Russian manned spacecraft module. Study 1968. Three identical stages of 34,491 kg each clustered around the core. Translunar Injection Stage.
Spacecraft delta v: 3,185 m/s (10,449 ft/sec).
AKA: Block 1.
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Gross mass: 103,474 kg (228,121 lb).
Thrust: 691.30 kN (155,410 lbf).
Specific impulse: 326 s.
LK-700 Russian manned lunar lander. Chelomei's direct-landing alternative to Korolev's L3 manned lunar landing design. Developed at a low level 1964 to 1974, reaching mockup and component test stage. 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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