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Saturn V-Centaur
Part of Saturn V

S-1C details

S-1C details
Credit: © Mark Wade

American orbital launch vehicle. MSFC study, 1968. S-ID stage-and-a-half first stage and Saturn IVB second stage. Centaur available as third stage for deep space missions. 30% performance improvement over Saturn V-A/Saturn INT-20 with standard Saturn IC first stage.

Status: Study 1968. Payload: 118,000 kg (260,000 lb). Thrust: 33,737.90 kN (7,584,582 lbf). Gross mass: 3,054,750 kg (6,734,570 lb). Height: 113.00 m (370.00 ft). Diameter: 10.06 m (33.00 ft). Apogee: 185 km (114 mi).

LEO Payload: 118,000 kg (260,000 lb) to a 185 km orbit at 28.00 degrees. Payload: 39,000 kg (85,000 lb) to a Mars flyby. Flyaway Unit Cost 1985$: 701.800 million.

Stage Data - Saturn V-Centaur



Family: orbital launch vehicle. People: von Braun. Country: USA. Engines: RL-10A-3. Stages: Saturn IC, Saturn II, Centaur D/E, Saturn IVB (S-V).

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