基于欧拉—拉格朗日方法的复合材料机翼前缘鸟撞模拟

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振动与冲击 ›› 2012, Vol. 31 ›› Issue (7) : 137-141.

论文

基于欧拉—拉格朗日方法的复合材料机翼前缘鸟撞模拟

杜龙

作者信息 +

Finite Element Analysis of Bird Strike on Composite Wing Leading Edge Based on the Coupling Eulerian-Lagrangian Method

Du Long

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文章历史 +

摘要

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，研究了鸟体速度、密度和蒙皮铺层形式等对鸟撞动响应的影响，计算了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了分析，所得结果对工程设计具有参考意义。

Abstract

Along with the large-scale application of composite materials on aircraft structures, bird strike problem has become more prominent. Numerical analyses of bird strike on composite wing leading edge has been performed using ABAQUS based on the Coupling Eulerian-Lagrangian (CEL) method. Parametric analyses for dynamic response have been performed using different bird velocities, densities and skin ply arrangements. The bird strike damage in composite wing has been simulated when leading edge is filled with foam core. The destructive mechanism of composite skin was analysed. The results give a good reference to engineering designs.

导出引用

杜龙. 基于欧拉—拉格朗日方法的复合材料机翼前缘鸟撞模拟[J]. 振动与冲击, 2012, 31(7): 137-141

Du Long. Finite Element Analysis of Bird Strike on Composite Wing Leading Edge Based on the Coupling Eulerian-Lagrangian Method[J]. Journal of Vibration and Shock, 2012, 31(7): 137-141