S-IV: Difference between revisions
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The '''S-IV''' was the [[Multistage rocket|second stage]] of the [[Saturn I]], a [[Rocket| rocket-powered]] [[launch vehicle]] used by [[NASA]] for early flights in the [[Project Apollo|Apollo]] program. |
The '''S-IV''' was the [[Multistage rocket|second stage]] of the [[Saturn I]], a [[Rocket| rocket-powered]] [[launch vehicle]] used by [[NASA]] for early flights in the [[Project Apollo|Apollo]] program. |
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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.<ref name="stages1">Bilstein |
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.<ref name="stages1">{{Harvnb|Bilstein|1999|loc=p. 157}}</ref> |
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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-10|RL-10A-3]] engines. Each one of the engines supplied {{convert|66.7|kN}} of thrust for a total of about {{convert|400|kN}}. 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.<ref name="stages2">Bilstein |
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-10|RL-10A-3]] engines. Each one of the engines supplied {{convert|66.7|kN}} of thrust for a total of about {{convert|400|kN}}. 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.<ref name="stages2">{{Harvnb|Bilstein|1999|loc=pp. 166-168}}</ref><ref>{{Harvnb|Apollo Summary Report|1975|loc=p. 187}}</ref> |
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==See also== |
==See also== |
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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}} |
*{{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 | month = April | |
*{{cite web | url = http://history.nasa.gov/alsj/APSR-JSC-09423.pdf |format=PDF| title = Apollo Program Summary Report (Large file) | author = NASA | month = April |year = 1975 |ref=CITEREFApollo_Summary_Report1975}} |
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Revision as of 15:03, 20 August 2010
 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). Stages to Saturn: A Technological History of the Apollo/Saturn Launch. DIANE Publishing. Retrieved 2010-05-04.
{{cite book}}: Text "chapter-6" ignored (help) - NASA (1975). "Apollo Program Summary Report (Large file)" (PDF).
{{cite web}}: Unknown parameter|month=ignored (help)