跨声速风洞全模颤振试验技术  

Wind tunnel technique for transonic full-model flutter test

作　　者：路波[1,2] 吕彬彬[2] 罗建国[2] 余立[2] 杨兴华[2] 郭洪涛[2] 曾开春[2] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100191 [2]中国空气动力研究与发展中心高速空气动力研究所,绵阳62100

出　　处：《航空学报》2015年第4期1086-1092,共7页Acta Aeronautica et Astronautica Sinica

摘　　要：介绍了跨声速全模颤振试验的发展现状和存在的问题。探讨了全模颤振试验对风洞和支撑系统等试验设备的要求。对于风洞,主要从风洞洞体和流场等方面分析了进行颤振试验所需要具备的性能,并以中国空气动力研究与发展中心的2.4m跨声速风洞为例,介绍了进行颤振试验必须要采取的控制措施。对于支撑系统,则从模型运动自由度、支撑系统稳定性和支撑系统频率等方面的要求,阐述了设计支撑系统的困难,并简要分析了目前国内外发展的多种全模颤振支撑系统的结构原理及其优缺点。然后介绍了系统安全的保证措施,包括支撑系统稳定性分析、风洞紧急停车控制系统和模型保护装置等。最后根据飞行器发展的需求,探讨了今后需要完善和发展的几个主要问题。A review on the status of transonic wind tunnel technique for full-model flutter test is presented in this paper.The requirements on wind tunnel facility and supporting system are introduced.For wind tunnel,some special requirements on the size of wind tunnel and its quality of flow field for flutter test are analyzed.Taking example of the 2.4m＇transonic wind tunnel in the China Aerodynamic Research and Development Center,the demand control of flow states for flutter tests is introduced.As to the full-model support,the restrictions to design appropriate supporting system are emphasized from model rigid-body freedoms,stability and frequencies of the total system.Several full-model support systems are given and analyzed as examples for design reference.Then some measures to guarantee system security are presented,including static and dynamic stability of the system,emergency brake of the wind tunnel,and model protect.Finally,according to the requirements of vehicle development,several major orientation problems that we need to improve and develop in the future are discussed.

关 键 词：气动弹性 全模颤振 悬浮支撑系统 风洞试验 跨声速 

分 类 号：V211.7[航空宇航科学与技术—航空宇航推进理论与工程]