Template:Infobox rocket stage/sandbox

Side by side comparison

{{Infobox rocket stage}}

{{Infobox rocket stage/sandbox}}

"name" "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" Ares V EDS P516 1 J-2X P2228 1,310 kilonewtons (290,000 lbf) Specific impulse 448 seconds (vacuum) Propellant LH2/LOX SLS Block II EDS P2048 24 metres (79 ft) P516 3 J-2X P2228 3,930 kilonewtons (880,000 lbf) Specific impulse 448 seconds (vacuum) Propellant LH2/LOX "name" P516 "engines" P2228 "thrust" Specific impulse "SI" Burn time "time" Propellant "fuel"

"name" "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" Ares V EDS P516 1 J-2X P2228 1,310 kilonewtons (290,000 lbf) Specific impulse 448 seconds (vacuum) Propellant LH2/LOX SLS Block II EDS P2048 24 metres (79 ft) P516 3 J-2X P2228 3,930 kilonewtons (880,000 lbf) Specific impulse 448 seconds (vacuum) Propellant LH2/LOX Engine details P516 "engines" P2228 "thrust" Specific impulse "SI" Burn time "time" Propellant "fuel"

Template documentation[view] [edit] [history] [purge]

Usage

{{{name}}}

[[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}}}
Engine details
P516	{{{engines}}}
P2228	{{{thrust}}}
Specific impulse	{{{SI}}}
Burn time	{{{time}}}
Propellant	{{{fuel}}}

All parameters except engines, thrust, and fuel are optional.

<syntaxhighlight lang="wikitext" style="overflow:auto;">

</syntaxhighlight>

Obsolete (legacy) parameters

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.

<syntaxhighlight lang="wikitext" style="overflow:auto;"> | alt-height = | alt-diameter = | alt-mass = | alt-propmass = | alt-thrust = | engines = | thrust = | SI = | time = | fuel = </syntaxhighlight>

Example

S-II

The Apollo 6 S-II stage during stacking operations in the VAB
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
P516	5 Rocketdyne J-2
P2228	4,400 kN (1,000,000 lbf)
Specific impulse	421 seconds (4.13 km/s)
Burn time	367 s
Propellant	LOX/LH2

<syntaxhighlight lang="wikitext" style="overflow:auto;">

S-II

The Apollo 6 S-II stage during stacking operations in the VAB
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
P516	5 Rocketdyne J-2
P2228	4,400 kN (1,000,000 lbf)
Specific impulse	421 seconds (4.13 km/s)
Burn time	367 s
Propellant	LOX/LH2

</syntaxhighlight>

Tracking categories

• Category:Pages using infobox rocket stage with unknown parameters (0)
• Category:Rocketry articles with outdated infoboxes (23)

See also

The above documentation is transcluded from Template:Infobox rocket stage/doc. (edit | history)
Editors can experiment in this template's sandbox (edit | diff) and testcases (create) pages.
Add categories to the /doc subpage. Subpages of this template.