飞机尾翼前缘结构鸟撞仿真与改进设计

基于疏散鸟体动能的防鸟撞策略，以提高结构刚度和抑制变形为目标，采用光滑粒子流体动力学(SPH)方法对现有飞机尾翼前缘结构鸟撞过程进行了数值研究。根据模拟结果，通过增加单向斜支板结构和采用纤维/金属复合材料，实现了从结构和材料两个方面对尾翼前缘结构进行改进设计。结果表明，前缘增加的单向斜支板结构可以通过疏散鸟体动能来降低鸟撞冲击对尾翼内部结构的破坏，而采用纤维金属复合材料则减轻了前缘曲翼约10%的质量，且提高了整体刚度，并使结构在鸟撞过程中最大变形降低到原始构型的25%。通过分析不同铺层方式下材料的破坏模式和吸能效果，发现合理的铺层设计可显著提高尾翼前缘结构的抗鸟撞性能。

BIRD STRIKE SIMULATION AND IMPROVED DESIGN OF LEADING EDGE STRUCTURE OF AIRCRAFT TAIL

In order to improve structural stiffness and to reduce the structural deformation of existing aircraft tail leading edge structures, a smoothed particle hydrodynamics method is used to numerically study bird-strike problems based on the strategy of reducing bird-strike energy. According to simulation results, the improved design of a tail leading edge structure is realized from two aspects of structure and material by adding a unidirectional inclined support plate structure and using fiber-metal composite materials. The simulation results show that: the unidirectional inclined support plate structure added at the leading edge reduces the bird-strike damage of the tail structure by evacuating the kinetic energy of the bird body, while using fiber-metal composite materials reduces the mass of the curved wing structure on leading edge by about 10%, improves the overall stiffness, and reduces the maximum deformation of the structure to 25% of the original configuration. It is found that reasonable layup design can significantly improve the bird strike performance of the tail leading edge structure of an aircraft by analyzing the failure mode and energy absorption effect of materials under different ply arrangements.