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gptkbp:instance_of
|
gptkb:Team_Rocket
|
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gptkbp:application
|
gptkb:Space_Launch_System
|
|
gptkbp:average_temperature
|
-250 to 1500 ° C
|
|
gptkbp:check_in_time
|
150 seconds
|
|
gptkbp:combustor_type
|
staged combustion
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:designed_by
|
gptkb:Rocketdyne
|
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gptkbp:development
|
gptkb:NASA
|
|
gptkbp:development_cost
|
$50 million
|
|
gptkbp:diameter
|
1.2 m
|
|
gptkbp:engine
|
gptkb:RD-0146_engine
gas-generator cycle
RD-0148 engine
|
|
gptkbp:engine_configuration
|
single-chamber
|
|
gptkbp:environmental_impact
|
low
|
|
gptkbp:exhaust_system
|
converging-diverging nozzle
|
|
gptkbp:facilities
|
gptkb:NASA_Marshall_Space_Flight_Center
|
|
gptkbp:first_flight
|
gptkb:1990
|
|
gptkbp:fuel_type
|
gptkb:RP-1
liquid oxygen and RP-1
cryogenic tank
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RD-0147 engine
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:invention
|
multiple patents filed
|
|
gptkbp:is_tested_for
|
gptkb:B-2_Test_Stand
|
|
gptkbp:launch_platform
|
mobile launch platform
|
|
gptkbp:launched
|
50
|
|
gptkbp:legacy
|
influenced future designs
|
|
gptkbp:length
|
3.5 m
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:number_of_rooms
|
6.9 MPa
|
|
gptkbp:operational_use
|
military and commercial
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:oxidizer_storage
|
cryogenic tank
|
|
gptkbp:performers
|
yes
|
|
gptkbp:propulsion
|
147 k N
490:1
|
|
gptkbp:reliability
|
high
|
|
gptkbp:research_institutes
|
various universities
|
|
gptkbp:safety_record
|
excellent
|
|
gptkbp:specific_impulse
|
300 seconds
|
|
gptkbp:status
|
retired
|
|
gptkbp:used_in
|
launch vehicles
|
|
gptkbp:user_countries
|
yes
|
|
gptkbp:weight
|
300 kg
|
|
gptkbp:bfsParent
|
gptkb:RD-0146_engine
|
|
gptkbp:bfsLayer
|
7
|