Saturn MS-IC-3B

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Saturn MS-IC-3B

Part of Saturn IC

LOx/Kerosene propellant rocket stage. S-IC with 20 foot stretch, 1.8 million lb thrust F-1's, 5.6 million pounds propellant capacity (fuel offloaded to 4.99 million for LEO or 4.80 million lbs for LOR mission).

Status: Study 1967. Thrust: 45,925.50 kN (10,324,463 lbf). Gross mass: 2,718,800 kg (5,993,900 lb). Unfuelled mass: 178,700 kg (393,900 lb). Specific impulse: 304 s. Specific impulse sea level: 265 s. Burn time: 162 s. Height: 48.15 m (157.97 ft). Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft).

No Engines: 5.

Country: USA. Engines: F-1A. Launch Vehicles: Saturn V-3B. Propellants: Lox/Kerosene.

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