Difference between revisions of "Mars design reference mission"
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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 no.5, with the latest addendum in 2014<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 no.5, with the latest addendum in 2014<ref>https://en.wikipedia.org/wiki/Mars_Design_Reference_Mission</ref>. |
===History=== | ===History=== | ||
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*7 to 11 launches, 110 to 140 tonnes at LEO per launch. 10m x 30m shrouds. | *7 to 11 launches, 110 to 140 tonnes at LEO per launch. 10m x 30m shrouds. | ||
*In-situ fuel production for vehicle return. | *In-situ fuel production for vehicle return. | ||
| − | *Nuclear | + | *Nuclear surface power for energy production. |
*Multiple launches, multiple mission phases. | *Multiple launches, multiple mission phases. | ||
| − | *40 tonnes cargo to surface. | + | *40 tonnes cargo to surface. Inflatable aeroshell, one 114 tonnes vehicle or 2x 89 tonnes vehicles |
*Long term cryogenic storage required. | *Long term cryogenic storage required. | ||
| + | *High speed Earth entry. | ||
===References=== | ===References=== | ||
<references /> | <references /> | ||
Latest revision as of 14:35, 10 November 2020
The Mars design reference mission is a series of missions plans that have been regularly updated by NASA. The current version is no.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, version 5
- Crew of six. Long stay mission. 180 days transit times.
- Pre deploy cargo. First phase of the mission in 2030.
- 7 to 11 launches, 110 to 140 tonnes at LEO per launch. 10m x 30m shrouds.
- In-situ fuel production for vehicle return.
- Nuclear surface power for energy production.
- Multiple launches, multiple mission phases.
- 40 tonnes cargo to surface. Inflatable aeroshell, one 114 tonnes vehicle or 2x 89 tonnes vehicles
- Long term cryogenic storage required.
- High speed Earth entry.
