Encyclopedia Astronautica
Tsyklon 3-1


N2O4/UDMH propellant rocket stage. Loaded/empty mass 127,000/8,300 kg. Thrust 3,032.00 kN. Vacuum specific impulse 301 seconds. SL-14;11K69

Cost $ : 6.000 million.

AKA: 11S691.
Status: Active.
Gross mass: 127,000 kg (279,000 lb).
Unfuelled mass: 8,300 kg (18,200 lb).
Height: 18.75 m (61.51 ft).
Diameter: 3.00 m (9.80 ft).
Span: 3.00 m (9.80 ft).
Thrust: 3,032.00 kN (681,620 lbf).
Specific impulse: 301 s.
Specific impulse sea level: 270 s.
Burn time: 120 s.
Number: 249 .

More... - Chronology...


Associated Countries
Associated Engines
  • RD-261 Glushko N2O4/UDMH rocket engine. 3032 kN. Tsyklon 3 stage 1. In production. Based on RD-251 Isp=301s. First flight 1977. 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...

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...

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