|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
satellite launches
|
|
gptkbp:check_in_time
|
approximately 300 seconds
|
|
gptkbp:combustor_type
|
gas-generator cycle
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:current_status
|
in production
|
|
gptkbp:design
|
gptkb:NASA_Marshall_Space_Flight_Center
10 years
|
|
gptkbp:development
|
gptkb:NASA
|
|
gptkbp:development_cost
|
$100 million
|
|
gptkbp:engine
|
staged combustion
|
|
gptkbp:engine_configuration
|
single nozzle
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:exhaust_system
|
bell nozzle
|
|
gptkbp:first_flight
|
gptkb:1963
Centaur in 1970
|
|
gptkbp:flight_style
|
over 200
|
|
gptkbp:fuel_type
|
liquid hydrogen
|
|
gptkbp:has_variations
|
multiple
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RL10
|
|
gptkbp:ignition_system
|
gptkb:spark_plug
|
|
gptkbp:inspiration
|
future rocket designs
|
|
gptkbp:key_feature
|
high efficiency
|
|
gptkbp:launch_vehicle
|
multiple launch vehicles
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:notable_achievements
|
first use of liquid hydrogen in a rocket engine
|
|
gptkbp:notable_mission
|
Centaur upper stage
|
|
gptkbp:notable_users
|
gptkb:Atlas_V
|
|
gptkbp:number_of_rooms
|
1,000 psi
|
|
gptkbp:operated_by
|
gptkb:United_Launch_Alliance
|
|
gptkbp:operational_history
|
over 50 years
|
|
gptkbp:operational_status
|
in service
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:part_of
|
gptkb:NASA's_Space_Launch_System
|
|
gptkbp:project
|
gptkb:RL10_X
|
|
gptkbp:propulsion
|
22,000 lbf
18.3
LH2/ LOX
|
|
gptkbp:reliability
|
high
|
|
gptkbp:specific_impulse
|
450 seconds
|
|
gptkbp:successor
|
gptkb:RL10_C
|
|
gptkbp:used_in
|
gptkb:Delta_IV
gptkb:Centaur_AC
gptkb:Centaur_D
gptkb:Centaur_G
gptkb:Centaur_G_Prime
gptkb:Centaur_IV
gptkb:Centaur_II
gptkb:Atlas_II
upper stage of rockets
|
|
gptkbp:weight
|
1,200 lb
|
|
gptkbp:bfsParent
|
gptkb:Delta_Cryogenic_Second_Stage
gptkb:Atlas-Centaur
gptkb:Aerojet_Rocketdyne_engines
|
|
gptkbp:bfsLayer
|
5
|