Experimental and numerical investigation of open hole carbon fiber composite laminates under compression with three different stacking sequences

Abstract

The open hole composite laminates with different stacking sequence were tested and the failure modes and strength were recorded. A progressive damage model of the open-hole composite laminate under compression was developed and in-plane damage is modeled by using the three-dimensional continuum shell elements and cohesive element was adopted for delamination failure simulation. Based on the ABAQUS user subroutine UMAT, this model simulates damage initiation, propagation and final failure. With different failure criteria, the strength and failure modes of open-hole laminates under compression were predicted in this model. Compared with the experiment results, the effects of different stacking sequences on the strength and final failure modes of composite laminates are analyzed.