Hypersonic aircraft leading edge thermal protection method

Abstract

The invention relates to a hypersonic aircraft leading edge thermal protection method. The method comprises the steps of: designing a pneumatic support rod, and fixing the pneumatic support rod at theforemost end of an aircraft; designing a dredging type thermal protection structure of the aircraft; obtaining key parameters influencing peak interference heat flow; optimizing the local shape of the leading edge area of the aircraft; carrying out shock tunnel heat measurement test verification on the obtained aircraft leading edge area; completing the design of the dredging type thermal protection structure, obtaining the cooling effect and the law of influencing the cooling effect parameters, and obtaining the optimal dredging type thermal protection structure; carrying out an arc wind tunnel thermal assessment test on the obtained optimal dredging type thermal protection structure; and determining whether the dredging type thermal protection structure is designed or not according to the result of the thermal assessment test. The feasibility of the thermal protection scheme of the leading edge area can be ensured while the overall performance indexes such as the lift-drag ratio ofthe aircraft are not reduced, and the thermal protection problem of the leading edge area of a hypersonic aircraft can be effectively solved.

Description

technical field [0001] The invention belongs to the technical field of heat reduction and drag reduction of aircraft, and in particular relates to a thermal protection method for the leading edge of a hypersonic aircraft. Background technique [0002] For a hypersonic vehicle with a complex shape in the vicinity of a high Mach number, the shape of the high lift-to-drag ratio and the working requirements of the air-breathing engine make the radius of the leading edge of the projectile / protective cover not too large, and the leading edge area is subjected to severe aerodynamic heating. The enthalpy dissociated flow will also have complex nonlinear coupling with the thermal protection material, which puts forward extremely stringent requirements on the temperature resistance, oxidation resistance and reliability of the thermal protection structure in the leading edge area. At present, the commonly used thermal protection materials are difficult to ensure that the leading edge a...

AI Technical Summary

Problems solved by technology

At present, the commonly used thermal protection materials are difficult to ensure that the leading edge area will not be ablated in large quantities, and the means of hard resistance of thermal protection materials alone cannot ensure the feasibility of the thermal protection scheme. The heat reduction optimization design of the thermal protection scheme for the leading edge area has become the development of the aircraft. Bottleneck problem

[0003] For a hypersonic vehicle in close space with a flight Mach number exceeding 15 for a long time, the temperature of its leading edge area may exceed 3000 ° C. It is difficult to ensure that the leading edge area will not be ablated by a large amount of anti-corrosion methods, and the use of active thermal protection methods such as air film / sweating cooling will bring additional air sources and control equipment, and the technical route is not yet mature.

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