The wing structures of long-range, high-speed flight vehicles bear vibration during the flying time. 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. In this paper, the high-temperature environment test system and vibration test system were combined to conduct a thermal-vibration test for the composite trilaminated wing structure that comprised composite materials and metallic materials. The vibration characteristics of the composite trilaminated wing structure, such as natural frequency and vibration mode, were obtained in 200°C, 300 oC and 400 oC environments. The results provide an important basis for the dynamic characteristics analysis and safety and reliablity design of wing structures comprised composite materials and metallic materials under a thermal-vibration environment.