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.
AKA: 8K81 Stage 1.
More... - Chronology...
Status: Design 1962.
Gross mass: 107,500 kg (236,900 lb).
Unfuelled mass: 6,600 kg (14,500 lb).
Height: 20.00 m (65.00 ft).
Diameter: 3.00 m (9.80 ft).
Span: 3.00 m (9.80 ft).
Thrust: 2,235.00 kN (502,447 lbf).
Specific impulse: 311 s.
Specific impulse sea level: 278 s.
Burn time: 135 s.
Number: 4 .
RD-0202 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. More...
RD-0209 Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Developed 1961-65. Engine unit consisting of 1 RD-0211 for tank pressurization and three RD-0210. Modification of RD-0208 with tank pressurization. Further developed into RD--0211. First flight 1965. More...
RD-0208 Kosberg N2O4/UDMH rocket engine. UR-200 stage 1. Developed 1961-65. Stage 1 had three RD-0208 plus one RD-0209. Further developed into RD-0210. More...
RD-0203 Kosberg N2O4/UDMH rocket engine. 559 kN. UR-200 stage 1. Hardware. DU consisting of 4 RD-0204 gimballed motors. Staged combustion cycle. Isp=311s. First flight 1964. More...
RD-0204 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. 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-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...
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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