Front edge impact, micro through passage and air film cooling structure of hypersonic vehicle

A technology of air film cooling and high-speed aircraft, which is applied in the direction of heat reduction structure, aircraft parts, fuselage, etc., which can solve the problems of inability to apply, high surface temperature, inability to meet the requirements of material strength and service life, and achieve the solution of inability to effectively cool Effect

Inactive Publication Date: 2011-08-17
BEIHANG UNIV
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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. Al...

Method used

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  • Front edge impact, micro through passage and air film cooling structure of hypersonic vehicle
  • Front edge impact, micro through passage and air film cooling structure of hypersonic vehicle
  • Front edge impact, micro through passage and air film cooling structure of hypersonic vehicle

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Embodiment

[0019] In the present invention, an impact chamber 1 is opened inside the leading edge 5 of the high-speed aircraft, and an impact hole 2 with a diameter of 0.5 mm to 1.0 mm is opened in the middle of the impact cavity 1. Small straight channels 3 with the same number of impact holes, the size of the inlet cross-section of the straight channels is (0.5mm~1.0mm)×(0.5mm~1.0mm), and a certain number of gas channels are set in the area where the surface temperature of the outer wall of the small straight channels exceeds 1200K. The film holes 7, the diameter of the air film holes 7 are 0.5 mm to 1.0 mm, and the distance between the air film holes 7 is 1.5 mm to 2.0 mm. The included angle between the gas film hole and the fluid flow direction in the tiny straight channel is 20°-50°, generally 30° is selected, and the angle can be slightly changed according to the strength of the heat exchange effect. The cooling medium enters the impact chamber 1 from the circular impact hole 2, fo...

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Abstract

The invention discloses a front edge impact, micro through passage and air film cooling structure of a hypersonic vehicle. The structure is characterized by comprising an impact cavity, impact holes, micro through passages and air film holes, wherein the impact cavity is positioned in a front edge of a high-speed vehicle; a row of impact holes are formed at axis positions on the middle part at one side of the impact cavity close to a vehicle body; two ends of the impact holes are communicated with the impact cavity and an air supply cavity; the two micro through passages are formed at positions of the impact cavity close to corresponding impact holes on the upper surface and the lower surface of the surface of a wedged body of the vehicle; the impact holes and the corresponding micro through passages are positioned in a plane; and the outer wall of each micro through passage is provided with the air film holes. The structure can be used for cooling a region with high heat flux density, so that the problem that a local high temperature region cannot be effectively cooled due to space limitation is substantially solved.

Description

technical field [0001] The invention relates to a front edge impact + tiny straight channel + air film cooling structure of a hyper-vehicle, which belongs to the field of local heat exchange with high heat flux density such as aviation, spaceflight, and power machinery. 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 red...

Claims

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Application Information

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IPC IPC(8): B64C1/38B64C3/36
Inventor 孙纪宁罗翔张传杰丁水汀邓宏武
Owner BEIHANG UNIV
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