|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:application
|
gptkb:Space_Launch_System
|
|
gptkbp:challenges
|
cryogenic handling
|
|
gptkbp:check_in_time
|
approximately 500 seconds
|
|
gptkbp:collaboration
|
gptkb:NASA_and_ESA
|
|
gptkbp:collaborative_projects
|
with international space agencies
|
|
gptkbp:combustor_type
|
staged combustion
|
|
gptkbp:control_system
|
digital
|
|
gptkbp:cooling_system
|
regenerative cooling
|
|
gptkbp:debut
|
gptkb:1993
|
|
gptkbp:design_purpose
|
heavy payload launch
|
|
gptkbp:development
|
1990s
|
|
gptkbp:development_cost
|
estimated at $1 billion
|
|
gptkbp:educational_use
|
in aerospace engineering programs
|
|
gptkbp:engine
|
staged combustion cycle
|
|
gptkbp:engine_configuration
|
vertical
|
|
gptkbp:engine_thrust_to_weight_ratio
|
approximately 50:1
|
|
gptkbp:environmental_impact
|
low emissions
|
|
gptkbp:first_flight
|
gptkb:1994
|
|
gptkbp:fuel_capacity
|
approximately 2.5 m
approximately 5.5 m
|
|
gptkbp:fuel_economy
|
high
|
|
gptkbp:fuel_type
|
liquid hydrogen
cryogenic
|
|
gptkbp:has_documentation
|
available for research purposes
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
H-2 engine
|
|
gptkbp:ignition_system
|
hypergolic
|
|
gptkbp:inspiration
|
future rocket designs
|
|
gptkbp:is_a_supporter_of
|
conducted during development
|
|
gptkbp:is_tested_for
|
gptkb:Tanegashima_Space_Center
|
|
gptkbp:launch_date
|
several per year
|
|
gptkbp:launch_platform
|
gptkb:Japan_Aerospace_Exploration_Agency_(JAXA)
|
|
gptkbp:legacy
|
paved the way for future Japanese rockets
|
|
gptkbp:manufacturer
|
gptkb:Mitsubishi_Heavy_Industries
|
|
gptkbp:material
|
lightweight alloys
|
|
gptkbp:notable_features
|
high efficiency
|
|
gptkbp:notable_launches
|
H-IIA and H-IIB rockets
|
|
gptkbp:number_of_rooms
|
2
approximately 20 MPa
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:oxidation_states
|
liquid oxygen
cryogenic
|
|
gptkbp:part_of
|
gptkb:Japanese_space_program
|
|
gptkbp:propulsion
|
1,000 k N
|
|
gptkbp:reliability
|
high
|
|
gptkbp:research_and_development
|
ongoing improvements
|
|
gptkbp:retirement_year
|
gptkb:2009
|
|
gptkbp:safety_record
|
excellent
|
|
gptkbp:specific_impulse
|
450 seconds
|
|
gptkbp:successor
|
gptkb:LE-7_engine
|
|
gptkbp:successor_engines
|
LE-5 and LE-7
|
|
gptkbp:type
|
liquid-fueled
|
|
gptkbp:used_in
|
gptkb:H-II_rocket
|
|
gptkbp:weight
|
approximately 3,000 kg
|
|
gptkbp:bfsParent
|
gptkb:H-1_engines
|
|
gptkbp:bfsLayer
|
6
|