Kosberg N2O4/UDMH rocket engine. 559 kN. UR-200 stage 1. Hardware. Diameter is per chamber. Staged combustion cycle. Variant of RD-0203 with additional pressure sensor. Isp=311s. First flight 1964.
Application: UR-200 stage 1.
Thrust (sl): 500.000 kN (112,400 lbf). Thrust (sl): 51,000 kgf. Engine: 381 kg (839 lb). Area Ratio: 29.8. Thrust to Weight Ratio: 149.5. Oxidizer to Fuel Ratio: 2.6.
More... - Chronology...
Gross mass: 1,961 kg (4,323 lb).
Unfuelled mass: 1,524 kg (3,359 lb).
Height: 1.80 m (5.90 ft).
Diameter: 0.89 m (2.91 ft).
Thrust: 559.00 kN (125,668 lbf).
Specific impulse: 311 s.
Specific impulse sea level: 278 s.
Burn time: 136 s.
First Launch: 1961-64.
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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