CEV Spacehab SM

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CEV Spacehab SM

Part of Orion CEV

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.

Status: Study 2005. Thrust: 44.10 kN (9,914 lbf). Gross mass: 11,500 kg (25,300 lb). Unfuelled mass: 1,500 kg (3,300 lb). Specific impulse: 350 s. Height: 3.40 m (11.10 ft). Diameter: 5.00 m (16.40 ft).

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.

Family: Manned spacecraft module. Country: USA. Spacecraft: CEV Spacehab. Propellants: Lox/Kerosene.

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