Encyclopedia Astronautica
Tsyklon 3-2


N2O4/UDMH propellant rocket stage. Loaded/empty mass 53,300/4,800 kg. Thrust 941.00 kN. Vacuum specific impulse 318 seconds.

Cost $ : 3.000 million.

AKA: 11S692.
Status: Active.
Gross mass: 53,300 kg (117,500 lb).
Unfuelled mass: 4,800 kg (10,500 lb).
Height: 10.08 m (33.07 ft).
Diameter: 3.00 m (9.80 ft).
Span: 3.00 m (9.80 ft).
Thrust: 941.00 kN (211,545 lbf).
Specific impulse: 318 s.
Burn time: 160 s.
Number: 249 .

More... - Chronology...


Associated Countries
Associated Engines
  • RD-262 Glushko N2O4/UDMH rocket engine. 941 kN. Tsyklon 3 stage 2. In production. Based on RD-252 Isp=317s. 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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