gptkbp:instance_of
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gptkb:Team_Rocket
|
gptkbp:application
|
gptkb:Space_Launch_System
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gptkbp:average_temperature
|
1,500 K
up to 3,000 K
|
gptkbp:check_in_time
|
150 seconds
approximately 150 seconds
|
gptkbp:combustor_type
|
staged combustion
expander cycle
|
gptkbp:control_system
|
digital
|
gptkbp:cooling_system
|
regenerative cooling
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gptkbp:country_of_origin
|
gptkb:United_States
|
gptkbp:debut
|
gptkb:1996
|
gptkbp:design_purpose
|
heavy-lift launch vehicle
|
gptkbp:designed_by
|
gptkb:Aerojet_Rocketdyne
|
gptkbp:developed_by
|
gptkb:Aerojet_Rocketdyne
|
gptkbp:development
|
gptkb:1990
gptkb:1996
|
gptkbp:development_cost
|
$1 billion
|
gptkbp:diameter
|
2.4 m
|
gptkbp:elevation
|
up to 200 km
|
gptkbp:engine_power
|
10,000 seconds
|
gptkbp:engine_type
|
liquid bipropellant
|
gptkbp:environmental_impact
|
low
|
gptkbp:exhaust_system
|
bell nozzle
|
gptkbp:exported_to
|
gptkb:Russia
|
gptkbp:first_flight
|
gptkb:2000
|
gptkbp:fuel_economy
|
high
|
gptkbp:fuel_type
|
RP-1 and Liquid Oxygen
turbopump
|
gptkbp:future_plans
|
upgrades and modifications
|
https://www.w3.org/2000/01/rdf-schema#label
|
RD-180 rocket engine
|
gptkbp:ignition_system
|
hypergolic
|
gptkbp:inspired_by
|
gptkb:RD-170
|
gptkbp:invention
|
multiple patents
|
gptkbp:investment
|
1,500 psi
|
gptkbp:launch_price
|
$100 million
|
gptkbp:launch_site
|
Cape Canaveral, Vandenberg Air Force Base
|
gptkbp:launched
|
over 80
|
gptkbp:length
|
4.5 m
|
gptkbp:manufacturer
|
gptkb:NPO_Energomash
|
gptkbp:material
|
titanium and steel
|
gptkbp:number_of_rooms
|
two
1,200 psi
2,500 psi
|
gptkbp:propulsion
|
yes
400,000 lbf
180,000 lbf
46:1
|
gptkbp:reliability
|
high
|
gptkbp:research_and_development
|
ongoing
|
gptkbp:safety_record
|
excellent
|
gptkbp:specific_impulse
|
311 seconds
|
gptkbp:status
|
in use
|
gptkbp:success_rate
|
over 90%
|
gptkbp:used_by
|
gptkb:United_Launch_Alliance
|
gptkbp:used_in
|
gptkb:Atlas_V
|
gptkbp:weight
|
3,000 kg
3,800 kg
|
gptkbp:bfsParent
|
gptkb:Viktor_Mikhailovich_Glushko
|
gptkbp:bfsLayer
|
6
|