高速飞行器中空翼结构高温热振动特性试验研究  

EXPERIMENTAL STUDY ON HIGH TEMPERATURE THERMAL-VIBRATION CHARACTERISTICS FOR HOLLOW WING STRUCTURE OF HIGH-SPEED FLIGHT VEHICLES

作　　者：吴大方[1] 赵寿根[1] 潘兵[1] 王岳武[1] 王杰[1] 牟朦[1] 朱林[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院

出　　处：《力学学报》2013年第4期598-605,共8页Chinese Journal of Theoretical and Applied Mechanics

基　　金：国家自然科学基金资助项目(11172026;11002012)~~

摘　　要：远程高速飞行器飞行速度快,滞空时间长,飞行过程中翼、舵等结构会出现长时间的剧烈振动,由气动加热产生的高温还会使飞行器材料和结构的弹性性能发生变化,从而引起翼、舵等结构振动特性的改变.因此获得高温与振动复合环境下的远程高速飞行器翼、舵等结构的振动特性参数对于高速飞行器的安全设计具有非常重要的意义.将高温热环境试验系统与振动试验系统相结合,在对中空翼面结构进行振动激励的同时使用红外辐射加热方式对翼面结构生成可控的热环境,并通过自行设计的耐高温引伸装置将中空翼结构的振动信号传递到非高温区进行数据采集与分析的方式,实现了高达800 C～900 C的力热复合环境下的翼结构固有频率、模态等振动特性参数的试验测试,其试验结果为远程高速飞行器中空翼结构在高温振动环境下的动特性分析和安全可靠性设计提供了重要依据.During long time and high speed flight,high-speed aircraft structure,such as the wing and rudder,bears not only prolonged serious vibration,but also harsh aerodynamic heating.The high temperatures caused by aerodynamic heating can greatly change the elasticity properties of the materials in a high-speed flight vehicle,leading to an alteration in the vibration characteristics of high-speed flight vehicle structures.Knowledge of the vibration characteristics of these key structures is critical to the safety design of high-speed flight vehicles.In this paper,vibration excitation was exerted to a hollow wing under controlled thermal environments by combining a self-developed transient aerodynamic heating device with a vibration test system.A self-designed extension configuration withstanding high temperature is used to transfer the vibration signals to the non-high temperature zone for vibration data acquisition.With this novel method,accurate measurements of various vibration characteristics parameters,such as natural frequency and vibration modal,can be achieved in a thermal-mechanical environment with a highest temperature up to 900 C.Experimental results provide an important basis for the dynamic characteristic analysis and safety design of the hollow wing structure used in a long-range high-speed flight vehicles under high-temperature thermal-vibration conditions.

关 键 词：振动特性 高速飞行器 热试验 翼结构 

分 类 号：V216.2[航空宇航科学与技术—航空宇航推进理论与工程] V216.4