Propellant supplying system, rocket engine and rocket

Abstract

The invention provides a propellant supplying system, a rocket engine and a rocket and relates to the technical field of gas propelling devices. The propellant supplying system comprises a fuel supplying system, an oxidizing agent supplying system and a control device. A pipeline of the fuel supplying system is provided with a first flow adjusting valve, and / or a pipeline of the oxidizing agent supplying system is provided with a second flow adjusting valve. The first flow adjusting valve and the second flow adjusting valve are connected with the control device. By means of the propellant supplying system, when a large flow adjusting ratio is achieved, the control device can control the flow of fuel through the first flow adjusting valve and control the flow of oxidizing agents through thesecond flow adjusting valve, the number of pipelines is greatly reduced, the overall structure can be reduced, and the overall weight is reduced; and in addition, due to the fact that the number of pipelines is reduced, the flowing path of fuel or oxidizing agents is shortened, and therefore the pressure losses of fuel and oxidizing agents in the flowing process are reduced.

Description

technical field [0001] The invention relates to the technical field of gas propulsion devices, in particular to a propellant supply system, a rocket engine and a rocket. Background technique [0002] In recent years, the development of the aerospace field has put forward higher requirements for traditional variable thrust rocket engines. In manned moon landing, Mars exploration or deep space exploration missions, the rocket engine needs to work in ejection mode, sub-combustion / super-combustion mode and pure rocket mode. The thrust of the rocket engine under different working conditions Therefore, the rocket engine needs to have a large range of thrust variation, and the thrust adjustment of the rocket engine is realized by the flow adjustment of the propellant. [0003] The flow adjustment of the propellant supply system in the prior art is mainly realized through injector adjustment and pipeline adjustment, among which, the pipeline adjustment is mainly realized by the par...

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Problems solved by technology

[0003] The flow adjustment of the propellant supply system in the prior art is mainly realized through injector adjustment and pipeline adjustment, among which, the pipeline adjustment is mainly realized by the parallel connection of multiple sets of pipelines. In the case of small flow changes, the adjustment Good condition, but for large flow ratios (e.g. greater than 10:1), the propellant supply system has a large number of lines and a bulky structure

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