基于内聚力模型的飞机风挡与无人机碰撞仿真及试验验证

Simulation and Test Verification of Collision Between Aircraft Windshield and UAV Based on Cohesive Zone Model

为有效支持无人机撞击飞机仿真分析,降低试验研究成本,开展无人机与某型运输类飞机风挡碰撞试验及有限元仿真方法研究。研究建立符合实际尺寸和曲面构型的风挡和无人机的建模方法;考虑到碰撞后风挡玻璃的裂纹萌生和扩展的不可预测性和复杂性,通过Python二次开发在风挡模型中玻璃单元间及玻璃层与胶层间嵌入零厚度内聚力单元,研究给出基于固有内聚力的风挡玻璃有限元模型。研究发现,对应工况的仿真结果与试验结果基本一致,证明内聚力模型应用在该仿真中的有效性。同时相对于常规的单元删除法,基于内聚力模型的仿真结果更加接近试验结果,证明所建立方法的精度更高。

In order to effectively support the simulation analysis of unmanned aerial vehicle(UAV)impact on aircraft and reduce the cost of experimental research,the test and finite element simulation method research of collision between UAV and windshield of a transport category aircraft were carried out.The modeling method of windshield and UAV was studied and established according to the actual size and curved surface configuration.Considering the unpredictability and complexity of crack initiation and propagation of windshield glass after impact,zero-thickness cohesive elements were embedded between glass elements and between glass layer and rubber layer in the windshield model through Python programming,and the finite element model of windshield based on intrinsic cohesion was presented.It is found that the simulation results of corresponding conditions are basically consistent with the experimental results,which validates the cohesive zone model in the simulation.And compared with the conventional element deletion method,the simulation results based on the cohesive zone model are closer to the experimental results,which demonstrates that the established method has higher accuracy.