Schematics of the S-IV
|Manufacturer||Douglas Aircraft Company|
|Country of origin||United States|
|Used on||Saturn I (stage 2)|
|Height||12.19 m (40.0 ft)|
|Diameter||5.49 m (18.0 ft)|
|Gross mass||50,576 kg (111,501 lb)|
|Propellant mass||45,359 kg (100,000 lb)|
|Empty mass||5,217 kg (11,500 lb)|
|First flight||January 29, 1964|
|Last flight||July 30, 1965|
|S-IV 100 series|
|Engines||6 RL-10 engines|
|Thrust||400 kN (90,000 lbf)|
|Specific impulse||410 s (4.0 km/s)|
|Burn time||482 s|
The S-IV stage was a large LOX/LH2-fueled rocket stage used for the early test flights of the Saturn I rocket. It formed the second stage of the Saturn I and was powered by a cluster of six RL-10A-3 engines. Each one of the engines supplied 66.7 kilonewtons (15,000 lbf) of thrust for a total of about 400 kilonewtons (90,000 lbf). The cryogenic LH2 (liquid hydrogen) and LOX (liquid oxygen) tanks were separated by a common bulkhead. The forward bulkhead of the LOX tank formed the aft bulkhead of the LH2 tank. This saved up to 20% of structural weight.
- Bilstein, Roger E. (1999). "6". Stages to Saturn: A Technological History of the Apollo/Saturn Launch. DIANE Publishing. Retrieved 2010-05-04.
- NASA (April 1975). "Apollo Program Summary Report (Large file)" (PDF).