American manned spacecraft module. Study 1966. Calculated mass based on mission requirements, drawing of spacecraft, dimensions of propellant tanks.
Spacecraft delta v: 2,400 m/s (7,800 ft/sec).
AKA: Landing Module.
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Gross mass: 20,000 kg (44,000 lb).
Unfuelled mass: 3,300 kg (7,200 lb).
Height: 1.80 m (5.90 ft).
Diameter: 4.21 m (13.81 ft).
Thrust: 88.06 kN (19,797 lbf).
Specific impulse: 311 s.
Gemini Lunar Surface Rescue Spacecraft American manned lunar lander. Study 1966. This version of Gemini would allow a direct manned lunar landing mission to be undertaken in a single Saturn V flight, although it was only proposed as an Apollo rescue vehicle. 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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