|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:NASA_missions
|
|
gptkbp:average_temperature
|
-423 to 600 degrees Fahrenheit
|
|
gptkbp:check_in_time
|
8.5 minutes
|
|
gptkbp:control_system
|
digital
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut
|
over 130 flights
|
|
gptkbp:designed_by
|
gptkb:Rocketdyne
|
|
gptkbp:development
|
1970s to 1980s
|
|
gptkbp:development_cost
|
$1 billion
|
|
gptkbp:durability
|
gptkb:true
|
|
gptkbp:engine
|
modular
staged combustion
|
|
gptkbp:engine_configuration
|
vertical
|
|
gptkbp:engine_power
|
high efficiency
|
|
gptkbp:engine_test_facility
|
gptkb:NASA_Stennis_Space_Center
|
|
gptkbp:engine_test_stand
|
E-1 Test Stand
|
|
gptkbp:engine_type
|
gptkb:RS-25_D
gptkb:Team_Rocket
|
|
gptkbp:exhaust_system
|
bell nozzle
|
|
gptkbp:first_flight
|
gptkb:1981
|
|
gptkbp:fuel_capacity
|
14.5 feet
5.5 feet
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
liquid hydrogen and liquid oxygen
turbopump
|
|
gptkbp:future_prospects
|
gptkb:SLS_(Space_Launch_System)
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RS-25 H
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:is_tested_for
|
static fire tests
|
|
gptkbp:launch_vehicle
|
gptkb:Space_Shuttle
|
|
gptkbp:maintenance
|
scheduled
|
|
gptkbp:number_of_engines
|
four
|
|
gptkbp:number_of_rooms
|
gptkb:single
2050 psi
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:operational_use
|
gptkb:human_spaceflight
|
|
gptkbp:oxidizer_pump_type
|
turbopump
|
|
gptkbp:propulsion
|
50:1
1900 k N
|
|
gptkbp:retirement_year
|
gptkb:2011
|
|
gptkbp:specific_impulse
|
452 seconds
|
|
gptkbp:successor
|
gptkb:RS-25_E
|
|
gptkbp:used_in
|
gptkb:Space_Shuttle
|
|
gptkbp:weight
|
3,000 pounds
|
|
gptkbp:bfsParent
|
gptkb:Rocketdyne_RS-25
|
|
gptkbp:bfsLayer
|
5
|