Test and numerical simulation of damage on an aircraft wing leading edge impacted by an unmanned aerial vehicle

The increasing prevalence of Unmanned Aerial Vehicles (UAVs) in airspace has highlighted critical threats to aircraft flight safety. This study establishes a methodological framework for quantifying dynamic impact loads generated by UAV strikes. The controlled impact tests between UAVs and aircraft wing leading edges were carried out by a new test setup, the deformation characteristics and failure modes of composite wing structures were systematically documented. A high-fidelity numerical model was developed using the explicit finite element analysis software PAM-CRASH, enabling detailed simulation of the temporal-spatial evolution of impact dynamics. Validation analysis demonstrated strong concordance between simulation and test results. Expanding the scope beyond UAV impacts, this research pioneers a comparative analysis framework by incorporating equivalent-mass bird strike simulations under identical kinetic conditions. Further parametric studies examined the influence of impact velocities and UAV flight attitudes on structural damage patterns. The multidisciplinary approach provides aviation regulators with empirically validated computational models and impact scenario databases, directly supporting the development of next-generation airworthiness standards for UAV-integrated airspace systems.