Nitrous oxide kerosene two-component liquid rocket engine power system

Abstract

The invention discloses a nitrous oxide and kerosene two-component liquid rocket engine power system which comprises a nitrous oxide storage tank, a kerosene storage tank, an engine, a nitrous oxide inlet of an injector of the engine, an oxidation pipeline, a kerosene inlet of the kerosene storage tank, a kerosene outlet of the kerosene storage tank and a kerosene outlet of the kerosene storage tank. A kerosene inlet of the injector is further communicated with an outlet of the kerosene storage tank through a liquid pipeline, the injector of the engine is used for injecting nitrous oxide and kerosene into a combustion chamber of the engine at a constant pressure drop, and the combustion chamber is used for providing a constant-pressure combustion place for atomized, evaporated and mixed nitrous oxide and kerosene; compared with an existing attitude and orbit control engine using toxic hydrazine propellants, the attitude and orbit control engine has the advantages that the ground operation cost is low, personnel work is safe, and the attitude and orbit control engine is environment-friendly; compared with an existing attitude and orbit control engine using a hydrogen peroxide propellant, the attitude and orbit control engine can be safely stored for a long time and is longer in service life.

Description

Technical field [0001] The invention belongs to the field of liquid rocket engines, and in particular relates to a nitrous oxide kerosene two-component liquid rocket engine power system. Background technique [0002] Attitude control engines are used for attitude control, orbit correction, position maintenance, etc. of spacecraft. For 100-niu level attitude control engines, hydrogen peroxide propellant or hydrazine propellant is mainly used. [0003] The hydrogen peroxide attitude control engine adopts the form of single-component catalytic decomposition, which requires an additional supercharging system for propellant supply. The vacuum specific impulse is low, about 150s, and the high activity of hydrogen peroxide makes it not very safe and easy to explode. [0004] Although the attitude control engine using hydrazine propellant has sufficient vacuum specific impulse, my country's first-generation 490N orbit control engine has a vacuum specific impulse of 305s when the ar...

AI Technical Summary

Problems solved by technology

[0005] The purpose of the present invention is to provide a nitrous oxide kerosene two-component liquid rocket engine power system to solve the problem of complex extrusion system on the existing attitude control engine, occupying the mass of the spacecraft, poisonous propellant and unable to be safely stored and used for a long time question

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