Abstract: 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℃. 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.