RD-0205 8D46 on stage 8S816 (UR-200)
Credit: © Mark Wade
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.
AKA: 8K81 Stage 2.
More... - Chronology...
Status: Retired 2007.
Gross mass: 25,810 kg (56,900 lb).
Unfuelled mass: 2,400 kg (5,200 lb).
Height: 10.00 m (32.00 ft).
Diameter: 2.20 m (7.20 ft).
Span: 2.20 m (7.20 ft).
Thrust: 612.90 kN (137,785 lbf).
Specific impulse: 322 s.
Burn time: 113 s.
Number: 236 .
RD-0205 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. More...
RD-0206 Kosberg N2O4/UDMH rocket engine. 575.5 kN. UR-200 stage 2. Developed 1961-64. Staged combustion cycle. Isp=326s. First flight 1964. More...
RD-0207 Kosberg N2O4/UDMH rocket engine. 30.9 kN. UR-200 stage 2 vernier. Developed 1961-64. Gas generator cycle. Four vernier thrusters. Isp=297s. First flight 1964. More...
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...
UR-200A Russian intercontinental boost-glide missile. Version that would boost the Raketoplan combat re-entry vehicle, which would use aerodynamic horizontal and vertical manoeuvring to penetrate enemy space defences and be practically invulnerable. More...
Proton-K/DM-2 Russian orbital launch vehicle. This improved four stage version uses the Block DM-2 / 11S861 fourth stage, which has its own guidance unit. This reduces payload but does not require the spacecraft's guidance system to provide steering commands to booster. Replaced the original Block DM / 11S86 version from 1982 to 1995. Used for launch of Glonass navigation satellites into medium earth orbit; and launch of Luch, Ekran-M, Potok, Raduga, Gorizont, Raduga-1, Elektro, and Gals communications satellites into geosynchronous orbit. Commercial version with Saab payload adapter-seperation system for Western payloads was dubbed 'Block DM1'. More...
Proton-K/DM-2M This four stage version uses the Block DM-2M / 11S861-01 upper stage, which has its own self-contained guidance unit. This reduces payload but does not require the spacecraft's guidance system to provide steering commands to booster. Used for launches of Russian geosynchronous satellites from 1994 on. 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...
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