Space Transportation Systems H-IIA Launch Vehicle

In Operation

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.
H-IIA launch service operations have been transferred to Mitsubishi Heavy Industries, LTD. ahead of the launch of H-IIA Flight 13. JAXA is in charge of launch safety management (including ground safety confirmation, flight safety assurance, and overall countdown control and supervision.)

Major Characteristics

Major Specifications of the H-IIA launch vehicle

Length (m) 53
Liftoff mass (t) 289 (without payload mass)
Guidance Method Inertial Guidance Method
Item
First Stage SRB-A SSB Second Stage Payload
Length (m) 37.2 15.1 14.9 9.2 12
Diameter (m) 4 2.5 1 4 4.07
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
Auxiliary engine
Gimballed nozzle system Gimballed nozzle system Gimbal engine system
Gas jet system
-
Avionics Control Systems,
Telemetry Transmitter
- - Guidance Navigation,
and Control Systems,
Rader Transponder,
Telemetly Transmitter,
Command Destruct Receiver
-

Launch Capability (H-IIA Standard)

Orbit Altitude Payloads
Geosynchronous Transfer Orbit
(GTO)
about 36,000km about 4t
Low Earth Orbit
(Inclination:30 degrees
about 300km about 10t
Sun Synchronous Orbit
(Summer/Other seasons)
about 800km about 4t /
about 3.8t
Escape from the Earth Gravitation Planetary Mission about 2.5t

H-IIA Lineup

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.

Launch Records

Flight No. Model Launch Date Payload
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)

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