Difference between revisions of "Template:Infobox rocket engine/doc"
Jump to navigation
Jump to search
imported>WOSlinker (tidy style) |
imported>Anythingcouldhappen (Added gimbal/TVC to all templates; restart & throttle to all but solid) |
||
| Line 42: | Line 42: | ||
|thrust(Vac) = | |thrust(Vac) = | ||
|thrust(SL) = | |thrust(SL) = | ||
| + | |throttle_range = | ||
|thrust_to_weight= | |thrust_to_weight= | ||
|chamber_pressure= | |chamber_pressure= | ||
| Line 49: | Line 50: | ||
|total_impulse = | |total_impulse = | ||
|burn_time = | |burn_time = | ||
| + | |restarts = | ||
| + | |gimbal = | ||
|capacity = | |capacity = | ||
| Line 105: | Line 108: | ||
|total_impulse = | |total_impulse = | ||
|burn_time = | |burn_time = | ||
| + | |gimbal = | ||
|capacity = | |capacity = | ||
| Line 151: | Line 155: | ||
|thrust(Vac) = | |thrust(Vac) = | ||
|thrust(SL) = | |thrust(SL) = | ||
| + | |throttle_range = | ||
|thrust_to_weight= | |thrust_to_weight= | ||
|chamber_pressure= | |chamber_pressure= | ||
| Line 158: | Line 163: | ||
|total_impulse = | |total_impulse = | ||
|burn_time = | |burn_time = | ||
| + | |restarts = | ||
| + | |gimbal = | ||
|capacity = | |capacity = | ||
| Line 202: | Line 209: | ||
|thrust(Vac) = | |thrust(Vac) = | ||
|thrust(SL) = | |thrust(SL) = | ||
| + | |throttle_range = | ||
|thrust_to_weight= | |thrust_to_weight= | ||
|chamber_pressure= | |chamber_pressure= | ||
| Line 209: | Line 217: | ||
|total_impulse = | |total_impulse = | ||
|burn_time = | |burn_time = | ||
| + | |restarts = | ||
| + | |gimbal = | ||
|capacity = | |capacity = | ||
| Line 287: | Line 297: | ||
* '''thrust(SL)''' | * '''thrust(SL)''' | ||
* '''thrust_at_altitude''' | * '''thrust_at_altitude''' | ||
| + | * '''throttle_range''' | ||
* '''thrust_to_weight_ratio''' | * '''thrust_to_weight_ratio''' | ||
| Line 295: | Line 306: | ||
* '''burn_time''' | * '''burn_time''' | ||
| − | + | * '''restarts''' | |
| + | * '''gimbal''' | ||
* '''capacity''' | * '''capacity''' | ||
: tankage | : tankage | ||
Revision as of 04:39, 31 May 2015
| 40px | This is a documentation subpage for Template:Infobox rocket engine. It contains usage information, categories and other content that is not part of the original template page. |
Template:TOCright This template is intended for use on articles about rocket engines. See example for result.
Contents
Empty premade templates
{{Infobox rocket engine
|name =
|image =
|image_size =
|caption =
|country_of_origin=
|date =
|first_date =
|last_date =
|designer =
|manufacturer =
|purpose =
|associated =
|predecessor =
|successor =
|status =
|type =liquid
|oxidiser =
|fuel =
|mixture_ratio =
|cycle =
|pumps =
|description =
|combustion_chamber=
|nozzle_ratio =
|thrust =
|thrust_at_altitude=
|thrust(Vac) =
|thrust(SL) =
|throttle_range =
|thrust_to_weight=
|chamber_pressure=
|specific_impulse=
|specific_impulse_vacuum=
|specific_impulse_sea_level=
|total_impulse =
|burn_time =
|restarts =
|gimbal =
|capacity =
|dimensions =
|length =
|diameter =
|dry_weight =
|used_in =
|references =
|notes =
}}
|
{{Infobox rocket engine
|name =
|image =
|image_size =
|caption =
|country_of_origin=
|date =
|first_date =
|last_date =
|designer =
|manufacturer =
|purpose =
|associated =
|predecessor =
|successor =
|status =
|type =solid
|oxidiser =
|fuel =
|grain =
|core =
|casing =
|nozzle =
|description =
|combustion_chamber=
|nozzle_ratio =
|thrust =
|thrust_at_altitude=
|thrust(Vac) =
|thrust(SL) =
|thrust_to_weight=
|chamber_pressure=
|specific_impulse=
|specific_impulse_vacuum=
|specific_impulse_sea_level=
|total_impulse =
|burn_time =
|gimbal =
|capacity =
|dimensions =
|length =
|diameter =
|dry_weight =
|used_in =
|references =
|notes =
}}
|
{{Infobox rocket engine
|name =
|image =
|image_size =
|caption =
|country_of_origin=
|date =
|first_date =
|last_date =
|designer =
|manufacturer =
|purpose =
|associated =
|predecessor =
|successor =
|status =
|type =hybrid
|oxidiser =
|fuel =
|description =
|combustion_chamber=
|nozzle_ratio =
|thrust =
|thrust_at_altitude=
|thrust(Vac) =
|thrust(SL) =
|throttle_range =
|thrust_to_weight=
|chamber_pressure=
|specific_impulse=
|specific_impulse_vacuum=
|specific_impulse_sea_level=
|total_impulse =
|burn_time =
|restarts =
|gimbal =
|capacity =
|dimensions =
|length =
|diameter =
|dry_weight =
|used_in =
|references =
|notes =
}}
|
{{Infobox rocket engine
|name =
|image =
|image_size =
|caption =
|country_of_origin=
|date =
|first_date =
|last_date =
|designer =
|manufacturer =
|purpose =
|associated =
|predecessor =
|successor =
|status =
|type =mono
|fuel =
|description =
|combustion_chamber=
|nozzle_ratio =
|thrust =
|thrust_at_altitude=
|thrust(Vac) =
|thrust(SL) =
|throttle_range =
|thrust_to_weight=
|chamber_pressure=
|specific_impulse=
|specific_impulse_vacuum=
|specific_impulse_sea_level=
|total_impulse =
|burn_time =
|restarts =
|gimbal =
|capacity =
|dimensions =
|length =
|diameter =
|dry_weight =
|used_in =
|references =
|notes =
}}
|
Parameters
- name
Image
- image
- caption
- imsize
Origins
- country of origin
- date
- first flight
- last flight
- designer
- manufacturer
- purpose - "booster", "apogee kick", etc.
- predecessor
- successor
- associated
- status
Type
- type
- solid
- liquid
- hybrid
- mono / monopropellant
Solids
- oxidiser / fuel
- grain
- core
- casing
- nozzle
liquid
- oxidiser / fuel
- mixture_ratio
- cycle
- pumps
hybrid
- oxidiser / fuel
monopropellant
- fuel
others
Just use the "type" and "description" fields.
Configuration
- description
- combustion_chamber
- nozzle_ratio
Performance
- thrust
- thrust(Vac)
- thrust(SL)
- thrust_at_altitude
- throttle_range
- thrust_to_weight_ratio
- specific_impulse
- specific_impulse_vacuum
- specific_impulse_sea_level
- total_impulse
- burn_time
- restarts
- gimbal
- capacity
- tankage
Dimensions
- dimensions - use for overall description, otherwise use more specific fields
- length
- diameter
- dry_weight
Applications
- used_in
References
- references
- notes
Template:Spaceflight infoboxes