Encyclopedia Astronautica
H-II



h2lifto.jpg
H-2 Liftoff
Credit: NASDA
Japanese orbital launch vehicle. 3 stage vehicle consisted of 2 x H-II SRB boosters + core vehicle.

LEO Payload: 10,060 kg (22,170 lb) to a 200 km orbit at 30.40 degrees. Payload: 3,930 kg (8,660 lb) to a GTO. Failures: 2. First Fail Date: 1994-08-28. Last Fail Date: 1999-11-15.

Status: Retired 1999.
Gross mass: 260,000 kg (570,000 lb).
Payload: 10,060 kg (22,170 lb).
Height: 49.00 m (160.00 ft).
Diameter: 4.00 m (13.10 ft).
Thrust: 3,970.00 kN (892,490 lbf).
Apogee: 200 km (120 mi).
First Launch: 1994.02.03.
Last Launch: 1999.11.15.
Number: 7 .

More... - Chronology...


Associated Countries
Associated Spacecraft
  • ETS Japanese technology satellite. 7 launches, 1975.09.09 (Kiku 1) to 2006.12.16 (Kiku 8). More...
  • GMS Japanese earth weather satellite. 5 launches, 1977.07.14 (Himawari 1) to 1995.03.18 (Himawari 5). The Geostationary Meteorological Satellite series were spin-stabilized satellites. More...
  • FS-1300 American communications satellite bus. Operational, first launch 1989.06.05. More...
  • VEP Japanese technology satellite. 2 launches, 1994.02.03 (VEP) and 2001.08.29 (VEP-2). Monitored H-2 launch vehicle performance. National name MYOJO. More...
  • OREX Japanese re-entry vehicle technology satellite. One launch, 1994.02.03. NASDA ballistic capsule used to test materials and acquire data related to atmospheric re-entry for use in design of Japanese HOPE spaceplane. Launch vehicle H-2. More...
  • SFU Japanese materials science satellite. One launch, 1995.03.18. Carried materials, astronomy, biological experiments; released and later retrieved by space shuttle. More...
  • Fuji Japanese amateur radio communications satellite. One launch, 1996.08.17, JAS-2. Japanese amateur radio satellite. More...
  • ADEOS Japanese earth atmosphere satellite. 2 launches, 1996.08.17 (ADEOS) and 2002.12.14 (Adeos 2). The polar orbiting ADEOS spacecraft was to perform Earth, atmospheric, and oceanographic remote sensing. More...
  • ETS-7 Target Japanese rendezvous technology satellite. One launch, 1997.11.27, Orihime. Attached to Hikoboshi. Docking target for ETS-7. More...
  • ETS-7 Japanese rendezvous technology satellite. One launch, 1997.11.27, Hikoboshi. Technology satellite, to accomplish remote automatic rendezvous and docking. More...
  • TRMM American earth atmosphere satellite. One launch, 1997.11.27. TRMM was an international mission dedicated to measuring tropical and subtropical rainfall. More...
  • Kakehashi Japanese communications satellite. One launch, 1998.02.21. Name means 'Bridge', was called Communications and Broadcasting Experimental Test Satellite (COMETS) before launch. It contained Ka-band communications and inter-satellite data relay payloads. More...

See also
  • H-2 Heavy lift Japanese indigenous launch vehicle. The original H-2 version was cancelled due to high costs and poor reliability and replaced by the substantially redesigned H-2A.

    3 stage vehicle consisted of 2 x H-II SRB + 1 x H-II stage 1 + 1 x H-II stage 2 More...


Associated Manufacturers and Agencies
  • Mitsubishi Japanese manufacturer of rockets, spacecraft, and rocket engines. Mitsubishi Electric Corp, Japan. More...

Associated Launch Sites
  • Tanegashima Japan's main launch site for he larger N and H launch vehicles. In use for sounding rockets from 1967 and orbital launches from 1975. As of 2007 over 140 major launches had been made from the site. More...

Associated Stages
  • H-2-0 Solid propellant rocket stage. Loaded/empty mass 70,400/11,250 kg. Thrust 1,540.00 kN. Vacuum specific impulse 273 seconds. More...
  • H-2-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 98,100/11,900 kg. Thrust 1,078.00 kN. Vacuum specific impulse 446 seconds. More...
  • LE-5EC Lox/LH2 propellant rocket stage. Loaded/empty mass 16,700/2,700 kg. Thrust 121.50 kN. Vacuum specific impulse 452 seconds. More...

H-II Chronology


1994 February 3 - . 22:20 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. LV Configuration: H-II H-II-1F.
  • OREX - . Payload: Ryusei. Mass: 865 kg (1,906 lb). Nation: Japan. Class: Technology. Type: Re-entry vehicle technology satellite. Spacecraft: OREX. Decay Date: 1994-02-03 . USAF Sat Cat: 22978 . COSPAR: 1994-007A. Apogee: 451 km (280 mi). Perigee: 450 km (270 mi). Inclination: 30.5000 deg. Period: 93.50 min. Summary: Orbital Reentry Experiment. Orbital Re-entry Experiment Vehicle (OREX) Ryusei. Acquisition of data related to atmospheric reentry. Launch vehicle H-II rocket test flight H-II 1F. Launching organization NASDA. Launch time 2220:00 UT. .
  • VEP - . Payload: Myojo / LAPS. Mass: 2,391 kg (5,271 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: VEP. USAF Sat Cat: 22979 . COSPAR: 1994-007B. Apogee: 36,261 km (22,531 mi). Perigee: 449 km (278 mi). Inclination: 28.6000 deg. Period: 645.00 min. Vehicle Evaluation Payload; monitored H-2 performance. Vehicle Evaluation Payload (VEP) MYOJO. Provides a ranging function as well as functions to measure the acceleration and deformation, in order to confirm the accuracy of the H-II rocket orbit injection and understand the environment of the payload equipme nt. Launch vehicle H-II rocket test flight H-II 1F. Launching organization NASDA. Launch time 2220:00 UT.

1994 August 28 - . 07:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. LV Configuration: H-II H-II-2F. FAILURE: LAPS apogee kick motor failed to ignite. Partial Failure.. Failed Stage: 3.
  • Kiku 6 - . Payload: ETS 6. Mass: 3,800 kg (8,300 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 23230 . COSPAR: 1994-056A. Apogee: 38,677 km (24,032 mi). Perigee: 8,565 km (5,322 mi). Inclination: 13.2300 deg. Period: 861.84 min. Summary: Failed to reach geostationary orbit; Engineering Test Satellite; partial mission success. Also tested ion engines for NSSK..

1995 March 18 - . 08:01 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. LV Configuration: H-II H-II-3F.
  • SFU - . Mass: 4,000 kg (8,800 lb). Nation: Japan. Agency: NASDA. Class: Materials. Type: Materials science satellite. Spacecraft: SFU. Decay Date: 1996-01-20 . USAF Sat Cat: 23521 . COSPAR: 1995-011A. Apogee: 483 km (300 mi). Perigee: 471 km (292 mi). Inclination: 28.5000 deg. Period: 94.10 min. Summary: Space Flyer Unit; carried materials, astronomy, biological experiments; retrieved by STS-72 1/20/96..
  • Himawari 5 - . Payload: GMS 5. Mass: 746 kg (1,644 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: GMS. USAF Sat Cat: 23522 . COSPAR: 1995-011B. Apogee: 35,791 km (22,239 mi). Perigee: 35,784 km (22,235 mi). Inclination: 0.6000 deg. Period: 1,436.00 min. Geostationary Meteorological Satellite; carried search and rescue package. Stationed at 140.2 deg E. Positioned in geosynchronous orbit at 160 deg E in 1995; 140 deg E in 1995-1999 As of 5 September 2001 located at 139.99 deg E drifting at 0.028 deg W per day. As of 2007 Mar 10 located at 45.88E drifting at 3.134W degrees per day.

1996 August 17 - . 01:53 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. LV Configuration: H-II H-II-4F.
  • ADEOS - . Nation: Japan. Agency: NASDA. Class: Earth. Type: Atmosphere satellite. Spacecraft: ADEOS. USAF Sat Cat: 24277 . COSPAR: 1996-046A. Apogee: 800 km (490 mi). Perigee: 799 km (496 mi). Inclination: 98.6000 deg. Period: 100.90 min.
  • JAS-2 - . Nation: Japan. Agency: JARL. Class: Communications. Type: Civilian communications satellite. Spacecraft: Fuji. USAF Sat Cat: 24278 . COSPAR: 1996-046B. Apogee: 1,323 km (822 mi). Perigee: 801 km (497 mi). Inclination: 98.6000 deg. Period: 106.50 min. Summary: Japanese amateur radio satellite..

1997 November 27 - . 21:27 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. LV Configuration: H-II H-II-6F.
  • TRMM - . Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Atmosphere satellite. Spacecraft: TRMM. USAF Sat Cat: 25063 . COSPAR: 1997-074A. Apogee: 403 km (250 mi). Perigee: 395 km (245 mi). Inclination: 35.0000 deg. Period: 92.50 min. Summary: TRMM was an international mission dedicated to measuring tropical and subtropical rainfall. The spacecraft and four instruments were provided by the USA, while Japan provided one instrument and launch services..
  • Orihime - . Payload: ETS-7 Target. Nation: Japan. Agency: NASDA. Manufacturer: Toshiba. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS-7 Target. Decay Date: 1999-01-27 . USAF Sat Cat: 25424 . COSPAR: 1997-074E. Apogee: 458 km (284 mi). Perigee: 346 km (214 mi). Inclination: 34.5000 deg. Period: 92.60 min. Summary: Attached to Hikoboshi. It would later separate and serve as a passive docking target for the Hikobishi active automatic docking technology spacecraft..
  • Hikoboshi - . Payload: ETS-7. Nation: Japan. Agency: NASDA. Manufacturer: Toshiba. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS-7. USAF Sat Cat: 25064 . COSPAR: 1997-074B. Apogee: 548 km (340 mi). Perigee: 545 km (338 mi). Inclination: 35.0000 deg. Period: 95.50 min. The Orihime and Hikoboshi satellites undocked and redocked on July 7 1998 in the FP-1 test of automated docking systems. Despite claims of the NASDA space agency that this is a first, automated Russian craft have docked on many occasions since the Kosmos-186/188 docking in 1968.

1998 February 21 - . 07:55 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. LV Configuration: H-II H-II-5F.
  • Kakehashi - . Payload: COMETS. Nation: Japan. Agency: NASDA. Manufacturer: Toshiba; NEC. Class: Communications. Type: Civilian communications satellite. Spacecraft: Kakehashi. USAF Sat Cat: 25175 . COSPAR: 1998-011A. Apogee: 17,727 km (11,015 mi). Perigee: 1,033 km (641 mi). Inclination: 30.1000 deg. Period: 328.10 min. Kakehashi, meaning 'Bridge', was called Communuications and Broadcasting Experimental Test Satellite (COMETS) before launch. It contained Ka-band communications and inter-satellite data relay payloads. Premature shutdown 44 seconds into the H-II second stage second burn put the satellite into a much lower than planned orbit. The on-board Unified Propulsion System was used to raise it to a more useful orbit.

1999 November 15 - . 07:29 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. LV Configuration: H-II H-II-8F. FAILURE: Failure during first stage burn.. Failed Stage: 1.
  • MTSAT - . Nation: Japan. Agency: NASDA. Manufacturer: Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. COSPAR: F991115A. Multi-functional Transportation Satellite intended to provide communications and air traffic control for the Japanese transportation ministry and a meteorological data for the Japanese Meteorological Agency. The spacecraft had a mass of 1223 kg dry and was a follow-on to the GMS (Himawari) weather satellite series.

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