Isayev N2O4/UDMH rocket engine. 3.090 kN. Salyut 6, 7and Mir orbital propulsion maneuvering engine. In Production. Probably derived from engine of propulsion system KDU-426. Pressure fed engine.
Application: Salyut 6, 7and Mir orbital propulsion maneuvering engine.
Engine: 39 kg (85 lb). Thrust to Weight Ratio: 8.18.
AKA: S5.79; KRD-79.
More... - Chronology...
Status: In Production.
Unfuelled mass: 39 kg (85 lb).
Height: 0.55 m (1.80 ft).
Diameter: 0.84 m (2.75 ft).
Thrust: 3.09 kN (695 lbf).
Salyut 6 Russian manned space station. One launch, 1977.09.29. The Salyut 6 space station was the most successful of the DOS series prior to Mir. It was aloft for four years and ten months, completing 27,785 orbits of the earth. More...
37K-Mir Russian manned space station. Cancelled 1983. The basic 37K design consisted of a 4.2 m diameter pressurized cylinder with a docking port at the forward end. It was not equipped with its own propulsion system. More...
Salyut 7 Russian manned space station. One launch, 1982.04.19. Salyut 7 was the back-up article for Salyut 6 and very similar in equipment and capabilities. More...
Mir Russian manned space station. One launch, 1986.02.20. Improved model of the Salyut DOS-17K space station with one aft docking port and five ports in a spherical compartment at the forward end of the station. More...
Associated Manufacturers and Agencies
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.
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