为了在热模态试验中获得难于测量的超过1 000℃的高温环境下复合材料翼面结构的振动特性参数,将高温瞬态热试验系统与振动试验系统相结合,建立了可对高超声速飞行器耐高温复合材料翼面结构进行1 100℃高温环境下热模态研究的热/振联合试验系统。通过自行研制的耐高温陶瓷导杆引伸装置将复合材料翼面结构上的振动信号传递至非高温区域,使用常温加速度传感器对高温环境下高超声速飞行器翼面结构上的振动信号进行数据识别;并运用时-频联合分析技术对试验数据进行分析处理,实现了在1 100℃热/振复合环境下对复合材料翼面结构的模态频率、模态振型等关键振动特性参数的试验测试。研究结果为高超声速飞行器复合材料翼面结构在高温环境下的动特性分析及安全可靠性设计提供了重要依据。 In order to obtain the vibration characteristic parameters of the composite airfoil with high temperature exceeding 1 000 ℃ in the thermal modal test, the high temperature transient thermal test system was combined with the vibration test system to establish the hypersonic vehicle Thermal / Vibration Joint Test System for High Temperature Composited Airfoil Structures to Study the Thermal Modalities at 1 100 ℃ High Temperature. Through the self-developed high-temperature ceramic guide rod extension device, the vibration signal of the composite airfoil structure is transmitted to the non-high temperature area, and the ambient temperature acceleration sensor is used to identify the vibration signals of the hypersonic vehicle’s airfoil structure under the high temperature environment. The time-frequency analysis technique is used to analyze and test the experimental data to test and test the key vibration characteristics such as modal frequency and mode shape of the composite airfoil in a hot / vibration environment of 1 100 ℃. The results provide an important basis for the dynamic characteristics analysis and safety and reliability design of the composite aerofoil wing structure of hypersonic vehicles under high temperature.