A thermal protection method for leading edge of hypersonic vehicle

Abstract

The invention relates to a thermal protection method for the leading edge of a hypersonic aircraft. Design the aerodynamic strut and fix it at the front end of the aircraft; design the air-draining thermal protection structure of the aircraft; obtain the key parameters that affect the peak disturbance heat flow; optimize the local shape of the aircraft's leading edge area; obtain the aircraft's leading edge area Conduct shock wave wind tunnel thermal test verification; complete the design of the dredging thermal protection structure, obtain the cooling effect and the law of the parameters affecting the cooling effect, and obtain the best dredging thermal protection structure; the best dredging thermal protection structure obtained Carry out the arc wind tunnel thermal assessment test; determine whether the design of the dredging thermal protection structure is completed according to the results of the thermal assessment test. The invention can ensure the feasibility of the thermal protection scheme of the leading edge area without reducing the overall performance index such as the lift-to-drag ratio of the aircraft, and can effectively solve the thermal protection problem of the leading edge area of ​​the hypersonic aircraft.

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.

Images