高超声速飞行器复合材料翼面结构1100℃高温环境下的热模态试验

Thermal modal test of composite wing structure in high-temperature environments up to 1100 ℃ for hypersonic flight vehicles

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 parameters of composite wing structure that are difficult to measure in high-temperature environments beyond 1 000 ℃in thermal modal test,high-temperature transient heating test system and vibration test system were combined to establish a thermal/vibration joint test system that was able to perform research on the thermal modal of high-temperature-resistant composite wing structure subjected to high temperature up to 1 100℃for hypersonic flight vehicles.A self-developed extension configuration of high-temperatureresistant ceramic pole was used to transfer the vibration signals of the composite wing structure to non high-temperature zone.Ordinary acceleration sensors were applied to identify the vibration signals of the composite wing structure in high-temperature environments for hypersonic flight vehicles.Test data were analyzed by using a time-frequency joint analysis technique,and then the key vibration characteristic parameters of composite wing structure(e.g.the modal frequency and modal vibration shape)in a thermal/vibration coupled environment up to 1 100 ℃were obtained.The research results can provide an important basis for the dynamic performance analysis and safety design of composite wing structure in high-temperature environments for hypersonic flight vehicles.