N2O4/UDMH propellant rocket stage. Loaded mass 20,000 kg. Thrust 682.00 kN.
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Gross mass: 20,000 kg (44,000 lb).
Height: 7.70 m (25.20 ft).
Diameter: 1.90 m (6.20 ft).
Thrust: 682.00 kN (153,319 lbf).
Burn time: 74 s.
Number: 33 .
RD-0244 Kosberg N2O4/UDMH rocket engine. 682 kN. R-29RM / RSM-54 (SS-N-23) stage 1. Out of Production. Main engine in system RD-0243. Staged combustion cycle. Submerged in propellant tank. Isp=310s. First flight 1985. More...
Associated Launch Vehicles
Shtil Russian intercontinental ballistic orbital launch vehicle. Three stage vehicle based on R-29RM SLBM. More...
Shtil-1/1N Russian intercontinental ballistic orbital launch vehicle. Three stage vehicle based on R-29RM SLBM. More...
Sineva Russian liquid-propellant submarine-launched ballistic missile. First aunch 2004.02.18; entered service 2007. Competitor was the solid-propellant Bulava. More...
Associated Manufacturers and Agencies
Makeyev Russian manufacturer of rockets, spacecraft, and rocket engines. Makeyev Design Bureau, Kolomna, Russia. 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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