N2O4/UDMH rocket stage. 760.00 kN (170,855 lbf) thrust. Mass 49,000 kg (108,027 lb).
AKA: R-36M St 2.
More... - Chronology...
Gross mass: 49,000 kg (108,000 lb).
Unfuelled mass: 3,000 kg (6,600 lb).
Height: 6.00 m (19.60 ft).
Diameter: 3.00 m (9.80 ft).
Thrust: 760.00 kN (170,850 lbf).
Burn time: 153 s.
RD-0229 Kosberg N2O4/UDMH rocket engine. R-36M / RS-20A (SS-18 mod-1) stage 2. Out of Production. Main engine. Staged combustion cycle. Used on Ikar launch vehicle. First flight 1974. More...
RD-0228 Kosberg N2O4/UDMH rocket engine. 755 kN. R-36M / RS-20A (SS-18 mod-1) stage 2. Out of Production. Comprises single-chamber main engine RD-0229 plus four-chamber steering engine RD-0230. Further developed to RD-0255. More...
Associated Launch Vehicles
R-36M Ukrainian intercontinental ballistic missile. The R-36M replaced the R-36 in 288 existing silos and was additionally installed in 20 new super-hardened silos. More...
Associated Manufacturers and Agencies
Yuzhnoye Ukrainian manufacturer of rockets, spacecraft, and rocket engines. Yangel Design Bureau, Dnepropetrovsk, Ukraine. 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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