S-IV: Difference between revisions
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{{Short description|Upper stage for NASA's Saturn I rocket}} |
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{{Infobox rocket stage |
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|name = S-IV |
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|caption = Schematics of the S-IV |
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|manufacturer = [[Douglas Aircraft Company]] |
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|country = United States |
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|rockets = [[Saturn I]] (stage 2) |
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|height = {{convert|12.19|m|ft|abbr=on}} |
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|diameter = {{convert|5.49|m|ft|abbr=on}} |
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|mass = {{convert|50,576|kg|lb|abbr=on}} |
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|propmass = {{Convert|45,359|kg|lb|sigfig=3|abbr=on}} |
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| empty = {{Convert|5,217|kg|lb|sigfig=3|abbr=on}} |
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| status = Retired |
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| launches = 6 |
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| success = 6 |
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| fail = 0 |
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| first = January 29, 1964 |
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| last = July 30, 1965 |
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{{Infobox rocket/stage |
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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. |
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| name = S-IV 100 series |
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|engines = 6 [[RL-10 (rocket engine)|RL-10]] engines |
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|thrust = {{convert|400|kN|lbf|abbr=on}} |
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| SI = {{Convert|410|isp|abbr=on}} |
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| burntime = 482 s |
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| fuel = [[LH2|LH<sub>2</sub>]] / [[Liquid oxygen|LOX]] |
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}} |
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}} |
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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> |
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| ⚫ | The S-IV stage was a large LOX/ |
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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 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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== Specifications: == |
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Height: 12.19 m<br /> |
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{{reflist}} |
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Diameter: 5.49 m<br /> |
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{{refbegin}} |
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Engines: 6 RL-10<br /> |
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*{{cite book|title=Stages to Saturn: A Technological History of the Apollo/Saturn Launch |url=https://books.google.com/books?id=JnoZTbVLx0MC|author=Bilstein, Roger E.|publisher=DIANE Publishing |year=1999|accessdate=2010-05-04|chapter=6| isbn=9780788181863 |ref=CITEREFBilstein1999}} |
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Thrust: 400 kN<br /> |
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Fuel: liquid hydrogen (LH2)<br /> |
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{{refend}} |
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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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{{Upper stages}} |
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==See also== |
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[[Saturn I#S-IV stage|S-IV stage of the Saturn I]] |
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[[Category:Apollo program]] |
[[Category:Apollo program]] |
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[[Category:Rocket stages]] |
[[Category:Rocket stages]] |
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[[Category:Saturn I]] |
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[[fi:S-IV]] |
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Latest revision as of 00:19, 27 December 2023
 Schematics of the S-IV | |
| Manufacturer | Douglas Aircraft Company |
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| Country of origin | United States |
| Used on | Saturn I (stage 2) |
| General characteristics | |
| Height | 12.19 m (40.0 ft) |
| Diameter | 5.49 m (18.0 ft) |
| Gross mass | 50,576 kg (111,501 lb) |
| Propellant mass | 45,359 kg (100,000 lb) |
| Empty mass | 5,217 kg (11,500 lb) |
| Launch history | |
| Status | Retired |
| Total launches | 6 |
| Successes (stage only) | 6 |
| Failed | 0 |
| First flight | January 29, 1964 |
| Last flight | July 30, 1965 |
| S-IV 100 series | |
| Powered by | 6 RL-10 engines |
| Maximum thrust | 400 kN (90,000 lbf) |
| Specific impulse | 410 s (4.0 km/s) |
| Burn time | 482 s |
| Propellant | LH2 / LOX |
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
[edit]- ^ 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. ISBN 9780788181863. Retrieved 2010-05-04.
- NASA (April 1975). "Apollo Program Summary Report (Large file)" (PDF).