Kosberg N2O4/UDMH rocket engine. 2236 kN. UR-200 stage 1. Engine unit (DU - dvigatelnaya ustanovka) consisting of 1 RD-0204 for tank pressurization and three RD-0203. Isp=311s. First flight 1963.
Application: UR-200 stage 1.
Chambers: 4. Engine: 1,525 kg (3,362 lb). Area Ratio: 29.8. Thrust to Weight Ratio: 149.5. Oxidizer to Fuel Ratio: 2.6.
More... - Chronology...
Unfuelled mass: 1,525 kg (3,362 lb).
Height: 1.80 m (5.90 ft).
Thrust: 2,236.00 kN (502,672 lbf).
Specific impulse: 311 s.
Specific impulse sea level: 278 s.
Burn time: 136 s.
First Launch: 1961-64.
Number: 9 .
Associated Launch Vehicles
Initial UR-500 Russian orbital launch vehicle. While Chelomei's OKB was still preparing the UR-200 draft project, it was proposed to use this as the basis for the UR-500 heavy universal rocket, with five times the payload capacity. These initial 1961 studies consisted of 4 two-stage UR-200 rockets lashed together, the first and second stages working in parallel in clusters. A third stage would be modified from the UR-200 second stage. However analysis indicated that the payload capacity could not meet the military's requirements. More...
UR-200 Russian intercontinental ballistic missile. Universal rocket designed by Chelomei to cover the ICBM, FOBS, satellite launch vehicle, and spaceplane booster roles. Flight tested in 1963-1964 but cancelled in favour of Yangel's R-36. 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.
UR-200-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 107,500/6,600 kg. Thrust 2,235.00 kN. Vacuum specific impulse 311 seconds. Tsniimash has 1:10 structural simulation model. Developed 1960-1965. Orevo has sectioned hardware. All data accurate except empty mass prorated between first and second stages. More...
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