Gas film heat insulation and cooling device for gas source of solid fuel gas generator

Abstract

The invention discloses a gas film heat insulation and cooling device for a gas source of a solid fuel gas generator. The device is composed of an aircraft hood, a generator fixing support, the solid fuel gas generator, a fuel gas filtering and rectifying storage box, a gas adjusting and conveying system and a gas distribution device; the generator fixing support is fastened to the inner walls of the upper side and the lower side of the aircraft hood through screws, and the solid fuel gas generator is fastened to the right side of the middle of the generator fixing support through bolts; the fuel gas filtering and rectifying storage tank is connected with the solid fuel gas generator through a flange and is sealed through an O-shaped ring; and the gas adjusting and conveying system and the gas filtering and rectifying storage box are connected through a pipe joint and sealed through a spherical conical surface, and the gas distribution device and the gas adjusting and conveying system are connected through the pipe joint and sealed through the spherical conical surface. According to the device, clean gas with low temperature and stable conveying pressure can be obtained, a gas source supply system can be greatly simplified, and ablation of an aircraft hood material is greatly reduced.

Description

technical field [0001] The invention relates to a gas film heat insulation and cooling device for a gas source of a solid gas generator, which is used for active heat insulation on the outer surface of a hypersonic vehicle hood, and belongs to the technical field of heat protection and heat insulation of a hypersonic vehicle. Background technique [0002] When space planes, space shuttles, missiles, rockets and other hypersonic vehicles (hereinafter referred to as "vehicles") fly in the atmosphere at high speed for a long time, the outer surface of the hood will generate high dynamic pressure and strong aerodynamic heating effect. The high temperature generated by the harsh aerodynamic heating effect will significantly reduce the strength limit and structural bearing capacity of the aircraft shell material. The basic purpose of aircraft thermal protection is to ensure the structural safety of the aircraft in the harsh environment of aerodynamic heating, and to keep the inner...

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Problems solved by technology

[0003] At present, aircraft heat protection and heat insulation technologies mainly fall into three categories: passive heat protection, active heat protection, and semi-active heat protection. Among them, passive heat protection mainly relies on the heat-resistant structure and the material itself to absorb or radiate heat, and does not require working fluid. , this scheme is simple and reliable, and is widely used at present, but the heat protection time is short; active cooling mainly relies on the cooling fluid to take away most of the heat flow and reflect a small part of the heat. This scheme has a long heat protection time , but the cooling medium storage tank and conveying system need to be designed inside the device, the structure is more complicated and the space occupied is larger; the semi-active thermal protection is between passive heat protection and active heat protection, and mainly adopts two forms of heat pipe structure and ablation structure , the heat protection time is longer, there is no need for storage tanks and conveying systems, and the heat pipe structure is more complicated than the ablation structure and takes up a lot of space;

[0004] Considering that the aerodynamic structure on the surface of the aircraft hood is relatively complex, and at the same time, limited by the use temperature of the metal shell and internal components, the size of the bullet diameter, etc., a single passive heat protection (such as heat-resistant tiles, carbon-carbon materials, carbon-silicon materials, etc.) material) or semi-active heat protection (such as ablation structure) can no longer meet the thermal protection requirements at higher speeds and longer periods of time

The harsh aerodynamic heating effect produced by high-speed and long-term flight will lead to changes in the aerodynamic surface of the aircraft, thereby affecting the flight stability of the aircraft

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