带飞行控制系统飞机颤振试飞的结构动响应研究  

On Structural Dynamic Response of an Aircraft in Flight Flutter Test

作　　者：李秋彦[1] 陈国平[1] 杨智春[2] 

机构地区：[1]南京航空航天大学航空宇航学院,南京210016 [2]西北工业大学航空学院,西安710072

出　　处：《机械科学与技术》2007年第9期1163-1166,共4页Mechanical Science and Technology for Aerospace Engineering

摘　　要：对带飞行控制系统飞机在颤振飞行试验中的结构动力响应分析进行了研究,建立了采用FES(flight excitation system)系统激励和小火箭激励两种方式的动力学分析模型,在此基础上构建了软件分析平台并对某型带飞行控制系统飞机进行了应用,为该飞机颤振试飞激励方式和参数选取提供了参考依据。最后提出了气动伺服弹性和结构动响应研究下一步的发展方向。We study the structural dynamic response of an aircraft with flight control system in flight flutter test. First according to the excitation systems adopted in flight flutter test-FES （Flight Excitation System） or small rocket system, the dynamic model of an aircraft with flight control system is built and the corresponding analytical software system is also developed. Then, we propose an analytical method, and apply it to a real aircraft to calculate its dynamic response. Comparison is made between responses of aircraft with and without consideration of the effect of the flight control system. The results show that the flight control system has an obvious effect on the lower frequency modal responses which are dominant in the structural dynamic response of the aircraft. The present studies are helpful for engineers to choose exciting method and to determine exciting system parameters in aircraft flight flutter test.

关 键 词：飞行控制系统 飞行颤振试验 飞机结构动响应 

分 类 号：V215.34[航空宇航科学与技术—航空宇航推进理论与工程]