S-IV: Difference between revisions
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*{{cite book|title=Stages to Saturn: A Technological History of the Apollo/Saturn Launch |url=http://books.google.com/books?id=JnoZTbVLx0MC|author=Bilstein, Roger E.|publisher=DIANE Publishing |year=1999|accessdate=2010-05-04|chapter=6|ref=CITEREFBilstein1999}} |
*{{cite book|title=Stages to Saturn: A Technological History of the Apollo/Saturn Launch |url=http://books.google.com/books?id=JnoZTbVLx0MC|author=Bilstein, Roger E.|publisher=DIANE Publishing |year=1999|accessdate=2010-05-04|chapter=6|ref=CITEREFBilstein1999}} |
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*{{cite web | url = http://history.nasa.gov/alsj/APSR-JSC-09423.pdf |format=PDF| title = Apollo Program Summary Report (Large file) | author = NASA | |
*{{cite web | url = http://history.nasa.gov/alsj/APSR-JSC-09423.pdf |format=PDF| title = Apollo Program Summary Report (Large file) | author = NASA |date=April 1975 |ref=CITEREFApollo_Summary_Report1975}} |
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Revision as of 15:00, 29 January 2014
 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 ft) |
| Diameter | 5.49 m (18 ft) |
| S-IV | |
| Powered by | 6 RL-10 engines |
| Maximum thrust | 400 kN |
| Burn time | ~410 seconds |
| Propellant | LOX/LH2 |
The S-IV was the second stage of the Saturn I, a rocket-powered launch vehicle 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 about ten tons of structural weight.[2][3]
See also
References
- ^ Bilstein 1999, p. 157
- ^ Bilstein 1999, pp. 166-168
- ^ 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).