N2O4/UDMH propellant rocket stage. Loaded/empty mass 49,300/3,700 kg. Thrust 940.40 kN. Vacuum specific impulse 317 seconds.
Cost $ : 3.000 million.
More... - Chronology...
Gross mass: 49,300 kg (108,600 lb).
Unfuelled mass: 3,700 kg (8,100 lb).
Height: 9.40 m (30.80 ft).
Diameter: 3.00 m (9.80 ft).
Span: 3.00 m (9.80 ft).
Thrust: 940.40 kN (211,410 lbf).
Specific impulse: 317 s.
Burn time: 160 s.
Number: 107 .
RD-252 Glushko N2O4/UDMH rocket engine. 940.5 kN. R-36-0 stage 2; Tsyklon 2 stage 2. In production. Used modified chamber from RD-219, nozzle is conventional, so performance is higher. Isp=317s. First flight 1965. More...
Associated Launch Vehicles
Tsiklon-2 Ukrainian orbital launch vehicle. A government decree of 24 August 1965 ordered development by Yangel of a version of his R-36 rocket to orbit Chelomei's IS (Istrebitel Sputnik) ASAT and US (Upravlenniye Sputnik) naval intelligence satellites. The Tyklon 2 definitive operational version replaced the 11K67 launch vehicle from 1969 and was an adaptation of the 8K69 (SS-9) two stage ICBM. The IS and US Raketoplan-derived payloads had their own engines for insertion into final orbit. 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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