| N2O单组元微推力器高空模拟实验研究 |
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| 引用本文： | 李茂,韩乐,方杰,孙威,蔡国飙.N2O单组元微推力器高空模拟实验研究[J].推进技术,2011,32(3):307-311. |
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| 作者姓名： | 李茂 韩乐 方杰 孙威 蔡国飙 |
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| 作者单位： | 北京航空航天大学宇航学院,北京,100191 |
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| 摘 要： | 在真空舱中进行了N2O单组元两种尺寸的微推力器的高空模拟试验研究,分析了微推力器设计参数对比冲等性能的影响。结果表明,两种尺寸微推力器的最大比冲分别为1.608 N.s/g和1.639 N.s/g,热损失、床载和床长对微推力器性能影响明显,存在最佳床载值、床载和床长的匹配。
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| 关 键 词： | 微推力器 N2O单组元推进剂 高空模拟试验 比冲性能 分解温度 |
| 收稿时间： | 2010/5/26 0:00:00 |
| 修稿时间： | 2010/11/10 0:00:00 |
Simulated altitude experimental investigation for N2Omonopropellant micro-thruster |
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| LI Mao,HAN Yue,FANG Jie,SUN Wei and CAI Guo-biao.Simulated altitude experimental investigation for N2Omonopropellant micro-thruster[J].Journal of Propulsion Technology,2011,32(3):307-311. |
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| Authors: | LI Mao HAN Yue FANG Jie SUN Wei and CAI Guo-biao |
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| Institution: | LI Mao,HAN Yue,FANG Jie,SUN Wei,CAI Guo-biao(School of Astronautics,Beijing Univ.of Aeronautics and Astronautics,Beijing 100191,China) |
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| Abstract: | Simulated altitude experiments for two different size monopropellant micro-thrusters were conducted in a vacuum chamber with a micro thrust measurement facility.The maximal specific impulses,measured in the experiment,were 1.608 N · s/g and 1.639 N · s/g for the different size micro-thrusters,respectively.The analysis of the influence of the key design parameters on the micro-thruster performance was also carried out.Results show that the performance is influenced remarkably by the heat loss,the catalyze bed load,as well as the catalyze bed length.There exist an optimum catalyze bed load and an optimum matching of the catalyze bed load to the catalyze bed length. |
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| Keywords: | Micro-thruster Nitrogen oxide monopropellant Simulated altitude test Specific impulse performance Decomposition temperature |
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