Abstract: Carbon/glass fiber hybrid composite (C/GFRP) laminates are widely used in unmanned aerial vehicles (UAV) and other aircraft structures due to their lightweight characteristics. However, in battlefield, UAVs are susceptible to threats from high-velocity debris impacts, where their impact resistance directly determines the safety of weapon systems. Additionally, when composite laminates are subjected to impacts, multiple damage modes including matrix and fiber tensile/compressive failures and interlaminar fracture interact competitively. The correlation between key parameters and impact resistance requires further investigation. In this study, a multiple damage mode of carbon/glass fiber hybrid composites was developed. The damage details and failure modes under various ply configurations were systematically analyzed. Simulations revealed the correlation between ply configurations and impact resistance. The results indicate that, under the same fiber content and angle combination, increasing the hybrid interface ratio reduced delamination damage and lowered residual velocity. Under the fixed hybrid interface ratio, increasing the ply angle gradient between adjacent layers could decrease the damage area and enhance energy dissipation. And a new ply configuration proposed in this study improved critical damage displacement and dispersed damage zones. This research provides a theoretical basis for optimizing UAV composite laminates under high-velocity impacts through refined multi-damage mode regulation, offering significant engineering guidance for enhancing UAV protection systems.