N2O4/UDMH propellant rocket stage. Loaded/empty mass 4,600/1,407 kg. Thrust 78.71 kN. Vacuum specific impulse 317 seconds.
Cost $ : 2.000 million.
AKA: 11S693; S5M.
More... - Chronology...
Gross mass: 4,600 kg (10,100 lb).
Unfuelled mass: 1,407 kg (3,101 lb).
Height: 2.58 m (8.46 ft).
Diameter: 2.25 m (7.38 ft).
Span: 2.25 m (7.38 ft).
Thrust: 78.71 kN (17,694 lbf).
Specific impulse: 317 s.
Burn time: 125 s.
Number: 249 .
RD-861 Yuzhnoye N2O4/UDMH rocket engine. 78.710 kN. Tsyklon 2 and 3 stage 3; Ikar. In production. Isp=317s. Based on RD-854. Thrust vector control by 4 nozzles (thrust 98 N each) fed from a gas generator. First flight 1965. More...
RD-861K Yuzhnoye N2O4/UDMH rocket engine. 77.630 kN. Tsyklon 2 and 3 stage 3; Ikar. Developed 2005. Isp=330s. High pressure fuel was used to gimbal the engine in two planes, replacing four thrust vector engines on the basic RD-861. More...
Associated Launch Vehicles
Tsiklon-3 Ukrainian orbital launch vehicle. The Tsyklon 3 was developed in 1970-1977 as a part of a program to reduce the number of Soviet booster types. The first two stages were derived from the 8K68 version of the R-36 ICBM, while the restartable third stage was derived from that of the R-36-O. Compared to the Tsyklon 2, the launch vehicle increased payload to 4 metric tons, provided for completely automated launch operations, and had increased orbital injection accuracy. 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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