复合材料尾翼前缘结构抗鸟撞仿真及试验验证研究

目的 依据适航条款25.631的要求，对飞机复材尾翼前缘结构抗鸟撞能力进行仿真分析及试验验证。方法 根据复材鸟撞仿真计算的需要，建立了获取复材动态力学性能参数的试验矩阵，开展了复材动态力学性能测试及本构模型参数标定。应用标定后的复材本构模型参数，对尾翼前缘结构的抗鸟撞能力进行了仿真分析，同时开展了试验验证。结果 试验结果与仿真结果良好的一致性，表明建立的鸟撞数值仿真模型能够较合理地预计尾翼前缘结构的损伤。结论 建立的试验证矩阵和经试验验证过的复材鸟撞仿真分析方法对飞机结构抗鸟撞设计具有一定的指导作用。

Simulation and Experimental Verification Composite Structure of Empennage Leading Edge against Bird Impact

The work aims to carry out the simulation analysis and experimental verification to the bird impact resistance of the leading edge structure of composite empennage according to the requirements of airworthiness standards CCAR25.631. The experiment matrix was designed to obtain the dynamic mechanical property parameters of the composite according to the simulation requirements of composite against bird impact, and the dynamic mechanical property test and constitutive model parameter calibration were carried out. Based on the calibrated composite constitutive model parameters, the bird impact resistance of the leading edge structure of the empennage was simulated and verified by experiments. The good consistence between the experiment results and the simulation results showed that the bird impact numerical simulation model established could reasonably predict the damage of the leading edge structure of the empennage. Therefore, the simulation analysis method verified by test matrix and experiment for composite against bird impact has a certain guiding role in the bird impact resistance design of aircraft structures.