直升机桨叶鸟撞试验方法的数值模拟  

Numerical simulation of bird impact on helicopter blade

作　　者：林长亮[1] 王浩文[2] 陈仁良[1] 

机构地区：[1]南京航空航天大学直升机旋翼动力学国家级重点实验室,江苏南京210016 [2]清华大学航天航空学院,北京100084

出　　处：《振动工程学报》2012年第6期667-673,共7页Journal of Vibration Engineering

摘　　要：由于直升机旋翼的工作特点,使得全尺寸旋翼鸟撞试验很难进行,而在飞行器结构抗鸟撞的设计过程中,鸟撞试验是最终、最有效的检验方法,因此开展直升机桨叶鸟撞试验研究十分必要。采用Arbitrary Lagrangian Euleri-an(ALE)流固耦合方法分别对旋转状态的桨叶鸟撞以及端部受集中载荷作用的静止状态桨叶鸟撞进行了数值模拟,通过数值模拟结果对比,发现两种状态下桨叶的动态响应结果很接近,说明采用集中载荷替代离心载荷的静态鸟撞试验可以较好地模拟旋转状态下桨叶鸟撞试验,从而为直升机动部件鸟撞试验研究提供理论依据。The bird impact test for full-size rotor is difficult because of working characteristics of tlhe helicopter rotor. Howev- er, in the design process of crashworthy aircraft structure, bird impact test is the ultimate and the most effective verification method. Therefore it is quite necessary to study the test method for bird impact on helicopter blade. Arbitrary Lagrangian Eulerian （ALE） fluid-solid coupling method was adopted to simulate bird impact on rotating blade as well as on stationary one whose end was under concentrated loads, respectively. After comparison of numerical simulation results, it was found that dynamic response of blade under the above two states is quite approximate. This shows that static bird impact test adopting centralized loads instead of centrifugal ones can better simulate the test of bird impact on rotating blade, thus providing a reference method for research of bird impact on helicopter rotor.

关 键 词：直升机 桨叶 鸟撞 数值模拟 试验方法 

分 类 号：V215.1[航空宇航科学与技术—航空宇航推进理论与工程] V216.5