航天推进技术研究院主办
[1]雷娟萍,马杰,刘昌波.星球着陆下降发动机及我国登月下降发动机设想[J].火箭推进,2010,36(05):1-6.
LEI Juan-ping,MA Jie,LIU Chang-bo.Lander descent engine and assumption of Chinese LMDE[J].Journal of Rocket Propulsion,2010,36(05):1-6.
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LEI Juan-ping,MA Jie,LIU Chang-bo.Lander descent engine and assumption of Chinese LMDE[J].Journal of Rocket Propulsion,2010,36(05):1-6.
星球着陆下降发动机及我国登月下降发动机设想
《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]
卷:
36
期数:
2010年05期
页码:
1-6
栏目:
研究与设计
出版日期:
2010-10-15
- Title:
- Lander descent engine and assumption of Chinese LMDE
- 文章编号:
- (2010)05-0001-06
- Keywords:
- landing explorer; descent engine; variable thrust engine
- 分类号:
- V438-34
- 文献标志码:
- A
- 摘要:
- 星球着陆下降发动机探测器在外星上进行软着陆时起着关键的作用，目前我国还没有进行软着陆的成熟的发动机，对比较典型的月球和火星着陆下降发动机的特点和种类进行总结，提出了我国着陆下降发动机的方案设想，为我国着陆下降发动机的研制提供技术支持。
- Abstract:
- The lander descent propulsion system plays an important role in soft landing of planet explorer. There is no mature soft-landing engine in China nowadays. The typital Lunar excursion descent engine system and Mars explorer descent engine are introduced. The trend of development in this field is pointed out and the assumption of Chinese LMDE is proposed in this paper. It will provide a technical support for Chinese descent propulsion system.
参考文献/References:
[1] DAWSON Matt, BREWSTER Gerry, CONRAD Chris, et al. Monopropellant hydrazine 700 lbf throttling terminal descent engine for mars science laboratory, AIAA 2007-5481[R]. USA:NASA, 2007. [2]ELVERUM G, STAUDHAMMER P, MILLER J, et al. The descent engine for the lunar module, AIAA 1996-521[R]. USA:NASA, 1996. [3]DRESSLER G A. Summary of deep throtting rocket engines with emphasis on apollo LMDE, AIAA 2006-5220[R]. USA:NASA, 2006. [4]MCALLISTER J Greg, CAREY Parish. Phoenix landing propulsion system performance, AIAA 2009-5264[R]. USA:NASA, 2009. [5]MORRISEY D C. Historical perspective: Viking mars lander propulsion[J]. Journal of Propulsion and Power, 1992, 8(2): 320-331. [6]GILROY R, SACKHEIM R. The lunar module descent engine-a historical perspective, AIAA 1998-2385 [R]. USA:NASA, 1998. [7]HARDGROVE J, KRIEG W. High performance throttling and pulsing rocket engine, AIAA 1984-1254[R]. USA:NASA, 1984. [8]GAVITT K, MUELLER T. TRW LCPE 650 Klbf LOX/LH2 test results, AIAA 2000-3853 [R]. USA:NASA, 2000. [9]BOTWIN R. Flight performance of the LM ascent and descent propulsion systems, AIAA 2007-5481[R]. USA: NASA, 2007. [10]NORRIS, VERNON D W. Apollo propulsion system perfor-mance evaluation, AIAA 1970-0673[R]. USA: NASA, 1970. [11]周战锋, 胡春波, 李江, 等. 变推力固体火箭发动机喉栓烧蚀试验研究[J]. 固体火箭技术, 2009, 32(1): 163－166. [12]张小平, 丁丰年, 马杰. 我国载人登月重型运载火箭动力系统探讨[J]. 火箭推进, 2009, 35(2): 11－16. [13]龙乐豪. 我国载人登月技术途径探讨[J]. 前沿科学,
相似文献/References:
[1]刘昌波,兰晓辉,李福云.载人登月舱下降发动机技术研究[J].火箭推进,2011,37(02):8.
LIU Chang-bo,LAN Xiao-hui,LI Fu-yun.Conceptual schemes of China lunar excursion module descent engine[J].Journal of Rocket Propulsion,2011,37(05):8.
备注/Memo
收稿日期：2010-０3-１３；修回日期：2010-05-16
基金项目：中国航天科技集团公司支撑项目
作者简介： 雷娟萍（1980—），女，工程师，研究领域为液体火箭发动机系统
更新日期/Last Update:
1900-01-01