The invention discloses a 1400-DEG C high-temperature thermal-mechanical
coupling test device for the aerofoil structure of a hypersonic vehicle, which comprises a
test sample of the aerofoil structure of the hypersonic vehicle, a
silicon-
molybdenum heating array, a water-cooled
metal-loading component, a U-shaped water-cooled channel, a
force sensor, a hydraulic
actuator, a temperature sensor and a computer. Because the water-cooled
metal-loading component is designed into a U-shaped hollow structure, the problems of high-temperature
softening and deformation existing in the
metal-loading component at 1400 DEG C are solved by using a method of cooling the inside of the metal loaded component with flowing liquid, the high-temperature (up to 1400 DEG C) thermal-mechanical
coupling test on the aerofoil structure can be realized, and the ultimate strength of the aerofoil structure in high-temperature thermal-mechanical complex environment and other important parameters can be obtained, thereby providing a reliable basis for the
safety design of a hypersonic vehicle structure in high-speed, high-temperature thermal-mechanical
coupling environments.