Thermal modal test of composite wing structure in high-temperature environments up to 1 100 ℃ for hypersonic flight vehicles

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-temperature-resistant 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.