N2O4/UDMH propellant rocket stage. Loaded/empty mass 42,900/5,400 kg. Thrust 725.02 kN. Vacuum specific impulse 295 seconds.
Cost $ : 4.000 million.
AKA: Geostationary Satellite Launch Vehicle.
More... - Chronology...
Gross mass: 42,900 kg (94,500 lb).
Unfuelled mass: 5,400 kg (11,900 lb).
Height: 11.60 m (38.00 ft).
Diameter: 2.80 m (9.10 ft).
Span: 2.80 m (9.10 ft).
Thrust: 725.02 kN (162,990 lbf).
Specific impulse: 295 s.
Specific impulse sea level: 200 s.
Burn time: 149 s.
Number: 4 .
Viking 4 SEP N2O4/UDMH rocket engine. 721 kN. Isp=296s. Used on Ariane 1, GSLV, PSLV. First flight 1979. More...
Associated Launch Vehicles
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...
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