Russian manned spacecraft module. Study 1968. Main engine of 13,400 kgf and three engines for soft landing / midcourse maneuvers of 1,670 kgf each. Trans-earth injection / midcourse manoeuvre stage.
Spacecraft delta v: 2,804 m/s (9,199 ft/sec).
AKA: Block 1V.
More... - Chronology...
Gross mass: 11,670 kg (25,720 lb).
Unfuelled mass: 2,675 kg (5,897 lb).
Thrust: 180.54 kN (40,587 lbf).
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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