![]() | This template uses Lua: |
This template is intended for use on articles about rocket engines and spacecraft propulsion. See example for result.
{{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) =<!--if throttle range >100%, specify corresponding throttle-->
|thrust(SL) =
|throttle_range =<!--leave blank if no throttle-->
|thrust_to_weight=
|chamber_pressure=
|specific_impulse=
|specific_impulse_vacuum=
|specific_impulse_sea_level=
|total_impulse =
|mass_flow =
|burn_time =
|restarts =<!--leave blank if not restartable-->
|gimbal =<!--gimbal range in °, leave blank if none-->
|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 =
|mass_flow =
|burn_time =
|gimbal =<!--gimbal range in °, or other TVC method, leave blank if none-->
|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) =<!--if throttle range >100%, specify corresponding throttle-->
|thrust(SL) =
|throttle_range =<!--leave blank if no throttle-->
|thrust_to_weight=
|chamber_pressure=
|specific_impulse=
|specific_impulse_vacuum=
|specific_impulse_sea_level=
|total_impulse =
|mass_flow =
|burn_time =
|restarts =<!--leave blank if not restartable-->
|gimbal =<!--gimbal range in °, leave blank if none-->
|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) =<!--if throttle range >100%, specify corresponding throttle-->
|thrust(SL) =
|throttle_range =<!--leave blank if no throttle-->
|thrust_to_weight=
|chamber_pressure=
|specific_impulse=
|specific_impulse_vacuum=
|specific_impulse_sea_level=
|total_impulse =
|mass_flow =
|burn_time =
|restarts =<!--leave blank if not restartable-->
|gimbal =<!--gimbal range in °, leave blank if none-->
|capacity =
|dimensions =
|length =
|diameter =
|dry_weight =
|used_in =
|references =
|notes =
}}
|
Just use the "type" and "description" fields.
No description.
Parameter | Description | Type | Status | |
---|---|---|---|---|
Name | name | Name of the rocket engine | String | optional |
Image | image | Filename for image of the rocket engine, do not include the "File:" or "Image:" prefix | File | optional |
Image size | image_size imsize | Image size in pixels | String | optional |
alt | alt | no description | Unknown | optional |
image_alt | image_alt | no description | Unknown | optional |
Caption | caption | Image caption | String | optional |
Country of origin | country_of_origin | Country of origin | String | optional |
date | date | no description | Unknown | optional |
First flight date | first_date | Date of the first flight, use {{Start date|YYYY|MM|DD|df=y}}
| String | optional |
Last flight date | last_date | Date of the last flight, use {{End date|YYYY|MM|DD|df=y}}
| String | optional |
Designer | designer | Designer of the engine, can be linked | String | optional |
Manufacturer | manufacturer | Manufacturer of the engine, can be linked, but do not link if the same as the designer | String | optional |
purpose | purpose | no description | Unknown | optional |
Associated launch vehicles | associated | List of launch vehicles this rocket engine is associated with | String | optional |
Predecessor | predecessor | Predecessor rocket engine | String | optional |
Successor | successor | Successor rocket engine | String | optional |
status | status | no description | Unknown | optional |
Type | type | Type of rocket engine, use liquid, solid, hybrid or mono (for monopropellant)
| String | required |
Fuel | fuel | Type of fuel used | String | optional |
Oxidizer | oxidizer oxidiser | Type of oxidizer used | String | optional |
grain | grain | no description | Unknown | optional |
core | core | no description | Unknown | optional |
casing | casing | no description | Unknown | optional |
nozzle | nozzle | no description | Unknown | optional |
mixture_ratio | mixture_ratio | no description | Unknown | optional |
cycle | cycle | no description | Unknown | optional |
pumps | pumps | no description | Unknown | optional |
combustion_chamber | combustion_chamber | no description | Unknown | optional |
nozzle_ratio | nozzle_ratio | no description | Unknown | optional |
description | description | no description | Unknown | optional |
Thrust, vacuum | thrust(Vac) | Thrust of the engine, in vacuum, use {{cvt|VALUEHERE|kN}}
| String | optional |
Thrust, sea level | thrust(SL) | Thrust of the engine, at sea level, use {{cvt|VALUEHERE|kN}}
| String | optional |
Thrust | thrust | no description | Unknown | deprecated |
thrust_at_altitude | thrust_at_altitude | no description | Unknown | optional |
thrust_to_weight | thrust_to_weight | no description | Unknown | optional |
chamber_pressure | chamber_pressure | no description | Unknown | optional |
Specific impulse | specific_impulse | no description | Unknown | deprecated |
Specific impulse, vacuum | specific_impulse_vacuum | Specific impulse of the engine, in vacuum, use {{cvt|VALUEHERE|isp}}
| String | optional |
Specific impulse, vacuum | specific_impulse_sea_level | Specific impulse of the engine, at sea level, use {{cvt|VALUEHERE|isp}}
| Unknown | optional |
total_impulse | total_impulse | no description | Unknown | optional |
Burn time | burn_time | The length of time the engine burns normally, in seconds
| String | optional |
capacity | capacity | no description | Unknown | optional |
throttle_range | throttle_range | no description | Unknown | optional |
mass_flow | mass_flow | no description | Unknown | optional |
Restarts | restarts | How many times the engine can be restarted, leave blank if not restartable | Unknown | optional |
Gimbal range | gimbal | Gimbal range in °, leave blank if none-->
| String | optional |
dimensions | dimensions | no description | Unknown | optional |
Length | length | Length of the engine, in metres, use {{cvt|VALUE|m}}
| String | optional |
Diameter | diameter | Diameter of the engine at widest part (typically nozzle tip), in metres, use {{cvt|VALUE|m}}
| String | optional |
Dry weight | dry_weight | Mass of unfueled rocket engine in kilograms, use {{cvt|MASS|kg}}
| String | optional |
used_in | used_in | no description | Unknown | optional |
embedded | embedded | no description | Unknown | optional |
module | module | no description | Unknown | optional |
references | references | no description | Unknown | optional |
notes | notes | no description | Unknown | optional |