Encyclopedia Astronautica
UR-700-1


N2O4/UDMH propellant rocket stage. Loaded/empty mass 3,210,000/222,100 kg. Thrust 40,364.00 kN. Vacuum specific impulse 322 seconds. Includes propellant tanks which fed stage two engines from liftoff to first stage cutoff.

No Engines: 6.

Status: Development ended 1968.
Gross mass: 3,210,000 kg (7,070,000 lb).
Unfuelled mass: 222,100 kg (489,600 lb).
Height: 53.60 m (175.80 ft).
Diameter: 17.60 m (57.70 ft).
Span: 24.90 m (81.60 ft).
Thrust: 40,364.00 kN (9,074,188 lbf).
Specific impulse: 322 s.
Specific impulse sea level: 301 s.
Burn time: 151 s.

More... - Chronology...


Associated Countries
Associated Engines
  • RD-270 Glushko N2O4/UDMH rocket engine. 6713 kN. UR-700, R-56 stage 1. Development ended 1968. Isp=322s. Developed 1962-1971, largest rocket engine ever built in the Soviet Union, answer to F-1. Tested but cancelled before combustion instability problems solved. 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...

Associated Propellants
  • 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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