全尺寸复合材料垂尾前缘抗鸟撞仿真与试验

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。

Simulation and Experiments of Bird Impact Resistance of Full-scale Composite Leading Edge of Vertical Empennage

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 .