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gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:certification
|
NASA certified
|
|
gptkbp:check_in_time
|
approximately 8.5 minutes
|
|
gptkbp:combustor_type
|
staged combustion
3,300 degrees Fahrenheit
|
|
gptkbp:control_system
|
digital
|
|
gptkbp:cooling_system
|
active cooling system
|
|
gptkbp:debut
|
gptkb:2015
|
|
gptkbp:designed_for
|
gptkb:Space_Launch_System
|
|
gptkbp:developed_by
|
gptkb:NASA
|
|
gptkbp:development_cost
|
over $1 billion
|
|
gptkbp:durability
|
designed for multiple flights
|
|
gptkbp:engine
|
gptkb:advanced_technology
gptkb:NASA_Michoud_Assembly_Facility
gptkb:Rocketdyne
gptkb:RS-25
vertical
various space missions
ongoing research and development
staged combustion cycle
extensive operational history
upgraded components
|
|
gptkbp:engine_configuration
|
liquid bipropellant
detailed specifications available
upgraded for SLS
|
|
gptkbp:engine_delivery
|
delivered to Kennedy Space Center
|
|
gptkbp:engine_design_life
|
designed for long life
|
|
gptkbp:engine_development_timeline
|
long development timeline
|
|
gptkbp:engine_launch_history
|
multiple launches
|
|
gptkbp:engine_nozzle_type
|
expanding nozzle
|
|
gptkbp:engine_performance_testing
|
rigorous performance testing
|
|
gptkbp:engine_power
|
high reliability
high efficiency
multiple flights
documented performance metrics
|
|
gptkbp:engine_testing_duration
|
varied testing durations
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:first_flight
|
gptkb:2021
|
|
gptkbp:fuel_capacity
|
3.7 meters
4.6 meters
|
|
gptkbp:fuel_type
|
cryogenic
turbopump
|
|
gptkbp:has_programs
|
gptkb:Space_Shuttle
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RS-25 Q
|
|
gptkbp:ignition_system
|
gptkb:spark_plug
|
|
gptkbp:investment
|
approximately 1,000 psi
|
|
gptkbp:is_tested_for
|
gptkb:NASA_Stennis_Space_Center
extensive ground testing
|
|
gptkbp:launch_site
|
gptkb:Kennedy_Space_Center
|
|
gptkbp:number_of_engines
|
four
|
|
gptkbp:operational_status
|
active
|
|
gptkbp:operational_use
|
gptkb:NASA_missions
|
|
gptkbp:oxidizer_pump_type
|
turbopump
|
|
gptkbp:propulsion
|
yes
high thrust-to-weight ratio
approximately 1,100,000 pounds
approximately 512,000 pounds
|
|
gptkbp:successor
|
gptkb:Space_Shuttle_Main_Engine
|
|
gptkbp:used_in
|
gptkb:Artemis_missions
|
|
gptkbp:uses
|
liquid oxygen
liquid hydrogen
|
|
gptkbp:weight
|
approximately 3,000 kg
|
|
gptkbp:bfsParent
|
gptkb:Rocketdyne_RS-25
|
|
gptkbp:bfsLayer
|
5
|