Glushko N2O4/UDMH rocket engine. 3032 kN. Tsyklon 3 stage 1. In production. Based on RD-251 Isp=301s. First flight 1977.
Application: Tsyklon 3 stage 1.
Chambers: 6. Engine: 1,764 kg (3,888 lb). Chamber Pressure: 83.00 bar. Area Ratio: 14.7. Thrust to Weight Ratio: 175.27. Oxidizer to Fuel Ratio: 2.6.
Status: In production.
More... - Chronology...
Unfuelled mass: 1,764 kg (3,888 lb).
Height: 1.76 m (5.78 ft).
Diameter: 0.75 m (2.44 ft).
Thrust: 3,032.00 kN (681,620 lbf).
Specific impulse: 301 s.
Specific impulse sea level: 270 s.
Burn time: 120 s.
First Launch: 1967-69.
Number: 121 .
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 Manufacturers and Agencies
Glushko Russian manufacturer of rocket engines and rockets. Glushko Design Bureau, Russia. 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...
Russian Arms Catalogue, Vol 5 and 6, Military Parade, Moscow via Dietrich Haeseler.
Siddiqi, Asif A, Soviet Space Web Page, 1999 via Dietrich Haeseler. Web Address when accessed: here.
GKB Yuzhnoe "Yangel", Data sheets Paris Airshow 1997 via Dietrich Haeseler.
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 More...
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