S-IV: Difference between revisions
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[[Image:S-IV rocket stage.jpg|thumb]] |
[[Image:S-IV rocket stage.jpg|thumb]] |
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The '''S-IV''' was the [[Multistage rocket |
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 is similar to, but distinct from, the later [[S-IVB]] stage used on the [[Saturn IB]] and [[Saturn V]] rockets. |
The S-IV is similar to, but distinct from, the later [[S-IVB]] stage used on the [[Saturn IB]] and [[Saturn V]] rockets. |
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Oxidizer: liquid oxygen (LOX)<br /> |
Oxidizer: liquid oxygen (LOX)<br /> |
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Burn time: approx. 410 s<br /> |
Burn time: approx. 410 s<br /> |
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Burnout altitude (for Saturn I): up to 450 km |
Burnout altitude (for Saturn I): up to 450 km |
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==See also== |
==See also== |
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[[Saturn I#S-IV stage |
[[Saturn I#S-IV stage|S-IV stage of the Saturn I]] |
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==References== |
==References== |
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{{cite web | url = http://history.nasa.gov/apsr/Apollopt1-1.pdf | title = Apollo Program Summary Report, Part 1 | author = NASA | |
{{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 }} |
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[[Category:Apollo program]] |
[[Category:Apollo program]] |
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Revision as of 19:30, 28 December 2008
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 is similar to, but distinct from, the later S-IVB stage used on the Saturn IB and Saturn V rockets.
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 Satun 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.
Specifications:
Height: 12.19 m
Diameter: 5.49 m
Engines: 6 RL-10
Thrust: 400 kN
Fuel: liquid hydrogen (LH2)
Oxidizer: liquid oxygen (LOX)
Burn time: approx. 410 s
Burnout altitude (for Saturn I): up to 450 km
See also
References
NASA (1975). "Apollo Program Summary Report, Part 1" (PDF). {{cite web}}: Unknown parameter |month= ignored (help)