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Research on 1 N mono-propellant rocket engine with low freezing point propellant(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2009年05期
Page:
13-17
Research Field:
研究与设计
Publishing date:

Info

Title:
Research on 1 N mono-propellant rocket engine with low freezing point propellant
Author(s):
Liu Weil; Hu Weil; Zhou Junl; Liu Jiangqian92; Fang Ta02
1 Xi"an Aerospace Propulsion Institute，Xi"an 710100，China； 2 Beijing Institute of Aerospace Testing Technology，Beijing，1 00074，China
Keywords:
low freezing point; thrust chamber; development
PACS:
V434
DOI:
-
Abstract:
The development of a 1 N monopropellant thruster with low freezing point propellant is discussed．The research of catalytic decomposition in mono—propellant rocket engine，including the principle of catalytic decomposition，the analysis of propellant selection，the design of thrust chamber。main problems and resolving metIlods，was introduced．Characteritics of a four—system— propellant with low freezing point were analyzed．The propellant could be catalyzed and decomposed rapidly．The newly designed thrust chamber achieved its stable operation in circumstances of low— temperature．Test results show that the thruster Can start quickly and smoothly with high reliability．

References:

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[4]刘俊，李小芳．600N单组元推力室研制[J]．火箭推进， 2006，32(5)：7—11．
[5]沈军，刘伟强，汤建华．单组元发动机推力室在轨温度 数值仿真[J]．推进技术，2003，(3)：10--12+90．
[6]聂万胜，陈新华，戴德海，等．姿控推进系统发动机关机 的管路瞬变特性田．推进技术，2003，(1)：7-9．

Memo

Memo:
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Last Update: 1900-01-01