SEP N2O4/UDMH rocket engine. 693 kN. In production. Isp=281s. Used on Ariane 1, GSLV space launchers. First flight 1979.
Thrust (sl): 611.600 kN (137,493 lbf). Thrust (sl): 62,366 kgf. Engine: 776 kg (1,710 lb). Chamber Pressure: 55.00 bar. Area Ratio: 11. Thrust to Weight Ratio: 91.0631443298969. Coefficient of Thrust vacuum: 1.77769748966301. Coefficient of Thrust sea level: 1.57769748966301.
Status: In production.
More... - Chronology...
Unfuelled mass: 776 kg (1,710 lb).
Height: 2.87 m (9.41 ft).
Diameter: 0.95 m (3.11 ft).
Thrust: 693.00 kN (155,792 lbf).
Specific impulse: 281 s.
Specific impulse sea level: 248 s.
Burn time: 145 s.
Number: 60 .
Associated Launch Vehicles
Ariane 1 French orbital launch vehicle. First version of the Ariane launch vehicle. More...
GSLV Indian mixed-propulsion orbital launch vehicle for geosynchronous satellites using a Lox/LH2 upper stage developed from Russian technology. 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...
Ariane 1-1 N2O4/UDMH propellant rocket stage. Loaded/empty mass 160,030/13,750 kg. Thrust 2,771.94 kN. Vacuum specific impulse 281 seconds. More...
GSLV-0 N2O4/UDMH propellant rocket stage. Loaded/empty mass 45,600/5,600 kg. Thrust 735.00 kN. Vacuum specific impulse 281 seconds. More...
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