A Numerical Model for CFRP Fragmentation Under Hypervelocity Impacts

Space debris represents a substantial hazard to satellites, posing the risk of collisions that can lead to partial or total break-ups. In the last years, carbon fiber reinforced plastic (CFRP) has started to be used increasingly more extensively on spacecraft due to its high strength-to-weight ratio. Despite its wide use, to date its fragmentation behaviour under hypervelocity impact conditions has not yet been fully understood and modelled. In this context, this paper presents a numerical model for CFRP fragmentation recently developed by the Space Debris Group of the University of Padova. The model is constructed and validated from experimental data, collected both from dedicated tests and literature; it consists in a set of semi-empirical equations describing the fragmentation pattern on CFRP plates and the distribution of generated fragments. The model input includes various parameters, such as the impact velocity, the impact angle, and the CFRP layup, to determine the fragmentation behaviour. It is also capable to determine delamination effects and the extension of the damaged area in function of the material fiber orientations and weaves. Finally, the developed model is currently under inclusion into the material library of the Collision Simulation Tool Solver (CSTS), a software developed by the research group to describe hypervelocity break-up and fragmentation processes.