Lightweight modularized liquid attitude and orbit control engine

Abstract

The invention discloses a lightweight modularized liquid attitude and orbit control engine which comprises a shell, a combustion chamber, an injector, a high-temperature-resistant sealing gasket, a bearing, a propellant inlet connector, a sealing spherical surface, a sealing ring and a shaft type electromagnetic valve. According to the invention, the engine is subjected to lightweight modular design, and a shaft type electromagnetic valve and rotary sliding type injector structure is adopted, so that the working mode of function interchange among the engine injectors is realized on the basis of basically not increasing the weight of a power system and the layout space, and the redundancy and reliability of an engine module are improved. Under a certain condition, the number of the injectors in the engine module can be even reduced, and the layout space and the weight of each engine are reduced.

Description

Technical field [0001] The present invention relates to a light modular liquid label engine, mainly used for attitude and track control in the fields of aerospace. Background technique [0002] Liquid Leaves Control Engines are mainly used in aerospace sectors for the attitude of the aircraft, orbital control. Since the power system therefore belongs to the above-level application product, the layout space of the liquid post-rail engine is more demanding during the design process, and the margin of redundant design can be made smaller. [0003] The traditional liquid rocket engine has a combustion chamber to fix the corresponding structural mode one by one by one by one, when a problem occurs, the engine cannot continue to work properly, and can only be replaced by the remaining redundant backup engines; if there is no backup engine In the case of it, it will bring a great failure risk to the system flight. [0004] On the other hand, the redundant mode of the backup design is us...

AI Technical Summary

Problems solved by technology

[0003] The traditional liquid rocket engine adopts a fixed and one-to-one structural model of the combustion chamber and the injector. When a problem occurs, the engine can no longer continue to work normally, and can only be replaced by the rest of the redundant backup engines; if there is no backup engine In the case of the system, it will bring a great risk of failure to the flight of the system

[0004] On the other hand, for a liquid attitude control power system with multiple engines, the redundant mode of the backup design greatly increases the weight and cost of the power system, and is not conducive to the miniaturization of the system

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