典型服役热环境下舵面结构动力学特性试验技术

Experimental Technology for Dynamic Characteristics of Rudder Surface Structures under Typical Service Thermal Environment

高超声速飞行器高速飞行过程会遭受严重的气动力叠加热载荷的复杂载荷联合作用,尤其是舵面结构,其在复杂载荷下的结构动力学特性是影响装备服役安全及可靠飞行的关键因素,通过试验进行验证和评估是一种有效的研究手段。舵面结构典型服役工况下表面温度高,迎风面与背风面气动热温差往往达到数百摄氏度,需要在试验中进行精确模拟。以C/SiC舵面结构为研究对象,设计并搭建了瞬态热环境下结构动力学特性试验系统,构建了一种加载温度高、迎风面与背风面温差大的典型服役热载荷环境,开展了舵面结构在该环境下的动力学特性试验研究,获取了结构的动力学特性变化规律。研究成果为典型服役热环境对现代高超声速飞行器舵面结构的动力学特性影响研究提供了重要验证手段。

The hypersonic vehicle will be subjected to severe aerodynamic superimposed heating loads during high-speed flight,especially the control surface structure,which is structure dynamic characteristics under complex loads are the key factors affecting the safe and reliable flight of the hypersonic vehicle,and it is an effective research method to verify and evaluate through experiment.The C/SiC rudder surface structure was taken as the research object,and the structure dynamic characteristics test system under the transient thermal environment was designed and built.A typical service thermal load environment with high loading temperature and large temperature difference between the windward and leeward surfaces was built.The dynamic characteristics test of the rudder surface structure under this environment was carried out,and the change rules of the structure dynamic characteristics were obtained.The research results provide an important verification means for the research on the influence of typical service thermal environment on the dynamic characteristics of modern hypersonic vehicle control surface structure.