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gptkbp:instance_of
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gptkb:aircraft
gptkb:rocket
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gptkbp:bfsLayer
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4
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gptkbp:bfsParent
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gptkb:JAXA
gptkb:Japanese_Aerospace_Exploration_Agency
gptkb:Japanese_Aerospace_Exploration_Agency_(JAXA)
gptkb:Japan_Aerospace_Exploration_Agency_(JAXA)
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gptkbp:collaborations
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International partnerships
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gptkbp:controls
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Digital control system
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gptkbp:debut_year
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Over 30 launches
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gptkbp:design
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To launch satellites into orbit
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gptkbp:developer
|
gptkb:1994
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gptkbp:diameter
|
4 meters
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gptkbp:elevation
|
4 meters
53 meters
220,000 kg
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|
gptkbp:engine
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Single engine in first stage
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gptkbp:engine_type
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gptkb:LE-7_A
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|
gptkbp:events
|
Few failures
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gptkbp:first_flight
|
gptkb:2001
gptkb:2004
gptkb:2019
gptkb:39
2001-08-29
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gptkbp:fuel_type
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Liquid hydrogen and liquid oxygen
|
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gptkbp:guidance_system
|
Inertial guidance system
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gptkbp:height
|
53 meters
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|
https://www.w3.org/2000/01/rdf-schema#label
|
H-IIA 215
|
|
gptkbp:launch_date
|
2004-2009
2005-02-24
2019-01-18
several launches per year
|
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gptkbp:launch_site
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gptkb:Tanegashima_Space_Center
JAXA control center
Japan Aerospace Exploration Agency (JAXA
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gptkbp:launch_vehicle
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gptkb:H-IIA
Expendable launch vehicle
4 meters in diameter
H-II family
Two stages
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gptkbp:launched
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gptkb:Akasaki_satellite
|
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gptkbp:manufacturer
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gptkb:Mitsubishi_Heavy_Industries
|
|
gptkbp:market
|
approximately $90 million
|
|
gptkbp:mission
|
commercial
geostationary transfer orbit
|
|
gptkbp:mission_duration
|
gptkb:unknown
|
|
gptkbp:notable_achievement
|
Successful deployment of communication satellites
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gptkbp:notable_album
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gptkb:H-IIA_215_F17
H-IIA 215 was used to launch the Akasaki satellite.
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|
gptkbp:number_of_stages
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gptkb:HM-7_B_engine
2
LE-7 A engine
|
|
gptkbp:operational_area
|
15 years
|
|
gptkbp:operational_status
|
retired
|
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gptkbp:operator
|
gptkb:Mitsubishi_Heavy_Industries
|
|
gptkbp:primary_source
|
Satellite launch
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gptkbp:production_years
|
gptkb:2003
|
|
gptkbp:propulsion
|
1,000 k N
1,000 k N in first stage
|
|
gptkbp:rate_of_fire
|
approximately 3 minutes
|
|
gptkbp:release_region
|
gptkb:battle
|
|
gptkbp:reliability
|
very reliable
|
|
gptkbp:seating_capacity
|
gptkb:Himawari_weather_satellites
4 meters in diameter
Multiple payload configurations
4,000 kg to geostationary transfer orbit
DSN-1
4,000 kg to GTO
|
|
gptkbp:setting
|
215 configuration
|
|
gptkbp:succeeded_by
|
gptkb:theorem
high
over 90%
multiple successful launches
|
|
gptkbp:successor
|
gptkb:H-IIA_216
gptkb:H-IIB_rocket
|