gptkbp:instance_of
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gptkb:Team_Rocket
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gptkbp:challenges
|
overcome during development
|
gptkbp:collaboration
|
with NASA
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gptkbp:configuration
|
two-stage
H-IIA 202, H-IIA 204
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gptkbp:debut
|
multiple successful launches
|
gptkbp:design
|
15 years
|
gptkbp:design_features
|
modular design
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gptkbp:diameter
|
4 meters
|
gptkbp:durability
|
gptkb:none
|
gptkbp:engine_type
|
liquid-fueled
|
gptkbp:environmental_impact
|
assessed by JAXA
|
gptkbp:failure_launches
|
gptkb:1
|
gptkbp:first_flight
|
2004-02-20
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gptkbp:fuel_type
|
RP-1 and liquid oxygen
|
gptkbp:future_prospects
|
influence on new designs
|
gptkbp:guidance_system
|
inertial navigation
|
gptkbp:height
|
53 meters
|
https://www.w3.org/2000/01/rdf-schema#label
|
H-IIA 202 series
|
gptkbp:influences
|
future Japanese launch vehicles
|
gptkbp:launch_date
|
annual
|
gptkbp:launch_platform
|
gptkb:ground
Japan Aerospace Exploration Agency (JAXA
|
gptkbp:launch_price
|
$90 million
|
gptkbp:launch_site
|
gptkb:Tanegashima_Space_Center
|
gptkbp:launch_statistics
|
available on spaceflight databases
|
gptkbp:launch_vehicle
|
H-II family
|
gptkbp:launch_window
|
varies
|
gptkbp:legacy
|
successor to H-IIA 201 series
|
gptkbp:manufacturer
|
gptkb:Mitsubishi_Heavy_Industries
|
gptkbp:media_coverage
|
extensive during operational years
|
gptkbp:mission
|
decommissioned
|
gptkbp:notable_launches
|
H-IIA 202 launch of Akasaki satellite
|
gptkbp:number_of_engines
|
2
|
gptkbp:number_of_stages
|
gptkb:HM-7_B
gptkb:LE-7_A
|
gptkbp:operational_period
|
2004-2020
|
gptkbp:operational_status
|
retired
|
gptkbp:payload_capacity
|
4 meters
1,500 kg
4,000 kg
vertical integration
|
gptkbp:primary_mission
|
satellite deployment
|
gptkbp:propulsion
|
1,000 k N
|
gptkbp:public_interest
|
high in Japan
|
gptkbp:reliability
|
high
|
gptkbp:safety_record
|
excellent
|
gptkbp:specification
|
available on JAXA website
|
gptkbp:success
|
gptkb:30
|
gptkbp:success_rate
|
98%
|
gptkbp:bfsParent
|
gptkb:H-IIA_292_rocket
|
gptkbp:bfsLayer
|
5
|