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Space


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.)

The H2A202 is the H-IIA standard type of this series. Two solid rocket boosters (SRB-A) are equipped. Capable of launching up to four (4) metric tons into Geostationary Transfer Orbit (GTO). In the H2A204 Launch Vehicle Configuration four solid rocket boosters (SRB-A) are attached. The H2A204 configuration is capable of launching six (6) metric tons into Geostationary Transfer Orbit (GTO).

On 24 November 2015 an H-IIA rocket carrying a Canadian communications satellite lifted off Tuesday, marking the first time a commercial satellite had been launched into space by the Japanese-built booster. The price tag for the latest launch came to around ¥12 billion, still much higher than the cost of a similar launch using California-based Space Exploration Technologies Corp.’s Falcon 9 rocket, which costs ¥8 billion or less.

The H-IIA F29 with Telstar 12 VANTAGE onboard lifted off at 3:50:00 p.m. on Nov. 24, (Japan Standard Time) from the Tanegashima Space Center. The launch vehicle flew smoothly, and, at about 4 hours and 27 minutes after liftoff, the separation of the Telstar 12 VANTAGE was confirmed.

H-IIA F29 incorporated the outcome of the H-IIA UPGRADE. Following a long coast, the 3rd burn of the upgraded 2nd stage was conducted successfully. Then, Telstar 12 VANTAGE was injected closer to geostationary orbit. The H-IIA UPGRADE brought unique capabilities to the H-IIA launch vehicle. The upgrade enables the H-IIA to perform a long coast flight, and allows the second stage engine to ignite for the third time at the apogee. With these new capabilities, the H-IIA was able to inject the Telstar 12 VANTAGE closer to geostationary orbit than conventional geostationary transfer orbit.

JAXA plans to launch six H3 rockets annually, phasing out the older H-IIA rocket, its current mainstay, after its 50th launch later this fiscal year, which runs through March 2025.

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

H2A202 Launch Vehicle Configuration

H2A202 Launch Vehicle Configuration

  1. Payload Fairing
  2. Satellite (Spacecraft)
  3. Payload Adapter
  4. Payload Support Structure
  5. Cryogenic Helium Gas Bottles
  6. Second Stage Liquid Hydrogen Tank
  7. Second Stage Liquid Oxygen Tank
  8. Avionics Equipment Panel
  9. RCS (Reaction Control System)
  10. Ambient Helium Gas Bottles
  11. Second Stage Engine (LE-5B Engine)
  12. Interstage Section
  13. First Stage Liquid Oxygen Tank
  14. Center Body Section
  15. First Stage Liquid Hydrogen Tank
  16. Solid Rocket Boosters (SRB-A)
  17. First Stage Engine Section
  18. Auxiliary Engine
  19. Ambient He bottles
  20. First Stage Engine (LE-7A Engine)
  21. SRB-A Movable Nozzle

H2A204 Launch Vehicle Configuration

H2A204 Launch Vehicle Configuration

  1. Payload Fairing
  2. Satellite (Spacecraft)
  3. Payload Adapter
  4. Payload Support Structure
  5. Cryogenic Helium Gas Bottles
  6. Second Stage Liquid Hydrogen Tank
  7. Second Stage Liquid Oxygen Tank
  8. Avionics Equipment Panel
  9. RCS (Reaction Control System)
  10. Ambient Helium Gas Bottles
  11. Second Stage Engine (LE-5B Engine)
  12. Interstage Section
  13. First Stage Liquid Oxygen Tank
  14. Center Body Section
  15. First Stage Liquid Hydrogen Tank
  16. Solid Launch Vehicle Boosters (SRB-A)
  17. First Engine Section
  18. Auxiliary Engine
  19. Ambient He bottles
  20. First Stage Engine (LE-7A Engine)
  21. SRB-A Movable Nozzle




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