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Saturn IB 1st stage.jpg
Diagram of the S-IB first stage of the Saturn IB rocket
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
Total launches9
(stage only)
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

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).


  1. ^ "Saturn IB History". Retrieved 2014-09-01.
  2. ^ "Saturn IB". Encyclopedia Astronautica.