This article needs additional citations for verification. (July 2009) |
Manufacturer | Boeing |
---|---|
Country of origin | United States |
Used on | Saturn V |
General characteristics | |
Height | 42 m (138 ft) |
Diameter | 10 m (33 ft) |
Gross mass | 2,280,000 kg (5,030,000 lb) |
Empty mass | 130,000 kg (290,000 lb) |
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[1] |
Specific impulse | 263 s (2.58 km/s) |
Burn time | 150 seconds |
Propellant | RP-1/LOX |
The S-IC (pronounced S-one-C[2][3]) 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, most of its mass of more than 2,000 t (4,400,000 lb) 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)[1] 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.