以典型蒙皮结构为研究对象，分别对由2024－T3铝合金和碳纤维复合材料交替层压而成的FMLs以及2024－T3铝合金蒙皮进行高速冲击有限元仿真，并进行了损伤对比。其中，铝合金层和碳纤维层均采用最大应变准则。利用碰撞模拟分析软件PAM-CRASH以及采用SPH弹体对冲击模型进行仿真，结果显示在相同冲击能量下，加了支承结构的蒙皮在损伤抗性方面有了明显提升，并在此基础上分析不同的纤维铺层角度和铺层方式对FMLs蒙皮性能的影响。%Taking certain typed aircraft skin as the target of study ,this paper established high velocityim-pact finite element simulation models with skin materials 2024-T3 aluminum alloy and carbon fiber alu-minum alloy laminated plates .Then the results of the simulation was analyzed while the maximum strain criterion was used for Al alloy layer and carbon fiber layer .Large crash simulation analysis software PAM-CRASH was employed and the projectile was replaced by a SPH model .Through calculation the results of simulation showed that the skin with the support structure had been significantly improvedin terms of damage resistance under the same impact energy .Based on that ,the influence of different fiber ply angle and ply mode on the performance of FMLs skin was analyzed .
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