|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:space_exploration
|
|
gptkbp:check_in_time
|
approximately 10 minutes
|
|
gptkbp:combustion_chamber_material
|
Inconel
|
|
gptkbp:combustor_type
|
expander cycle
|
|
gptkbp:control_system
|
digital control system
|
|
gptkbp:cooling_system
|
film cooling
|
|
gptkbp:debut
|
multiple launches
|
|
gptkbp:design
|
10 flights
|
|
gptkbp:development
|
gptkb:NASA
2005-2015
|
|
gptkbp:development_cost
|
$100 million
|
|
gptkbp:diameter
|
4.5 ft
|
|
gptkbp:durability
|
not reusable
|
|
gptkbp:elevation
|
up to 100 km
|
|
gptkbp:engine
|
expander cycle
|
|
gptkbp:engine_configuration
|
single engine
single nozzle
|
|
gptkbp:engine_power
|
high performance
|
|
gptkbp:engine_type
|
gptkb:Team_Rocket
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:exhaust_system
|
bell nozzle
|
|
gptkbp:first_flight
|
gptkb:2015
|
|
gptkbp:fuel_economy
|
high efficiency
efficient fuel consumption
|
|
gptkbp:fuel_type
|
liquid hydrogen
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RL10 B-2
|
|
gptkbp:ignition_system
|
pyrotechnic
|
|
gptkbp:investment
|
1,000 psi
|
|
gptkbp:is_tested_for
|
gptkb:NASA's_Marshall_Space_Flight_Center
static fire tests
|
|
gptkbp:key_feature
|
high specific impulse
|
|
gptkbp:launch_platform
|
gptkb:United_Launch_Alliance
|
|
gptkbp:launch_vehicle
|
gptkb:Atlas_V
|
|
gptkbp:length
|
15.5 ft
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:nozzle_expansion_ratio
|
30:1
|
|
gptkbp:number_of_rooms
|
3,000 psi
|
|
gptkbp:operational_status
|
in service
|
|
gptkbp:operational_use
|
satellite launches
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:part_of
|
gptkb:NASA's_Space_Launch_System
|
|
gptkbp:propulsion
|
18.6
22,300 lbf
|
|
gptkbp:specific_impulse
|
450 seconds
|
|
gptkbp:successor
|
gptkb:RL10_C-1
|
|
gptkbp:used_in
|
Centaur upper stage
|
|
gptkbp:weight
|
1,200 lb
|
|
gptkbp:bfsParent
|
gptkb:RL10_rocket_engine
|
|
gptkbp:bfsLayer
|
6
|