Numerical investigation on dynamic response and damage mechanism of fiber metal laminates (FMLs) wing leading edge subjected to high-velocity hail impact

This paper presents a systematic numerical study on the dynamic response and damage mechanism of fiber metal laminates (FMLs) wing leading edge subjected to high-velocity hail impact. A comprehensive finite element (FE) model, incorporating the hail ice, FMLs skin, aluminum honeycomb core, and supporting structure, is developed. The effects of varying impact velocities, impact locations, and multiple impacts on the structural response and damage behavior are analyzed. The results show that the impact velocity significantly affects the displacement response and energy absorption mode of the structure, with the bottom panel absorbing more energy under high-velocity impacts. Additionally, the closer the impact location is to the edge, the more pronounced the supporting effect, which leads to lower stress and reduced delamination. Multiple impacts cause a significant decline in structural performance, with hail ices potentially penetrating the skin and inducing larger delaminated areas. This study validates the effectiveness of the numerical model in simulating the hail impact process and provides an appropriate reference for the hail resistance design and airworthiness certification of aircraft wing leading edges.