| 600N单组元推力室的研制 |
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| 引用本文： | 刘俊,李小芳. 600N单组元推力室的研制[J]. 火箭推进, 2006, 32(5): 12-16 |
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| 作者姓名： | 刘俊 李小芳 |
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| 作者单位： | 上海航天动力机械研究所,上海,200233 |
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| 摘 要： | 600N单组元推力室使用DT-3推进剂,催化床床载率高达6g/cm2·s,头部采用两组环形分布的喷注扩散器并进行了模块化设计,身部采用了隔热装置,推力室具有结构紧凑、工艺简单、重量轻等特点。热试车结果表明,推力室起动迅速、平稳,性能可靠。
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| 关 键 词： | 液体火箭发动机 推力室参数测量 |
| 文章编号： | (2006)05-0012-05 |
| 收稿时间： | 2006-04-03 |
| 修稿时间： | 2006-06-19 |
Development of a 600N monopropellant thruster |
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| Liu Jun,Li Xiaofang. Development of a 600N monopropellant thruster[J]. Journal of Rocket Propulsion, 2006, 32(5): 12-16 |
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| Authors: | Liu Jun Li Xiaofang |
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| Abstract: | The development of a 600N monopropellant thruster is discussed. Higher catalyst bed loading, new modularized diffuser of injector, device of heat insulation in the chamber are described. The thruster is characterized by compact structure, simple technics and lightweight. Test results show that the thruster can start quickly and smoothly with high reliability. Its success is the base of developing higher thrust , higher bed loading thruster for spacecraft. |
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| Keywords: | liquid propellant rocket engine thruster parameter measurement |
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