S-IB

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[]