Aerodynamic and thermal combined test system and method

Abstract

The invention belongs to a hypersonic aerodynamic thermal test technology, and particularly relates to an aerodynamic thermal combined test system and method. The system comprises an arc heater, a stretcher and a test chamber, the test chamber is arranged below the stretcher, the test chamber is fixedly connected with the stretcher, one side of the test chamber is connected with the arc heater, and the other side of the test chamber is connected with wind tunnel accessory equipment. According to the invention, the aerodynamic environment during orbit flight of an aerospace craft can be simulated as truly as possible, and the structural strength of a heat-proof material is examined in the specific environment, so that the problem of self thermal coupling interference test of test equipment is solved, and the system error of self thermal coupling interference of a test system in the test is reduced. According to the invention, aerodynamic thermal examination is completed by using the test piece and adopting a supersonic flat plate free jet test technology, so that the test result is more accurate.

Description

technical field [0001] The invention belongs to hypersonic aerodynamic thermal test technology, in particular to an aerodynamic thermal combined test system and test method. Background technique [0002] When a hypersonic vehicle flies in the atmosphere at high speed, the thermal protection system is subjected to multiple thermal-mechanical coupling effects such as high-enthalpy aerodynamic heating, mechanical load, aerodynamic shear force, and thermal stress generated by temperature gradients. Ablation spalling, mechanical load, aerodynamic shear force and thermal stress will damage the material base to produce micro-cracks, accelerate the process of ablation spalling of heat-resistant materials, these will cause the material structure deformation and strength change of the aircraft, affect the precise control or endanger the safety of the aircraft. Simulating the ablation and load-bearing environment of heat-resistant materials and structures as realistically as possible ...

AI Technical Summary

Problems solved by technology

The static heating method does not have the aerodynamic shearing of the material during orbital flight, and the heating of the material is generally uniform in the circumferential direction, which cannot simulate the single-sided heating condition in the real application process of the heat-resistant material

However, with the dynamic heating method of the gas flow wind tunnel, the composition of the hot air flow is complex, and it can only be evaluated for heat-resistant materials (such as engine turbine blades) in some specific application environments.

[0004] When carrying out the structural assessment of heat-resistant materials in an aerodynamic thermal environment, it needs to be carried out in a vacuum environment, and it is used to support the model for thermal assessment. The tension transmission mechanism may be thermally deformed during the test process, and the thermal coupling problem of the entire test system itself will bring a large system error to the test, and may even cause the test to fail

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