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Thermodynamic cycle analysis of Mars CO 2 thermal rocket

  • Yu Daren*
  • , Lv Xiaowu
  • , Yao Zhanli
  • , Bao Wen
  • *Corresponding author for this work

Research output: Chapter in Book/Report/Conference proceedingConference contributionpeer-review

Abstract

In-situ resource utilization (ISRU) is recognized as an enabling technology for exploration of Mars. The collection methods of CO 2 on Mars are analyzed, and an implementation scheme of propulsion utilizes Mars CO 2 in raw form, CO 2 thermal rocket, is proposed. It can be used for attitude control and main propulsion during landing or takeoff, and it may be the potential propulsion for Mars airship, a promising Mars aerial platform capable of flight within the Martian environment. This paper illustrates influencing factors and potential application approaches of the new propulsion, and the cycle characteristic of the new propulsion is analyzed, the results show that the thrust specific power consumption (TSPO) is about the order of magnitude of 1N/kW, and variation of performance is mainly concerned with the high side pressure, electric heat temperature etc, and the new propulsion exist an optimum temperature.

Original languageEnglish
Title of host publication2009 Asia-Pacific Power and Energy Engineering Conference, APPEEC 2009 - Proceedings
DOIs
StatePublished - 2009
Externally publishedYes
Event2009 Asia-Pacific Power and Energy Engineering Conference, APPEEC 2009 - Wuhan, China
Duration: 27 Mar 200931 Mar 2009

Publication series

NameAsia-Pacific Power and Energy Engineering Conference, APPEEC
ISSN (Print)2157-4839
ISSN (Electronic)2157-4847

Conference

Conference2009 Asia-Pacific Power and Energy Engineering Conference, APPEEC 2009
Country/TerritoryChina
CityWuhan
Period27/03/0931/03/09

Keywords

  • CO thermal rocket
  • Freezing
  • ISUR
  • Thermodynamic analysis

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