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gptkbp:instance_of
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gptkb:Space_Launch_System
gptkb:Team_Rocket
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|
gptkbp:collaborations
|
International partnerships
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|
gptkbp:configuration
|
215 configuration
|
|
gptkbp:control_system
|
Digital control system
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|
gptkbp:debut
|
Over 30 launches
|
|
gptkbp:design_purpose
|
To launch satellites into orbit
|
|
gptkbp:development
|
gptkb:1994
|
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gptkbp:diameter
|
4 meters
|
|
gptkbp:elevation
|
4 meters
53 meters
220,000 kg
|
|
gptkbp:engine_burn_time
|
approximately 3 minutes
|
|
gptkbp:engine_configuration
|
Single engine in first stage
|
|
gptkbp:engine_type
|
gptkb:LE-7_A
|
|
gptkbp:first_flight
|
gptkb:2001
gptkb:2004
gptkb:2019
2001-08-29
|
|
gptkbp:flight_style
|
gptkb:39
|
|
gptkbp:fuel_type
|
Liquid hydrogen and liquid oxygen
|
|
gptkbp:guidance_system
|
Inertial guidance system
|
|
gptkbp:height
|
53 meters
|
|
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
|
|
gptkbp:launch_event
|
Few failures
|
|
gptkbp:launch_platform
|
JAXA control center
Japan Aerospace Exploration Agency (JAXA
|
|
gptkbp:launch_price
|
approximately $90 million
|
|
gptkbp:launch_site
|
gptkb:Tanegashima_Space_Center
|
|
gptkbp:launch_vehicle
|
gptkb:H-IIA
Expendable launch vehicle
H-II family
Two stages
|
|
gptkbp:launch_vehicle_payload_fairing
|
4 meters in diameter
|
|
gptkbp:manufacturer
|
gptkb:Mitsubishi_Heavy_Industries
|
|
gptkbp:mission_duration
|
gptkb:unknown
|
|
gptkbp:mission_type
|
commercial
|
|
gptkbp:notable_achievements
|
Successful deployment of communication satellites
|
|
gptkbp:notable_launches
|
gptkb:H-IIA_215_F17
H-IIA 215 was used to launch the Akasaki satellite.
|
|
gptkbp:number_of_stages
|
gptkb:HM-7_B_engine
2
LE-7 A engine
|
|
gptkbp:operational_period
|
15 years
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:operator
|
gptkb:Mitsubishi_Heavy_Industries
|
|
gptkbp:orbit_type
|
geostationary transfer orbit
|
|
gptkbp:payload_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:primary_use
|
Satellite launch
|
|
gptkbp:production_years
|
gptkb:2003
|
|
gptkbp:propulsion
|
1,000 k N
1,000 k N in first stage
|
|
gptkbp:release_country
|
gptkb:Yes
|
|
gptkbp:reliability
|
very reliable
|
|
gptkbp:success
|
gptkb:true
multiple successful launches
|
|
gptkbp:success_rate
|
high
over 90%
|
|
gptkbp:successor
|
gptkb:H-IIA_216
gptkb:H-IIB_rocket
|
|
gptkbp:used_to_launch
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gptkb:Akasaki_satellite
|
|
gptkbp:bfsParent
|
gptkb:JAXA
gptkb:Japanese_Aerospace_Exploration_Agency
gptkb:Japanese_Aerospace_Exploration_Agency_(JAXA)
gptkb:Japan_Aerospace_Exploration_Agency_(JAXA)
|
|
gptkbp:bfsLayer
|
4
|