Isayev N2O4/UDMH rocket engine. 3.089 kN. Soyuz-T orbital correction engine. In Production. Pressure-fed engine. Used as long duration engine for correction orbits of satellites. Isp=292s.
Application: Soyuz-T orbital correction engine.
Engine: 270 kg (590 lb). Chamber Pressure: 8.80 bar. Thrust to Weight Ratio: 1.16. Oxidizer to Fuel Ratio: 1.85.
More... - Chronology...
Status: In Production.
Unfuelled mass: 270 kg (590 lb).
Height: 1.24 m (4.05 ft).
Diameter: 2.10 m (6.80 ft).
Thrust: 3.09 kN (694 lbf).
Specific impulse: 292 s.
Burn time: 570 s.
First Launch: 1968-74.
Soyuz T Russian manned spacecraft. 18 launches, 1978.04.04 (Cosmos 1001) to 1986.03.13 (Soyuz T-15). Soyuz T had a long gestation, beginning as the Soyuz VI military orbital complex Soyuz in 1967. 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...
Haeseler, Dietrich, Visit to the museum of Chemical Machining Design Bureau, Kalinin 1994 via Dietrich Haeseler.
Kudryavtsev, V M, et.al., Osnovy Teorii i Rascheta, Moscow, Vysshaya Shkola, 1993 via Dietrich Haeseler.
Siddiqi, Asif A, Soviet Space Web Page, 1999 via Dietrich Haeseler. Web Address when accessed: here.
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