|Table of Contents|

Preliminary design of propulsion system for Mars exploration(PDF)

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

Issue:
2014年02期
Page:
44-48
Research Field:
研究与设计
Publishing date:

Info

Title:
Preliminary design of propulsion system for Mars exploration
Author(s):
LIU Chuan;  LIU Jun;  QIU Xin;  LIN Qing-guo
Shanghai Institute of Space Propulsion, Shanghai 201112, China
Keywords:
Mars exploration;  propulsion system;  preliminary design;  key technology
PACS:
V434-34
DOI:
-
Abstract:
Mars Exploration is an important content of deep space exploration. It is significant to understand and master the characteristics of Mars lander for Mars exploration. The system composi- tion and working principle of the propulsion systems of foreign Mars landers are analyzed in this paper. The preliminary design scheme of Mars lander propulsion system in China is introduced. According to the engineering status, the key technologies associated with Mars lander propulsion system are presented.

References:

[1]王海涛, 付丽璋, 蒋万松. 凤凰号火星探测器着陆过程[J]. 航天返回与遥感, 2009, 30(3): 8-15.
[2]褚英志, 李秀伟, 周晓东. 火星探测关键技术分析[J]. 测试技术学报, 2007, 21（增刊）: 63-66.
[3]MORRISEY D C. Historical perspective-Viking Mars lan- der propulsion, AIAA-1989-2391[R]. USA: AIAA, 1989.
[4]BARBE T J, PICHA F Q. In-flight propulsion system cha- racterization for both Mars exploration rover spacecraft, AIAA-2004-3695[R]. USA: AIAA, 2004.
[5]D'AMARIO L A. Mars exploration rovers navigation re- sults, AIAA-2004-4980[R]. USA: AIAA, 2004.
[6]PLEMMONS D, WILCHER K. Spectroscopic plume ana- lysis of the Phoenix Mars Lander hydrazine mono- propellant thrusters, AIAA-2007-5706[R]. USA: AIAA, 2007.
[7]DESAI P N. Entry, descent, and landing performance of the Mars Phoenix Lander, AIAA-2008-7346[R]. USA: AIAA, 2008.
[8]DAWSON Matt. Monopropellant hydrazine 700 lbf thrott- ling terminal descent engine for Mars science laboratory, AIAA-2007-5481 [R]. USA: AIAA, 2007.
[9]PARIS A D, NOVAK K S, KELLY F P, et al. Overview of the Mars science laboratory cruise phase system thermal vacuum test, AIAA-2010-6189[R]. USA: AIAA, 2010.
[10]MCRIGHT P, POPP C, PIERCE C, et al. Confidence testing of shell-405 and S-405 catalysts in a mono- propellant hydrazine thruster, AIAA-2005-3952[R]. USA: AIAA, 2005.

Memo

Memo:
-
Last Update: 1900-01-01