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gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:Space_Launch_System
|
|
gptkbp:challenges
|
overcoming thermal stresses
|
|
gptkbp:check_in_time
|
approximately 600 seconds
|
|
gptkbp:collaboration
|
joint projects with NASA
|
|
gptkbp:combustor_type
|
staged combustion
|
|
gptkbp:control_system
|
electronic control
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut
|
multiple successful launches
|
|
gptkbp:design_purpose
|
orbital insertion
|
|
gptkbp:developed_by
|
gptkb:ISAS
|
|
gptkbp:development
|
1980s to 1990s
|
|
gptkbp:engine
|
gptkb:collaboration
staged combustion cycle
controlled shutdown
multiple start capability
|
|
gptkbp:engine_configuration
|
single nozzle
|
|
gptkbp:engine_type
|
gptkb:Team_Rocket
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:exhaust_system
|
bell nozzle
|
|
gptkbp:first_flight
|
gptkb:1994
|
|
gptkbp:fuel_capacity
|
2.5 m
4.5 m
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
liquid hydrogen
|
|
gptkbp:future_prospects
|
inspiration for new designs
|
|
gptkbp:has_documentation
|
available for research
|
|
gptkbp:has_tour
|
gptkb:stage_play
|
|
gptkbp:historical_significance
|
pioneered liquid rocket technology
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
LE-5 A engine
|
|
gptkbp:ignition_system
|
hypergolic ignition
|
|
gptkbp:invention
|
several related patents filed
|
|
gptkbp:investment
|
20 bar
|
|
gptkbp:is_tested_for
|
extensive ground testing
KSC Test Stand
|
|
gptkbp:launch_site
|
gptkb:Tanegashima_Space_Center
|
|
gptkbp:launch_vehicle
|
H-II
|
|
gptkbp:legacy
|
influenced future designs
|
|
gptkbp:manufacturer
|
gptkb:Mitsubishi_Heavy_Industries
|
|
gptkbp:material
|
lightweight alloys
|
|
gptkbp:number_of_rooms
|
one
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:operational_use
|
used in multiple missions
|
|
gptkbp:oxidation_states
|
liquid oxygen
|
|
gptkbp:performance
|
high efficiency
|
|
gptkbp:propulsion
|
66.67
100 k N
LH2/ LOX
|
|
gptkbp:research_focus
|
advanced propulsion technology
|
|
gptkbp:safety_features
|
redundant systems
|
|
gptkbp:specific_impulse
|
450 s
|
|
gptkbp:specification
|
detailed in engineering reports
|
|
gptkbp:successor
|
gptkb:LE-5_B_engine
|
|
gptkbp:used_in
|
gptkb:H-II_rocket
|
|
gptkbp:weight
|
approximately 1,500 kg
|
|
gptkbp:bfsParent
|
gptkb:H-IIA_264
|
|
gptkbp:bfsLayer
|
5
|