SEP N2O4/UDMH rocket engine. 721 kN. Isp=296s. Used on Ariane 1, GSLV, PSLV. First flight 1979.
Thrust (sl): 487.100 kN (109,504 lbf). Thrust (sl): 49,674 kgf. Engine: 850 kg (1,870 lb). Chamber Pressure: 54.00 bar. Area Ratio: 31. Thrust to Weight Ratio: 86.4917647058824. Oxidizer to Fuel Ratio: 1.7. Coefficient of Thrust vacuum: 1.80035299087596. Coefficient of Thrust sea level: 1.22627891680189.
Unfuelled mass: 850 kg (1,870 lb).
More... - Chronology...
Height: 3.68 m (12.07 ft).
Diameter: 2.60 m (8.50 ft).
Thrust: 721.00 kN (162,087 lbf).
Specific impulse: 296 s.
Specific impulse sea level: 200 s.
Burn time: 132 s.
Number: 23 .
Associated Launch Vehicles
Ariane 1 French orbital launch vehicle. First version of the Ariane launch vehicle. More...
PSLV Indian third-generation launch vehicle, large enough to carry polar-orbiting earth resources satellites. 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...
Kudryavtseva, V M, ed., Zhidkostnikh Raketnikh Dvigatley, Visshaya Shkola, Moscow, 1993.
Ariane 1-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 37,130/3,625 kg. Thrust 720.97 kN. Vacuum specific impulse 296 seconds. More...
GSLV-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 42,900/5,400 kg. Thrust 725.02 kN. Vacuum specific impulse 295 seconds. More...
PSLV-2 N2O4/UDMH propellant rocket stage. Loaded/empty mass 45,800/5,300 kg. Thrust 725.02 kN. Vacuum specific impulse 293 seconds. More...
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