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Saturn S-IC-TLB stage
Part of Saturn IC 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): S-IC Technology Liquid Booster: 260 inch liquid booster with 2 x F-1 engines, recoverable/reusable.

AKA: Saturn S-IC-TLB. Status: Study 1967. Thrust: 15,532.70 kN (3,491,890 lbf). Gross mass: 952,500 kg (2,099,900 lb). Unfuelled mass: 68,000 kg (149,000 lb). Specific impulse: 304 s. Specific impulse sea level: 265 s. Burn time: 167 s. Height: 36.36 m (119.29 ft). Diameter: 6.61 m (21.68 ft). Span: 10.58 m (34.71 ft).

No Engines: 2.



Country: USA. Engines: F-1. Launch Vehicles: Saturn S-IC-TLB. Propellants: Lox/Kerosene.

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