"Himawari-9" lifted off for space! Launch Success of H-IIA F31.
The H-IIA Launch Vehicle No. 31 with the Geostationary Meteorological Satellite "Himawari-9" onboard lifted off at 3:20 p.m. on November 2, 2016 (Japan Standard Time) from the Tanegashima Space Center. The launch vehicle flew as planned, and at about 27 minutes and 51 seconds after liftoff, the separation of the "Himawari-9" was confirmed. Press Release JAXA channel [YouTube] Meteorological Satellite Center of JMA ...
- Nov. 25, 2016 (17:00) [release]
- Launch of the H-IIA Launch Vehicle No. 32 with X-band defense telecommunication satellite-2 on board
About H-IIA Launch Vehicle
Leading edge, efficient and economical technology Japanese main large-scale launch vehicle, H-IIA
H-IIA, Japan?s primary large-scale launch vehicle, is designed to meet diverse launch demands, at lower cost and with a high degree of reliability, by making the best use of the H-II launch-vehicle technology. The simplified design and improved efficiency of the manufacturing and launch processes of H-IIA have achieved one of the highest performance to cost ratio of launch system in the world, reducing the cost of launches by a half or more.
JAXA is conducting the H-IIA upgrade project to improve the H-IIA launch capability and its global competitiveness.
Major Specifications of the H-IIA launch vehicle
|Liftoff mass (t)||289 (without payload mass)|
|Guidance Method||Inertial Guidance Method|
|First Stage||SRB-A||SSB||Second Stage||Payload|
|Mass (t)||114||151 (2 units)||31 (2 units)||20||1.4|
|Propellant mass||101.1||130 (2 units)||52.4 (4 units)||16.9||-|
|Thrust (KN)||1,098||5,040 (2 units)||1,490 (2 units)||137||-|
|Burning time (s)||390||100||60||530||-|
|Propellant||Lox/LH2||Polybutadiene composite solid propellant||Polybutadiene composite solid propellant||Lox/LH2||-|
|Propellant Loading Method||Turbo pomp||-||-||Turbo pomp||-|
|Specific Impulse (s)||440||283||282||448||-|
|Attitude control method||Gimbal engine system
|Gimballed nozzle system||Gimballed nozzle system||Gimbal engine system
Gas jet system
and Control Systems,
Command Destruct Receiver
Launch Capability (H-IIA Standard)
|Geosynchronous Transfer Orbit
|about 36,000km||about 4t|
|Low Earth Orbit
|about 300km||about 10t|
|Sun Synchronous Orbit
|about 800km||about 4t / about 3.8t|
|Escape from the Earth Gravitation||Planetary Mission||about 2.5t|
H-IIA Launch Vehicle can be in various configurations by installing solid rocket boosters (SRB-As) additionally. H-IIA can answer various launch needs of payload size and weight by its family members.
* Currently, only H2A202 and H2A204 types are in operation.
Upgrading JAXA's flagship launch vehicle
JAXA is proud of the launch success rate of the H-IIA Launch Vehicle, which is among the highest levels in the world. However, as it has been 14 years since its maiden launch, some issues have been raised such as the aging launch facility and the need for a larger payload launch capacity. JAXA is conducting the H-IIA upgrade project to tackle those issues. We will achieve more efficient launch vehicle operations by improving H-IIA launch capability and its global competitiveness, and simplifying the ground facility.
H-IIA Upgrade Project
Improved function and performance
(1) Enhanced launch capacity of a geostationary satellite
By increasing the duration of flight time and the number of engine ignitions, more flexible flight patterns become possible, and the launch capability of a geostationary satellite is also increased.
- H-IIA UPGRADE - Moving to a new stage
Enhanced launch performance to cope with geostationary satellite launch ? Adopting it to the H-IIA Launch Vehicle No. 29
(2) Easing the onboard environmental restriction for payloads
The onboard environment has been improved for payloads to among the highest levels in the world by adopting a mechanism that is not based on pyrotechnics.
Reducing maintenance/renovation costs of facility
(3) Simplified ground facility
Ground tracking radars are no longer necessary as the onboard flight safety navigation sensor was developed.
|Flight No.||Model||Launch Date||Payload|
|F31||H2A202||11/2/2016||Geostationary Meteorological Satellite "Himawari-9"|
|F30||H2A202||2/17/2016||X-ray Astronomy Satellite "Hitomi" (ASTRO-H)|
|H2A204||11/24/2015||Telstar 12 VANTAGE|
|F28||H2A202||3/26/2015||IGS (Information Gathering Satellites)|
|F27||H2A202||2/1/2015||IGS (Information Gathering Satellites)|
|F26||H2A202||12/3/2014||Asteroid Explorer "Hayabusa2"|
|F25||H2A202||10/7/2014||Geostationary Meteorological Satellite "Himawari-8"|
|F24||H2A202||5/24/2014||Advanced Land Observing Satellite-2 "DAICHI-2" (ALOS-2)|
|F23||H2A202||2/28/2014||Global Precipitation Measurement/Dual-frequency Precipitation Radar (GPM/DPR)|
|F22||H2A202||1/27/2013||IGS (Information Gathering Satellites)|
|F21||H2A202||5/18/2011||Global Change Observation Mission 1st - Water "SHIZUKU" (GCOM-W1)
Small Demonstration Satellite-4 (SDS-4)
|F20||H2A202||12/12/2011||IGS (Information Gathering Satellites)|
|F19||H2A202||9/23/2011||IGS (Information Gathering Satellites)|
|F18||H2A202||9/11/2010||Quasi-Zenith Satellite-1 "MICHIBIKI"|
|F17||H2A202||5/21/2010||Venus Climate Orbiter "AKATSUKI" (PLANET-C)
Interplanetary Kite-craft Accelerated by Radiation Of the Sun "IKAROS"
|F16||H2A202||11/28/2009||IGS (Information Gathering Satellites)|
|F15||H2A202||1/23/2009||Greenhouse gases Observing SATellite "IBUKI" (GOSAT)
Small Demonstration Satellite-1 (SDS-1)
|F14||H2A2024||2/23/2008||Wideband InterNetworking engineering test and Demonstration Satellite "KIZUNA" (WINDS)|
|F13||H2A2022||9/14/2007||SELenological and ENgineering Explorer "KAGUYA" (SELENE)|
|F12||H2A2024||2/24/2007||IGS (Information Gathering Satellites)|
|F11||H2A204||12/18/2006||Engineering Test Satellite VIII "KIKU No.8" (ETS-VIII)|
|F10||H2A202||9/11/2006||IGS (Information Gathering Satellites)|
|F9||H2A2024||2/18/2006||Multi-functional Transport Satellite-2 "Himawari-7" (MTSAT-2)|
|F8||H2A2022||1/24/2006||Advanced Land Observing Satellite "Daichi" (ALOS)|
|F7||H2A2022||2/26/2005||Multi-Functional Transport Satellite-1 Replacement "Himawari-6" (MTSAT-1R)|
|F6||H2A2024||11/29/2003||IGS (Information Gathering Satellites)
* H-IIA F6 was consequently destroyed by a destruction command from the ground as the vehicle did not gain enough height and speed due to the failure.
|F5||H2A2024||3/28/2003||IGS (Information Gathering Satellites)|
|F4||H2A202||12/14/2002||Advanced Earth Observation Satellite-II "Midori II" (ADEOS-II)
Engineering Test Satellite "Micro-LabSat"
Whale Ecology Observation Satellite (WEOS)
Federation Satellite (FedSat)
|F3||H2A2024||9/10/2002||Data Relay Test Satellite "KODAMA" (DRTS)
Unmanned Space Experiment Recovery System (USERS)
|TF2||H2A2024||2/4/2002||Mission Demonstration test Satellite-1 "TSUBASA" (MDS-1)
H-IIA Vehicle Evaluation Payload #3 (VEP-3)
DASH (Demonstrator of Atmospheric Reentry System with Hyper Velocity)
|TF1||H2A202||8/29/2001||Laser Ranging Equipment (LRE)
H-IIA Vehicle Evaluation Payload #2 (VEP-2)