Melnikov N2O4/UDMH rocket engine. 2.943 kN. Ikar stage 4 for Soyuz-Ikar. Design 1999. Isp=325s. Derived from propulsion module of Yantar spysat, with over 30 flights to 1998. Increased versatility compared to Block L due to capability for 50 restarts.
Engine thrusts: 1 x 2943 N + 4 x 110 N + 4 x 52 N + 8 x 5.88 N.
Application: Ikar stage 4 for Soyuz-Ikar.
Chambers: 1 + 4 + 4 + 8. Engine: 820 kg (1,800 lb). Chamber Pressure: 9.00 bar. Thrust to Weight Ratio: .36. Restarts: 50.
Status: Design 1999.
More... - Chronology...
Unfuelled mass: 820 kg (1,800 lb).
Height: 2.56 m (8.39 ft).
Diameter: 2.72 m (8.92 ft).
Thrust: 2.94 kN (662 lbf).
Specific impulse: 326 s.
Burn time: 600 s.
Associated Launch Vehicles
Soyuz 11A511U / Ikar Russian orbital launch vehicle. Standard Soyuz universal booster with the Ikar upper stage, derived from the propulsion system for the Kozlov Yantar series of spy satellites. More...
Associated Manufacturers and Agencies
Melnikov Russian manufacturer of rocket engines. Melnikov 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...
Sorokin, Vladislav, "'Yantarnaya istoriya'", Novosti Kosmonavtiki, 1997, Issue 17, page 57.
Soyuz Launcher User Manual, via Dietrich Haeseler.
Launch Kit Flight 02, Starsem Paris 1999 (http://www.starsem.com/newsst_kit.html) via Dietrich Haeseler.
Ikar N2O4/UDMH propellant rocket stage. Loaded/empty mass 3,164/820 kg. Thrust 2.94 kN. Vacuum specific impulse 326 seconds. Derived from propulsion module of Yantar spysat, over 30 flights to 1998. 50 restarts. More...
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