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.
Application: R-36M2 / RS-20V (SS-18 Mod-4) stage 2.
Chambers: 1 + 4.
Thrust: 755.00 kN (169,730 lbf).
More... - Chronology...
First Launch: 1983-89.
Number: 42 .
Associated Launch Vehicles
Dnepr Ukrainian orbital launch vehicle based on decommissioned R-36M2 intercontinental ballistic missiles. More...
Associated Manufacturers and Agencies
Kosberg Russian manufacturer of rocket engines. Kosberg 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...
Golubev, A A, KB KhimAvtomatiki - Straniy Istorii, Vol. 1, Voronezh 1995 via Dietrich Haeseler.
Lardier, C, "SS-18", Air et Cosmos, 2 Sept. 1994 via Dietrich Haeseler.
Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
R-36M2-2 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. More...
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