Statements (126)
| Predicate | Object |
|---|---|
| gptkbp:instance_of |
gptkb:Space_Launch_System
gptkb:Team_Rocket |
| gptkbp:collaboration |
NASA, ESA.
|
| gptkbp:configuration |
204
|
| gptkbp:control_system |
Digital control system
|
| gptkbp:debut |
Part of the H-IIA program
over 30 launches since introduction. |
| gptkbp:design_purpose |
satellite launch.
|
| gptkbp:development_cost |
estimated at $1 billion.
|
| gptkbp:diameter |
4 meters
|
| gptkbp:durability |
not reusable.
|
| gptkbp:elevation |
4 meters.
53 meters. |
| gptkbp:engine_configuration |
single engine.
|
| gptkbp:engine_type |
gptkb:LE-7_A
liquid-fueled. |
| gptkbp:first_flight |
gptkb:2001
2014-02-22 2004-08-29 |
| gptkbp:fuel_type |
Liquid hydrogen and kerosene
|
| gptkbp:guidance_system |
Inertial guidance system
inertial navigation. |
| gptkbp:height |
53 meters
|
| https://www.w3.org/2000/01/rdf-schema#label |
H-IIA 204
|
| gptkbp:last_successful_launch |
2021-03-30.
|
| gptkbp:launch_control_agency |
JAXA.
|
| gptkbp:launch_date |
2021-03-30
2014-12-03 Approx. 30 minutes approximately 2-3 per year 2004-08-29 |
| gptkbp:launch_event |
100%
over 95% successful |
| gptkbp:launch_frequency_per_year |
2-3.
|
| gptkbp:launch_mass |
approximately 300 tons
200,000 kg |
| gptkbp:launch_platform |
gptkb:JAXA
Japan Aerospace Exploration Agency (JAXA Mitsubishi Heavy Industries. Tanegashima. |
| gptkbp:launch_price |
approximately $90 million.
|
| gptkbp:launch_provider_country |
Japan.
|
| gptkbp:launch_site |
gptkb:Tanegashima_Space_Center
Tanegashima Space Center. |
| gptkbp:launch_vehicle |
gptkb:H-IIA
ongoing. active. 2. high reliability. planned upgrades. 204. 53m height, 4m diameter. Launch Complex 1. advanced guidance systems. commercial and scientific missions. expendable launch vehicle. high payload capacity. medium-lift. operational since 2004. satellite deployment. significant in Japanese space history. solid rocket boosters. two-stage. |
| gptkbp:launch_vehicle_collaborations |
international partnerships.
|
| gptkbp:launch_window |
varies by mission.
|
| gptkbp:launched |
gptkb:20
gptkb:Akasaki_satellite multiple over 40 several months. Standard configuration over 30. two solid rocket boosters. |
| gptkbp:manufacturer |
gptkb:Mitsubishi_Heavy_Industries
|
| gptkbp:mission |
gptkb:H-IIA_205
successful high. DSN-1 H-IIA 203 |
| gptkbp:mission_duration |
approximately 30 minutes
|
| gptkbp:mission_type |
satellite deployment
Satellite launch commercial, scientific. |
| gptkbp:notable_achievements |
successful ISS resupply missions.
|
| gptkbp:notable_launches |
H-IIA 204 launched Akasaki satellite
H-IIA 204 launched Akasaki satellite. |
| gptkbp:number_of_engines |
1 main engine.
|
| gptkbp:number_of_stages |
gptkb:LE-5_B_engine
2 LE-7 A engine |
| gptkbp:operational_since |
2004.
|
| gptkbp:operational_status |
Retired
active |
| gptkbp:operator |
gptkb:Mitsubishi_Heavy_Industries
|
| gptkbp:orbit_type |
geostationary transfer orbit
|
| gptkbp:orbital_inclination |
20 degrees
geostationary. |
| gptkbp:payload_capacity |
gptkb:H-IIA_202
gptkb:satellite 4 meters 4,000 kg 4 meters in diameter 4,000 kg to geostationary transfer orbit Multiple payloads deployed 4 meters. H-II Transfer Vehicle. done at Tanegashima. scientific, commercial. up to 4,000 kg. various orbits. various satellites. |
| gptkbp:primary_user |
gptkb:Japan_Aerospace_Exploration_Agency_(JAXA)
|
| gptkbp:propulsion |
1,000 k N
1,000 k N. |
| gptkbp:reliability |
gptkb:High
high |
| gptkbp:safety_record |
excellent.
|
| gptkbp:strategic_goals |
gptkb:0
|
| gptkbp:success |
gptkb:10
gptkb:true multiple satellite deployments. |
| gptkbp:success_rate |
over 90%
|
| gptkbp:upgrades |
upgraded engines.
|
| gptkbp:bfsParent |
gptkb:Team_Rocket
|
| gptkbp:bfsLayer |
3
|