S-IB

S-IB
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
Powered by8 H-1 engines
Maximum 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 an upgraded version of the S-I stage used on the earlier Saturn I rocket and 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).

  1. ^ Cite error: The named reference :0 was invoked but never defined (see the help page).
  2. ^ Wade, Mark (2001). "Saturn IB". Encyclopedia Astronautica. Archived from the original on May 4, 2002.