Glushko N2O4/UDMH rocket engine. 1236 kN. MR-UR-100 / RS-16 (SS-17) stage 1. Out of Production. First flight 1976. Modification of RD-263 engine. Isp=319s. First flight 1990.
Application: MR-UR-100 / RS-16 (SS-17) stage 1.
Thrust (sl): 1,147.000 kN (257,855 lbf). Thrust (sl): 117,000 kgf. Engine: 770 kg (1,690 lb). Chamber Pressure: 226.00 bar. Thrust to Weight Ratio: 163.63. Oxidizer to Fuel Ratio: 2.67.
Status: Out of Production.
More... - Chronology...
Unfuelled mass: 770 kg (1,690 lb).
Height: 2.15 m (7.05 ft).
Diameter: 1.08 m (3.55 ft).
Thrust: 1,236.00 kN (277,863 lbf).
Specific impulse: 319 s.
Specific impulse sea level: 296 s.
First Launch: 1969-76.
Associated Launch Vehicles
MR-UR-100 Ukrainian intercontinental ballistic missile. The Yangel MR-UR-100 was designed as a replacement for Chelomei's UR-100 at the end of its 10 year storage life. Although it could be installed in the same silos, it was 50% heavier. The competing design of Chelomei, the UR-100N, was also put into production when the Soviet hierarchy deadlocked and could not pick one design over the other. 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...
Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
MR-UR-100 St 1 N2O4/UDMH rocket stage. 1236.00 kN (277,864 lbf) thrust. Mass 59,000 kg (130,073 lb). More...
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