Saturn LCB-Alumizine-250 stage

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Saturn LCB-Alumizine-250 stage

Part of Saturn LRB stage series

N2O4/Alumizine propellant rocket stage. Boeing Low-Cost Saturn Derivative Study, 1967 (trade study of 260 inch first stages for S-IVB, all delivering 86,000 lb payload to LEO): Low Cost Booster, Single Pressure-fed N2O4/Alumizine Propellant engine, Ni-250 Hull.

AKA: Saturn LCB-Alumizine-250. Status: Study 1967. Thrust: 18,873.80 kN (4,242,999 lbf). Gross mass: 1,270,100 kg (2,800,000 lb). Unfuelled mass: 95,300 kg (210,100 lb). Specific impulse: 280 s. Specific impulse sea level: 260 s. Burn time: 168 s. Height: 31.40 m (103.00 ft). Diameter: 6.61 m (21.68 ft). Span: 9.26 m (30.38 ft).

Country: USA. Engines: PF N204/Alumizine-1925k. Launch Vehicles: Saturn LCB-Alumizine-250. Propellants: N2O4/Alumizine.

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