N2O4/UDMH propellant rocket stage. Loaded/empty mass 399,400/26,000 kg. Thrust 5,139.60 kN. Vacuum specific impulse 328 seconds.
No Engines: 3.
Status: Development ended 1968.
More... - Chronology...
Gross mass: 399,400 kg (880,500 lb).
Unfuelled mass: 26,000 kg (57,000 lb).
Height: 20.83 m (68.33 ft).
Diameter: 4.15 m (13.61 ft).
Span: 7.50 m (24.60 ft).
Thrust: 5,139.60 kN (1,155,428 lbf).
Specific impulse: 328 s.
Burn time: 225 s.
RD-254 Glushko N2O4/UDMH rocket engine. 1716 kN. N-1 upper stage, UR-700 stage 3. Study 1961. Proposed for use in N-1. High altitude version of RD-253 for 2nd stages. First flight 1974. More...
RD-253-11D48 Glushko N2O4/UDMH rocket engine. 1635 kN. Isp=316s. Six gimballed single chamber RD-253s provide the first stage power for the UR-500 Proton launch vehicle. First flown in 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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