N2O4/UDMH propellant rocket stage. Loaded/empty mass 41,114/4,374 kg. Thrust 760.00 kN. Vacuum specific impulse 340 seconds. Surplus ICBMs; failures based on ICBM tests through 1994.
Cost $ : 3.000 million.
More... - Chronology...
Gross mass: 41,114 kg (90,640 lb).
Unfuelled mass: 4,374 kg (9,643 lb).
Height: 5.70 m (18.70 ft).
Diameter: 3.00 m (9.80 ft).
Span: 3.00 m (9.80 ft).
Thrust: 760.00 kN (170,850 lbf).
Specific impulse: 340 s.
Burn time: 190 s.
Number: 125 .
RD-0255 Kosberg N2O4/UDMH rocket engine. 755 kN. R-36M2 / RS-20V (SS-18 Mod-4) stage 2. Comprises of single-chamber main engine RD-0256 plus four-chamber steering engines RD-0257. Development based on RD-0228 with thrust increase by 11%. First flight 1986. More...
Associated Launch Vehicles
R-36MU 15A18 Ukrainian intercontinental ballistic missile. Improved version of the R-36M with a new ten warhead MIRV bus, better guidance system, increased throw-weight, and increased range. More...
R-36M2 15A18M Ukrainian intercontinental ballistic missile. The R-36M2 was the Soviet Union's answer to the American 'Star Wars' anti-ballistic missile system. It was unusually named 'Voevoda' (an old Russian word for the leader of an army) in recognition of its planned role. In the end, it was only deployed in very limited numbers before the end of the Cold War. More...
Dnepr Ukrainian orbital launch vehicle based on decommissioned R-36M2 intercontinental ballistic missiles. 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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