|Table of Contents|

Lander descent engine and assumption of Chinese LMDE(PDF)

《火箭推进》[ISSN:1672-9374/CN:CN 61-1436/V]

Issue:
2010年05期
Page:
1-6
Research Field:
研究与设计
Publishing date:

Info

Title:
Lander descent engine and assumption of Chinese LMDE
Author(s):
LEI Juan-ping;  MA Jie;  LIU Chang-bo
Xi’an Aerospace Propulsion Institute, Xi’an 710100, China
Keywords:
landing explorer;  descent engine;  variable thrust engine
PACS:
V438-34
DOI:
-
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.

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,

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