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 is similar to, but distinct from, the [[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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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. |
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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<br /> |
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==See also== |
==See also== |
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Revision as of 22:56, 14 May 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 (April 1975). "Apollo Program Summary Report, Part 1" (PDF).