N2O4/UDMH propellant rocket stage. Loaded/empty mass 33,500/1,900 kg. Thrust 131.40 kN. Vacuum specific impulse 326 seconds. Estimated empty mass. Three used to propell LK-700 spacecraft towards moon.
Status: Development ended 1968.
More... - Chronology...
Gross mass: 33,500 kg (73,800 lb).
Unfuelled mass: 1,900 kg (4,100 lb).
Height: 6.20 m (20.30 ft).
Diameter: 2.70 m (8.80 ft).
Span: 2.70 m (8.80 ft).
Thrust: 131.40 kN (29,540 lbf).
Specific impulse: 326 s.
Burn time: 760 s.
11D423 Izotov N2O4/UDMH rocket engine. 134 kN. LK-700S manned lunar lander ascent stage engine. Development ended 1968. Isp=326s. Based UR-100 stage 2 engine. Gas generator cycle; 2 large turbine exhaust pipes. More...
RD-0210 Kosberg N2O4/UDMH rocket engine. 582.1 kN. Isp=326s. Cluster of four similar engines used in second stage of Proton - one providing tank pressurization (8D412K/RD-0211) and three (8D411K/RD-0210). Staged combustion cycle. First flight 1965. More...
Associated Launch Vehicles
UR-700 Russian heavy-lift orbital launch vehicle. The UR-700 was the member of Vladimir Chelomei's Universal Rocket family designed in the 1960's to allow direct manned flight by the LK-700 spacecraft to the surface of the moon. However Korolev's N1 was the selected Soviet super-booster design. Only when the N1 ran into schedule problems in 1967 was work on the UR-700 resumed. The draft project foresaw first launch in May 1972. But no financing for full scale development was forthcoming; by then it was apparent that the moon race was lost. 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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