Air film and micro straight channel cooling structure for front edge of hypersonic vehicle

Abstract

The invention discloses an air film and micro straight channel cooling structure for a front edge of a hypersonic vehicle, which comprises an air film cavity, air film holes and micro straight channels. The air film cavity is positioned inside the front edge of the hypersonic vehicle; the air film holes which are arranged in a stagger mode are formed near stagnation points of the front edge at the periphery of the air film cavity; two rows of micro straight channels are formed next to both upper and lower surfaces of a wedge-shaped body of the hypersonic vehicle; and the micro straight channels are communicated with the air film cavity and a high pressure water tank. On the premise of not changing the pneumatic appearance of the air vehicle, the air film cooling mode is combined with the micro channel cooling mode, so that the heat exchange efficiency is effectively improved.

Description

technical field [0001] The invention relates to a leading edge air film + tiny straight channel cooling structure of a hyper-vehicle, which belongs to the field of local heat exchange with high heat flux density in aviation, aerospace, power machinery and the like. Background technique [0002] The problem of aerodynamic heating is raised because of the need for the research and development of hypersonic vehicles. When the aircraft flies at supersonic or hypersonic speed, the air is subjected to strong compression and severe friction, and most of the kinetic energy is converted into heat energy, causing the temperature of the air around the aircraft to rise sharply. There is a large temperature difference between this high-temperature gas and the surface of the aircraft, and part of the heat energy is quickly transferred to the object surface. This heat transfer method is called aerodynamic heating. The high temperature generated by serious aerodynamic heating will reduce t...

AI Technical Summary

Problems solved by technology

Traditional passive cooling, such as radiative cooling, requires a high surface temperature to achieve high radiative heat flux density, so it cannot meet the requirements for material strength and service life. Although the thermal protection structure of the ablation layer can meet the requirements of high heat flux density, However, it cannot be applied to hypersonic vehicles with a flight time of tens of minutes or even hours.

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