CEV Spacehab SM
Spacecraft · USA
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American manned spacecraft module. Study 2005. The Support Module (SM) could provide 2.3 km/s delta-V, enough for lunar orbit insertion and trans-earth injection. It also was the primary source for electrical power during the mission.
Thermal control would be provided by radiators on the exterior with 2.35 m2 of area.
RCS Coarse No x Thrust: 4 x 4 x 440 N. Spacecraft delta v: 2,300 m/s (7,500 ft/sec). Electric System: 2.00 average kW.
Related
- Family
- Manned spacecraft module
- Country
- USA
- Spacecraft
- CEV Spacehab
- Propellants
- Lox/Kerosene