American manned spacecraft module. Study 1967. Calculated mass based on mission requirements, drawing of spacecraft, dimensions of propellant tanks.
Spacecraft delta v: 3,400 m/s (11,100 ft/sec).
AKA: Landing Module.
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Gross mass: 36,000 kg (79,000 lb).
Unfuelled mass: 6,000 kg (13,200 lb).
Height: 3.60 m (11.80 ft).
Diameter: 4.21 m (13.81 ft).
Thrust: 88.06 kN (19,797 lbf).
Specific impulse: 311 s.
Gemini Lunar Surface Survival Shelter American manned lunar habitat. Study 1967. Prior to an Apollo moon landing attempt, the shelter would be landed, unmanned, near the landing site of a stranded Apollo Lunar Module. 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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