摘要
对轻型直升机薄壁结构尾梁在发射空地导弹所产生的冲击波作用下的振动响应进行了有限元分析 ,根据计算结果提出了两种结构改进设计方案用于试验验证。试验使用的导弹模拟发射器产生的冲击波与实际导弹一致 ,用一个 1∶ 1的尾梁试验件实现了两种不同的结构改进方案 ,在不同的改进方案、导弹布置位置组合下 ,发射了6 0枚模拟导弹。试验表明对于轻型直升机薄壁无长桁主承力结构 ,只要以极小的重量代价改进结构设计 。
The dynamic response of a light helicopter Aft Transition and Tailcone (ATT), which is of thin shell structure, under the shock wave caused by anti-tank missile launching, is investigated by using Finite Element Method. Two improved structural designs are raised according to analysis results, and have been applied to tests for substantiations. The shock wave caused by the simulated launcher using for the tests is the same as that by the actual one, and the two designs are fulfilled in one ATT of full scale. 60 missile launchings under different combinations of the designs and missile locations. The tests indicate that, the fuselage-missile compatibility can be met by structural improvement with minor weight penalty for the primary force-taking structure of thin shell without stringer.
出处
《振动工程学报》
EI
CSCD
北大核心
2004年第2期170-174,共5页
Journal of Vibration Engineering
关键词
冲击波
薄壁结构
机弹相容性
直升机
振动响应
helicopter
thin shell structure
shock wave
fuselage-missile compatibility
