|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
satellite launches
|
|
gptkbp:collaboration
|
gptkb:NASA
|
|
gptkbp:combustor_type
|
gas-generator cycle
|
|
gptkbp:competes_with
|
gptkb:Blue_Origin's_BE-4
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:design_purpose
|
reusability
|
|
gptkbp:designed_for
|
launch vehicles
|
|
gptkbp:developed_by
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:development
|
gptkb:2014
|
|
gptkbp:development_cost
|
$1 billion
|
|
gptkbp:diameter
|
5 ft
|
|
gptkbp:engine
|
ongoing
gas generator cycle
|
|
gptkbp:engine_configuration
|
advanced design
single engine
single nozzle
|
|
gptkbp:engine_development_team
|
Aerojet Rocketdyne engineers
|
|
gptkbp:engine_power
|
high efficiency
optimized performance
|
|
gptkbp:engine_testing_schedule
|
2023-2024
|
|
gptkbp:engine_type
|
staged combustion
|
|
gptkbp:environment
|
gptkb:space
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:first_flight
|
gptkb:2020
planned for 2023
|
|
gptkbp:fuel_capacity
|
5 ft
15 ft
2000 lb
|
|
gptkbp:fuel_economy
|
high fuel efficiency
|
|
gptkbp:fuel_type
|
gptkb:RP-1
kerosene
|
|
gptkbp:future_prospects
|
commercial satellite launches
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Aerojet Rocketdyne's AR1
|
|
gptkbp:ignition_system
|
spark ignition
|
|
gptkbp:is_tested_for
|
gptkb:NASA_Stennis_Space_Center
ongoing
hot fire tests
Aerojet Rocketdyne facility
|
|
gptkbp:launch_date
|
2024
up to 10 per year
|
|
gptkbp:launch_platform
|
gptkb:United_Launch_Alliance
|
|
gptkbp:launch_price
|
$100 million
|
|
gptkbp:launch_vehicle
|
gptkb:ULA_Vulcan_Centaur
|
|
gptkbp:length
|
15 ft
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:number_of_rooms
|
1000 psi
|
|
gptkbp:oxidation_states
|
liquid oxygen
cryogenic
|
|
gptkbp:part_of
|
gptkb:Vulcan_Centaur_rocket
|
|
gptkbp:payload_capacity
|
up to 20,000 kg
|
|
gptkbp:performance
|
high thrust-to-weight ratio
|
|
gptkbp:projected_market
|
commercial space market
|
|
gptkbp:projected_service_life
|
20 launches
|
|
gptkbp:projected_thrust
|
500,000 lbf
|
|
gptkbp:propulsion
|
yes
RP-1 and LOX
500,000 lbf
|
|
gptkbp:reliability
|
high reliability
|
|
gptkbp:safety_features
|
redundant systems
|
|
gptkbp:status
|
in development
|
|
gptkbp:uses
|
gptkb:RP-1
liquid oxygen
|
|
gptkbp:weight
|
2,000 lb
|
|
gptkbp:bfsParent
|
gptkb:BE-4_engine
|
|
gptkbp:bfsLayer
|
5
|