基于Pam/crash软件，建立SPH鸟体模型，仿真分析了两种工况：芳纶与玻璃钢全尺寸复合材料垂尾前缘分别在3．6 kg鸟体以114 m/s速度冲击下的动力学特性；通过模拟与试验结果的对比，验证了仿真方法有效。结果表明：在鸟体与结构接触区域以及前缘与盒段连接区域，需要划分更为精细的网格以真实模拟实际情况；芳纶及玻璃钢前缘的抗鸟撞性能与蒙皮的具体铺层信息相关。仿真及试验方法对工程设计具有实际参考价值。%Numerical analyses of 3.6 kg birds impacting on full-scale composite leading edge ( FCLD) of aircraft′s vertical tail have been performed by employing Pam/Crash package and SPH bird model was built.The simulation method was validated according to comparisons of experiment and calculating re-sults.It is suggested that the grids of impact zones should be meshed as accurate as possible .The anti-impacting ability of aramid and glass fiber reinforced plastics ( FRP) leading edge is related to the layups of skin.Moreover ,the simulating and test processes can be utilized and referred by industry directly .
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