|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:Space_Launch_System
satellite launches
crew missions
deep space missions
interplanetary missions
cargo missions
|
|
gptkbp:average_temperature
|
-253 ° C to 30 ° C
|
|
gptkbp:budget
|
cost-effective solutions
|
|
gptkbp:challenges
|
engine cooling
|
|
gptkbp:collaboration
|
gptkb:European_Space_Agency
|
|
gptkbp:combustion_chamber_pressure
|
300 psi
|
|
gptkbp:combustor_type
|
staged combustion
|
|
gptkbp:competes_with
|
gptkb:RD-180
gptkb:Raptor
|
|
gptkbp:competitors
|
gptkb:Space_X_Raptor
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:customer_support
|
commercial satellite operators
|
|
gptkbp:debut
|
gptkb:2017
|
|
gptkbp:design
|
gptkb:Jeff_Bezos
|
|
gptkbp:design_philosophy
|
sustainability
|
|
gptkbp:designed_for
|
gptkb:Vulcan_Centaur
gptkb:New_Glenn
|
|
gptkbp:developed_by
|
gptkb:United_Launch_Alliance
gptkb:Blue_Origin
|
|
gptkbp:development
|
gptkb:2014
2014 to present
Blue Origin engineers
|
|
gptkbp:development_cost
|
$1 billion
estimated $1 billion
|
|
gptkbp:durability
|
designed for reusability
|
|
gptkbp:engine
|
staged combustion cycle
full-flow staged combustion
|
|
gptkbp:engine_configuration
|
single nozzle
|
|
gptkbp:engine_type
|
liquid bipropellant
|
|
gptkbp:environmental_impact
|
designed to reduce emissions
lower emissions than kerosene
|
|
gptkbp:first_flight
|
gptkb:2020
gptkb:2023
|
|
gptkbp:first_hot_fire_test
|
gptkb:2017
|
|
gptkbp:fuel_capacity
|
3.7 ft
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
kerosene
liquid oxygen and liquefied natural gas
|
|
gptkbp:funding
|
private investment
|
|
gptkbp:future_prospects
|
gptkb:Artemis_program
|
|
gptkbp:growth_rate
|
high volume production
|
|
gptkbp:historical_achievement
|
successful test flights
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
BE-4
|
|
gptkbp:ignition_system
|
dual expander cycle
|
|
gptkbp:impact
|
significant impact on space access
|
|
gptkbp:integration
|
modular design
|
|
gptkbp:is_tested_for
|
gptkb:Blue_Origin's_West_Texas_facility
gptkb:NASA's_Marshall_Space_Flight_Center
ongoing
hot fire tests
engine testing phase
|
|
gptkbp:launch_date
|
multiple launches per year
high frequency
up to 10 launches per year
|
|
gptkbp:launch_site
|
gptkb:Cape_Canaveral_Space_Force_Station
|
|
gptkbp:launch_vehicle
|
gptkb:Vulcan_Centaur
gptkb:New_Glenn
Vulcan family
|
|
gptkbp:length
|
15.5 ft
|
|
gptkbp:lifespan
|
15 years
|
|
gptkbp:manufacturer
|
gptkb:Blue_Origin
|
|
gptkbp:media_coverage
|
extensive
|
|
gptkbp:mission
|
deep space exploration
|
|
gptkbp:notable_feature
|
full-flow staged combustion cycle
|
|
gptkbp:number_of_rooms
|
3000 psi
|
|
gptkbp:operational_status
|
in development
|
|
gptkbp:operational_use
|
gptkb:Vulcan_Centaur_rocket
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:part_of
|
Blue Origin's engine family
|
|
gptkbp:partnership
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:partnerships
|
gptkb:United_Launch_Alliance
gptkb:NASA
|
|
gptkbp:performance
|
high performance
high reliability
|
|
gptkbp:production_status
|
in production
|
|
gptkbp:projected_market
|
growing space industry
|
|
gptkbp:propulsion
|
methane
550,000 lbf
230,000 lbf
250,000 lbf
183:1
over 250,000 lbf
|
|
gptkbp:public_perception
|
positive
|
|
gptkbp:regulatory_compliance
|
FAA certification
|
|
gptkbp:replaces
|
gptkb:RD-180
|
|
gptkbp:safety_features
|
redundant systems
multiple redundant systems
|
|
gptkbp:specific_impulse
|
310 seconds
approximately 310 seconds
|
|
gptkbp:target_market
|
government contracts
commercial spaceflight
|
|
gptkbp:upgrades
|
increased thrust version
|
|
gptkbp:used_by
|
gptkb:United_Launch_Alliance
|
|
gptkbp:used_in
|
gptkb:New_Glenn
|
|
gptkbp:uses
|
gptkb:RP-1
liquid oxygen
|
|
gptkbp:weight
|
3,000 lb
approximately 3,000 lb
|
|
gptkbp:bfsParent
|
gptkb:Blue_Origin
gptkb:Blue_Origin's_New_Glenn_rocket
|
|
gptkbp:bfsLayer
|
4
|