Prediction of Low-Velocity Face-on Impact Response of Composite Laminates using High-Fidelity Finite Element Modeling Techniques

In this paper the response of a polymer matrix composite (PMC) laminate subjected to low-velocity face-on impact is studied both experimentally and numerically. Experiments for face-on impact were carried out on a laminated composite specimen, and post impact inspection of the specimen was done using ultrasound techniques to obtain the damage extent through the thickness of the laminate. Two high-fidelity finite element (FE) models have been developed to capture the response and failure mechanisms seen in the experiments. The University of Washington (UW) model utilizes Enhanced Schapery Theory (EST) to capture the non-linearity due to matrix micro cracking as well as macro intra-lamina matrix cracking and fiber failure. Discrete Cohesive Zone Model (DCZM) is implemented to capture the interlamina failure initiatiation and propagation. An exisiting model from The Japan Aerospace Exploration Agency (JAXA), was extended to include mesh objectivity and this extended model, referred to as the enhanced continuum damage mechanics (ECDM) model, was used for predicting intra-lamina pre-peak nonlinearity as well as matrix cracking and fiber failure. The ECDM model utilizes commercially available cohesive methods to capture inter-lamina damage and failure. The commercial finite element code, ABAQUS Explicit, was used in combination with user defined material and element subroutines to implement these different modeling strategies.