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gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:NASA's_Space_Launch_System
|
|
gptkbp:average_temperature
|
-253 ° C
|
|
gptkbp:check_in_time
|
approximately 10 minutes
|
|
gptkbp:combustor_type
|
expander cycle
|
|
gptkbp:control_system
|
electronic control system
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:designed_by
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:development
|
1970s
|
|
gptkbp:development_cost
|
$100 million
|
|
gptkbp:diameter
|
4.5 ft
|
|
gptkbp:engine
|
expander cycle
|
|
gptkbp:engine_configuration
|
single nozzle
|
|
gptkbp:engine_type
|
gptkb:Team_Rocket
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:exhaust_system
|
bell nozzle
|
|
gptkbp:first_flight
|
gptkb:1998
|
|
gptkbp:fuel_type
|
liquid hydrogen
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RL10 A-3
|
|
gptkbp:ignition_system
|
pyrotechnic ignition
|
|
gptkbp:is_tested_for
|
flight tests
static fire tests
qualification tests
acceptance tests
development tests
|
|
gptkbp:launch_vehicle
|
gptkb:Delta_IV
gptkb:Space_Launch_System
gptkb:Atlas_V
|
|
gptkbp:length
|
15.5 ft
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:notable_launches
|
Centaur upper stage
|
|
gptkbp:number_of_rooms
|
1,000 psi
single combustion chamber
|
|
gptkbp:operational_status
|
in service
|
|
gptkbp:operational_use
|
gptkb:space_mission
satellite launches
crew missions
interplanetary missions
cargo missions
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:project
|
improved efficiency
increased thrust
RL10 C-1 upgrades
|
|
gptkbp:propulsion
|
18.6
22,300 lbf
gimbal system
|
|
gptkbp:reliability
|
high
|
|
gptkbp:safety_record
|
excellent
|
|
gptkbp:specific_impulse
|
450 seconds
|
|
gptkbp:successor
|
gptkb:RL10_C-1
|
|
gptkbp:used_in
|
upper stage of launch vehicles
|
|
gptkbp:weight
|
1,200 lb
|
|
gptkbp:bfsParent
|
gptkb:RL10_rocket_engine
|
|
gptkbp:bfsLayer
|
6
|