This template is intended for use on articles about rocket engines. See example for result.   Empty premade templates   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   = |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   = |burn_time       = |gimbal          =<!--gimbal range in °, or other TVC method, leave blank if none--> |capacity        =  |dimensions      = |length          = |diameter        = |dry_weight      =  |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   = |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           = }}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   = |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 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'''  Rocket engine Rocket engine