Template:Infobox rocket engine/doc

This template is intended for use on articles about rocket engines and spacecraft propulsion. See example for result.

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Liquid engines {{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 = }}

Solid engines {{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 = |gross = |used_in = |references = |notes = }}

Hybrid engines {{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 = |gross = |used_in = |references = |notes = }}

Monopropellant engines {{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 = }}

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

• mass_flow

• burn_time
• restarts
• gimbal
• capacity

tankage

Dimensions

• dimensions - use for overall description, otherwise use more specific fields
• length
• diameter
• dry_weight
• gross

Applications

• used_in

References

• references
• notes

Tracking Categories

• Category:Pages using infobox rocket engine with conflicting parameters (0)
• Category:Pages using infobox rocket engine with unknown parameters (0)
• Category:Rocket engines of the United Kingdom (13)
• Category:Rocket engines of the Soviet Union (58)
• Category:Monopropellant rocket engines (3)

Template Data

TemplateData documentation used by VisualEditor and other tools

See a monthly parameter usage report for Template:Infobox rocket engine in articles based on its TemplateData.

TemplateData for Infobox rocket engine

No description.

Template parameters

This template has custom formatting.

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}} Example {{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}} Example {{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) Suggested values liquid solid hybrid mono	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}} Example {{cvt|VALUEHERE|kN}}	String	optional
Thrust, sea level	thrust(SL)	Thrust of the engine, at sea level, use {{cvt|VALUEHERE|kN}} Example {{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}} Example {{cvt|VALUEHERE|isp}}	String	optional
Specific impulse, vacuum	specific_impulse_sea_level	Specific impulse of the engine, at sea level, use {{cvt|VALUEHERE|isp}} Example {{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 Example NNN 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--> Example NN°	String	optional
dimensions	dimensions	no description	Unknown	optional
Length	length	Length of the engine, in metres, use {{cvt|VALUE|m}} Example {{cvt|VALUE|m}}	String	optional
Diameter	diameter	Diameter of the engine at widest part (typically nozzle tip), in metres, use {{cvt|VALUE|m}} Example {{cvt|VALUE|m}}	String	optional
Dry weight	dry_weight	Mass of unfueled rocket engine in kilograms, use {{cvt|MASS|kg}} Example {{cvt|MASS|kg}}	String	optional
Gross mass	gross	Mass of solid rocket motor with propellant in kilograms, use {{cvt|MASS|kg}} Example {{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