Propellant supply system, rocket motor and rocket

Abstract

The invention provides a propellant supply system, a rocket engine and a rocket, and relates to the technical field of gas propulsion devices. Wherein, the propellant supply system includes a fuel supply system, an oxidizer supply system and a control device, the pipeline of the fuel supply system is provided with a first flow regulating valve, and / or, the pipeline of the oxidant supply system is provided with a second flow regulating valve; Both the first flow regulating valve and the second flow regulating valve are connected with the control device. When the propellant supply system achieves a large flow adjustment ratio, the control device adjusts the flow of the fuel through the first flow regulating valve, and adjusts the flow of the oxidant through the second flow regulating valve, which greatly reduces the number of pipelines, thereby reducing the overall structure to reduce overall weight. In addition, due to the reduction in the number of pipelines, the flow path of the fuel or oxidant is shortened, and the pressure loss of the fuel or oxidant during the flow process is 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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