N2O4/UDMH propellant rocket stage. Loaded/empty mass 2,057,400/205,400 kg. Thrust 28,553.00 kN. Vacuum specific impulse 267 seconds. NASA, Saturn Alternative Booster Studies, 1969 (trade study of 120, 156, 260 inch solid, and Storable liquid boosters for S-IVB. Reached opposite conclusion from Boeing study, that Pressure Fed Liquid Booster would be 6.5% more expensive than solid). Pre
Status: Study 1969.
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Gross mass: 2,057,400 kg (4,535,700 lb).
Unfuelled mass: 205,400 kg (452,800 lb).
Height: 33.57 m (110.13 ft).
Diameter: 10.06 m (33.00 ft).
Span: 10.06 m (33.00 ft).
Thrust: 28,553.00 kN (6,418,969 lbf).
Specific impulse: 267 s.
Specific impulse sea level: 245 s.
Burn time: 167 s.
PF N204/UDMH-2912k Notional N2O4/UDMH rocket engine. 28,552 kN. Study 1967. Isp=267s. Used on Saturn LCB-Storable-140 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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