S-IV

**S-IV**
General characteristics
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 ft)
Diameter	5.49 m (18 ft)

Engine details
Engines	6 RL-10 engines
Thrust	400 kN
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 lb_f) of thrust for a total of about 400 kilonewtons (90,000 lb_f). 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

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).

Upper stages

Active	Briz-KM Briz-M Castor 30 Centaur DM-03 Delta-K DCSS Fregat Volga SMA Star 27 Star 37 Star 48 Yuanzheng-1

Planned	Exploration Upper Stage KVTK

Retired	Agena Able Altair Astris Blok 2BL Blok D Burner Delta-D Delta-P EPKM FG-02 Ikar Inertial Upper Stage KVD-1 Payload Assist Module Saturn IV Saturn IVB Transfer Orbit Stage Transtage

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