S-IV

S-IV
Schematics of the S-IV
Manufacturer Douglas Aircraft Company
Country of origin United States
Used on Saturn I (stage 2)
General characteristics
Height 12.19 m (40.0 ft)
Diameter 5.49 m (18.0 ft)
Engine details
Engines 6 RL-10 engines
Thrust 400 kN (90,000 lbf)
Burn time ~410 seconds
Fuel LOX/LH2

The S-IV was the second stage of the Saturn I rocket used by NASA for early flights in the Apollo program.

The S-IV was manufactured by the Douglas Aircraft Company and later modified by them to the S-IVB, a similar but distinct stage used on the Saturn IB and Saturn V rockets.[1]

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.[2][3]

References

  1. ↑ Bilstein 1999, p. 157
  2. ↑ Bilstein 1999, pp. 166-168
  3. ↑ Apollo Summary Report 1975, p. 187

  • 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).
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