| 低冰点推进剂1N单组元发动机技术研究 |
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| 引用本文： | 刘伟,胡伟,周军,刘江强,方涛.低冰点推进剂1N单组元发动机技术研究[J].火箭推进,2009,35(5):13-17. |
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| 作者姓名： | 刘伟 胡伟 周军 刘江强 方涛 |
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| 作者单位： | 1. 西安航天动力研究所,陕西,西安,710100
2. 北京航天试验技术研究所,北京,100074 |
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| 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-30℃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。
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| 关 键 词： | 低冰点 推力室 研制 |
Research on 1N mono-propellant rocket engine with low freezing point propellant |
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| Liu Wei,Hu Wei,Zhou Jun,Liu Jiangqiang,Fang Tao.Research on 1N mono-propellant rocket engine with low freezing point propellant[J].Journal of Rocket Propulsion,2009,35(5):13-17. |
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| Authors: | Liu Wei Hu Wei Zhou Jun Liu Jiangqiang Fang Tao |
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| Institution: | 1 Xi＇an Aerospace Propulsion Institute, Xi＇an 710100, China; 2 Beijing Institute of Aerospace Testing Technology, Beijing, 100074, China) |
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| Abstract: | The development of a 1N 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 methods, 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 lowtemperature. Test results show that the thruster can start quickly and smoothly with high reliability. |
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| Keywords: | low freezing point thrust chamber development |
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