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Design Reference Mission 4 NTR
Part of American Mars Expeditions Family
STCAEM NTR
Credit: � Mark Wade |
American manned Mars expedition. Study 1998. The design reference mission 4.0 took into account all of the changes in payload masses as a result of further study of individual elements.
Status: Study 1998.
Overall mass required in low earth orbit was reduced only slightly, by 2.5%. The use of NTR bimodal propulsion, with a single nuclear reactor that provided both propulsion and electrical power during space operations, in lieu of a separate power source, was made baseline. Cryo/aerobrake and solar electric options were retained.
Design Reference Mission Bimodal Mission Summary:
- Summary: Refine DRM 3.0; NTR Bimodal "all-propulsive" option; source data from Borowski NTR
- Propulsion: Nuclear thermal
- Braking at Mars: aerodynamic
- Mission Type: conjunction
- Split or All-Up: split
- ISRU: ISRU
- Launch Year: 2011
- Crew: 6
- Mars Surface payload-metric tons: 33
- Outbound time-days: 180
- Mars Stay Time-days: 570
- Return Time-days: 150
- Total Mission Time-days: 900
- Total Payload Required in Low Earth Orbit-metric tons: 400
- Total Propellant Required-metric tons: 180
- Propellant Fraction: 0.45
- Mass per crew-metric tons: 66
- Launch Vehicle Payload to LEO-metric tons: 75
- Number of Launches Required to Assemble Payload in Low Earth Orbit: 6
- Launch Vehicle: Magnum
Family: Mars Expeditions.
Country: USA.
Agency: NASA.
Bibliography: 1989.
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