|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:bfsLayer
|
3
|
|
gptkbp:bfsParent
|
gptkb:spacecraft
gptkb:software
|
|
gptkbp:aircraft_operated
|
gptkb:software
|
|
gptkbp:average_temperature
|
-253 ° C to 3,000 ° C
|
|
gptkbp:check_in_time
|
8.5 minutes
|
|
gptkbp:controls
|
digital
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut_year
|
over 135 launches
|
|
gptkbp:design
|
100 flights
|
|
gptkbp:designed_by
|
gptkb:Rocketdyne
|
|
gptkbp:developer
|
gptkb:1970
$1 billion
|
|
gptkbp:diameter
|
2.4 m
|
|
gptkbp:durability
|
gptkb:battle
|
|
gptkbp:emissions_standard
|
converging-diverging
|
|
gptkbp:engine
|
gptkb:Space_Shuttle_Main_Engine_program
gptkb:NASA_Michoud_Assembly_Facility
four
vertical
staged combustion
clustered
optimized for high altitude
1976-2011
16 for SLS
detailed in NASA documents
developed from the J-2 engine
|
|
gptkbp:engine_type
|
gptkb:rocket
RS-25 D, RS-25 E
|
|
gptkbp:environmental_impact
|
low
|
|
gptkbp:first_flight
|
gptkb:1980
|
|
gptkbp:fuel_capacity
|
high
3,000 psi
12,000 kg/min
|
|
gptkbp:fuel_type
|
liquid hydrogen and liquid oxygen
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RS-25
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:is_tested_for
|
gptkb:NASA_Marshall_Space_Flight_Center
gptkb:NASA_Stennis_Space_Center
|
|
gptkbp:is_used_by
|
gptkb:NASA
|
|
gptkbp:is_used_in
|
gptkb:spacecraft
|
|
gptkbp:launch_site
|
gptkb:Kennedy_Space_Center
|
|
gptkbp:length
|
4.6 m
|
|
gptkbp:manufacturer
|
gptkb:Aerojet_Rocketdyne
|
|
gptkbp:market
|
$150 million per launch
|
|
gptkbp:mission
|
gptkb:Artemis_program
|
|
gptkbp:number_built
|
more than 100
|
|
gptkbp:operational_area
|
gptkb:spacecraft
|
|
gptkbp:operational_status
|
active
|
|
gptkbp:part_of
|
gptkb:spacecraft
|
|
gptkbp:propulsion
|
gptkb:battle
330 seconds in vacuum
512,000 lbf
|
|
gptkbp:rate_of_fire
|
gptkb:1976
|
|
gptkbp:reliability
|
high
|
|
gptkbp:successor
|
gptkb:RS-25_E
|
|
gptkbp:used_in
|
gptkb:spacecraft
|
|
gptkbp:weight
|
3,000 kg
|