|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:aircraft_operated
|
gptkb:Space_Launch_System
|
|
gptkbp:average_temperature
|
-253 to 650 ° C
-423° F to 3,000° F
|
|
gptkbp:check_in_time
|
8.5 minutes
|
|
gptkbp:combustion_chamber_material
|
Inconel
|
|
gptkbp:control_system
|
digital
|
|
gptkbp:cooling_system
|
liquid hydrogen
regenerative cooling
|
|
gptkbp:debut
|
gptkb:1975
|
|
gptkbp:developed_by
|
gptkb:NASA
|
|
gptkbp:development_cost
|
$1 billion
|
|
gptkbp:durability
|
gptkb:true
|
|
gptkbp:engine
|
gptkb:RS-25_E
gptkb:advanced_technology
gptkb:international_collaboration
gptkb:Rocketdyne
gptkb:Space_Shuttle
ongoing
technological advancements
rich history
ongoing research
vertical
closed cycle
engineering challenges
ongoing development
future missions
various space missions
over 30 years of service
crew and cargo missions
vertical assembly
controlled shutdown
significant in space exploration
dual start
support from aerospace community
|
|
gptkbp:engine_configuration
|
vertical
detailed
staged combustion cycle
clustered
detailed specifications
four engines on the orbiter
|
|
gptkbp:engine_future_use
|
gptkb:future_space_missions
|
|
gptkbp:engine_power
|
high performance
high reliability
high efficiency
reliable
proven
|
|
gptkbp:engine_serial_number
|
gptkb:RS-25_D
|
|
gptkbp:engine_type
|
liquid bipropellant
|
|
gptkbp:environmental_impact
|
low
|
|
gptkbp:exhaust_system
|
aerospike
|
|
gptkbp:first_flight
|
gptkb:1980
gptkb:1981
|
|
gptkbp:fuel_capacity
|
4.6 m
5.5 ft
3.7 m
14.5 ft
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
liquid hydrogen and liquid oxygen
cryogenic
|
|
gptkbp:has_programs
|
gptkb:NASA's_Space_Shuttle_program
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
RS-25 engines
|
|
gptkbp:ignition_system
|
up to 100
hypergolic
|
|
gptkbp:impact
|
significant impact on space exploration
|
|
gptkbp:is_tested_for
|
gptkb:Stennis_Space_Center
extensive
extensive testing
|
|
gptkbp:launch_site
|
gptkb:Kennedy_Space_Center
|
|
gptkbp:maintenance
|
periodic maintenance
|
|
gptkbp:manufacturer
|
gptkb:Rocketdyne
|
|
gptkbp:mission
|
gptkb:Artemis_I
gptkb:Artemis_program
|
|
gptkbp:nozzle_expansion_ratio
|
60:1
|
|
gptkbp:number_of_engines
|
four
|
|
gptkbp:number_of_rooms
|
3,000 psi
20.5 MPa
|
|
gptkbp:operates_in
|
gptkb:2011
|
|
gptkbp:operational_period
|
closed cycle
staged combustion
|
|
gptkbp:produces
|
over 200
135 engines
|
|
gptkbp:propulsion
|
yes
high thrust-to-weight ratio
gimbaled
190,000 lbf
1900 k N
|
|
gptkbp:specific_impulse
|
452 seconds
|
|
gptkbp:successor
|
gptkb:RS-25_E
|
|
gptkbp:system
|
gptkb:International_Space_Station
|
|
gptkbp:used_in
|
gptkb:Space_Shuttle
|
|
gptkbp:used_in_rocket
|
gptkb:Space_Launch_System
|
|
gptkbp:weight
|
3,000 kg
3,000 lb
|
|
gptkbp:bfsParent
|
gptkb:Space_Launch_System
gptkb:Artemis_I_rocket
|
|
gptkbp:bfsLayer
|
4
|