S-IB
![]() Diagram of the S-IB first stage of the Saturn IB rocket | |
Manufacturer | Chrysler[1] |
---|---|
Country of origin | United States |
Used on | Saturn IB (stage 1) |
General characteristics | |
Height | 25.5 m (84 ft) |
Diameter | 6.6 m (22 ft) |
Gross mass | 448,648 kg (989,100 lb) |
Derived from | S-I |
Launch history | |
Status | Retired |
Total launches | 9 |
Successes (stage only) | 9 |
First flight | February 26, 1966 |
Last flight | July 15, 1975 |
Powered by | 8 H-1 engines |
Maximum thrust | 7.1 MN (1,600,000 lbf) |
Specific impulse | 296 s (2.90 km/s) |
Burn time | 155 seconds |
Propellant | RP-1/LOX |
The S-IB stage was the first stage of the Saturn IB launch vehicle, which was used for Earth orbital missions.[2] It was composed of nine propellant containers, eight fins, a thrust structure assembly, eight H-1 rocket engines, and many other components. It also contained the ODOP transponder. The propellant containers consisted of eight Redstone-derived tanks (four holding liquid oxygen (LOX) and four holding RP-1) clustered around a Jupiter rocket-derived tank containing LOX. The four outboard engines gimballed to steer the rocket in flight, which required a few more engine components. The S-IB burned for nearly 2.5 minutes before separating at an altitude of 42 miles (68 km).
Specifications[]
- Height: 80.17 ft (24.44 m)
- Diameter: 21.42 ft (6.53 m)
- Number of fins: 8
- Finspan: 39.42 ft (12.02 m)
- Engines: 8 Rocketdyne H-1
- Thrust: 1,600,000 lbf (7,100 kN)
- Fuel: RP-1 (Refined kerosene) 41,000 US gal (155 m3)
- Oxidizer: Liquid oxygen (LOX) 66,277 US gal (251 m3) nominal capacity including 1.5% ullage volume (43,284 US gal / 163 m3 in four outer tanks plus 22,993 US gal / 87 m3 in center tank[3])
- Burn time: 2.5 min
- Burnout altitude: 37 nmi (69 km)
References[]
- ^ "Saturn IB History". Retrieved 2014-09-01.
- ^ "Saturn IB". Encyclopedia Astronautica.
- ^ NASA Marshall Spaceflight Center, Skylab Saturn IB Flight Manual (MSFC-MAN-206), 30 September 1972
Categories:
- Rocket stages