|
gptkbp:instance_of
|
gptkb:Team_Rocket
|
|
gptkbp:configuration
|
gptkb:H-IIA_202
|
|
gptkbp:debut
|
multiple successful launches
|
|
gptkbp:development
|
ongoing since 1994
|
|
gptkbp:diameter
|
4 meters
|
|
gptkbp:elevation
|
4 meters
53 meters
288,000 kg
|
|
gptkbp:engine
|
gptkb:Mitsubishi_Heavy_Industries
|
|
gptkbp:engine_type
|
gptkb:LE-7_A
|
|
gptkbp:first_flight
|
gptkb:2004
|
|
gptkbp:guidance_system
|
inertial navigation
|
|
gptkbp:height
|
53 meters
|
|
https://www.w3.org/2000/01/rdf-schema#label
|
H-IIA 267 rocket
|
|
gptkbp:launch_date
|
approximately 2-3 per year
September 14, 2018
|
|
gptkbp:launch_event
|
successful
|
|
gptkbp:launch_platform
|
gptkb:Tanegashima_Space_Center
Japan Aerospace Exploration Agency (JAXA
|
|
gptkbp:launch_site
|
gptkb:Tanegashima_Space_Center
|
|
gptkbp:launch_vehicle
|
gptkb:Tanegashima_Space_Center
gptkb:30
gptkb:H-IIB_rocket
2
high
expendable launch vehicle
ongoing since 1994
H-II family
1,000 k N
LE-7 A and solid rocket boosters
|
|
gptkbp:launch_vehicle_frequency
|
2-3 per year
|
|
gptkbp:launch_vehicle_guidance_system
|
inertial navigation
|
|
gptkbp:launch_vehicle_operational_period
|
2004-2018
|
|
gptkbp:launch_vehicle_payload_capacity_gto
|
4,000 kg
|
|
gptkbp:launch_vehicle_payload_fairing
|
4 meters in diameter
|
|
gptkbp:launch_window
|
varies by mission
|
|
gptkbp:launched
|
gptkb:30
|
|
gptkbp:manufacturer
|
gptkb:Mitsubishi_Heavy_Industries
|
|
gptkbp:mass
|
288,000 kg
|
|
gptkbp:notable_mission
|
H-IIA 267 launch of Akasaki satellite
|
|
gptkbp:number_of_stages
|
2
liquid-fueled
|
|
gptkbp:operational_period
|
2004-2018
|
|
gptkbp:operational_status
|
retired
|
|
gptkbp:payload_capacity
|
10,000 kg
4,000 kg
4 meters in diameter
10,000 kg to LEO
done at Tanegashima Space Center
|
|
gptkbp:propulsion
|
1,000 k N
|
|
gptkbp:purpose
|
gptkb:Space_Launch_System
|
|
gptkbp:recovery_method
|
gptkb:none
|
|
gptkbp:reliability
|
high
|
|
gptkbp:successor
|
gptkb:H-IIB_rocket
|
|
gptkbp:bfsParent
|
gptkb:Tanegashima_Space_Center
|
|
gptkbp:bfsLayer
|
4
|