 | This is a documentation subpage for Template:Infobox rocket stage. It may contain usage information, categories and other content that is not part of the original template page. |
 | This template uses Lua:
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| [[File:{{{image}}}|{{{image_size}}}|alt={{{alt}}}]]
{{{caption}}}
| |
| Manufacturer | {{{manufacturer}}} |
|---|---|
| Country of origin | {{{country-origin}}} |
| Used on | {{{rockets}}} |
| General characteristics | |
| Height | {{{height}}} ({{{alt-height}}}) |
| Diameter | {{{diameter}}} ({{{alt-diameter}}}) |
| Length | {{{length}}} |
| Width | {{{width}}} |
| Gross mass | {{{mass}}} ({{{alt-mass}}}) |
| Propellant mass | {{{propmass}}} ({{{alt-propmass}}}) |
| Empty mass | {{{empty}}} |
| Stages | {{{stages}}} |
| Associated stages | |
| Family | {{{family}}} |
| Derived from | {{{derived_from}}} |
| Derivatives | {{{derivatives}}} |
| Comparable | {{{comparable}}} |
| Launch history | |
| Status | {{{status}}} |
| Total launches | {{{launches}}} |
| Successes (stage only) | {{{success}}} |
| Failed | {{{fail}}} |
| Lower stage failed | {{{noburn}}} |
| Other | {{{other_outcome}}} |
| First flight | {{{first}}} |
| Last flight | {{{last}}} |
| Launch date | {{{only}}} |
| {{{stagedata}}} | |
| {{{name}}} | |
| Powered by | {{{engines}}} |
| Maximum thrust | {{{thrust}}} |
| Specific impulse | {{{SI}}} |
| Burn time | {{{time}}} |
| Propellant | {{{fuel}}} |
All parameters except engines, thrust, and fuel are optional.
{{Infobox rocket stage
<!-- Image -->
| image = <!--image filename (omit "Image:" prefix)-->
| caption = <!--image caption-->
<!-- Basic information -->
| name = <!--becomes infobox title-->
| manufacturer = <!--stage manufacturer-->
| country = <!--country of origin, do not use flag-->
| rockets = <!--vehicle(s) stage was used on-->
<!-- General characteristics -->
| height = <!--height in meters, use {{convert}}-->
| diameter = <!--diameter in meters, use {{convert}}-->
| mass = <!--gross mass in kilograms, use {{convert}}-->
| propmass = <!--propellant mass in kilograms, use {{convert}}-->
| empty = <!--dry mass in kilograms, use {{convert}}-->
<!-- Associated Stages -->
| family = <!--if a member of a family of stages-->
| derived_from = <!--if derived from another stage or stages-->
| derivatives = <!--if derivative stages-->
| comparable = <!--if any similar, unrelated stage-->
<!-- Launch history -->
| status = <!--active, retired, under development, cancelled, etc-->
| launches = <!--total launches to date-->
| success = <!--number of times stage has operated successfully-->
| fail = <!--number of times stage itself has failed-->
| noburn = <!--lower stage failed-->
| other_outcome = <!--other-->
| first = <!--date of first flight-->
| last = <!--date of last flight-->
| only = <!--date of launch if stage flew only once-->
<!--Engine details (optional)-->
| stagedata = <!--insert one of the following templates for each engine types:-->
{{Infobox rocket/stage
| name =
| engines = <!--number of engines used on the rocket stage-->
| solid = <!--set to "yes" (lowercase) to change Engines to Motor for solid motors-->
| thrust = <!--thrust provided by a single engine in kN, use {{cvt|THRUST|kN}}-->
|SI= <!--specific impulse of an individual engine, in seconds, use {{convert|ISP_IN_SECONDS|isp}}-->
| burntime = <!--burn time-->
| fuel = <!--fuel used in engine-->
}}
}}
These parameters are supported by the template to allow it to display properly on articles that have not yet been converted to the new format. They should not be introduced into new articles/transclusions.
| alt-height = <!--height in feet-->
| alt-diameter = <!--diameter in feet-->
| alt-mass = <!--gross mass in pounds-->
| alt-propmass = <!--propellant mass in pounds-->
| alt-thrust = <!--thrust in lbf-->
<!-- Engine details -->
| engines = <!--number and type of engines used stage, required-->
| thrust = <!--thrust provided by stage in kN, use {{convert}}, required-->
| SI = <!--specific impulse of stage in s-->
| time = <!--stage burn time in s -->
| fuel = <!--propellant used in stage, required-->
| |
| Manufacturer | North American |
|---|---|
| Country of origin | USA |
| Used on | Saturn V (stage 2) Saturn INT-21 (stage 2) |
| General characteristics | |
| Height | 24.9 m (82 ft) |
| Diameter | 10 m (33 ft) |
| Gross mass | 480,000 kg (1,058,000 lb) |
| Propellant mass | 443,000 kg (977,000 lb) |
| Empty mass | 36,200 kg (79,700 lb) |
| Launch history | |
| Status | Retired |
| Total launches | 13 |
| Successes (stage only) | 12 |
| Other | Partial failure (Apollo 6) |
| First flight | November 9, 1967 (AS-501) Apollo 4 |
| Last flight | May 14, 1973 (AS-513) Skylab 1 |
| Saturn V S-II | |
| Powered by | 5Rocketdyne J-2 |
| Maximum thrust | 4,400 kN (1,000,000 lbf) |
| Specific impulse | 421 seconds (4.13 km/s) |
| Burn time | 367 s |
| Propellant | LOX/LH2 |
{{Infobox rocket stage
| image = ap6-MSFC-6758331.jpg
| caption = The [[Apollo 6]] S-II stage during stacking operations in the [[Vehicle Assembly Building|VAB]]
| name = S-II
| manufacturer = [[North American Aviation|North American]]
| country = USA
| rockets = [[Saturn V]] (stage 2)<br>[[Saturn INT-21]] (stage 2)
| height = {{convert|24.9|m|abbr=on}}
| diameter = {{convert|10|m|abbr=on}}
| mass = {{convert|1058000|lbs|abbr=on|order=flip}}
| propmass = {{convert|977000|lbs|abbr=on|order=flip}}
| empty = {{convert|79700|lbs|abbr=on|order=flip}}
| status = Retired
| launches =13| success =12| other_outcome = Partial failure ([[Apollo 6]])
| first = November 9, 1967 (AS-501) [[Apollo 4]]
| last = May 14, 1973 (AS-513) [[Skylab 1]]
| stagedata =
{{Infobox rocket/stage
| name = Saturn V S-II
| engines =5[[Rocketdyne J-2]]
| thrust = {{convert|1000000|lbf|kN|abbr=on|order=flip}}
|SI= {{convert|421|isp}}
| burntime = 367 s
| fuel = [[Liquid oxygen|LOX]]/[[Liquid hydrogen|LH<sub>2</sub>]]
}}
}}
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| Spaceflight |
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| Spacecraft |
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| Space program |
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| Rocketry |
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