American manned spacecraft module. Study 1967. Calculated mass based on mission requirements, drawing of spacecraft, dimensions of propellant tanks.
RCS Coarse No x Thrust: 16 x 440 N. Spacecraft delta v: 1,000 m/s (3,200 ft/sec).
AKA: Service Module.
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Gross mass: 12,500 kg (27,500 lb).
Unfuelled mass: 2,500 kg (5,500 lb).
Height: 3.40 m (11.10 ft).
Diameter: 5.90 m (19.30 ft).
Thrust: 44.03 kN (9,898 lbf).
Specific impulse: 311 s.
Gemini LORV American manned lunar orbiter. Study 1967. This version of Gemini was studied as a means of rescuing an Apollo CSM crew stranded in lunar orbit. The Gemini would be launched unmanned on a translunar trajectory by a Saturn V. 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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