S-IB

Summary

S-IB
Saturn IB 1st stage.jpg
Diagram of the S-IB first stage of the Saturn IB rocket
ManufacturerChrysler[1]
Country of originUnited States
Used onSaturn IB (stage 1)
General characteristics
Height25.5 m (84 ft)
Diameter6.6 m (22 ft)
Gross mass448,648 kg (989,100 lb)
Derived fromS-I
Launch history
StatusRetired
Total launches9
Successes
(stage only)
9
First flightFebruary 26, 1966
Last flightJuly 15, 1975
Engines8 H-1 engines
Thrust7.1 MN (1,600,000 lbf)
Specific impulse296 s (2.90 km/s)
Burn time155 seconds
PropellantRP-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

  1. ^ "Saturn IB History". Retrieved 2014-09-01.
  2. ^ "Saturn IB". Encyclopedia Astronautica.
  3. ^ NASA Marshall Spaceflight Center, Skylab Saturn IB Flight Manual (MSFC-MAN-206), 30 September 1972