Cooperative air suction type liquid rocket engine propellant supply system

Abstract

The invention discloses a cooperative air suction type liquid rocket engine propellant supply system which comprises a liquid oxygen storage tank, a liquid hydrogen storage tank, a liquid oxygen pipeline, a liquid hydrogen pipeline, a high-temperature incoming flow air pipeline, a helium pipeline and a rocket thrust chamber. A rocket belly is formed between the liquid hydrogen storage tank and therocket thrust chamber; the liquid hydrogen pipeline is positioned at the rocket belly and is linearly arranged; the high-temperature incoming flow air pipeline and the helium pipeline are wound at the outer side of the liquid hydrogen pipeline in parallel, and the helium pipeline is located between the two pipelines; a telescopic arm with a telescopic length is mounted on the side wall of an airinlet; when the telescopic arm is lengthened, the air inlet is pushed out from the rocket belly to realize an air suction working mode; and when the length of the telescopic arm is shortened, the airinlet is stored in the rocket belly, and a pure rocket working mode is achieved. According to the cooperative air suction type liquid rocket engine propellant supply system, oxygen in the atmosphere can be utilized, the layout of internal pipelines of a traditional liquid rocket engine is optimized, the liquid rocket engine has the high specific impulse and the large thrust-weight ratio, and therefore the launching cost is reduced.

Description

technical field [0001] The invention relates to the field of aerospace power, in particular to a propellant supply system for a cooperative air-breathing liquid rocket engine. Background technique [0002] Among all kinds of aerospace power devices, liquid rocket engines are widely used because of their large specific impulse and easy control. The hydrogen-oxygen rocket engine is a liquid rocket engine that uses liquid oxygen as the oxidant and liquid hydrogen as the combustion agent. Liquid hydrogen and liquid oxygen are the only combination of liquid propellants with a specific impulse exceeding 400s. Due to their high specific impulse The advantages, can greatly reduce the rocket take-off weight, is widely used in launch vehicles. However, the hydrogen-oxygen rocket engine in my country started late, and compared with foreign countries, its thrust and specific impulse are relatively low. How to improve the performance of the hydrogen-oxygen rocket engine is the focus of ...

AI Technical Summary

Problems solved by technology

However, the hydrogen-oxygen rocket engine in my country started relatively late, and its thrust and specific impulse are relatively low compared with foreign countries. How to improve the performance of the hydrogen-oxygen rocket engine is the focus of research in the field of aerospace power in my country.

[0003] Traditional liquid rocket engines can be divided into pump type and squeeze type according to their propellant supply methods. However, there are some problems in the structure of these two methods: taking the pump type as an example, a large number of valves, pumps, etc. The use of the original parts needs to be driven by a power source, which creates a burden on the power supply subsystem of the rocket. The limited power supply capacity is not enough to drive the supply of propellant, and "small engines" such as gas generators and fuel start-up tanks are needed to realize the supply of propellant, resulting in The pump-pressed liquid rocket engine has a complex structure and is prone to failure

Although the squeeze-type liquid rocket engine has a simple structure, it needs to carry high-pressure gas cylinders and other components, resulting in a huge structural mass. It is generally suitable for propulsion systems with small thrust and low total impulse requirements, or for orbital attitude control engines for satellites.

These same propellant supply system problems exist for hydrogen-oxygen engines

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