Mars design reference mission: Difference between revisions
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The Mars design reference mission is a series of missions plans that have been regularly updated by NASA. The current version is version 5<ref>https://en.wikipedia.org/wiki/Mars_Design_Reference_Mission</ref>. | The Mars design reference mission is a series of missions plans that have been regularly updated by NASA. The current version is version 5, with the latest addendum in 2014<ref>https://en.wikipedia.org/wiki/Mars_Design_Reference_Mission</ref>. | ||
History | === History === | ||
* Version 1 1993. Based on Mars direct. 900 tonnes mission. Crew of six. | *Version 1 1993. Based on Mars direct. 900 tonnes mission. Crew of six. | ||
* Version 2 1997. | *Version 2 1997. | ||
* Version 3 1998. Reduced system mass, smaller launchers. 450 tonnes mission. | *Version 3 1998. Reduced system mass, smaller launchers. 450 tonnes mission. | ||
* Version 4 1998. Explored Nuclear thermal and electric propulsion variants | *Version 4 1998. Explored Nuclear thermal and electric propulsion variants | ||
* Version 5 2009<ref>https://www.nasa.gov/pdf/373665main_NASA-SP-2009-566.pdf</ref>. Addendum 2, 2014<ref>https://www.nasa.gov/sites/default/files/files/NASA-SP-2009-566-ADD2.pdf</ref>. Ares V. | *Version 5 2009<ref>https://www.nasa.gov/pdf/373665main_NASA-SP-2009-566.pdf</ref>. Addendum 2, 2014<ref>https://www.nasa.gov/sites/default/files/files/NASA-SP-2009-566-ADD2.pdf</ref>. Ares V. | ||
=== Basic parameters === | |||
* Crew of six | |||
* In-situ fuel production for vehicle return. | |||
* Nuclear reactors for energy production. | |||
* Multiple launches, multiple mission phases. | |||
===References=== | ===References=== | ||
<references /> | <references /> | ||
Revision as of 13:12, 11 June 2019
The Mars design reference mission is a series of missions plans that have been regularly updated by NASA. The current version is version 5, with the latest addendum in 2014[1].
History
- Version 1 1993. Based on Mars direct. 900 tonnes mission. Crew of six.
- Version 2 1997.
- Version 3 1998. Reduced system mass, smaller launchers. 450 tonnes mission.
- Version 4 1998. Explored Nuclear thermal and electric propulsion variants
- Version 5 2009[2]. Addendum 2, 2014[3]. Ares V.
Basic parameters
- Crew of six
- In-situ fuel production for vehicle return.
- Nuclear reactors for energy production.
- Multiple launches, multiple mission phases.