航天推进技术研究院主办
[1]刘伟,胡伟,周军,等.低冰点推进剂1N单组元发动机技术研究[J].火箭推进,2009,35(05):13-17.
Liu Weil,Hu Weil,Zhou Junl,et al.Research on 1 N mono-propellant rocket engine with low freezing point propellant[J].Journal of Rocket Propulsion,2009,35(05):13-17.
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Liu Weil,Hu Weil,Zhou Junl,et al.Research on 1 N mono-propellant rocket engine with low freezing point propellant[J].Journal of Rocket Propulsion,2009,35(05):13-17.
低冰点推进剂1N单组元发动机技术研究
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
35
期数:
2009年05期
页码:
13-17
栏目:
研究与设计
出版日期:
2009-10-30
- Title:
- Research on 1 N mono-propellant rocket engine with low freezing point propellant
- Keywords:
- low freezing point; thrust chamber; development
- 分类号:
- V434
- 文献标志码:
- A
- 摘要:
- 单组元发动机采用低冰点推进剂具有良好的低温冷起动和工作性能，对于实现 航天器的长期在轨驻留、轨道控制和姿态调整具有十分重要的意义。对一30cC低冰点四体系推 进剂的特性进行了分析，对低冰点推进剂小推力量级发动机催化分解技术进行了试验研究。 试验结果表明．发动机冷起动、关机正常，稳态、脉冲工作稳定，性能可靠。
- 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．
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[4]刘俊，李小芳．600N单组元推力室研制[J]．火箭推进，
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数值仿真[J]．推进技术，2003，(3)：10--12+90．
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备注/Memo
收稿日期：2009-07-24蚪；修回日期：2009-08-27。 作者简介：刘伟(198卜)，男，硕士。研究领域为液体火箭发动机结构设计及试验研究。
更新日期/Last Update:
1900-01-01