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gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:Space_Launch_System
|
|
gptkbp:burn_duration
|
300 seconds
|
|
gptkbp:combustor_type
|
gas-generator
|
|
gptkbp:control_system
|
digital
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut
|
over 50 launches
|
|
gptkbp:design
|
15 years
|
|
gptkbp:development_cost
|
$100 million
|
|
gptkbp:diameter
|
1.1 m
|
|
gptkbp:engine
|
multiple
expander cycle
|
|
gptkbp:engine_configuration
|
gptkb:single
|
|
gptkbp:engine_type
|
gptkb:RL10-CE
gptkb:Team_Rocket
|
|
gptkbp:exhaust_system
|
expander cycle
|
|
gptkbp:facilities
|
gptkb:NASA_Marshall_Space_Flight_Center
|
|
gptkbp:first_flight
|
gptkb:2016
|
|
gptkbp:fuel_feed_system
|
pump-fed
|
|
gptkbp:fuel_type
|
liquid hydrogen
|
|
gptkbp:gimbal_range
|
10 degrees
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RL10-CE5
|
|
gptkbp:ignition_system
|
gptkb:spark_plug
|
|
gptkbp:launch_vehicle
|
gptkb:Atlas_V
|
|
gptkbp:length
|
3.5 m
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:mission
|
orbital insertion
|
|
gptkbp:number_of_rooms
|
1,000 psi
|
|
gptkbp:operational_period
|
1,000 seconds
|
|
gptkbp:operational_use
|
gptkb:NASA_missions
gptkb:space
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:oxidizer_feed_system
|
pump-fed
|
|
gptkbp:performance
|
high efficiency
|
|
gptkbp:production_status
|
in service
|
|
gptkbp:propulsion
|
18.6
22,300 lbf
LH2/ LOX
|
|
gptkbp:reliability
|
proven
|
|
gptkbp:specific_impulse
|
450 seconds
|
|
gptkbp:success_rate
|
95%
|
|
gptkbp:used_in
|
Centaur upper stage
|
|
gptkbp:weight
|
1,200 lb
|
|
gptkbp:bfsParent
|
gptkb:RL10_engine
|
|
gptkbp:bfsLayer
|
5
|