Glushko N2O4/UDMH rocket engine. 4521 kN. R-36M / RS-20A (SS-18 Mod 1) stage 1. Consists of four RD-263 engines. Isp=318s. Used on Dnepr launch vehicle. First flight 1986.
Application: R-36M / RS-20A (SS-18 Mod 1) stage 1.
Chambers: 4. Engine: 3,600 kg (7,900 lb). Chamber Pressure: 206.00 bar. Thrust to Weight Ratio: 128.05. Oxidizer to Fuel Ratio: 2.67.
More... - Chronology...
Unfuelled mass: 3,600 kg (7,900 lb).
Height: 2.15 m (7.05 ft).
Diameter: 3.03 m (9.92 ft).
Thrust: 4,521.00 kN (1,016,361 lbf).
Specific impulse: 318 s.
Specific impulse sea level: 293 s.
First Launch: 1969-73.
Number: 42 .
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...
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...
Dnepr Ukrainian orbital launch vehicle based on decommissioned R-36M2 intercontinental ballistic missiles. More...
Associated Manufacturers and Agencies
Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, 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...
Haeseler, Dietrich, Information from NPO Energia museum exhibit, Nov. 1992 via Dietrich Haeseler.
Rakhmanin, V F, Odnazhdy i Navsegda, NPO Energomash, Moscow 1998 via Dietrich Haeseler.
Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
R-36M2-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 161,520/13,620 kg. Thrust 4,523.00 kN. Vacuum specific impulse 318 seconds. Surplus ICBMs; failures based on ICBM tests through 1994. More...
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