基于欧拉—拉格朗日方法的复合材料机翼前缘鸟撞模拟

Finite element analysis of bird striking on a composite wing leading edge based on eulerian-lagrangian method

复合材料大面积用于飞机结构后,其鸟撞问题变得更加突出。利用大型通用有限元程序ABAQUS,采用耦合欧拉-拉格朗日方法(CEL)对某型无人机复合材料机翼前缘的鸟撞问题进行模拟,研究鸟体速度、密度和蒙皮铺层形式等对鸟撞动响应的影响,计算机翼前缘填充泡沫后的鸟撞损伤,对复合材料蒙皮的鸟撞破坏机理进行分析,所得结果对工程设计具有参考意义。

Along with large-scale application of composite materials in aircraft structures, a bird striking problem has become more prominent. Numerical simulations for bird striking on a composite wing leading edge were performed using ABAQUS based on Eulerian-Lagrangian method. Parametric analyses for the dynamic response of bird striking were performed with different bird velocities; densities and wing skin ply arrangements. The damage due to bird striking in the composite wing was simulated when the leading edge was filled with foam core. The destructive mechanism due to bird striking of the composite wing skin was analysed. The results gave a reference for engineering designs.