|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
launch vehicles
|
|
gptkbp:challenges
|
engine performance optimization
|
|
gptkbp:check_in_time
|
approximately 150 seconds
|
|
gptkbp:collaboration
|
gptkb:NASA
|
|
gptkbp:combustor_type
|
gas-generator cycle
|
|
gptkbp:competitors
|
gptkb:Space_X_Merlin
gptkb:Arianespace_Vulcain_engine
gptkb:Blue_Origin_BE-4_engine
gptkb:ISRO's_Kestrel_engine
gptkb:India's_GSLV_engine
gptkb:Mitsubishi_Heavy_Industries_LE-7_engine
gptkb:Northrop_Grumman_Omeg_A_engine
gptkb:Relativity_Space_Terran_1_engine
gptkb:Rocket_Lab_Electron_engine
gptkb:Rocketdyne_F-1_engine
gptkb:Rocketdyne_RS-25_engine
gptkb:Russia's_RD-180_engine
gptkb:Sierra_Nevada_Dream_Chaser_engine
gptkb:Space_X_Merlin_engine
gptkb:Space_X_Raptor_engine
gptkb:Virgin_Galactic_Space_Ship_Two_engine
gptkb:Aerojet_Rocketdyne_AR1_engine
gptkb:Aerojet_Rocketdyne_RL10_engine
China's YF-100 engine
|
|
gptkbp:control_system
|
digital control system
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:design
|
Aerojet Rocketdyne engineers
|
|
gptkbp:design_purpose
|
reliability
reusability
|
|
gptkbp:designed_by
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:development
|
gptkb:2014
|
|
gptkbp:development_cost
|
$100 million
estimated at $200 million
|
|
gptkbp:diameter
|
4.5 ft
|
|
gptkbp:engine
|
gptkb:Partnerships
open cycle
staged combustion cycle
spark ignited
|
|
gptkbp:engine_configuration
|
single engine
detailed in technical documents
|
|
gptkbp:engine_type
|
liquid bipropellant engine
|
|
gptkbp:environmental_impact
|
low emissions
lower emissions than solid fuels
|
|
gptkbp:exhaust_system
|
bell nozzle
aerospike nozzle
|
|
gptkbp:first_flight
|
gptkb:2019
planned for 2023
|
|
gptkbp:first_test_fire
|
gptkb:2016
|
|
gptkbp:fuel_capacity
|
12 ft
3.5 ft
|
|
gptkbp:fuel_economy
|
high
high specific impulse
|
|
gptkbp:fuel_type
|
gptkb:RP-1
RP-1 and liquid oxygen
|
|
gptkbp:future_plans
|
upgraded version
|
|
gptkbp:historical_achievement
|
successful test fires
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
AR1 rocket engine
|
|
gptkbp:ignition_system
|
spark plug ignition
|
|
gptkbp:investment_focus
|
commercial spaceflight
|
|
gptkbp:is_tested_for
|
gptkb:NASA_Stennis_Space_Center
gptkb:NASA's_Stennis_Space_Center
ongoing
static fire tests
Aerojet Rocketdyne facilities
|
|
gptkbp:launch_date
|
multiple launches per year
|
|
gptkbp:launch_platform
|
gptkb:Northrop_Grumman
|
|
gptkbp:launch_price
|
$10 million
$20 million
|
|
gptkbp:launch_vehicle
|
gptkb:Antares_2.0
|
|
gptkbp:length
|
15 ft
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:number_of_rooms
|
1000 psi
|
|
gptkbp:operational_use
|
commercial spaceflight
commercial launches
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:part_of
|
gptkb:Antares_launch_system
Aerojet Rocketdyne's product line
|
|
gptkbp:partnerships
|
international space agencies
|
|
gptkbp:performance
|
high efficiency
|
|
gptkbp:power_off_duration
|
30 seconds
|
|
gptkbp:production_status
|
in development
|
|
gptkbp:project
|
5 years
|
|
gptkbp:projected_market
|
growing space industry
|
|
gptkbp:projected_service_life
|
10 years
|
|
gptkbp:projected_thrust
|
600,000 lbf
|
|
gptkbp:propulsion
|
gptkb:RP-1
liquid oxygen
RP-1 and LOX
500,000 lbf
> 400:1
|
|
gptkbp:public_interest
|
high due to commercial space race
|
|
gptkbp:regulatory_compliance
|
FAA approved
|
|
gptkbp:research_focus
|
advanced propulsion technologies
|
|
gptkbp:safety_features
|
redundant systems
multiple redundant systems
|
|
gptkbp:specific_impulse
|
305 seconds
|
|
gptkbp:target_payload
|
up to 5,000 kg to LEO
|
|
gptkbp:type
|
gptkb:Team_Rocket
|
|
gptkbp:upgrades
|
increased thrust capacity
|
|
gptkbp:used_in
|
gptkb:Antares_rocket
|
|
gptkbp:weight
|
1,200 lb
approximately 3,000 lb
|
|
gptkbp:bfsParent
|
gptkb:Aerojet_Rocketdyne_Propulsion
|
|
gptkbp:bfsLayer
|
5
|