多欧拉域耦合法在平尾鸟撞中的应用

鸟撞是威胁航空安全的重要因素之一。目前的研究多是对单一试件或结构的一次性鸟撞，而对鸟体穿透撞击部位后，对其他结构造成二次冲击的研究较少。为了研究这种问题，基于流固耦合算法，建立了多欧拉域耦合的某直升机平尾全尺寸模型。在考虑空气影响的前提下，详细分析了鸟撞平尾过程、前缘和前梁的损伤形式、平尾的位移响应、鸟撞载荷规律以及冲击载荷对平尾根部结构的影响，并与试验结果进行了对比。研究表明：鸟体在穿透前缘时未发生解体，其对前梁的二次冲击载荷同样很高，平尾结构设计需要考虑鸟撞是否会造成平尾根部断裂，鸟撞载荷具有阶跃函数的特点；结构响应时间对比冲击载荷有明显的滞后效应。

Multi-Euler domain coupling method in bird strike with flat tail

Bird strike is one of the important factors threatening aviation safety. At present, most of the studies are about one-time bird impact on a single specimen or structure, while few are about secondary impact on the structure caused by penetrating the impact site of the bird body. To study this problem, a full-size model for helicopter tail with multi-Euler coupling is established based on the fluid-solid coupling algorithm. Considering the influence of air, the process of bird strike to the flat tail, damage forms of leading edge and front beam, displacement response of the flat tail, law of the bird impact load, the effect of impact load on the structure of flat tail root are analyzed in detail and are verified with the experimental results. The research shows that if the bird body does not disintegrate when penetrating the leading edge, its secondary impact load on the front beam will also be at high level. The design of flat tail structure needs to consider whether the bird strike will cause the root fracture of flat tail. The bird impact load has the characteristic of step function. The response time of the structure has obvious hysteresis effect compared with the impact load.