N2O4/Alumizine propellant rocket stage. Loaded/empty mass 1,270,100/95,300 kg. Thrust 18,873.80 kN. Vacuum specific impulse 280 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/Alumizine Propellant engine, Ni-250 Hull
Status: Study 1967.
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Gross mass: 1,270,100 kg (2,800,000 lb).
Unfuelled mass: 95,300 kg (210,100 lb).
Height: 31.40 m (103.00 ft).
Diameter: 6.61 m (21.68 ft).
Span: 9.26 m (30.38 ft).
Thrust: 18,873.80 kN (4,242,999 lbf).
Specific impulse: 280 s.
Specific impulse sea level: 260 s.
Burn time: 168 s.
PF N204/Alumizine-1925k Notional N2O4/Alumizine rocket engine. 18,873 kN. Study 1967. Isp=280s. Used on Saturn LCB-Alumizine-250 launch vehicle. More...
Associated Launch Vehicles
Saturn LCB-Alumizine-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/Alumizine Propellant engine, Ni-250 Steel Hull. More...
N2O4/Alumizine Nitrogen tetroxide became the storable liquid propellant of choice from the late 1950's. Alumizine was a mixture of 43% aluminum powder suspended in anhydrous hydrazine with a gelling agent. The idea was to increase the heat of combustion due to the high enthalpy of formation of aluminum oxide as a combustion product, similar to the metallized kerosene ("Kerosol") tested by Saenger in the 30's. Alumizine was never flown and was only tested in static ground tests. A drum of alumizine exploded in California when it was not disposed of safely. The fuel was proposed for some pressure-fed 'big dumb booster' designs of the late 1960's. More...
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