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gptkbp:instance_of
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gptkb:Team_Rocket
|
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gptkbp:application
|
gptkb:Space_Launch_System
|
|
gptkbp:check_in_time
|
about 10 minutes
|
|
gptkbp:combustor_type
|
gas-generator cycle
|
|
gptkbp:control_system
|
digital control system
|
|
gptkbp:cooling_system
|
film cooling
active cooling system
|
|
gptkbp:debut
|
gptkb:2001
|
|
gptkbp:development
|
gptkb:NASA
|
|
gptkbp:development_cost
|
$1 billion
|
|
gptkbp:engine
|
extensive
modular design
ongoing improvements
staged combustion
commercial launches
potential for new missions
RS-68 A upgrades
part of ULA's fleet
|
|
gptkbp:engine_configuration
|
modular design
publicly available
single chamber
|
|
gptkbp:engine_power
|
high reliability
documented
optimized for heavy payloads
|
|
gptkbp:engine_testing_results
|
published
|
|
gptkbp:engine_thrust_vector_control
|
yes
|
|
gptkbp:engine_type
|
liquid bipropellant engine
RS-68 A
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:exhaust_system
|
converging-diverging nozzle
|
|
gptkbp:first_flight
|
gptkb:2002
|
|
gptkbp:fuel_capacity
|
5.5 ft
16.5 ft
|
|
gptkbp:fuel_type
|
liquid hydrogen and liquid oxygen
turbopump
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
Rocketdyne RS-68
|
|
gptkbp:ignition_system
|
gptkb:spark_plug
|
|
gptkbp:is_tested_for
|
gptkb:NASA_Stennis_Space_Center
completed
|
|
gptkbp:launch_site
|
gptkb:Cape_Canaveral
|
|
gptkbp:manufacturer
|
gptkb:Rocketdyne
|
|
gptkbp:number_of_engines
|
gptkb:1
|
|
gptkbp:number_of_rooms
|
1000 psi
single chamber
|
|
gptkbp:operational_use
|
gptkb:United_Launch_Alliance
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:oxidizer_pump_type
|
turbopump
|
|
gptkbp:propulsion
|
680,000 lbf
226:1
|
|
gptkbp:replaced_by
|
RS-68 A
|
|
gptkbp:specific_impulse
|
305 seconds
|
|
gptkbp:status
|
in service
|
|
gptkbp:used_in
|
gptkb:Delta_IV
|
|
gptkbp:weight
|
3,000 lb
|
|
gptkbp:bfsParent
|
gptkb:Delta_IV
|
|
gptkbp:bfsLayer
|
4
|