Injector used for double-component attitude control thruster

An injector and thruster technology, which is applied in the field of injector and spacecraft attitude control two-component thruster to achieve the effects of reducing structural temperature, avoiding overheating, and improving work safety and reliability

Active Publication Date: 2014-03-26
BEIJING INST OF CONTROL ENG
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  • Summary
  • Abstract
  • Description
  • Claims
  • Application Information

AI Technical Summary

Problems solved by technology

Compared with similar foreign products, the vacuum specific impulse exceeds the level of 285s, and there is a big gap

Method used

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  • Injector used for double-component attitude control thruster
  • Injector used for double-component attitude control thruster
  • Injector used for double-component attitude control thruster

Examples

Experimental program
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Effect test

Embodiment

[0041] An injector for a two-component attitude control thruster, such as figure 1 As shown, the injector includes a nozzle 1, a long plug 2, a connection plate 3, a connection pipe 4, an outer nozzle 5, an inner nozzle 6, a middle connection pipe 7, an injection body 8 and a connection post 9; the connection post 9 is three ; Long plug 2 is two;

[0042] Such as figure 2 As shown, the mouthpiece 1 is a stepped revolving body. There is a conical cavity 11 upstream of the revolving body. There is a through hole 12 in the center of the revolving body. The downstream of the revolving body is perpendicular to the through hole 12 and passes through the axis of the revolving body. Semi-cylindrical through hole 13; There is a triangular ring groove 14 on the outer surface of the rotating body, and the diameter of the rotating body at the triangular ring groove 14 is relatively small;

[0043] Such as image 3 As shown, the long plug 2 is a step-shaped rotary body, and the end fac...

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Abstract

The invention relates to an injector used for a double-component attitude control thruster and belongs to the technical field of spacecraft propulsion. The injector is used for the double-component attitude control thruster used for a spacecraft, wherein the thruster is high in performance and long in service life, and the injector is especially suitable for being used for the spacecraft attitude control double-component thruster. A connection mouth, a connection plate, an intermediate connection pipe and an inner nozzle in the injector form a combustion gas path propellant channel, and flow control and atomization on combustion gas path propellant are achieved through control over the structure of spiral channels; the connection mouth, the connection plate, the connection pipe, the inner nozzle and an outer nozzle form an oxygen path propellant channel, and flow control and atomization on oxygen path propellant are achieved through control over the structure of spiral channels.

Description

technical field [0001] The invention relates to an injector for a dual-component attitude control thruster, an injector for a high-performance and long-life dual-component thruster for a spacecraft, which belongs to the technical field of spacecraft propulsion, and is especially suitable for aerospace Attitude control of bicomponent thrusters. Background technique [0002] The dual-component thruster is the main reaction force actuator for spacecraft attitude control. It generates thrust by ejecting high-temperature and high-speed gas to perform spacecraft attitude control and orbit transfer. Among them, the injector is an important propellant organization and atomization device, which directly affects performance and life. [0003] For a long time, the performance of my country's long-life dual-component attitude control thrusters has been low, and the vacuum specific impulse is only about 275s, which has seriously restricted the improvement of the performance of my countr...

Claims

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Application Information

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Patent Type & Authority Applications(China)
IPC IPC(8): B64G1/26
Inventor 毛晓芳汪凤山张杰王平蔡坤陈磊孙民姚兆普李骥琦杨尚峰张凤何孟琪
Owner BEIJING INST OF CONTROL ENG
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