S-IV: Difference between revisions
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Winged Brick (talk | contribs) I read the reference and it did not say 10 tons which is HIGHLY implausible. |
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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">{{Harvnb|Bilstein|1999|loc=p. 157}}</ref> |
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">{{Harvnb|Bilstein|1999|loc=p. 157}}</ref> |
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The S-IV stage was a large LOX/LH<sub>2</sub>-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 [[RL10|RL-10A-3]] engines. Each one of the engines supplied {{convert|66.7|kN}} of thrust for a total of about {{convert|400|kN}}. The cryogenic LH<sub>2</sub> ([[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 LH<sub>2</sub> tank. This saved |
The S-IV stage was a large LOX/LH<sub>2</sub>-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 [[RL10|RL-10A-3]] engines. Each one of the engines supplied {{convert|66.7|kN}} of thrust for a total of about {{convert|400|kN}}. The cryogenic LH<sub>2</sub> ([[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 LH<sub>2</sub> tank. This saved up to 20% of structural weight.<ref name="stages2">{{Harvnb|Bilstein|1999|loc=pp. 166-168}}</ref><ref>{{Harvnb|Apollo Summary Report|1975|loc=p. 187}}</ref> |
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==References== |
==References== |
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Revision as of 22:39, 31 October 2016
 Schematics of the S-IV | |
| Manufacturer | Douglas Aircraft Company |
|---|---|
| Country of origin | United States |
| 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 | 400 kN |
| Burn time | ~410 seconds |
| Propellant | LOX/LH2 |
The S-IV was the second stage of the Saturn I rocket 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-10A-3 engines. Each one of the engines supplied 66.7 kilonewtons (15,000 lbf) of thrust for a total of about 400 kilonewtons (90,000 lbf). 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 up to 20% of structural weight.[2][3]
References
- ^ Bilstein 1999, p. 157
- ^ Bilstein 1999, pp. 166-168
- ^ Apollo Summary Report 1975, p. 187
- Bilstein, Roger E. (1999). "6". Stages to Saturn: A Technological History of the Apollo/Saturn Launch. DIANE Publishing. Retrieved 2010-05-04.
- NASA (April 1975). "Apollo Program Summary Report (Large file)" (PDF).