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 The Apollo 10 S-IC stage is hoisted in the Vehicle Assembly Building for stacking | |
| Manufacturer | Boeing |
|---|---|
| Country of origin | United States |
| Used on | Saturn V |
| General characteristics | |
| Height | 42 m (138 ft)[1] |
| Diameter | 10 m (33 ft)[1] |
| Gross mass | 2,214 t (4,881,000 lb)[1] |
| Propellant mass | 2,077 t (4,578,000 lb)[1] |
| Empty mass | 137 t (303,000 lb)[1] |
| Launch history | |
| Status | Retired |
| Total launches | 13 |
| Successes (stage only) | 13 |
| First flight | November 9, 1967 (Apollo 4) |
| Last flight | May 14, 1973 (Skylab 1) |
| Engine details | |
| Powered by | 5 × F-1 |
| Maximum thrust | 34,500 kN (7,750,000 lbf) at sea level[2] |
| Specific impulse | 263 s (2.58 km/s) |
| Burn time | 150 seconds |
| Propellant | RP-1/LOX |
The S-IC (pronounced S-one-C[3][4]) was the first stage of the American Saturn V rocket. The S-IC stage was manufactured by the Boeing Company. Like the first stages of most rockets, more than 90% of the mass at launch was propellant, in this case RP-1 rocket fuel and liquid oxygen (LOX) oxidizer. It was 42 m (138 ft) tall and 10 m (33 ft) in diameter. The stage provided 34,500 kN (7,750,000 lbf)[2] of thrust at sea level to get the rocket through the first 61 km (38 mi) of ascent. The stage had five F-1 engines in a quincunx arrangement. The center engine was fixed in position, while the four outer engines could be hydraulically gimballed to control the rocket.
- ^ a b c d e Cite error: The named reference
SaturnVNRwas invoked but never defined (see the help page). - ^ a b Thorne, Muriel, ed. (May 1983). NASA, The First 25 Years: 1958-1983 (PDF). Washington, D.C.: National Aeronautics and Space Administration. p. 69.
- ^ Murray, Charles A.; Cox, Catherine Bly (Jul 1989). Apollo, the race to the moon. Simon and Schuster. p. 54. ISBN 9780671611019.
- ^ Woods, W. David (2011-08-08). How Apollo Flew to the Moon. Springer Science & Business Media. p. 24. ISBN 9781441971791.