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Saturn LCB-Lox/RP-1 stage
Part of Saturn LRB stage series Family
LOx/Kerosene 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 LOx/RFP-1 engine.

AKA: Saturn LCB-Lox/RP-1. Status: Study 1967. Thrust: 20,306.60 kN (4,565,105 lbf). Gross mass: 1,360,800 kg (3,000,000 lb). Unfuelled mass: 108,900 kg (240,000 lb). Specific impulse: 275 s. Specific impulse sea level: 253 s. Burn time: 163 s. Height: 48.78 m (160.03 ft). Diameter: 6.61 m (21.68 ft). Span: 9.26 m (30.38 ft).



Country: USA. Engines: PF RP-1. Launch Vehicles: Saturn LCB-Lox/RP-1. Propellants: Lox/Kerosene.

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