| 推进剂通道结构对太阳热发动机影响数值研究 |
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| 引用本文： | 杨杰,杨立军.推进剂通道结构对太阳热发动机影响数值研究[J].航空动力学报,2010,25(5):1156-1162. |
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| 作者姓名： | 杨杰 杨立军 |
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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： | 运用数值模拟方法,通过改变推力室螺旋通道结构参数,对太阳热发动机(STP)能进行了详细的研究,深入分析了STP的推力,比冲、质量流量变化情况,得出了一般情况下螺旋通道的长度,宽度参数范围,同时比较了单、双通道的优缺点,所得的结论对STP推力室/热吸收室推进剂加热通道结构设计具有指导意义.
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| 关 键 词： | 太阳热发动机 推力室 对流换热 推力 比冲 |
| 收稿时间： | 4/6/2009 12:00:00 AM |
| 修稿时间： | 2009/10/24 0:00:00 |
Effects of propellant heat groove configuration on solar thermal propulsion performance |
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| YANG Jie and YANG Li-jun.Effects of propellant heat groove configuration on solar thermal propulsion performance[J].Journal of Aerospace Power,2010,25(5):1156-1162. |
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| Authors: | YANG Jie and YANG Li-jun |
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| Institution: | School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China;School of Astronautics, Beijing University of Aeronautics and Astronautics, Beijing 100191, China |
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| Abstract: | A detailed study of solar thermal propulsion (STP) performance was made using numerical simulation method by changing spiral groove parameter in this paper. The optimum design parameter was gotten according to analysis on STP's thrust,specific impulse and mass flow rate. Advantage and disadvantage of performances were also compared between single and double spiral groove STP. The conclusion provides a guidance to design of STP thrust chamber spiral groove. |
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| Keywords: | solar thermal propulsion(STP) thruster room convection heat transfer thrust specific impulse |
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