|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:bfsLayer
|
3
|
|
gptkbp:bfsParent
|
gptkb:software
|
|
gptkbp:aircraft_operated
|
gptkb:software
|
|
gptkbp:average_temperature
|
-253 to 650 ° C
-423° F to 3,000° F
|
|
gptkbp:check_in_time
|
8.5 minutes
|
|
gptkbp:compression_ratio
|
60:1
|
|
gptkbp:controls
|
gptkb:International_Space_Station
digital
|
|
gptkbp:cooling_system
|
liquid hydrogen
regenerative cooling
|
|
gptkbp:debut_year
|
gptkb:1975
|
|
gptkbp:developed_by
|
gptkb:NASA
|
|
gptkbp:developer
|
$1 billion
|
|
gptkbp:durability
|
gptkb:theorem
|
|
gptkbp:emissions_standard
|
aerospike
|
|
gptkbp:engine
|
gptkb:spacecraft
gptkb:RS-25_D
gptkb:RS-25_E
gptkb:advanced_technology
gptkb:future_space_missions
gptkb:international_collaboration
gptkb:Rocketdyne
ongoing
four
high performance
technological advancements
rich history
high reliability
ongoing research
high efficiency
vertical
closed cycle
reliable
detailed
engineering challenges
ongoing development
future missions
various space missions
proven
over 30 years of service
staged combustion cycle
clustered
crew and cargo missions
vertical assembly
controlled shutdown
detailed specifications
significant in space exploration
dual start
support from aerospace community
four engines on the orbiter
|
|
gptkbp:engine_type
|
liquid bipropellant
|
|
gptkbp:environmental_impact
|
low
|
|
gptkbp:first_flight
|
gptkb:1980
gptkb:1981
|
|
gptkbp:fuel_capacity
|
high
4.6 m
5.5 ft
3.7 m
14.5 ft
|
|
gptkbp:fuel_type
|
liquid hydrogen and liquid oxygen
cryogenic
Inconel
|
|
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:is_used_in
|
gptkb:software
|
|
gptkbp:launch_site
|
gptkb:Kennedy_Space_Center
|
|
gptkbp:maintenance
|
periodic maintenance
|
|
gptkbp:manufacturer
|
gptkb:Rocketdyne
|
|
gptkbp:mission
|
gptkb:Artemis_I
gptkb:Artemis_program
|
|
gptkbp:number_of_rooms
|
3,000 psi
20.5 M Pa
|
|
gptkbp:operates_in
|
gptkb:2011
|
|
gptkbp:operational_area
|
closed cycle
staged combustion
|
|
gptkbp:produced_by
|
over 200
135 engines
|
|
gptkbp:propulsion
|
gptkb:battle
high thrust-to-weight ratio
gimbaled
452 seconds
190,000 lbf
1900 k N
|
|
gptkbp:successor
|
gptkb:RS-25_E
|
|
gptkbp:used_in
|
gptkb:spacecraft
|
|
gptkbp:weight
|
3,000 kg
3,000 lb
|