Numerical investigation of composite laminates subject to low-velocity edge-on impact and compression after impact

In this paper, a shell based finite element (FE) model previously introduced for capturing the face-on impact and compressive strength after impact (CSAI) response of composite laminated structures is evaluated for predicting the dynamic response and damage due to edge-on impact and the resulting CSAI. The model utilizes an in-plane progressive damage and failure material model, Enhanced Schapery Theory (EST), for modeling the full field damage and failure of a single lamina in the 1-2 plane. The material model captures the pre-peak matrix non-linearity due to micro cracking using Schapery Theory (ST). The Bazant-Oh Crack Band (CB) model is utilized for matrix cracking and fiber rupture at the lamina level. Discrete cohesive elements are used for delamination initiation and propagation. Edge-on impact data for a range of impact energies is used for evaluating the models capability. The predicted impact damage state of the laminate is used for acquiring predictions of the CSAI of the laminate. The model predictions show promising results for the impact and CSAI response of an edge-on impacted coupon. The paper discusses the strengths of the model, the issues encountered, as well as topics for future study.