N2O4/UDMH propellant rocket stage. Loaded/empty mass 45,800/5,300 kg. Thrust 725.02 kN. Vacuum specific impulse 293 seconds.
Cost $ : 4.000 million.
AKA: Polar Satellite Launch Vehicle.
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Gross mass: 45,800 kg (100,900 lb).
Unfuelled mass: 5,300 kg (11,600 lb).
Height: 12.50 m (41.00 ft).
Diameter: 2.80 m (9.10 ft).
Span: 2.80 m (9.10 ft).
Thrust: 725.02 kN (162,990 lbf).
Specific impulse: 293 s.
Burn time: 158 s.
Number: 20 .
Viking 4 SEP N2O4/UDMH rocket engine. 721 kN. Isp=296s. Used on Ariane 1, GSLV, PSLV. First flight 1979. More...
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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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