N2O4/UDMH propellant rocket stage. Loaded/empty mass 160,030/13,750 kg. Thrust 2,771.94 kN. Vacuum specific impulse 281 seconds.
Cost $ : 14.500 million. No Engines: 4.
More... - Chronology...
Status: Out of production.
Gross mass: 160,030 kg (352,800 lb).
Unfuelled mass: 13,750 kg (30,310 lb).
Height: 18.40 m (60.30 ft).
Diameter: 3.80 m (12.40 ft).
Span: 8.30 m (27.20 ft).
Thrust: 2,771.94 kN (623,157 lbf).
Specific impulse: 281 s.
Specific impulse sea level: 248 s.
Burn time: 145 s.
Number: 25 .
Viking 2 SEP N2O4/UDMH rocket engine. 693 kN. In production. Isp=281s. Used on Ariane 1, GSLV space launchers. First flight 1979. More...
Associated Launch Vehicles
Ariane 1 French orbital launch vehicle. First version of the Ariane launch vehicle. 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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