 | S-1C details
Credit - © Mark Wade
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Orbital launch vehicle. Year: 1967. Family: Saturn V. Country: USA. Status: Study 1967. Saturn variant consisting of S-IC first stage and S-IVB second stage. Consideration was given to deleting one or more of the F-1 engines in the first stage.
| Liftoff Mass - kg | S-IC - No.
F-1 Motors | Payload - kg - 4.68 G limit | Payload - kg - 6.0 G limit |
| 1,107,000 | 2 | 36,000 | 27,000 |
| 1,655,000 | 3 | 78,000 | 47,000 |
| 2,209,000 | 4 | 132,000 | 63,000 |
| 2,299,000 | 5 | 133,000 | 72,000 |
Manufacturer: Von Braun. LEO Payload: 60,000 kg (132,000 lb). to: 185 km Orbit. at: 28.00 degrees. Liftoff Thrust: 33,737.900 kN (7,584,582 lbf). Total Mass: 2,478,120 kg (5,463,310 lb). Core Diameter: 10.06 m (33.00 ft). Total Length: 72.00 m (236.00 ft). Flyaway Unit Cost $: 391.500 million. in: 1985 unit dollars.
Stage Data - Saturn INT-20 - Stage Number: 1. 1 x Stage: Saturn IC. Gross Mass: 2,286,217 kg (5,040,245 lb). Empty Mass: 135,218 kg (298,104 lb). Thrust (vac): 38,703.160 kN (8,700,816 lbf). Isp: 304 sec. Burn time: 161 sec. Isp(sl): 265 sec. Diameter: 10.06 m (33.00 ft). Span: 19.00 m (62.00 ft). Length: 42.06 m (137.99 ft). Propellants: Lox/Kerosene. No Engines: 5. Engine: F-1.
- Stage Number: 3. 1 x Stage: Saturn IVB (S-V). Gross Mass: 119,900 kg (264,300 lb). Empty Mass: 13,300 kg (29,300 lb). Thrust (vac): 1,031.600 kN (231,913 lbf). Isp: 421 sec. Burn time: 475 sec. Isp(sl): 200 sec. Diameter: 6.61 m (21.68 ft). Span: 6.61 m (21.68 ft). Length: 17.80 m (58.30 ft). Propellants: Lox/LH2. No Engines: 1. Engine: J-2. Saturn V version of S-IVB stage
Bibliography and Further Reading - Lowther, Scott, Saturn: Development, Details, Derivatives and Descendants, Work in progress. Availabe chapters may be ordered directly from Scott Lowther at web site indicated. Accessed at: http://www.webcreations.com/ptm.
- Alexander, George, Aviation Week and Space Technology, "Manned Flight Planning Gap Delays Saturn Development", 1966-08-08, page 60.
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