 | Mars Direct
Credit - NASA
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Class: Manned. Type: Mars Expedition. Destination: Mars. Nation: USA. Agency: NASA. Mars Semi-Direct was a NASA concept bridge between Zubrin's Mars Direct and NASA's Design Reference Mission 1.0. It was essentially a low-cost version of Boeing's STCAEM.
Mars Semi-Direct Mission Summary:
- Summary: Concept bridge between Mars Direct and Design Reference Mission 1.0; low cost STCAEM
- Propulsion: Nuclear thermal
- Braking at Mars: aerodynamic
- Mission Type: conjunction
- Split or All-Up: split
- ISRU: ISRU
- Launch Year: 1997
- Crew: 4
- Mars Surface payload-metric tons: 40
- Outbound time-days: 180
- Mars Stay Time-days: 550
- Return Time-days: 170
- Total Mission Time-days: 900
- Total Payload Required in Low Earth Orbit-metric tons: 220
- Total Propellant Required-metric tons: 170
- Propellant Fraction: 0.77
- Mass per crew-metric tons: 55
- Launch Vehicle Payload to LEO-metric tons: 105
- Number of Launches Required to Assemble Payload in Low Earth Orbit: 2
- Launch Vehicle: Ares Mars Direct
Bibliography:- Griffin, Brand; Thomas, Brent; Vaughan, Diane, A Comparison of Transportation Systems for Human Missions to Mars, AIAA 2004-3834, 40th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit ,11-14 July 2004.
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© Mark Wade, 1997 - 2008 except where otherwise noted.
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