American manned spacecraft module. 22 launches, 1964.05.28 (Saturn 6) to 1975.07.15 (Apollo (ASTP)).
Structure: 1,910 kg (4,210 lb). Electrical Equipment: 1,200 kg (2,600 lb). RCS Coarse No x Thrust: 16 x 440 N. RCS specific imulse: 290 sec. RCS total impulse: 3,517 kgf-sec. Spacecraft delta v: 2,804 m/s (9,199 ft/sec). Electric System: 670.00 kWh. Electric System: 6.30 average kW.
AKA: Service Module.
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Gross mass: 24,523 kg (54,063 lb).
Unfuelled mass: 6,110 kg (13,470 lb).
Height: 7.56 m (24.80 ft).
Diameter: 3.90 m (12.70 ft).
Thrust: 97.86 kN (22,000 lbf).
Specific impulse: 314 s.
Apollo CSM American manned lunar orbiter. 22 launches, 1964.05.28 (Saturn 6) to 1975.07.15 (Apollo (ASTP)). The Apollo Command Service Module was the spacecraft developed by NASA in the 1960's as a standard spacecraft for earth and lunar orbit missions. More...
N2O4/UDMH Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Unsymmetrical Dimethylhydrazine ((CH3)2NNH2) became the storable liquid fuel of choice by the mid-1950's. Development of UDMH in the Soviet Union began in 1949. It is used in virtually all storable liquid rocket engines except for some orbital manoeuvring engines in the United States, where MMH has been preferred due to a slightly higher density and performance. More...
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