S-IV: Difference between revisions
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{{Infobox rocket stage |
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|name = S-IV |
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|image = S-IV rocket stage.jpg |
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|caption = Schematics of the S-IV |
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|manufacturer = [[Douglas Aircraft Company|Douglas]] |
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|country = USA |
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|rockets = [[Saturn I]] (stage 2) |
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|height = 12.19 m |
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|alt-height = 40 ft |
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|diameter = 5.49 m |
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|alt-diameter = 18 ft |
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|mass = |
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|alt-mass = |
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|engines = 6 [[RL-10 (rocket engine)|RL-10]] engines |
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|thrust = 600 kN |
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|alt-thrust = 134'885 lbf |
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|time = ~410 seconds |
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|fuel = [[LOX]]/[[LH2]] |
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}} |
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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 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. |
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== Specifications == |
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Height: 12.19 m<br /> |
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Diameter: 5.49 m<br /> |
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Engines: 6 RL-10<br /> |
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Thrust: 400 kN<br /> |
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Fuel: liquid hydrogen (LH2)<br /> |
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Oxidizer: liquid oxygen (LOX)<br /> |
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Burn time: approx. 410 s<br /> |
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Burnout altitude (for Saturn I): up to 450 km |
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==See also== |
==See also== |
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Revision as of 14:02, 5 April 2010
 Schematics of the S-IV | |
| Manufacturer | Douglas |
|---|---|
| Country of origin | USA |
| 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 | 600 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 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 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.
See also
References
NASA (1975). "Apollo Program Summary Report, Part 1" (PDF). {{cite web}}: Unknown parameter |month= ignored (help)