S-IV: Difference between revisions
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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. |
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 |
== Specifications == |
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Height: 12.19 m<br /> |
Height: 12.19 m<br /> |
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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 |
Burnout altitude (for Saturn I): up to 450 km |
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==See also== |
==See also== |
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Revision as of 21:02, 15 May 2009
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)