Electric drive propellant feeding system liquid-propellant rocket engine

A supply system and liquid rocket technology, applied in the field of aerospace science, can solve the problems of high development cost, long development cycle, complex structure, etc., and achieve the effects of short development cycle, low investment cost and simple system design

Inactive Publication Date: 2017-04-05
NORTHWESTERN POLYTECHNICAL UNIV
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

However, at present, all liquid rocket engines at home and abroad use a propellant supply system that uses turbine gas as the power to drive the pump to pressurize. This propellant supply system has a complex structure, high development costs, and a long development cycle.

Method used

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  • Electric drive propellant feeding system liquid-propellant rocket engine

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Embodiment Construction

[0013] The electric drive propellant supply system liquid rocket engine of the present invention, such as figure 1 As shown, it includes an oxidant delivery system A, a fuel delivery system B, and a thrust chamber 7, and the oxidant delivery system A and the fuel delivery system B are independently communicated with the thrust chamber 7, so as to deliver corresponding oxidant and fuel into the thrust chamber 7 , and mixed and burned in the thrust chamber 7, and sprayed out from the nozzle to generate reverse thrust. The above-mentioned oxidant delivery system A includes an oxidant cell 1 , an oxidant motor 2 and an oxidant pump 3 connected in sequence, and the oxidant pump 3 is used to connect with the oxidant storage tank and the thrust chamber 7 in pipelines.

[0014] The above-mentioned fuel delivery system B includes a fuel cell 5 , a fuel motor 6 and a fuel pump 4 connected in sequence, and the fuel pump 4 is used to connect the fuel storage tank and the thrust chamber 7 ...

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PUM

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Abstract

The invention discloses an electric drive propellant feeding system liquid-propellant rocket engine which comprises an oxidizing agent conveying system, a fuel conveying system and a thrust chamber. The oxidizing agent conveying system and the fuel conveying system are independently communicated with the thrust chamber, so that an oxidizing agent and fuel are correspondingly fed into the thrust chamber, are mixed in the thrust chamber and burn in the thrust chamber, and reaction thrust is generated. The oxidizing agent conveying system comprises an oxidizing agent battery, an oxidizing agent motor and an oxidizing agent pump which are sequentially connected, and the oxidizing agent pump is used for being connected with an oxidizing agent storage tank and a thrust chamber pipe. The electric drive propellant feeding system liquid-propellant rocket engine is simple in structure, high in reliability and miniaturized.

Description

technical field [0001] The invention belongs to the field of aerospace science and technology, and in particular relates to a liquid rocket engine for an electric drive propellant supply system. Background technique [0002] At present, the tools for humans to enter space are mainly disposable launch vehicles, which has led to high costs for humans to enter space. Reducing the cost of humans entering space is one of the goals pursued by scientific researchers. [0003] With the development of aerospace technology, liquid rocket engine technology is also improving, and its development trend is mainly low cost, fast response and high reliability. However, at present, all liquid rocket engines at home and abroad use a propellant supply system that uses turbine gas as power to drive a pump to pressurize. This propellant supply system has a complex structure, high development costs, and a long development cycle. Contents of the invention [0004] The technical problem to be so...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): F02K9/44F02K9/60F02K9/62
CPCF02K9/44F02K9/60F02K9/62
Inventor 刘洋付本帅何国强刘佩进胡春波裴净秋杨建刚李超
Owner NORTHWESTERN POLYTECHNICAL UNIV
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