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自由分子流微电热推力器(FMMR)流动模拟与喷嘴型面分析 被引量：1

Flow simulation and nozzle contour analysis on free molecule flow micro-resistojet
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摘要 FMMR是一种工作在自由分子流状态下的微电热推力器。考虑稀薄效应对FMMR喷嘴型面设计和分析的影响,采用直接蒙特卡罗(DSMC)方法模拟等截面、扩张型面、收缩-扩张型面3种不同喷嘴内的气体流动,分析了各种喷嘴型面对推力器性能的影响规律。结果表明,FMMR采用扩张喷嘴相对于等截面喷嘴,有较大的性能提升,推力最大可增加38%,比冲最大可增加23%;采用收缩-扩张喷嘴较扩张喷嘴能进一步使推力增加21%,但对比冲无明显改善。 The free molecule micro-resistojet（FMMR） is a kind of electric micro-thrustor working in free molecule flow state. In consideration of rarefaction effect on design and analysis of nozzle contour, three kinds of different nozzle contour gas flow were simulated by means of DSMC method, such as uniform cross-section flow, divergent contour flow and convergent-divergent contour flow. The effect law of various nozzle contours on thrustor performance was analyzed. The results show that compared with uniform crosssection, FMMR with divergent nozzle has more performance improvement. Thrust and specific impulse can be maximally increased by 38% and 23% respectively;the thrust of FMMR with convergent-divergent nozzle contour is increased by 21% than that with divergent nozzle contour, but specific impulse is hardly improved.
作者 陈茂林 毛根旺 杨涓 夏广庆
机构地区 西北工业大学航天学院
出处 《固体火箭技术》 EI CAS CSCD 北大核心 2008年第2期107-110,共4页 Journal of Solid Rocket Technology
基金 武器装备预研基金项目(9140C52030106HK03)
关键词 微推进 自由分子流推力器 直接蒙特卡罗法 数值模拟 micro-propulsion free molecule micro-resistojet DSMC method numerical simulation
分类号 V439.4 [航空宇航科学与技术—航空宇航推进理论与工程]
  • 相关文献

参考文献7

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二级参考文献12

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共引文献4

同被引文献80

  • 1周俐娜,王新兵.微空心阴极放电的流体模型模拟[J].物理学报,2004,53(10):3440-3446. 被引量：13
  • 2韩先伟,唐周强,陶文铨,张贵田,张恩昭.自由分子流微电热推力器工作特性和性能研究[J].固体火箭技术,2005,28(2):83-86. 被引量：4
  • 3Ahmed Z , Gimelshein S F, Ketsdever A. Numerical analysis of free- molecule micro-resistojet performance. Journal of Propulsion and Power,2006 ;22(4) :749 -756.
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  • 5Lee R H, Bauer A M, Killingsworth M D, et al. Performance charac- terization of the free molecule micro-resistojet utilizing water propel- lant. Collection of Technical Papers -- 43rd AIAA/ASME/SAE/AS- EE Joint Propulsion Conference, 2007:1748--1758.
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固体火箭技术
2008年 第2期

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