|
gptkbp:instance_of
|
gptkb:rocket
|
|
gptkbp:bfsLayer
|
4
|
|
gptkbp:bfsParent
|
gptkb:Tanegashima_Space_Center
|
|
gptkbp:debut_year
|
operated from 2004 to 2019
|
|
gptkbp:diameter
|
4 meters
|
|
gptkbp:elevation
|
4 meters
53 meters
200 tons
|
|
gptkbp:engine
|
staged combustion cycle
|
|
gptkbp:engine_type
|
gptkb:rocket
|
|
gptkbp:first_flight
|
gptkb:2004
gptkb:2019
|
|
gptkbp:fuel_type
|
kerosene and liquid oxygen
|
|
gptkbp:guidance_system
|
inertial guidance system
|
|
gptkbp:has_programs
|
H-IIA program
|
|
gptkbp:height
|
53 meters
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
H-IIA 265 rocket
|
|
gptkbp:launch_date
|
approximately once a year
|
|
gptkbp:launch_site
|
gptkb:Tanegashima_Space_Center
gptkb:JAXA
|
|
gptkbp:launch_vehicle
|
gptkb:H-IIA
98%
200 tons
expendable
expendable launch vehicle
two-stage design
two solid rocket boosters
H-II family
|
|
gptkbp:launched
|
gptkb:10
|
|
gptkbp:manufacturer
|
gptkb:Mitsubishi_Heavy_Industries
|
|
gptkbp:max_takeoff_weight
|
6,000 kg
15,000 kg
|
|
gptkbp:mission
|
H-IIA 265 launch of Akasaki satellite
|
|
gptkbp:number_of_issues
|
gptkb:0
|
|
gptkbp:number_of_stages
|
gptkb:LE-5_B
gptkb:LE-7_A
2
|
|
gptkbp:operational_area
|
2004-2019
commercial and government missions
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:origin
|
gptkb:Japan
|
|
gptkbp:primary_source
|
gptkb:spacecraft
|
|
gptkbp:propulsion
|
1,000 k N
|
|
gptkbp:reliability
|
very reliable
|
|
gptkbp:seating_capacity
|
6 tons
vertical integration
15 tons
4 meters in diameter
geostationary transfer orbit
H-IIA 265 launched the Hayabusa spacecraft
|
|
gptkbp:succeeded_by
|
high
|
|
gptkbp:successor
|
H-IIA 202 rocket
|