Russian manned spacecraft module. Study 1968. Differed from the lateral Block 1 stages in having an engine unit for orientation of the assembly. Main engine of 23,500 kgf and three engines for soft landing / midcourse maneuvers of 1,670 kgf each. Midcourse manoeuvre/lunar braking stage.
Spacecraft delta v: 3,000 m/s (9,800 ft/sec).
AKA: Block 11.
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Gross mass: 32,226 kg (71,046 lb).
Thrust: 279.58 kN (62,852 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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