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.
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]. , 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. , 2012, 31(7): 137-141.