Encyclopedia Astronautica
Tanegashima



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Tanegashima
Credit: © Mark Wade
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Tanegashima
Location of Tanegashima
Credit: © Mark Wade
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.

Minimum Inclination: 99.0 degrees. Maximum Inclination: 99.0 degrees.

Location: Tanegashima Space Center.
Longitude: 130.9681 deg.
Latitude: 30.3910 deg.

More... - Chronology...


Associated Countries
Associated Spacecraft
  • Oscar International series of amateur radio communications satellites. Operational, first launch 1961.12.12. Launched in a variety of configurations and by many nations. More...
  • ETS Japanese technology satellite. 7 launches, 1975.09.09 (Kiku 1) to 2006.12.16 (Kiku 8). More...
  • JISS Japanese earth ionosphere satellite. 2 launches, 1976.02.29 (ISS 1) to 1978.02.16 (ISS 2). JISS - national name "Ume". Spin-stabilized; Ionospheric Sounder, Radio Noise Receiver, Plasma Measuring Equipment, Ion Mass Spectrometer, and other instruments. 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...
  • Ayame Japanese communications technology satellite. 2 launches, 1979.02.06 (Ayame 1) and 1980.02.22 (Ayame 2). Experimental Communications Satellite (ECS). Communications and propagation experiments of satellite-communication systems. More...
  • AS 3000 American communications satellite. 25 launches, 1981.11.20 (RCA Satcom 4; RCA Satcom 3R) to 1996.01.14 (Koreasat 2). More...
  • CS-2 Japanese communications satellite. 2 launches, 1983.02.04 (Sakura 2A) to 1983.08.05 (Sakura 2B). Business communications. Launching organization NASDA (National Space Development Agency of Japan). More...
  • EGS Japanese earth geodetic satellite. One launch, 1986.08.12. Experimental Geophysical Payload; new launch vehicle test flight. EGS (Ajisai). Improvement of the accuracy of domestic geodetic triangulation network. More...
  • MABES Japanese technology satellite. One launch, 1986.08.12. MABES (Jindai). Experiment on the levitation of the magnetic bearing flywheel under zero-g condition. More...
  • Marine Observation Satellite Japanese earth sea satellite. 2 launches, 1987.02.19 (MOS-1) to 1990.02.07 (MOS-1b). The MOS 1A and 1B satellites, also known as Momo 1A and 1B, were Japan's first Earth resources satellites. More...
  • CS-3 Japanese communications satellite. 2 launches, 1988.02.19 (Sakura 3A) to 1988.09.16 (Sakura 3B). To continue communications services provided by the communications satellite 2 (CS-2). To meet increasing and diversifying demands for communications. More...
  • FS-1300 American communications satellite bus. Operational, first launch 1989.06.05. More...
  • Debut Japanese communications technology satellite. One launch, 1990.02.07. Boom, umbrella test. DEBUT "Orizuru". Experiment of extending and contracting boom; experiment of expanding and contracting aerodynamic brake. Launching organization NASDA. More...
  • JERS Japanese earth land resources satellite. One launch, 1992.02.11. JERS-1 (Japanese Research Satellite-1; FUYO-1) was Japan's second Earth observation satellite. 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...
  • 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...
  • SFU Japanese materials science satellite. One launch, 1995.03.18. Carried materials, astronomy, biological experiments; released and later retrieved by space shuttle. 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...
  • Fuji Japanese amateur radio communications satellite. One launch, 1996.08.17, JAS-2. Japanese amateur radio satellite. 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...
  • ETS-7 Target Japanese rendezvous technology satellite. One launch, 1997.11.27, Orihime. Attached to Hikoboshi. Docking target for ETS-7. 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...
  • LRE Japanese earth geodetic satellite. One launch, 2001.08.29. The 87 kg Laser Ranging Experiment was a passive mirror ball of diameter 51 cm and carried 24 glass sheets and 126 prisms on its surface. More...
  • MDS Japanese technology satellite. One launch, 2002.02.04. MDS (Mission Demonstration Satellite) was a technology demonstrator to flight-qualify commercial subsystems. More...
  • DASH 2002 Japanese re-entry vehicle technology satellite. One launch, 2002.02.04, DASH. DASH (Demonstrator of Atmospheric Reentry System and Hypervelocity) was a small secondary payload built by ISAS, the scientific space agency which was to merge with NASDA. More...
  • USERS Japanese materials science satellite. One launch, 2002.09.10. USERS (Unmanned Space Experiment Recovery System) was a Japanese microgravity experimental satellite. More...
  • DRTS Japanese geostationary communications satellite. One launch, 2002.09.10. DRTS (Data Relay Transponder Satellite) relayed images and data procured by the ADEOS 2 and ALOS satellites, and the KIBO module on ISS. More...
  • FedSat Australian communications satellite. One launch, 2002.12.14. FedSat contained high-tech communication, space science, navigation and computing equipment and was intended to help bring broadband Internet services to remote parts of Australia. More...
  • WEOS Kanta-Kun Japanese earth land resources satellite. One launch, 2002.12.14. Ecology satellite. More...
  • Mu-Labsat Japanese technology satellite. One launch, 2002.12.14. Technology satellite, which released two tiny subsatellites in an experiment to test an onboard tracking imager for inspector satellites. More...
  • IGS Japanese military surveillance satellite. Operational, first launched 2003.03.28. Japan's first military reconnaissance satellites, launched in optical and radar versions. More...
  • Daichi Japanese civilian surveillance radar satellite. One launch, 2006.01.24. Advanced Land Observing Satellite, which carried an L-band synthetic aperture radar, an optical 2. More...
  • DS2000 Japanese communications satellite bus. Operational, first launch 2006.02.18. Mitsubishi Electric developed the DS2000 standard satellite platform based on a design originally created for the DRTS and ETS-8 platforms for NASDA. More...
  • Kizuna Japanese communications satellite. One launch, 2008.02.23. More...
  • PRISM Japanese military surveillance radar satellite. One launch, 2009.01.23. Remote sensing picosatellite built by the University of Tokyo, with a 10-cm aperture Earth imager on a 1-meter deployable boom. More...
  • SOHLA Japanese military surveillance radar satellite. One launch, 2009.01.23. Satellite built by the Space Oriented Higashi-osaka Leading Association, Osaka, carrying a cloud cover imager. More...
  • SpriteSat Japanese science. One launch, 2009.01.23. Microsatellite stabilized by a gravity gradient boom to study atmospheric sprites, built by by Tohoku University, Sendai. More...
  • Kagayaki Japanese technology satellite. One launch, 2009.01.23. Technology satellite built by Sorun Corporation, Tokyo, with several technology payloads. More...
  • JAXA SDS Japanese technology satellite. One launch, 2009.01.23, SDS-1. JAXA Small Demonstration Satellite, a microsatellite with a camera, GPS receiver and sun sensor. More...
  • Ibuki Japanese earth atmosphere satellite. One launch, 2009.01.23. Greenhouse Gas Observing Satellite, renamed Ibuki after launch. More...
  • KKS Japanese military surveillance radar satellite. One launch, 2009.01.23. Picosatellite built by Kouku-kosen, the Tokyo Metropolitan College of Aeronautical Engineering, carrying an Earth imager. More...
  • Kukai Japanese tether technology satellite. One launch, 2009.01.23. Also named STARS, a Kagawa University picosatellite demonstrating a tethered space robot. It consisted of two tethered box-shaped packages, dubbed Ku and Kai. More...

See also
  • Delta The Delta launch vehicle was America's longest-lived, most reliable, and lowest-cost space launch vehicle. Development began in 1955 and it continued in service in the 21st Century despite numerous candidate replacements. More...
  • 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...

  • J All-solid rocket motor launch vehicle. Because of the high cost, the original J-1 design was superseded by an alternate J-1 F2 with a different booster stage. More...
  • Lambda All solid-propellant vehicle, Japan's first satellite launcher. The L-4S project simulated the procedures and demonstrated the capabilities required for orbital satellite launch essential to the follow-on Mu project. More...
  • MT-135 The MT-135 was a small single-stage sounding rocket designed to collect data on the middle atmosphere, such as ozone layer depletion. More...
  • Mu The Japanese Mu launcher series provided a flexible all-solid propellant launch vehicle for access to space. It was the first Japanese launch vehicle designed from the start as an orbital launch vehicle. More...
  • S Series of Japanese single-stage sounding rockets designed for low-cost observations of the ionosphere. More...

Associated Launch Vehicles
  • S-B Japanese sounding rocket. Single stage vehicle. More...
  • SA-II Japanese sounding rocket. Single stage vehicle. More...
  • LS-C Japanese test vehicle. Two stage vehicle consisting of 1 x LS-C Booster + 1 x LS-C More...
  • MT-135P Japanese sounding rocket. In 1969 the MT-135P was developed; featuring a parachute-equipped recoverable motor case for maritime safety. More...
  • S-C Japanese sounding rocket. Single stage vehicle. More...
  • JCR Japanese sounding rocket. Single stage vehicle. More...
  • ETV Japanese test vehicle. Three stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x LE-3 More...
  • N-1 Delta Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle. More...
  • TT-500 Japanese sounding rocket. Small, half-meter diameter, two stage suborbital rocket used for tracking system and microgravity tests. More...
  • N-2 Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle. More...
  • H-1 Japanese license-built version of Delta launch vehicle, with Japanese-developed upper stages. More...
  • TR-1 Japanese test vehicle. Single stage vehicle. More...
  • H-II Japanese orbital launch vehicle. 3 stage vehicle consisted of 2 x H-II SRB boosters + core vehicle. More...
  • J-1 Japanese all-solid orbital launch vehicle. Original version. More...
  • H-IIA 202 Japanese orbital launch vehicle. Three stage version of H-IIA consisting of 2 x H-II SRB-A + two-stage core vehicle. More...
  • H-IIA 2024 Japanese orbital launch vehicle. Three stage vehicle consisting of 4 x Castor 4XL + 2 x H-II SRB-A boosters + two-stage core vehicle. More...
  • H-IIB Japanese orbital launch vehicle, utilizing H-IIA engines, but with larger-diameter all-new stages. Designed to place Japanese ISS HTV logistics vehicle into orbit. More...

Associated Manufacturers and Agencies
  • NASDA Japanese agency overseeing development of rockets, spacecraft, and rocket engines. National Space Development Agency, Japan. More...

Associated Programs
  • BS Medium-scale broadcasting satellites for experimental purposes and communications to Japanese home islands. More...
  • CS Medium-capacity Communications Satellite for Experimental Purposes, a spin stabilized geostationary communications satellite. More...
  • Oscar Amateur radio satellite network. For over a third of a century a series of OSCAR satellites have been launched in a variety of configurations and by many nations. More...

Bibliography
  • McDowell, Jonathan, Jonathan's Space Home Page (launch records), Harvard University, 1997-present. Web Address when accessed: here.

Associated Launch Sites

Tanegashima Chronology


1967 - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: NAL-16. LV Configuration: NAL-16 NAL-16TR.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 45 km (27 mi).

1968 September 17 - . 07:10 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: SA-II. LV Configuration: SA-II SA-II A9.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 20 km (12 mi).

1968 September 19 - . 01:58 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: Lambda. Launch Vehicle: LS-C. LV Configuration: LS-C-D.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 100 km (60 mi).

1968 September 19 - . 07:01 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: NAL-16. LV Configuration: NAL-16 NAL-16H F1.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 100 km (60 mi).

1969 January 30 - . 01:31 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: NAL-16. LV Configuration: NAL-16 NAL-16 31D.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 50 km (31 mi).

1969 February 1 - . 01:40 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: NAL-25. LV Configuration: NAL-25 NAL-25 31.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 50 km (31 mi).

1969 February 6 - . 06:31 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: Lambda. Launch Vehicle: LS-C. LV Configuration: LS-C-1.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

1969 February 7 - . 06:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: S-C. LV Configuration: S-C SC-3.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 85 km (52 mi).

1969 February 8 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: S-C. LV Configuration: S-C SC-4.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 85 km (52 mi).

1969 February 8 - . 06:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: S-C. LV Configuration: S-C SC-1.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 85 km (52 mi).

1969 September 9 - . 06:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B SB-III F11.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1969 September 10 - . 06:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: Lambda. Launch Vehicle: LS-C. LV Configuration: LS-C-2.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

1969 September 15 - . 01:40 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-1.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1969 September 16 - . 06:40 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-2.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1969 September 20 - . 01:55 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: NAL-16. LV Configuration: NAL-16 NAL-16H F2.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 100 km (60 mi).

1969 September 20 - . 06:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: NAL-7. LV Configuration: NAL-7 NAL-7 F7.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 20 km (12 mi).

1970 February 1 - . 01:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-3.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1970 February 3 - . 06:03 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: Lambda. Launch Vehicle: LS-C. LV Configuration: LS-C-3.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

1970 February 4 - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-4.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1970 September 7 - . 06:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: NAL-7. LV Configuration: NAL-7 NAL-7 BS9.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 20 km (12 mi).

1970 September 9 - . 06:40 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: Lambda. Launch Vehicle: LS-C. LV Configuration: LS-C-4.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

1971 February 1 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-5.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1971 February 3 - . 01:35 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B SB-III A12.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1971 February 3 - . 06:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B SB-III A13.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1971 September 6 - . 01:35 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B SB-III A14.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1971 September 10 - . 06:47 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: Lambda. Launch Vehicle: LS-C. LV Configuration: LS-C-5.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

1971 September 11 - . 01:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B SB-III A15.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1971 September 17 - . 06:40 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-6.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1972 February 2 - . 06:56 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T1.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1972 February 6 - . 06:35 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-7.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1972 February 7 - . 06:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T2.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1972 August 30 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T3.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1972 August 30 - . 06:15 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T4.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1972 September 25 - . 06:05 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: Lambda. Launch Vehicle: LS-C. LV Configuration: LS-C-6.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

1973 February 5 - . 01:52 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T5.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1973 February 7 - . 01:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-8.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1973 February 8 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T6.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1973 September 5 - . 01:57 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T7.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1973 September 5 - . 06:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T8.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1973 September 7 - . 01:40 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-9.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1974 February 1 - . 06:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: JCR. LV Configuration: JCR-10.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 200 km (120 mi).

1974 February 2 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T9.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1974 February 9 - . 06:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: Lambda. Launch Vehicle: LS-C. LV Configuration: LS-C-7.
  • LE-3 test - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

1974 February 10 - . 06:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T10.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1974 September 2 - . 06:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Q. LV Family: Mu. Launch Vehicle: ETV. LV Configuration: ETV-1.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 128 km (79 mi).

1974 September 3 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T11.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1974 September 3 - . 06:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T12.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1975 January 30 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T13.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1975 February 5 - . 06:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Q. LV Family: Mu. Launch Vehicle: ETV. LV Configuration: ETV-2.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 167 km (103 mi).

1975 February 7 - . 01:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T14.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1975 August 17 - . 06:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-210. LV Configuration: TT-210 TT-210-1F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

1975 September 9 - . 05:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-1(F).
  • Kiku 1 - . Payload: ETS 1 (JETS). Mass: 85 kg (187 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 8197 . COSPAR: 1975-082A. Apogee: 1,103 km (685 mi). Perigee: 975 km (605 mi). Inclination: 47.0000 deg. Period: 106.00 min. JETS-1 (Japanese Engineering Test Satellite -1, national name 'Kiku') is intended for preliminary experiments for confirmation of the launching technologies, acquiring the satellite tracking and control technologies, and for extension tests of the extenda ble antennas, measurement of satellite environment, measurement of satellite attitudes, etc. Launch time 0530 GMT.

1975 September 10 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T15.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1976 January 27 - . 06:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-210. LV Configuration: TT-210 TT-210-2F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

1976 February 29 - . 03:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-2(F).
  • ISS 1 - . Payload: ISS a. Mass: 139 kg (306 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Ionosphere satellite. Spacecraft: JISS. USAF Sat Cat: 8709 . COSPAR: 1976-019A. Apogee: 1,003 km (623 mi). Perigee: 988 km (613 mi). Inclination: 69.7000 deg. Period: 105.00 min. Ionospheric sounding. Japanese Ionospheric Sounding Satellite (JISS - national name 'Ume') is intended for regular observations by means of radio waves of the global distribution of the critical frequencies of the ionosphere, and for utilization of the results of the observati on for radio wave forecasts and warning necessary for effective operation of short-wave radio-communication. Time of launch 0330UT.

1976 September 23 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T16.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1976 September 24 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-210. LV Configuration: TT-210 TT-210-3F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

1976 September 25 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T17.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1977 January 25 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500. LV Configuration: TT-500 TT-500-1F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1977 February 23 - . 08:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-3(F).
  • Kiku 2 - . Payload: ETS 2. Mass: 130 kg (280 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. Completed Operations Date: 1990-12-01 . USAF Sat Cat: 9852 . COSPAR: 1977-014A. Apogee: 35,860 km (22,280 mi). Perigee: 35,854 km (22,278 mi). Inclination: 11.9000 deg. Period: 1,439.70 min. Engineering test satellite. Engineering Test Satellite Type II (ETS II), Kiku 2. Launch by N launch vehicle no 3. Geographical longitude of the geostationary orbit: 130 deg E. Preliminary experiments to acquire technologies to launch,track, and control geostationary satellites. P ropagation experiment of millimetre and quasi-millimetre waves. Characteristics: Weight at launch 245 kg. Configuration: cylindrical. Height 191 cm including antenna. Diameter 141 cm. Attitude control: spin stabilization. Expected life at least 6 months. Positioned in geosynchronous orbit over the Pacific Ocean at 130 deg E in 1977-1990 As of 5 September 2001 located at 16.93 deg E drifting at 0.930 deg W per day. As of 2007 Mar 9 located at 85.65W drifting at 0.986W degrees per day.

1977 February 24 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T18.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1977 August 23 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T19.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1977 August 25 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500. LV Configuration: TT-500 TT-500-2F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1977 August 26 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T20.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1978 January 16 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500. LV Configuration: TT-500 TT-500-3F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1978 February 16 - . 04:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-4(F).
  • ISS 2 - . Payload: ISS b. Mass: 140 kg (300 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Ionosphere satellite. Spacecraft: JISS. USAF Sat Cat: 10674 . COSPAR: 1978-018A. Apogee: 1,216 km (755 mi). Perigee: 973 km (604 mi). Inclination: 69.4000 deg. Period: 107.20 min. Ionospheric sounding. Ionosphere Sounding Satellite-b . Launch time 0400 UT. Launch vehicle: N number 4. Spin-stabilized; Ionospheric Sounder, Radio Noise Receiver, Plasma Measuring Equipment, Ion Mass Spectrometer, and so on. The satellite is intended for regular observation of global distribution of critical frequencies of the ionosphere by means of radio waves. Weight about 141 kg. Shape: cylindrical, 3.9m diameter and 0.8m height. Expected life: probability of survival in 1.5 years is more than 70 percent.

1978 February 17 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T21.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1978 August 24 - . 01:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T22.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1978 August 25 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500. LV Configuration: TT-500 TT-500-4F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1978 August 26 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T23.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1979 January 27 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500. LV Configuration: TT-500 TT-500-5F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1979 February 6 - . 08:46 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-5(F). FAILURE: Third stage collided with ECS a.. Failed Stage: 3.
  • Ayame 1 - . Payload: ECS a; ECS 1. Mass: 260 kg (570 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Communications technology satellite. Spacecraft: Ayame. Completed Operations Date: 1979-02-09 . USAF Sat Cat: 11261 . COSPAR: 1979-009A. Apogee: 37,278 km (23,163 mi). Perigee: 29,407 km (18,272 mi). Inclination: 5.6000 deg. Period: 1,313.10 min. Experimental Communications Satellite. Experimental Communications Satellite (ECS). Launch time 0846 GMT. ECS was injected into the planned transfer orbit. On 9 Feb, however, ECS ceased radio transmissions about 10 seconds after the apogee kick motor was fired. Communicat ions and propagation experiments of satellite-communication systems. Operation and control experiment for geostationary satellites. Mass at launch 260 kg. Configuration - cylindrical. Height 1.9m including antenna. Diameter 1.4m. Spin stabilized. Last known longitude (13 June 1995) 146.23 deg W drifting at 33.817 deg E per day.

1979 February 7 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T24.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1979 August 25 - . 01:40 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500. LV Configuration: TT-500 TT-500-6F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1979 August 27 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T25.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1979 August 27 - . 06:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T26.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1980 January 28 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500. LV Configuration: TT-500 TT-500-7F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1980 February 22 - . 08:35 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-6(F).
  • Ayame 2 - . Payload: ECS b; ECS 2. Mass: 260 kg (570 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Communications technology satellite. Spacecraft: Ayame. Completed Operations Date: 1980-02-24 . USAF Sat Cat: 11715 . COSPAR: 1980-018A. Apogee: 36,839 km (22,890 mi). Perigee: 32,785 km (20,371 mi). Inclination: 1.4000 deg. Period: 1,386.60 min. Summary: Last known longitude (17 November 1988) 146.47 deg W drifting at 12.888 deg E per day..

1980 February 23 - . 01:55 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T27.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 55 km (34 mi).

1980 September 13 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T28.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1980 September 13 - . 22:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500A. LV Configuration: TT-500A TT-500A-8F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1980 September 15 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T29.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1981 January 14 - . 22:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500A. LV Configuration: TT-500A TT-500A-9F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1981 February 11 - . 08:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-7(F).
  • Kiku 3 - . Payload: ETS 4. Mass: 640 kg (1,410 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 12295 . COSPAR: 1981-012A. Apogee: 16,237 km (10,089 mi). Perigee: 305 km (189 mi). Inclination: 28.5000 deg. Period: 294.10 min. Kiku 3 (ETS-IV). Launching organization NASDA. Acquisition of the technology to handle a large-scale heavy satellite and test of the functions of on-board equipment and devices, as well as confirmation of the launching capacity of the N-II launch vehicle. Also tested ion thruster.

1981 February 12 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T30.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1981 August 1 - . 22:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500A. LV Configuration: TT-500A TT-500A-10F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1981 August 10 - . 20:03 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-8(F).
  • Himawari 2 - . Payload: GMS 2. Mass: 670 kg (1,470 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: GMS. Completed Operations Date: 1988-02-01 . USAF Sat Cat: 12677 . COSPAR: 1981-076A. Apogee: 36,034 km (22,390 mi). Perigee: 35,943 km (22,333 mi). Inclination: 12.9000 deg. Period: 1,446.40 min. Geostationary meteorological satellite. N launch vehicle flight number 8 (N-II launch vehicle). Launch time 2003 UT. Launching organization: National Space Development Agency of Japan (NASDA). Geostationary longitude 140 deg E. Function: 1) Observation of meteorological phenomena by the visible and infra-red spin scan radiometer. 2) Collection of weather data from various stations. 3) Distribution of weather data to earth stations. 4) Monitoring of solar particles. Positioned in geosynchronous orbit at 160 deg E in 1981; 140 deg E in 1981-1984; 145 deg E in 1984-1985; 120 deg E in 1985-1988 As of 31 August 2001 located at 33.93 deg E drifting at 2.598 deg W per day. As of 2007 Mar 9 located at 153.66W drifting at 2.594W degrees per day.

1982 February 2 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T31.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1982 February 3 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T32.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1982 August 15 - . 23:15 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500A. LV Configuration: TT-500A TT-500A-11F.
  • Test mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1982 September 3 - . 05:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-1 Delta. LV Configuration: N-1 N-9(F).
  • Kiku 4 - . Payload: ETS 3. Mass: 385 kg (848 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 13492 . COSPAR: 1982-087A. Apogee: 1,006 km (625 mi). Perigee: 988 km (613 mi). Inclination: 44.6000 deg. Period: 105.10 min. Engineering test satellite. Engineering Test Satellite III (ETS-III) launched 0500 GMT 3 Sep 1982 from Osaki launch site, Tanegashima. Launching organization: National Space Development Agency of Japan (NASDA). Verification of three axis attitude control function; verification of so lar array paddle deployment function; verification of active thermal control function; functional test of mission equipment in the space. N launch vehicle flight no 9.

1982 September 5 - . 01:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T33.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

1983 January 26 - . 23:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500A. LV Configuration: TT-500A TT-500A-12F.
  • Microgravity mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1983 February 4 - . 08:37 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-10(F).
  • Sakura 2A - . Payload: CS-2A. Mass: 772 kg (1,701 lb). Nation: Japan. Agency: NASDA. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-2. Completed Operations Date: 1990-12-04 . USAF Sat Cat: 13782 . COSPAR: 1983-006A. Apogee: 36,070 km (22,410 mi). Perigee: 35,994 km (22,365 mi). Inclination: 10.6000 deg. Period: 1,448.70 min. Business communications. Launch time 0837 GMT. Launching organization NASDA (National Space Development Agency of Japan). N launch vehicle No. 10(F) (N-II launch vehicle). Osaki launch site, NASDA Tanegashima Space Center, Kagoshima, Japan. Geostationary position 132 deg E. Estab lishment of domestic satellite telecommunications network mainly for natural disaster, emergency and for remote islands using submillimetre wavelength and microwavelength signals. Development of the technology of communications satellite. Positioned in geosynchronous orbit at 132 deg E in 1983-1988; 128 deg E in 1988-1990 As of 30 August 2001 located at 140.81 deg E drifting at 3.111 deg W per day. As of 2007 Mar 10 located at 31.02W drifting at 3.113W degrees per day.

1983 August 5 - . 20:29 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-11(F).
  • Sakura 2B - . Payload: CS-2B. Mass: 670 kg (1,470 lb). Nation: Japan. Agency: NASDA. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-2. Completed Operations Date: 1990-01-01 . USAF Sat Cat: 14248 . COSPAR: 1983-081A. Apogee: 36,210 km (22,490 mi). Perigee: 36,191 km (22,488 mi). Inclination: 5.1000 deg. Period: 1,457.30 min. CS-2b (Sakura 2b). Launch time 2029 GMT. Launching organization NASDA (National Space Development Agency of Japan). N launch vehicle flight no. 11 (N-II launch vehicle). Domestic satellite communications; development of communications satellite technolog y. Positioned in geosynchronous orbit at 136 deg E in 1983-1989; 128 deg E in 1989-1990 As of 4 September 2001 located at 154.41 deg E drifting at 5.251 deg W per day. As of 2007 Mar 10 located at 13.72E drifting at 5.257W degrees per day.

1983 August 18 - . 23:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: S. Launch Vehicle: TT-500A. LV Configuration: TT-500A TT-500A-13F.
  • Microgravity mission - . Nation: Japan. Agency: NASDA. Apogee: 300 km (180 mi).

1984 January 23 - . 07:58 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-12(F).
  • Yuri 2A - . Payload: BS-2a. Mass: 670 kg (1,470 lb). Nation: Japan. Agency: NASDA. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1989-07-01 . USAF Sat Cat: 14659 . COSPAR: 1984-005A. Apogee: 36,191 km (22,488 mi). Perigee: 36,072 km (22,414 mi). Inclination: 4.9000 deg. Period: 1,453.80 min. TV. BS-2a (Yuri-2a). Domestic satellite broadcasting; development of broadcasting satellite technology. Launch 0758 GMT. N launch vehicle flight no 12. Launching organization NASDA. Positioned in geosynchronous orbit at 110 deg E in 1984-1985; 108 deg E in 1985-1987; 110 deg E in 1987-1988 As of 28 August 2001 located at 69.57 deg E drifting at 4.403 deg W per day. As of 2007 Mar 10 located at 153.52W drifting at 4.395W degrees per day.

1984 August 2 - . 20:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-13(F).
  • Himawari 3 - . Payload: GMS 3. Mass: 303 kg (668 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: GMS. Completed Operations Date: 1995-06-22 . USAF Sat Cat: 15152 . COSPAR: 1984-080A. Apogee: 35,942 km (22,333 mi). Perigee: 35,877 km (22,292 mi). Inclination: 9.8000 deg. Period: 1,442.40 min. Stationed at 140 deg E; also studied alpha particles, electrons. GMS-3 (Himawari-3). Launch 2030 GMT. Improvement of meteorological observation. Development of meteorological satellite technology. N Launch vehicle flight no 13. Launching organization NASDA. Positioned in geosynchronous orbit at 140 deg E in 1984-1989; 120 deg E in 1989-1995 As of 28 August 2001 located at 146.92 deg E drifting at 1.558 deg W per day. As of 2007 Mar 11 located at 168.90W drifting at 1.566W degrees per day.

1986 February 12 - . 07:55 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-14(F).
  • Yuri 2B - . Payload: BS-2b. Mass: 677 kg (1,492 lb). Nation: Japan. Agency: NASDA. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1991-10-24 . USAF Sat Cat: 16597 . COSPAR: 1986-016A. Apogee: 36,135 km (22,453 mi). Perigee: 35,996 km (22,366 mi). Inclination: 2.7000 deg. Period: 1,450.40 min. Stationed at 117 deg E. BS-2b (Yuri-2b). Domestic satellite broadcasting; development of broadcasting satellite technology. Launching organization NASDA. N launch vehicle flight no 14. Launch time 0755 GMT. Positioned in geosynchronous orbit at 110 deg E in 1986-1991 As of 5 September 2001 located at 13.60 deg W drifting at 3.524 deg W per day. As of 2007 Mar 11 located at 77.04E drifting at 3.551W degrees per day.

1986 August 12 - . 20:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-15(F).
  • EGS - . Payload: EGP. Mass: 685 kg (1,510 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Geodetic satellite. Spacecraft: EGS. USAF Sat Cat: 16908 . COSPAR: 1986-061A. Apogee: 1,497 km (930 mi). Perigee: 1,479 km (919 mi). Inclination: 50.0000 deg. Period: 115.70 min. Experimental Geophysical Payload; new launch vehicle test flight. EGS (Ajisai). Improvement of the accuracy of domestic geodetic triangulation network. Determination of accurate location of remote islands. Clarification of the relationship between Japanese geodetic system network and those of other areas of the world. L aunch vehicle H-I (two-stage) test flight no. 1. Launch time 2045 GMT. Launching organization NASDA.
  • Oscar 12 - . Payload: JAS-1. Mass: 50 kg (110 lb). Nation: Japan. Agency: JARL. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. USAF Sat Cat: 16909 . COSPAR: 1986-061B. Apogee: 1,497 km (930 mi). Perigee: 1,479 km (919 mi). Inclination: 50.0000 deg. Period: 115.70 min. Japanese Amateur Satellite. JAS-1 (Fuji). Amateur satellite communications. Development of amateur satellite technology. Launch vehicle H-I (two-stage) test flight no. 1. Launch time 2045 GMT. Launching organization NASDA. Fuji-OSCAR 12 was launched piggyback with a Japanese experimental geodetic satellite Ajisai (EGS). Weight 50 kg. 26-sided polyhedron, 40 x 40 x 47 cm. FO-12 was the first Japanese amateur satellite developed by the Japan Amateur Radio League (English version) with system design and integration performed at NEC. FO-12 was taken out of service November 5, 1989 because of battery failure.
  • MABES - . Payload: Jindai/LE-5. Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: MABES. USAF Sat Cat: 16910 . COSPAR: 1986-061C. Apogee: 1,604 km (996 mi). Perigee: 1,483 km (921 mi). Inclination: 50.0000 deg. Period: 117.00 min. Summary: MABES (Jindai). Experiment on the levitation of the magnetic bearing flywheel under zero-g condition. .

1987 February 19 - . 01:23 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: N-2. LV Configuration: N-2 N-16(F).
  • MOS-1 - . Payload: Momo 1. Mass: 745 kg (1,642 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Sea satellite. Spacecraft: Marine Observation Satellite. USAF Sat Cat: 17527 . COSPAR: 1987-018A. Apogee: 909 km (564 mi). Perigee: 907 km (563 mi). Inclination: 99.1000 deg. Period: 103.20 min. Summary: Ocean remote sensing. MOS-1 (Momo-1). Observation of marine phenomena such as sea color and temperature. Establishment of common technology necessary for Earth observation satellites. Launching organization NASDA. Launch time 0123 GMT..

1987 August 27 - . 09:20 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-17(F).
  • Kiku 5 - . Payload: ETS 5. Mass: 550 kg (1,210 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. Completed Operations Date: 1997-09-10 . USAF Sat Cat: 18316 . COSPAR: 1987-070A. Apogee: 36,072 km (22,414 mi). Perigee: 36,029 km (22,387 mi). Inclination: 7.9000 deg. Period: 1,449.60 min. Stationed at 150 deg E. ETS-V (Kiku-5). Establishment of basic technology for bus systems needed for 3-axis stabilized geostationary satellites. Accumulation of key technologies required for high performance in the next generation of applications satellites; Experiment of mobile satellite communications for the control of aircrafts over the Pacific Ocean, and for the communication, navigational aid, search and rescue of ships. H-I (3-stage) launch vehicle. Launching organization NASDA. Launch time 0920 GMT. Positioned in geosynchronous orbit at 150 deg E in 1987-1997 As of 5 September 2001 located at 92.55 deg W drifting at 3.394 deg W per day. As of 2007 Mar 10 located at 49.74W drifting at 3.380W degrees per day.

1988 February 19 - . 10:05 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-18(F).
  • Sakura 3A - . Payload: CS-3A. Mass: 1,100 kg (2,400 lb). Nation: Japan. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-3. Completed Operations Date: 1996-09-28 . USAF Sat Cat: 18877 . COSPAR: 1988-012A. Apogee: 36,415 km (22,627 mi). Perigee: 36,376 km (22,602 mi). Inclination: 4.9000 deg. Period: 1,467.30 min. Stationed at 132 deg E. CS-3A (Sakura 3-A). To continue communications services provided by the communications satellite 2 (CS-2). To meet increasing and diversifying demands for communications. To develop technologies for communications satellites. Launch vehicle H18F. Launchin g organization NASDA. Launch time 1005 GMT. Positioned in geosynchronous orbit at 132 deg E in 1988-1996 As of 2 September 2001 located at 85.60 deg E drifting at 7.699 deg W per day. As of 2007 Mar 10 located at 71.73E drifting at 7.700W degrees per day.

1988 September 5 - . 23:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: TR-1. Launch Vehicle: TR-1. LV Configuration: TR-1 TR-1-1.
  • H-II 1/4 Scale model test flight - . Nation: Japan. Agency: NASDA. Apogee: 85 km (52 mi).

1988 September 16 - . 09:59 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-19(F).
  • Sakura 3B - . Payload: CS-3B. Mass: 1,100 kg (2,400 lb). Nation: Japan. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-3. Completed Operations Date: 1997-11-10 . USAF Sat Cat: 19508 . COSPAR: 1988-086A. Apogee: 36,093 km (22,427 mi). Perigee: 36,071 km (22,413 mi). Inclination: 4.0000 deg. Period: 1,451.20 min. Telephone communications; 136 deg E. CS-3B (Sakura 3-B). To continue communications services provided by the communications satellite 2 (CS-2). To meet increasing and diversifying demands for communications; to develop technologies for communications satellites. Launch vehicle H-I (H19F). La unching organization NASDA. Launch time 0959 GMT. Positioned in geosynchronous orbit at 149 deg E in 1988; 136 deg E in 1988-1997; 154 deg E in 1997 As of 28 August 2001 located at 128.96 deg W drifting at 3.783 deg W per day. As of 2007 Mar 10 located at 177.82E drifting at 3.765W degrees per day.

1989 January 26 - . 23:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: TR-1. Launch Vehicle: TR-1. LV Configuration: TR-1 TR-1-2.
  • H-II 1/4 Scale model test flight - . Nation: Japan. Agency: NASDA. Apogee: 80 km (49 mi).

1989 August 19 - . 23:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: TR-1. Launch Vehicle: TR-1. LV Configuration: TR-1 TR-1-3.
  • H-II 1/4 Scale model test flight - . Nation: Japan. Agency: NASDA. Apogee: 85 km (52 mi).

1989 September 5 - . 19:11 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1-6R H-20(F).
  • Himawari 4 - . Payload: GMS 4. Mass: 725 kg (1,598 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: GMS. Completed Operations Date: 2000-02-24 . USAF Sat Cat: 20217 . COSPAR: 1989-070A. Apogee: 36,807 km (22,870 mi). Perigee: 36,410 km (22,620 mi). Inclination: 6.2000 deg. Period: 1,478.30 min. Stationed at 140 deg E. GMS-4 (Himawari-4). Improvement of meteorological observation. Development of meteorological satellite technology. Launch vehicle H-I (H20F). Launching organization NASDA. Launch time 1911 GMT. Positioned in geosynchronous orbit at 160 deg E in 1989; 140 deg E in 1989-1995; 120 deg E in 1995-1999 As of 4 September 2001 located at 126.83 deg E drifting at 10.301 deg W per day. As of 2007 Mar 9 located at 71.28W drifting at 10.305W degrees per day.

1990 February 7 - . 01:33 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-21(F).
  • MOS-1b - . Payload: Momo 1B. Mass: 740 kg (1,630 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Sea satellite. Spacecraft: Marine Observation Satellite. USAF Sat Cat: 20478 . COSPAR: 1990-013A. Apogee: 909 km (564 mi). Perigee: 908 km (564 mi). Inclination: 99.1000 deg. Period: 103.20 min. Summary: Marine observation. Continuation of Earth observation functions of MOS-1; establishment of common technology necessary for Earth-observation satellites. Launching organization NASDA. Name MOS-1b 'Momo-1b'. Launch time 0133 UT..
  • Oscar 20 - . Payload: JAS 1b. Mass: 50 kg (110 lb). Nation: Japan. Agency: JARL. Program: Oscar. Class: Communications. Type: Amateur radio communications satellite. Spacecraft: Oscar. USAF Sat Cat: 20480 . COSPAR: 1990-013C. Apogee: 1,745 km (1,084 mi). Perigee: 912 km (566 mi). Inclination: 99.0000 deg. Period: 112.20 min. Summary: JAS-1b 'Fuji-2'. Continuation of amateurradio services of JAS-1; extension of amateur radio communications area; advancement of amateur radio technology. Launching organization NASDA. Launch time 0133 UT..
  • Debut - . Payload: Orizuru. Mass: 50 kg (110 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: Debut. USAF Sat Cat: 20479 . COSPAR: 1990-013B. Apogee: 1,743 km (1,083 mi). Perigee: 911 km (566 mi). Inclination: 99.0000 deg. Period: 112.20 min. Summary: Boom, umbrella test. DEBUT 'Orizuru'. Experiment of extending and contracting boom; experiment of expanding and contracting aerodynamic brake. Launching organization NASDA. Launch time 0133 UT..

1990 August 28 - . 09:05 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-22(F).
  • Yuri 3A - . Payload: BS-3a. Mass: 1,115 kg (2,458 lb). Nation: Japan. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1998-04-20 . USAF Sat Cat: 20771 . COSPAR: 1990-077A. Apogee: 36,245 km (22,521 mi). Perigee: 36,157 km (22,466 mi). Inclination: 3.5000 deg. Period: 1,457.30 min. Japanese DBS; 110 deg E. Continuation of broadcasting services by BS-2; accommodations to increasing and diversifying demands for broadcasting; establishment of common technology necessary for broadcasting satellite. Launching organization NASDA. Launch time 0905 GMT. BS-3a 'Yuri -3a'. Positioned in geosynchronous orbit at 110 deg E in 1990-1998 As of 2 September 2001 located at 84.62 deg E drifting at 5.278 deg W per day. As of 2007 Mar 10 located at 83.70W drifting at 5.275W degrees per day.

1991 August 25 - . 08:40 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-23(F).
  • Yuri 3B - . Payload: BS-3b. Mass: 1,115 kg (2,458 lb). Nation: Japan. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Completed Operations Date: 1999-04-05 . USAF Sat Cat: 21668 . COSPAR: 1991-060A. Apogee: 36,244 km (22,520 mi). Perigee: 36,171 km (22,475 mi). Inclination: 3.2000 deg. Period: 1,457.70 min. Summary: TV; 110 deg E. Positioned in geosynchronous orbit at 110 deg E in 1991-1999 As of 3 September 2001 located at 91.59 deg E drifting at 5.350 deg W per day. As of 2007 Mar 9 located at 152.69E drifting at 5.334W degrees per day..

1991 September 15 - . 23:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: TR-1. Launch Vehicle: TR-1A. LV Configuration: TR-1A TR-1A-1.
  • Microgravity mission - . Nation: Japan. Agency: NASDA. Apogee: 270 km (160 mi).

1992 February 11 - . 01:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-24(F).
  • JERS-1 - . Payload: ERS-1. Mass: 1,340 kg (2,950 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Earth resources satellite. Spacecraft: JERS. Completed Operations Date: 1998-10-12 . Decay Date: 2001-12-03 . USAF Sat Cat: 21867 . COSPAR: 1992-007A. Apogee: 568 km (352 mi). Perigee: 567 km (352 mi). Inclination: 97.7000 deg. Period: 96.00 min. Japanese Research Satellite-1. JERS-1 (FUYO-1). To verify functions and performance of optical sensors and a Synthetic Aperture Radar and to establish an integrated system for observing the Earth's resources; to perform observations and measurements for land survey, agriculture, forest ry, fishery, environmental preservation, disaster prevention and coastal surveillance. Launch time 0150 GMT. Launching organization NASDA. The Japanese Fuyo-1 (ERS-1) satellite failed on Oct 12, 1998 after six years of operation.

1992 August 19 - . 23:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: TR-1. Launch Vehicle: TR-1A. LV Configuration: TR-1A TR-1A-2.
  • Microgravity mission - . Nation: Japan. Agency: NASDA. Apogee: 290 km (180 mi).

1993 September 16 - . 23:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: TR-1. Launch Vehicle: TR-1A. LV Configuration: TR-1A TR-1A-3.
  • Microgravity mission - . Nation: Japan. Agency: NASDA. Apogee: 264 km (164 mi).

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.

1995 August 24 - . 22:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: TR-1. Launch Vehicle: TR-1A. LV Configuration: TR-1A TR-1A-4.
  • Microgravity mission - . Nation: Japan. Agency: NASDA. Apogee: 270 km (160 mi).

1996 February 11 - . 23:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: J. Launch Vehicle: J-1. LV Configuration: J-1 J-1-1F.
  • Hyflex Spacecraft test - . Nation: Japan. Agency: NASDA. Apogee: 110 km (60 mi).

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..

1996 September 24 - . 22:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: TR-1. Launch Vehicle: TR-1A. LV Configuration: TR-1A TR-1A-5.
  • Microgravity mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

1997 September 25 - . 00:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: TR-1. Launch Vehicle: TR-1A. LV Configuration: TR-1A TR-1A-6.
  • Microgravity mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

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.

1998 November 18 - . 23:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: TR-1. Launch Vehicle: TR-1A. LV Configuration: TR-1A TR-1A-7.
  • Microgravity mission - . Nation: Japan. Agency: NASDA. Apogee: 100 km (60 mi).

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.

2001 August 29 - . 07:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202. LV Configuration: H-IIA 202 H-IIA-1F.
  • LRE - . Mass: 3,500 kg (7,700 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Geodetic satellite. Spacecraft: LRE. USAF Sat Cat: 26898 . COSPAR: 2001-038A. Apogee: 36,214 km (22,502 mi). Perigee: 271 km (168 mi). Inclination: 28.0000 deg. Launch postponed from february, July 22 and August 25. First launch of the H-2A launch vehicle. A failure after all of the problems with the earlier H-2 version would probably have resulted in cancellation of the program. The Laser Ranging Experiment satellite carried 126 laser retro reflectors and separated from the second stage at 0739 GMT into its operational 'Molniya' type orbit. The eventual goal of H-2A was to launch geosynchronous spacecraft at costs comparable to those of other countries. The LRE remained in a simulated geosynchronous transfer orbit; laser reflections from it would be used to precisely ascertain the orbital injection accuracy of the H-2A.
  • VEP-2 - . Mass: 3,500 kg (7,700 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: VEP. USAF Sat Cat: 26899 . COSPAR: 2001-038B. Apogee: 35,979 km (22,356 mi). Perigee: 291 km (180 mi). Inclination: 28.6000 deg. Period: 636.60 min. Summary: Vehicle Evaluation Payload-2 consisted of ballast and monitoring instrumentation that remained attached to the launch vehicle's second stage. It included a Doppler ranging experiment for orbit determination..

2002 February 4 - . 02:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-2F.
  • MDS-1 - . Mass: 304 kg (670 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: MDS. USAF Sat Cat: 27367 . COSPAR: 2002-003A. Apogee: 35,753 km (22,215 mi). Perigee: 373 km (231 mi). Inclination: 28.3000 deg. Period: 633.80 min. Technology qualification flight - maiden flight of H-2A booster. Launch delayed from January 31 and February 3. The second stage began its first burn at 0251 UTC and at 0257 UTC entered a 500 km circular parking orbit. After a 12 minute coast the second burn put stage 2 in geostationary transfer orbit. At 0315 UTC the small DASH vehicle was meant to separate from the upper adapter, but this apparently did not occur. At 0325 UTC VEP-3/upper adapter/DASH combination separated from the second stage, followed by two semi-cylindrical side panels, revealing the previously enclosed MDS-1 technology satellite which was ejected at 0331 UTC. At 0425 UTC the second stage was scheduled to make a third burn to test engine restart, completing the H-2A-2F mission.
  • DASH - . Mass: 70 kg (154 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: DASH 2002. USAF Sat Cat: 27368 . COSPAR: 2002-003B. Apogee: 35,778 km (22,231 mi). Perigee: 357 km (221 mi). Inclination: 28.3000 deg. Period: 634.00 min. The VEP-3 launch instrumentation package mounted on top of the DASH had a mass of 33 kg. The side adapter panels were halves of a 4.1m long 4.0m diameter cylinder. DASH (Demonstrator of Atmospheric Reentry System and Hypervelocity) was to test the reentry system for the MUSES-C asteroid probe. The plan was to fire the deorbit motor three days after launch, then separate the reentry capsule which would enter the Earth's atmosphere at 10 km/s and land in the Hodh el Gharbi region of Mauritania at about 8.5W 17.2N. Typical satellite reentries are at only 7.5 km/s, while hyperbolic (escape) velocity at the top of the atmosphere is over 11 km/s, so DASH would have been travelling much faster than typical reentry vehicles, but not quite at escape velocity.

2002 September 10 - . 08:20 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-3F.
  • USERS - . Mass: 1,726 kg (3,805 lb). Nation: Japan. Agency: NASDA. Manufacturer: Mitsubishi. Class: Materials. Type: Materials science satellite. Spacecraft: USERS. Decay Date: 2007-06-15 . USAF Sat Cat: 27515 . COSPAR: 2002-042A. Apogee: 508 km (315 mi). Perigee: 497 km (308 mi). Inclination: 30.4000 deg. Period: 94.70 min. Launch delayed from August 2002. First operational flight of H-2A booster. USERS (Unmanned Space Experiment Recovery System) was a Japanese microgravity experimental satellite. After 8.5 months in orbit, a reentry vehicle was to be returned to earth with the materials manufacturered in space.
  • DRTS - . Payload: Kodama (DRTS-W). Mass: 2,800 kg (6,100 lb). Nation: Japan. Agency: NASDA. Manufacturer: Mitsubishi. Class: Communications. Type: Civilian communications satellite. Spacecraft: DRTS. USAF Sat Cat: 27516 . COSPAR: 2002-042B. Apogee: 35,804 km (22,247 mi). Perigee: 35,770 km (22,220 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Launch delayed from August 2002. First operational flight of H-2A booster. DRTS (Data Relay Transponder Satellite) was a Japanese geostationary communications spacecraft which was to relay images and data procured by the to-be-launched ADEOS 2 and ALOS satellites, and the KIBO module on ISS, after being parked over 90 E. However the engine failed after a couple of burns. As of 2007 Mar 11 located at 90.76E drifting at 0.005W degrees per day.

2002 December 14 - . 23:04 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202. LV Configuration: H-IIA 202 H-IIA-4F.
  • Adeos 2 - . Payload: Midori 2. Mass: 3,730 kg (8,220 lb). Nation: Japan. Agency: NASDA. Manufacturer: Mitsubishi. Class: Earth. Type: Earth resources satellite. Spacecraft: Adeos. USAF Sat Cat: 27597 . COSPAR: 2002-056A. Apogee: 806 km (500 mi). Perigee: 804 km (499 mi). Inclination: 98.7000 deg. Period: 101.00 min. Summary: Environment Monitoring, Aeronomy..
  • WEOS Kanta-Kun - . Mass: 50 kg (110 lb). Nation: Japan. Agency: NASDA. Manufacturer: Chiba. Class: Earth. Type: Earth resources satellite. Spacecraft: WEOS Kanta-Kun. USAF Sat Cat: 27600 . COSPAR: 2002-056D. Apogee: 804 km (499 mi). Perigee: 789 km (490 mi). Inclination: 98.7000 deg. Period: 100.80 min. Summary: Ecology..
  • Mu-Labsat - . Mass: 65 kg (143 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: Mu-Labsat. USAF Sat Cat: 27598 . COSPAR: 2002-056B. Apogee: 806 km (500 mi). Perigee: 793 km (492 mi). Inclination: 98.7000 deg. Period: 100.90 min. Technology. In 2003 the satellite released two tiny subsatellites in an experiment to test an onboard tracking imager for inspector satellites. The RITE (Remote Inspection Technology Experiment) targets are disks about 0.1m in diameter. They were released from Micro-LabSat on 2003 Mar 14 at 0140 UTC and 2003 May 14 at 0150 UTC
  • FedSat - . Mass: 58 kg (127 lb). Nation: Australia. Agency: CSS. Manufacturer: CRCSS. Class: Communications. Type: Civilian communications satellite. Spacecraft: FedSat. USAF Sat Cat: 27599 . COSPAR: 2002-056C. Apogee: 805 km (500 mi). Perigee: 791 km (491 mi). Inclination: 98.7000 deg. Period: 100.80 min. FedSat contained high-tech communication, space science, navigation and computing equipment and was intended to help bring broadband Internet services to remote parts of Australia. Data from its three-year mission was to be shared between Japan and Australia.

2003 March 28 - . 01:27 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-5F.
  • IGS-1a - . Mass: 850 kg (1,870 lb). Nation: Japan. Agency: NASDA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: IGS. USAF Sat Cat: 27698 . COSPAR: 2003-009A. Apogee: 495 km (307 mi). Perigee: 483 km (300 mi). Inclination: 97.3000 deg. Period: 94.20 min. Optical reconnaisance satellite. First Japanese military space mission. Dual payload. Delayed from February 2003. The Tanegashima facility was under strict security, guarded by 400 police officers wearing bullet-proof vests. Waters near the pad were patrolled by the coast guard.
  • IGS-1b - . Mass: 1,200 kg (2,600 lb). Nation: Japan. Agency: NASDA. Class: Surveillance. Type: Civilian surveillance radar satellite. Spacecraft: IGS. USAF Sat Cat: 27699 . COSPAR: 2003-009B. Apogee: 500 km (310 mi). Perigee: 489 km (303 mi). Inclination: 97.3000 deg. Period: 94.20 min. Summary: Radar satellite..

2003 November 29 - . 04:33 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-6F. FAILURE: Destroyed by range safety after solid booster nozzle burn-through resulted in motor not separating from core.. Failed Stage: 0.
  • IGS-2a - . Mass: 850 kg (1,870 lb). Nation: Japan. Agency: NASDA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: IGS. COSPAR: F20031129A. Summary: The launch failure meant that Japan's planned intelligence satellite constellation was crippled. The system was already in trouble due to the reported poor performance of the first two elements launched..
  • IGS-2b - . Mass: 1,200 kg (2,600 lb). Nation: Japan. Agency: NASDA. Class: Surveillance. Type: Civilian surveillance radar satellite. Spacecraft: IGS. COSPAR: F20031129B.

2005 February 26 - . 09:25 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2022. LV Configuration: H-IIA 2022 H-IIA-7F.
  • Himawari 6 - . Payload: MT-Sat 1R. Mass: 3,300 kg (7,200 lb). Nation: Japan. Agency: MLIT. Manufacturer: Palo Alto. Class: Earth. Type: Weather satellite. Spacecraft: FS-1300. USAF Sat Cat: 28622 . COSPAR: 2005-006A. Apogee: 35,798 km (22,243 mi). Perigee: 35,778 km (22,231 mi). Inclination: 0.0000 deg. Period: 1,436.20 min. Return to flight after earlier failure; first commercial mission for H-2A. Delayed from August 2003, January 2004, and February 24, 2005. The dual-purpose satellite was to provide weather data for the Japanese Meteorological Agency (as with others in the Himawari-GMS series), and air traffic control support (airplane-ATC voice/data links, GPS augmentation and airplane position tracking) for the Japanese Civil Aviation Bureau. As of 2007 Mar 11 located at 140.26E drifting at 0.000E degrees per day.

2006 January 24 - . 01:33 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2022. LV Configuration: H-IIA 2022 H-IIA-8F.
  • Daichi - . Payload: ALOS-1. Mass: 3,850 kg (8,480 lb). Nation: Japan. Agency: JAXA. Manufacturer: Toshiba. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: Daichi. USAF Sat Cat: 28931 . COSPAR: 2006-002A. Apogee: 697 km (433 mi). Perigee: 693 km (430 mi). Inclination: 98.2000 deg. Period: 98.70 min. Summary: Advanced Land Observing Satellite, which carried an L-band synthetic aperture radar, an optical 2.5-meter resolution mapping camera, and a 10-meter resolution visible/near-infrared radiometer..

2006 February 18 - . 06:27 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-9F.
  • MTSAT-2 - . Payload: MT-Sat 2. Mass: 3,000 kg (6,600 lb). Nation: Japan. Agency: MLIT. Manufacturer: Mitsubishi. Class: Earth. Type: Weather satellite. Spacecraft: DS2000. USAF Sat Cat: 28937 . COSPAR: 2006-004A. Apogee: 35,803 km (22,246 mi). Perigee: 35,771 km (22,227 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Multifunctional Transport Satellite. An aeronautical payload provided communications relay between aircraft and air traffic control; GPS augmentation navigation for aircraft; and transmitted the location of aircraft to air traffic control. A Japan Advanced Meteorological Imager weather camera had one visible and four infrared channels. MTSAT-2 was built by Mitsubishi using the new DS2000 bus. As of 2007 Mar 8 located at 144.93E drifting at 0.016W degrees per day.

2006 September 11 - . 04:35 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202. LV Configuration: H-IIA 202 H-IIA-10.
  • IGS-3A - . Mass: 850 kg (1,870 lb). Nation: Japan. Agency: JIDF. Manufacturer: Melco. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: IGS. USAF Sat Cat: 29393 . COSPAR: 2006-037A. Apogee: 491 km (305 mi). Perigee: 484 km (300 mi). Inclination: 97.3000 deg. Summary: Information Gathering Satellite / Optical-2 military surveillance satellite, launched to replace IGS O-1 launched in 2003, which demonstrated technical problems. The first replacement, IGS-O-2, was lost in a launch failure in 2003..

2006 December 16 - . 06:32 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 204. LV Configuration: H-IIA 204 H-IIA-11.
  • Kiku 8 - . Payload: ETS-8. Mass: 5,817 kg (12,824 lb). Nation: Japan. Agency: JAXA. Manufacturer: Melco. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 29656 . COSPAR: 2006-059A. Apogee: 35,798 km (22,243 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.0500 deg. Period: 1,436.11 min. Engineering Test Satellite-8 was a Japanese prototype/operational demonstration for a number of new technologies: a large satellite bus, large-scale deployable 40-m-span antennae, mobile satellite communications system, mobile satellite digital multimedia broadcasting, and basic positioning using high-accuracy time standard devices. It will be positioned in geosynchronous orbit at 146 degrees East. JAXA developed two portable terrestrial systems to communicate directly with the satellite - a tiny telephone and a portable laptop computer. The satellite was to have a lifetime of ten years. As of 2007 Mar 11 located at 145.97E drifting at 0.010W degrees per day.

2007 February 24 - . 04:41 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-12.
  • IGS-2 - . Payload: IGS 4A. Mass: 1,200 kg (2,600 lb). Nation: Japan. Agency: JAXA; CSICE. Manufacturer: Melco. Class: Surveillance. Type: Civilian surveillance radar satellite. Spacecraft: IGS. USAF Sat Cat: 30586 . COSPAR: 2007-005A. Summary: Information Gathering Satellite Radar-2. Japanese military satellite using a synthetic aperture radar for all-weather, 24-hour, high-resolution surveillance of the earth..
  • IGS-3V - . Payload: IGS 4B. Mass: 850 kg (1,870 lb). Nation: Japan. Agency: JAXA; CSICE. Manufacturer: Melco. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: IGS. USAF Sat Cat: 30587 . COSPAR: 2007-005B. Optical-3 Verification Satellite, an experimental satellite on a six-month mission to test payloads planned for the Optical-3 second-generation Japanese military optical surveillance satellite. The production-type Optical-3 satellite was expected to launch in 2009.

2007 September 14 - . 01:31 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2022. LV Configuration: H-IIA 2022 H-IIA-13.
  • Kaguya - . Payload: Selene. Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. USAF Sat Cat: 32054 . COSPAR: 2007-039A. Another of a series of new lunar probes to be launched in the next few years by China, India, Japan, USA, and Europe. Selene was dubbed Kaguya, a Japanese moon goddess, after launch. It included an HDTV camera. In lunar orbit two subsatellites would be released to provide continuous communications as well as better characterize the moon's gravity field. By 30 September Kaguya was in a 2243 km x 378,132 km lunar transfer orbit. On 3 October at 21:00 GMT it entered its initial 101 km x 11741 km x 95 deg lunar orbit. It then began maneuvers to enter its operational 100 km circular orbit, releasing the subsatellites on 9 and 12 October.
  • Okina - . Payload: Selene. Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. USAF Sat Cat: 32055 . COSPAR: 2007-039B. Summary: The Okina relay satellite was released from Kaguya into a 115 km x 2,399 km lunar orbit at 00:36 GMT on 9 October 2007..
  • Ouna - . Payload: Selene. Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. USAF Sat Cat: 32056 . COSPAR: 2007-039C. Summary: The Ouna (VRAD) subsatellite was released from Kaguya into a 127 km x 795 km lunar orbit at 04:28 GMT on 12 October 2007..

2008 February 23 - . 08:55 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 2024. LV Configuration: H-IIA 2024 s/n F14.
  • Kizuna - . Mass: 2,700 kg (5,900 lb). Nation: Japan. Agency: Mitsubishi. Class: Communications. Type: Military communications satellite. Spacecraft: Kizuna. USAF Sat Cat: 32500 . COSPAR: 2008-007A. Apogee: 35,799 km (22,244 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. WINDS, the Wide-band Internetworking Engineering Test and Demonstration Satellite, was designed to demonstrate delivery of high bandwidth Ka-band Internet service to remote areas of Japan and Southeast Asia from geostationary orbit at 143 deg E. Users with a small 45 cm in diameter antenna could receive data at up to 155 Mbps and transmit data at up to 6 Mbps.

2009 January 23 - . 03:54 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • Ibuki - . Mass: 1,750 kg (3,850 lb). Nation: Japan. Agency: JAXA. Manufacturer: Mitsubishi. Class: Earth. Type: Earth resources satellite. Spacecraft: Ibuki. USAF Sat Cat: 33492 . COSPAR: 2009-002A. Apogee: 672 km (417 mi). Perigee: 669 km (415 mi). Inclination: 98.0000 deg. Period: 98.20 min. Summary: Greenhouse Gas Observing Satellite, renamed Ibuki after launch. The satellite carried a TANSO-FTS IR spectrometer and TANSO-CAI cloud and aerosol imager..
  • PRISM - . Mass: 5.00 kg (11.00 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: PRISM. USAF Sat Cat: 33493 . COSPAR: 2009-002B. Apogee: 641 km (398 mi). Perigee: 614 km (381 mi). Inclination: 98.0000 deg. Period: 97.30 min. Summary: Remote sensing picosatellite built by the University of Tokyo, with a 10-cm aperture Earth imager on a 1-meter deployable boom..
  • SDS-1 - . Mass: 100 kg (220 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft: JAXA SDS. USAF Sat Cat: 33494 . COSPAR: 2009-002C. Apogee: 668 km (415 mi). Perigee: 663 km (411 mi). Inclination: 98.0000 deg. Period: 98.00 min. Summary: JAXA Small Demonstration Satellite, a microsatellite with a camera, GPS receiver and sun sensor..
  • SOHLA-1 - . Mass: 50 kg (110 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: SOHLA. USAF Sat Cat: 33495 . COSPAR: 2009-002D. Apogee: 667 km (414 mi). Perigee: 654 km (406 mi). Inclination: 98.0000 deg. Period: 98.00 min. Summary: Satellite built by the Space Oriented Higashi-osaka Leading Association, Osaka, carrying a cloud cover imager..
  • SpriteSat - . Mass: 50 kg (110 lb). Nation: Japan. Agency: Mitsubishi. Class: Earth. Type: Earth resources satellite. Spacecraft: SpriteSat. USAF Sat Cat: 33496 . COSPAR: 2009-002E. Apogee: 668 km (415 mi). Perigee: 658 km (408 mi). Inclination: 98.0000 deg. Period: 98.00 min. Summary: Microsatellite stabilized by a gravity gradient boom to study atmospheric sprites, built by by Tohoku University, Sendai..
  • Kagayaki - . Mass: 28 kg (61 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft: Kagayaki. USAF Sat Cat: 33497 . COSPAR: 2009-002F. Apogee: 670 km (410 mi). Perigee: 668 km (415 mi). Inclination: 98.0000 deg. Period: 98.10 min. Summary: Technology satellite built by Sorun Corporation, Tokyo, with several technology payloads..
  • Kukai - . Mass: 5.00 kg (11.00 lb). Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft: Kukai. USAF Sat Cat: 33498 . COSPAR: 2009-002G. Apogee: 667 km (414 mi). Perigee: 647 km (402 mi). Inclination: 98.0000 deg. Period: 97.90 min. Summary: Also named STARS, a Kagawa University picosatellite demonstrating a tethered space robot. It consisted of two tethered box-shaped packages, dubbed Ku and Kai..
  • KKS 1 - . Mass: 3.00 kg (6.60 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Military surveillance radar satellite. Spacecraft: KKS. USAF Sat Cat: 33499 . COSPAR: 2009-002H. Apogee: 667 km (414 mi). Perigee: 651 km (404 mi). Inclination: 98.0000 deg. Period: 97.90 min. Summary: Picosatellite built by Kouku-kosen, the Tokyo Metropolitan College of Aeronautical Engineering, carrying an Earth imager..

2009 September 10 - . 17:01 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y2. LV Family: H-2. Launch Vehicle: H-IIB.
  • HTV-1 - . Mass: 16,000 kg (35,000 lb). Nation: Japan. Agency: JAXA. Program: ISS. Class: Manned. Type: Manned spacecraft. Flight: ISS EO-20; ISS EO-19. Spacecraft: HTV. Decay Date: 2009-09-13 . USAF Sat Cat: 35817 . COSPAR: 2009-048A. Apogee: 342 km (212 mi). Perigee: 334 km (207 mi). Inclination: 51.6000 deg. Period: 91.30 min. First launch of the H-IIB booster and the HTV International Space Station resupply spacecraft. HTV-1 rendezvoused with the ISS on 17 September, stationkeeping 10 m away. It was grappled by the station's Canadarm and berthed to the Harmony port of the station and then unloaded.

2009 November 28 - . 01:21 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202. LV Configuration: H-IIA 202 s/n F16.
  • IGS O-3 - . Nation: USA. Agency: Mitsubishi. Spacecraft: IGS. USAF Sat Cat: 36104 . COSPAR: 2009-066A. Summary: Information Gathering Satellite, an optical surveillance satellite operated by Japan's Cabinet Satellite Intelligence Center..

2010 May 20 - . 21:58 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • Hayato - . Payload: K-SAT. Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Mitsubishi. Spacecraft: Cubesat. Decay Date: 2010-06-28 . USAF Sat Cat: 36573 . COSPAR: 2010-020A. Apogee: 172 km (106 mi). Perigee: 166 km (103 mi). Inclination: 30.0000 deg. Period: 87.90 min. Summary: Cubesat for Kagoshima University, released in parking orbit..
  • Waseda-SAT2 - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Surveillance satellite. Spacecraft: Cubesat. Decay Date: 2010-07-12 . USAF Sat Cat: 36574 . COSPAR: 2010-020B. Apogee: 183 km (113 mi). Perigee: 177 km (109 mi). Inclination: 30.0000 deg. Period: 88.10 min. Summary: Cubesat for Waseda University, Tokyo, released in parking orbit..
  • Negai - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Mitsubishi. Class: Surveillance. Type: Surveillance satellite. Spacecraft: Cubesat. Decay Date: 2010-06-26 . USAF Sat Cat: 36575 . COSPAR: 2010-020C. Apogee: 190 km (110 mi). Perigee: 176 km (109 mi). Inclination: 30.0000 deg. Period: 88.20 min. Summary: Cubesat for Soka University, Tokyo, released in parking orbit..
  • Akatsuki - . Payload: Planet-C. Mass: 320 kg (700 lb). Nation: Japan. Agency: Mitsubishi. Class: Venus. Type: Venus probe. Spacecraft: Akatsuki. USAF Sat Cat: 36576 . COSPAR: 2010-020D. Summary: Venus-orbiting weather satellite with visible, infrared and ultraviolet cameras. Reached Venus on 6 December 2010 but the main engine malfunctioned, preventing the braking burn into Venus orbit. The spacecraft sailed past Venus into solar orbit..
  • Ikaros - . Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Solar sail technology satellite. Spacecraft: Ikaros. USAF Sat Cat: 36577 . COSPAR: 2010-020E. Solar sail test vehicle. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg. Deployed sail by 11 June, and acceleration due to the pressure of the light from the sun was as expected. Flyby of Venus at 80,000 km distance at 07:39 GMT on 8 December 2010 returned images of sail with crescent Vensu in the background.
  • Unitec-1 - . Nation: Japan. Agency: Mitsubishi. Class: Technology. Type: Technology satellite. Spacecraft: Unitec. USAF Sat Cat: 36578 . COSPAR: 2010-020F. Summary: Space qualification of university-built computers. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg..

2010 September 11 - . 11:17 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • QZS-1 - . Payload: Michibiki. Nation: Japan. Agency: Mitsubishi. Class: Navigation. Type: Navigation satellite. Spacecraft: QZS. USAF Sat Cat: 37158 . COSPAR: 2010-045A. Apogee: 38,944 km (24,198 mi). Perigee: 32,632 km (20,276 mi). Inclination: 40.9000 deg. Period: 1,436.20 min. Quasi-Zenith Satellite System; carried an L-band navigation package to augment GPS and a C-band transponder for communications. Placed in an inclined geosynchronous orbit that brings nearly overhead of Japan at peak usage hours, providing a better navigation and communications signal to users which normally would have equatorial geosynchronous satellite and medium-earth-orbit navigation satellite signals interfered with by tall buildings or steep canyons.

2011 January 22 - . 05:37 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y2. LV Family: H-2. Launch Vehicle: H-IIB.
  • HTV 2 - . Payload: Kounotori 2. Mass: 16,000 kg (35,000 lb). Nation: Japan. Program: ISS. Class: Manned. Type: Manned logistics spacecraft. Flight: ISS EO-26; ISS EO-25. Spacecraft: HTV. Duration: 67.00 days. Decay Date: 2011-03-30 . USAF Sat Cat: 37351 . COSPAR: 2011-003A. Apogee: 355 km (220 mi). Perigee: 350 km (210 mi). Inclination: 51.6000 deg. Period: 91.60 min. Second Japanese H-II Transfer Vehicle, delivering equipment and supplies to the International Space Station. Detached from the station by the station's robot arm and released into space on 28 March at 15:46 GMT. Following retrofire burned up over the Pacific Ocean on 30 March at 03:09 GMT on 30 March.

2011 September 23 - . 04:36 GMT - . Launch Site: Tanegashima. LV Family: H-2. Launch Vehicle: H-IIA 202.
  • IGS 6A - . Nation: Japan. Class: Surveillance. Type: Surveillance satellite. Spacecraft: IGS. USAF Sat Cat: 37813 . COSPAR: 2011-050A. Summary: IGS Optical-4 satellite to replenish Japan's military reconnaisance satellite constellation..

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