Encyclopedia Astronautica
RD-0205



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RD-0205 8D46
RD-0205 8D46 on stage 8S816 (UR-200)
Credit: © Mark Wade
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RD-0205
Credit: KBKhA
Kosberg N2O4/UDMH rocket engine. 606.4 kN. UR-200 stage 2. Engine unit consisting of 1 RD-0206 maine engine and 4 RD-0207 vernier/steering engines. Version of 8D44 and 8D45 with extended nozzle. Developed 1961. Isp=322s. First flight 1963.

Application: UR-200 stage 2.

Engine: 552 kg (1,216 lb). Area Ratio: 48.07. Thrust to Weight Ratio: 113.2. Oxidizer to Fuel Ratio: 2.625.

AKA: 8D46.
Gross mass: 622 kg (1,371 lb).
Unfuelled mass: 552 kg (1,216 lb).
Height: 2.33 m (7.63 ft).
Diameter: 1.47 m (4.82 ft).
Thrust: 606.40 kN (136,324 lbf).
Specific impulse: 322 s.
Burn time: 150 s.
First Launch: 1961-64.
Number: 9 .

More... - Chronology...


Associated Countries
See also
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...

Associated Propellants
  • 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...

Bibliography
  • Golubev, A A, KB KhimAvtomatiki - Straniy Istorii, Vol. 1, Voronezh 1995 via Dietrich Haeseler.

Associated Stages
  • UR-200-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 25,810/2,400 kg. Thrust 612.90 kN. Vacuum specific impulse 322 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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