|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:average_temperature
|
3,000 ° F
|
|
gptkbp:check_in_time
|
8.5 minutes
|
|
gptkbp:control_system
|
digital
computerized
|
|
gptkbp:cooling_system
|
liquid hydrogen
regenerative cooling
|
|
gptkbp:debut
|
gptkb:1980
|
|
gptkbp:development
|
1970s to 1980s
|
|
gptkbp:development_cost
|
$1 billion
|
|
gptkbp:durability
|
yes
|
|
gptkbp:engine
|
gptkb:NASA_Marshall_Space_Flight_Center
gptkb:space_exploration
gptkb:RS-25_D
ongoing
modular
staged combustion
significant in aerospace history
|
|
gptkbp:engine_configuration
|
gptkb:complex
vertical
detailed
190,000 lbf at sea level
|
|
gptkbp:engine_nozzle_expansion_ratio
|
60:1
|
|
gptkbp:engine_power
|
high
documented
multiple flights
optimized for space travel
|
|
gptkbp:engine_thrust_vector_control
|
yes
|
|
gptkbp:engine_type
|
liquid-fueled
|
|
gptkbp:environmental_impact
|
low
|
|
gptkbp:exhaust_system
|
converging-diverging
|
|
gptkbp:first_flight
|
gptkb:1981
gptkb:2011
|
|
gptkbp:fuel_capacity
|
14.5 ft
8.4 ft
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
liquid hydrogen and liquid oxygen
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RS-25 M
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:is_tested_for
|
gptkb:NASA_Stennis_Space_Center
extensive
|
|
gptkbp:launch_site
|
gptkb:Kennedy_Space_Center
|
|
gptkbp:manufacturer
|
gptkb:Rocketdyne
|
|
gptkbp:mission
|
gptkb:International_Space_Station
|
|
gptkbp:notable_mission
|
gptkb:STS-1
|
|
gptkbp:number_of_engines
|
four
|
|
gptkbp:number_of_rooms
|
gptkb:single
3,000 psi
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:part_of
|
gptkb:Space_Shuttle
|
|
gptkbp:propulsion
|
190,000 lbf
63:1
|
|
gptkbp:replaced_by
|
gptkb:RS-25_E
|
|
gptkbp:specific_impulse
|
452 seconds in vacuum
|
|
gptkbp:successor
|
gptkb:RS-25_E
|
|
gptkbp:total_engines_built
|
gptkb:16
|
|
gptkbp:used_in
|
gptkb:Space_Shuttle
|
|
gptkbp:weight
|
3,000 lb
|
|
gptkbp:bfsParent
|
gptkb:Rocketdyne_RS-25
|
|
gptkbp:bfsLayer
|
5
|