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A liquid rocket engine combined compact acoustic cavity structure

A liquid rocket and engine technology, applied in rocket engine devices, machines/engines, mechanical equipment, etc., can solve the problems of destroying the working stability of the engine, burning the engine, etc., to improve the ability to resist unstable combustion, and to have strong technical scalability Effect

Active Publication Date: 2022-04-01
SHANGHAI INST OF SPACE PROPULSION
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Unstable combustion will destroy the working stability of the engine, especially high-frequency unstable combustion will cause the engine to burn out instantly

Method used

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  • A liquid rocket engine combined compact acoustic cavity structure
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Embodiment Construction

[0013] The present invention will be described in further detail below in conjunction with the accompanying drawings and specific embodiments.

[0014] figure 2 It is the structural diagram of the acoustic cavity of the present invention. The example of the present invention is a double component 250N thrust chamber, which is made up of a head 1 and a body 2 .

[0015] What this example embodiment adopts is dinitrogen tetroxide as oxidant, and monomethylhydrazine is as fuel. The two propellant components organize the distribution of the propellant through the nozzle, atomization, mixing, vaporization and combustion in the combustion chamber. The acoustic cavity structure is also suitable for engines such as MON-1 / MON-3 as oxidizers and hydrazine, unsymmetrical dimethylhydrazine, etc. as fuels.

[0016] The thrust chamber of the embodiment of the present invention is made of refractory metal material, the head material is TC4 titanium alloy, the body material is niobium-tun...

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Abstract

The invention relates to a technology for suppressing unstable combustion of small and medium-thrust attitude-orbit control engines used in spacecraft propulsion systems. Insufficient ratio, reducing the combustion recirculation area caused by the structure of the acoustic cavity, and improving the engine's ability to resist unstable combustion. The invention provides a combined compact acoustic cavity structure of a liquid rocket engine. The acoustic cavity structure is composed of two parts: a straight hole on the head and a chute on the body. The acoustic cavity structure is located at the joint of the head and the body; The specific structural form of the acoustic cavity structure is determined through calculations and tests for different engines, so as to ensure that the engine's ability to resist unstable combustion can be effectively improved. The acoustic cavity structure is suitable for metal material engines, and can also be used for C / SiC composite material or C / C composite material engines.

Description

technical field [0001] The invention relates to a technology for suppressing unstable combustion of a small-and-medium-thrust attitude-orbit control engine used in a spacecraft propulsion system, in particular to a combined compact acoustic cavity structure of a liquid rocket engine. Background technique [0002] The engine is the heart of spacecraft such as launch vehicles and satellites, and the thrust chamber is the core component of the rocket engine. In order to improve engine performance, it is necessary to increase the combustion efficiency in the thrust chamber, but high combustion efficiency is usually accompanied by unstable combustion. Unstable combustion will destroy the working stability of the engine, especially high-frequency unstable combustion will cause the engine to burn out instantly. [0003] Space attitude and orbit control liquid rocket engines usually use acoustic chambers to suppress the occurrence of unstable combustion. The acoustic cavity is usu...

Claims

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Application Information

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Patent Type & Authority Patents(China)
IPC IPC(8): F02K9/62
CPCF02K9/62
Inventor 刘昌国陈泓宇赵婷唐梅叶超
Owner SHANGHAI INST OF SPACE PROPULSION