Isayev N2O4/UDMH rocket engine. 18.850 kN. Mars 2 and 3 maneuver engine. Out of Production. Pump-fed engine. Could be throttled to 7.05 kN / 9.5 MPa / 2850 m/s. . Chamber pressure 133,2 - 95 bar. Isp=312s.
Application: Mars 2 and 3 maneuver engine.
Throttled thrust(vac): 7.050 kN (1,585 lbf). Chamber Pressure: 133.20 bar. Oxidizer to Fuel Ratio: 1.9.
More... - Chronology...
Status: Out of Production.
Thrust: 18.85 kN (4,238 lbf).
Specific impulse: 312 s.
Burn time: 560 s.
First Launch: 1970-73.
Mars M-71 Russian Mars lander. 3 launches, 1971.05.10 (Cosmos 419) to 1971.05.28 (Mars 3). Mars spacecraft built by Lavochkin for 1971 campaign. The spacecraft consists of a bus/orbiter module and an attached descent/lander module. 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...
Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
Glushko, V P (ed), Kosmonavtika Entsiklopedi, Moscow 1985 via Dietrich Haeseler.
Kudryavtsev, V M, et.al., Osnovy Teorii i Rascheta, Moscow, Vysshaya Shkola, 1993 via Dietrich Haeseler.
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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