Jump to content

S-IV: Difference between revisions

From Wikipedia, the free encyclopedia
Browse history interactively
← Previous editNext edit →
Content deleted Content added
VisualWikitext
Added infobox instead of specifications.
No edit summary
Line 3: Line 3:
|image = S-IV rocket stage.jpg
|image = S-IV rocket stage.jpg
|caption = Schematics of the S-IV
|caption = Schematics of the S-IV
|manufacturer = [[Douglas Aircraft Company|Douglas]]
|manufacturer = [[Douglas Aircraft Company]]
|country = USA
|country = United States
|rockets = [[Saturn I]] (stage 2)
|rockets = [[Saturn I]] (stage 2)
|height = 12.19 m
|height = 12.19 m
Line 18: Line 18:
|fuel = [[LOX]]/[[LH2]]
|fuel = [[LOX]]/[[LH2]]
}}
}}
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.


The S-IV is similar to, but distinct from, the later [[S-IVB]] stage used on the [[Saturn IB]] and [[Saturn V]] rockets.
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 1999 p. 157</ref>


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]] engines. 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.
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]] engines. 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 1999 pp. 166-168</ref>


==See also==
==See also==
[[Saturn I#S-IV stage|S-IV stage of the Saturn I]]
[[Saturn I#S-IV stage|S-IV stage of the Saturn I]]

==References==
==References==
{{reflist}}
⚫
{{cite web | url = http://history.nasa.gov/apsr/Apollopt1-1.pdf |format=PDF| title = Apollo Program Summary Report, Part 1 | author = NASA | month = April | year = 1975 }}
{{refbegin}}
*{{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 web | url = http://history.nasa.gov/apsr/Apollopt1-1.pdf |format=PDF| title = Apollo Program Summary Report, Part 1 | author = NASA | month = April | year = 1975 }}
{{refend}}


[[Category:Apollo program]]
[[Category:Apollo program]]

Revision as of 14:29, 5 April 2010

S-IV
Schematics of the S-IV
ManufacturerDouglas Aircraft Company
Country of originUnited States
Used onSaturn I (stage 2)
General characteristics
Height12.19 m (40 ft)
Diameter5.49 m (18 ft)
S-IV
Powered by6 RL-10 engines
Maximum thrust600 kN
Burn time~410 seconds
PropellantLOX/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-10 engines. 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]

See also

S-IV stage of the Saturn I

References

  1. ^ Bilstein 1999 p. 157
  2. ^ Bilstein 1999 pp. 166-168
  • 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, Part 1" (PDF). {{cite web}}: Unknown parameter |month= ignored (help)
Retrieved from "https://en.wikipedia.org/w/index.php?title=S-IV&oldid=354109225"