N2O4/UDMH propellant rocket stage. Loaded/empty mass 1,451,500/108,900 kg. Thrust 21,232.30 kN. Vacuum specific impulse 267 seconds. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, Ni-250 Hull
Status: Study 1967.
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Gross mass: 1,451,500 kg (3,200,000 lb).
Unfuelled mass: 108,900 kg (240,000 lb).
Height: 40.70 m (133.50 ft).
Diameter: 6.61 m (21.68 ft).
Span: 9.26 m (30.38 ft).
Thrust: 21,232.30 kN (4,773,211 lbf).
Specific impulse: 267 s.
Specific impulse sea level: 245 s.
Burn time: 163 s.
PF N204/UDMH-2165k Notional N2O4/UDMH rocket engine. 21,232 kN. Study 1967. Isp=267s. Used on Saturn LCB-Storable-250 launch vehicle. More...
Associated Launch Vehicles
Saturn LCB-Storable-250 American orbital launch vehicle. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb pyld to LEO): Low Cost Booster, Single Pressure-fed N2O4/UDMH Propellant engine, Ni-250 Steel Hull. 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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