1400-DEG C high-temperature thermal-mechanical coupling test device for aerofoil structure of hypersonic vehicle

Abstract

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.

Description

technical field [0001] The invention relates to a 1400°C high-temperature thermomechanical coupling test device for the airfoil structure of a hypersonic aircraft, especially when performing the aerodynamic and thermal environment test simulation of the airfoil structure of a hypersonic aircraft, the test device can measure the airfoil at a temperature as high as 1400°C Important parameters such as the thermal strength limit of the structure provide an important basis for the thermal strength design of the hypersonic vehicle structure in an extreme high-temperature thermodynamic composite environment. Background technique [0002] With the development of aerospace technology, the design flight speed of long-range maneuvering aircraft is constantly increasing. At the same time, the combat performance requirements of high-speed, high-precision, and high-maneuverability aircraft in modern warfare have caused countries all over the world to compete to develop hypersonic aircraft...

AI Technical Summary

Problems solved by technology

[0006] The technical solution of the present invention is to overcome the deficiencies of the prior art and provide a 1400°C high-temperature thermomechanical coupling test device for the airfoil structure of a hypersonic aircraft. The problem of high-temperature softening and deformation of the lower metal loading parts can realize the high-temperature thermal-mechanical coupling test of the airfoil structure of the hypersonic vehicle, and provide a reliable basis for the safety design of the hypersonic vehicle structure in a high-speed, high-temperature thermal-mechanical coupling environment

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