finite element method. The method that has been used to extend the delaminated area is based on linear fracture mechanics and the applied tool is the virtual crack closure technique. The results show that due to the expansion of the delaminated area in a composite laminate, the load-carrying capacity of the structure is reduced. Despite the simplicity and efficiency of this method, the strain energy release rates at different fracture modes in the delamination region can be calculated and predicted.