Encyclopedia Astronautica
Japan



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Tanegashima
Credit: © Mark Wade
Japan

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Associated People
  • Onishi Onishi, Takuya (1975-) Japanese pilot mission specialist astronaut, 2009-on. More...
  • Yui Yui, Kimiya (1970-) Japanese pilot mission specialist astronaut, 2009-on. More...
  • Kanai Kanai, Norishige (1976-) Japanese physician mission specialist astronaut, 2009-on. More...
  • Akiyama Akiyama, Tohiro (1942-) Japanese journalist cosmonaut. Flew on Mir Kosmoreporter. First Japanese to fly in space. More...
  • Tani, I Tani, I (-1943) Japanese Professor. Japanese airplane technical designer. More...
  • Mohri Mohri, Mamoru (1948-) Japanese chemist mission specialist astronaut. Flew on STS-47, STS-99. NASDA; Spacelab-J specialist. More...
  • Mukai Mukai, Chiaki (1952-) Japanese physician payload specialist astronaut. Flew on STS-65, STS-95. Surgeon, first Japanese female astronaut. More...
  • Doi Doi, Dr Takao (1954-) Japanese engineer mission specialist astronaut 1985-2009. Flew on STS-87, STS-123. More...
  • Wakata Wakata, Koichi (1963-) Japanese engineer mission specialist astronaut. Flew on STS-72, STS-92, STS-119. More...
  • Kikuchi Kikuchi, Ryoko (1964-) Japanese journalist cosmonaut, 1989-1990. Graduated from the University of Tokyo in Chinese language Journalist, Tokyo Broadcasting Corporation. Reporter for world news with TBS, reporting from Moscow and then again from Tokyo. More...
  • Furukawa Furukawa, Satoshi (1964-) Japanese physician mission specialist astronaut, 1999-on. Underwent cosmonaut training in Russia, then Astronaut training in USA. Flew on ISS EO-28. More...
  • Noguchi Noguchi, Soichi (1965-) Japanese engineer mission specialist astronaut. Flew on STS-114, ISS EO-22. More...
  • Hoshide Hoshide, Akihito (1968-) Japanese engineer mission specialist astronaut. Flew on STS-124. Underwent cosmonaut training in Russia, then Astronaut training in USA. More...
  • Yamazaki Yamazaki, Naoko (1970-) Japanese engineer mission specialist astronaut, 1999-on. Underwent cosmonaut training in Russia, then Astronaut training in USA. NASDA More...
  • Enomoto Enomoto, Daisuke 'Dice-K' (1971-) Japanese businessman cosmonaut, 2004-2006. More...

Associated Spacecraft
  • Akatsuki Venus-orbiting weather satellite with visible, infrared and ultraviolet cameras. Launched 2010.05.20, More...
  • Unitec Space qualification of university-built computers. Released in solar orbit 0.72 AU x 1.07 AU x 2.0 deg. Launched 2010.05.20, More...
  • Ikaros 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. Launched 2010.05.20, More...
  • Ohsumi Japanese technology satellite. 4 launches, 1966.09.26 (Ohsumi 1) to 1969.09.22 (Ohsumi 4). Small engineering test satellites lofted by Japan's first indigenous launch vehicle. More...
  • Osumi Japanese technology satellite. One launch, 1970.02.11, Ohsumi 5. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E. More...
  • SS Japanese earth magnetosphere satellite. 6 launches, 1970.09.25 (SS) to 1985.08.18 (SS-11 Suisei). Scientific observations in outer space. More...
  • Tansei Japanese technology satellite. 5 launches, 1971.02.16 (Tansei 1) to 1985.01.07 (SS-10 Sagikake). Series of spacecraft of varying configurations built for engineering tests of scientific satellite equipment. More...
  • ETS Japanese technology satellite. 7 launches, 1975.09.09 (Kiku 1) to 2006.12.16 (Kiku 8). More...
  • Corsa A Japanese technology satellite. One launch, 1976.02.04. Japanese technology satellite. 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...
  • CS-1 Japanese communications satellite. One launch, 1977.12.15, Sakura. This Medium-capacity Communications Satellite for Experimental Purposes was a spin stabilized geostationary communications satellite. More...
  • EXOS Japanese earth ionosphere satellite. 4 launches, 1978.02.04 (SS-05 Kyokko) to 1989.02.21 (Akebono). Optical investigations of ionosphere. EXOS-C (OHZORA). More...
  • Yuri Japanese communications technology satellite. One launch, 1978.04.07. Medium-scale broadcasting satellite for experimental purposes. 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...
  • Astro Japanese x-ray astronomy satellite. 4 launches, 1981.02.21 (SS-07 Hinotori) to 1993.02.20 (Asuka). X-ray experiments. Launching organization: ISAS (Institute of Space and Astronautical Science). 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...
  • HOPE Japanese spaceplane. Study 1986. Like Europe, the National Space Development Agency had big plans to develop a large carrier rocket and manned 'H2 Orbiting Plane' (HOPE). 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...
  • HTV Japanese unmanned spacecraft designed for launch by the H-IIB launch vehicle for International Space Station resupply. The HTV carried International Standard Payload Racks, and was docked using the ISS robot arm after rendezvous with the station. First launched 2009.09.10. More...
  • Hagoromo Japanese lunar orbiter. One launch, 1990.01.24. Lunar orbiter ejected from Muses A 3/19/90; contact lost after release; engineering test. Lunar Orbit (Selenocentric). More...
  • Hiten Japanese lunar orbiter. One launch, 1990.01.24. MUSES-A was renamed Hiten after launch. It developed of lunar swingby techniques for future missions and ejected a lunar orbiter. 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...
  • Solar Japanese solar satellite. One launch, 1991.08.30. X-ray imaging of Sun. 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...
  • DUVE Japanese earth atmosphere satellite. One launch, 1992.07.24. Diffuse Ultraviolet Explorer package bolted to Delta 2 2nd stage. More...
  • Geotail Japanese earth magnetosphere satellite. One launch, 1992.07.24. Measured magnetosphere and Earth's geomagnetic tail; Diffuse Ultraviolet Explorer package bolted to Delta 2 second stage. More...
  • VEP Japanese technology satellite. 2 launches, 1994.02.03 (VEP) and 2001.08.29 (VEP-2). Monitored H-2 launch vehicle performance. National name MYOJO. More...
  • OREX Japanese re-entry vehicle technology satellite. One launch, 1994.02.03. NASDA ballistic capsule used to test materials and acquire data related to atmospheric re-entry for use in design of Japanese HOPE spaceplane. Launch vehicle H-2. More...
  • Express 1 Japanese materials science satellite. One launch, 1995.01.15, EXPRESS RV. At first thought not to have reached orbit. Later reentry vehicle was discovered in Ghana having reentered and deployed its parachute on Jan 15. More...
  • SFU Japanese materials science satellite. One launch, 1995.03.18. Carried materials, astronomy, biological experiments; released and later retrieved by space shuttle. More...
  • Japanese Space Plane Japanese manned spacecraft. Study 1995. NAL / Mitsubishi Heavy Industries, Ltd. design for a single stage to orbit spaceplane. Crew of ten, empty mass 110 metric tons. LACE / Scramjet engines, 29 m wingspan. More...
  • Kankoh Maru Japanese manned spacecraft. Study 1995. Kawasaki design for single stage to orbit reusable booster. Would carry 50 passengers to orbiting hotels or fast intercontinental flights. 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...
  • Haruka Japanese radio astronomy satellite. One launch, 1997.02.12. The Muses B satellite was renamed 'Haruka', meaning 'Far-away', after launch. It formed the spacesegment of the VLBI Space Observatory Program. More...
  • ETS-7 Target Japanese rendezvous technology satellite. One launch, 1997.11.27, Orihime. Attached to Hikoboshi. Docking target for ETS-7. More...
  • ETS-7 Japanese rendezvous technology satellite. One launch, 1997.11.27, Hikoboshi. Technology satellite, to accomplish remote automatic rendezvous and docking. More...
  • 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...
  • ASTRO E Japanese x-ray astronomy satellite. 2 launches, 2000.02.10 (ASTRO E) and 2005.07.10 (Suzaku). ASTRO-E was to be fifth in a series of Japanese astronomy satellites devoted to observations of celestial X-ray sources. More...
  • LDREX Japanese communications technology satellite. 2 launches, 2000.12.20 (LDREX) and 2006.10.13 (LDREX). Japan's NASDA space agency sponsored the LDREX experimental antenna. More...
  • Alflex Japanese spaceplane. Study 2000. Unmanned glider to test technology for Japanese HOPE spaceplane. Wing area 9.45 square meters. More...
  • Alpex Japanese spaceplane. Study 2000. Kawasaki unmanned glider to test technologies for HOPE spaceplane. Wing area 7.57 square meters. 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...
  • 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...
  • USERS Japanese materials science satellite. One launch, 2002.09.10. USERS (Unmanned Space Experiment Recovery System) was a Japanese microgravity experimental satellite. 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...
  • SERVIS Japanese technology satellite. First launch 2003.10.30. More...
  • Kirari Japanese communications satellite. One launch, 2005.08.23. Optical Inter-Orbit Communications Engineering Test Satellite. Its laser communications experiment was be used in with ESA's Artemis geostationary satellite. More...
  • Reimei Japanese technology satellite. One launch, 2005.08.23. Plasma Science Technology. INDEX, renamed Reimei ("Dawn") after launch, was a test satellite with new lightweight satellite components, and a demonstration auroral imager payload. More...
  • ASCA Japanese x-ray astronomy satellite. Study 2005. The Advanced Satellite for Cosmology and Astrophysics was a high throughput spectroscopic observatory. 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...
  • Akari Japanese infrared astronomy satellite. One launch, 2006.02.21, Astro F (Akari). Carried a 0.67m-diameter liquid-helium-cooled infrared telescope with detectors ranging from the near infrared to 60 and 170 micron channels in the far IR. More...
  • Cute Japanese technology satellite. 2 launches, 2006.02.21 (Cute 1.7) and 2008.04.28 (Cute-1.7-APD-II). Student subsatellites. More...
  • SSSat Japanese technology satellite. One launch, 2006.09.22. Solar sail experiment. More...
  • Hinode Japanese solar satellite. One launch, 2006.09.22. Solar satellite with a large optical telescope and an X-ray telescope built by the Smithsonian Observatory. More...
  • Hitsat Japanese technology satellite. One launch, 2006.09.22, SSSat. More...
  • Kizuna Japanese communications satellite. One launch, 2008.02.23. More...
  • SEEDS Japanese technology satellite. One launch, 2008.04.28. Nihon University at Tokyo nanosat. More...
  • NASDA Japanese Experiment Module Japanese manned space station module. Launched to ISS in three sections, 2008-2009. The Japanese Experiment Module (JEM) has been a rare island of stability in the often tumultuous Space Station program. 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...
  • Kagayaki Japanese technology satellite. One launch, 2009.01.23. Technology satellite built by Sorun Corporation, Tokyo, with several technology payloads. More...
  • Ibuki Japanese earth atmosphere satellite. One launch, 2009.01.23. Greenhouse Gas Observing Satellite, renamed Ibuki after launch. 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...
  • 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...
  • 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...
  • 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...
  • 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...
  • Hyflex Japanese spaceplane. Unmanned testbed for Japanese HOPE spaceplane. More...

Associated Engines
  • H-1-3 Nissan solid rocket engine. 77 kN. Isp=291s. Used on H-1 launch vehicle. First flight 1986. More...
  • H-2-0 Nissan solid rocket engine. 1540 kN. Isp=273s. Used as strap-on booster on H-2, first stage on J-1. First flight 1994. More...
  • H-2/J-1-1 Nissan solid rocket engine. 1556.6 kN. In Production. Used in J-1-1. Isp=273s. More...
  • HIMES Mitsubishi lox/lh2 rocket engine. 137.3 kN. Design 1999. Isp=452s. Used on H-2 HIMES launch vehicle. More...
  • LACE/LE-5 Mitsubishi air augmented Liquid Air/LH2 rocket engine. 147.1 kN. Design 1999. Isp=1200s. Used on H-2 HIMES launch vehicle. More...
  • LE-3 Rocketdyne N2O4/Aerozine-50 rocket engine. 53.340 kN. MHI(Japan)/Rocketdyne Upper Stage. Pressure-fed. Isp=285s. More...
  • LE-5A Mitsubishi lox/lh2 rocket engine. 121.5 kN. Isp=452s. Used on H-2 launch vehicle. First flight 1994. More...
  • LE-5B Mitsubishi lox/lh2 rocket engine. 137 kN. In production. Isp=447s. Improved model of the LE-5A for second stage of the H-II rocket; used hydrogen for the cooling of the thrust chamber, then as the gas to drive the turbine. First flight 2001. More...
  • LE-5 Mitsubishi lox/lh2 rocket engine. 103 kN. Isp=450s. Used on H-1 launch vehicle. First flight 1986. More...
  • LE-7 Mitsubishi lox/lh2 rocket engine for H-2 upper stage. 1078 kN. Staged combustion turbopump. No throttle capability. Isp=446s. First flight 1994. More...
  • LE-7A Mitsubishi lox/lh2 rocket engine. 1098 kN. In production. Isp=438s. Improved model of the original LE-7 for the first stage of the H-II rocket with a two stage combustion cycle system. First flight 2001. More...
  • M-13 Nissan solid rocket engine. 1262.4 kN. Isp=263s. Used on Mu-3S launch vehicle. First flight 1969. More...
  • M-23-Mu Nissan solid rocket engine. 524 kN. Isp=285s. Used on Mu-3S launch vehicle. First flight 1969. More...
  • M-23-J Nissan solid rocket engine. 524.8 kN. In development. Isp=282s. Used on J-1 launch vehicle. First flight 1996. More...
  • M-3B-J Nissan solid rocket engine. 132.1 kN. In development. Isp=294s. Used on J-1 launch vehicle. First flight 1996. More...
  • M-3B-Mu Nissan solid rocket engine. 132.1 kN. Isp=294s. Used on Mu-3S launch vehicle. First flight 1969. More...
  • M-V-4 Nissan solid rocket engine. 52 kN. Isp=298s. Used on M-V launch vehicle. First flight 1997. More...
  • M14 Nissan solid rocket engine. 3780.3 kN. Isp=276s. Used on M-V launch vehicle. First flight 1997. More...
  • M24 Nissan solid rocket engine. 1245.3 kN. Isp=288s. Used on M-V launch vehicle. First flight 1997. More...
  • M34 Nissan solid rocket engine. 294.2 kN. Isp=301s. Used on M-V launch vehicle. First flight 1997. More...
  • MB-35 Rocketdyne lox/lh2 rocket engine. 156 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed. More...
  • MB-45 Rocketdyne lox/lh2 rocket engine. 200 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages, announced February 2000. More...
  • MB-60 Rocketdyne lox/lh2 rocket engine. 266.7 kN. Design 2004. Isp=467s. Mitsubishi / Boeing joint project for an engine for Delta IV cryogenic upper stages. Expander bleed, pump-fed. More...
  • SB-735 Nissan solid rocket engine. 327.8 kN. Isp=263s. Used on Mu-3S launch vehicle. First flight 1969. More...
  • SRB-A Nissan solid rocket engine. 2250 kN. In production. Monolithic motor, shorter than that for H-2, using Thiokol filament wound composite structure. Isp=280s. First flight 2001. More...
  • UM-129A Nissan solid rocket engine. 77.5 kN. In Production. Used in H-1-3. Isp=291s. More...

Associated Launch Vehicles
  • Kappa Japanese sounding rocket. The Kappa series represented Japan's first large post-war indigenously-developed sounding rockets. They led eventually to the Lambda and Mu solid rocket satellite launchers. More...
  • Kappa 2 Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 3 Booster + 1 x Kappa 1 More...
  • Kappa 3 Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 3 Booster + 1 x Kappa 1 More...
  • Kappa 4 Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 4 Booster + 1 x Kappa 4 More...
  • K150 Japanese sounding rocket. 1/1.6 subscale test rocket used in development of the Kappa 9L sounding rockets. More...
  • Kappa 5 Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 4 Booster + 1 x Kappa 4 More...
  • K245 Japanese sounding rocket. Subscale test rocket used in development of the Kappa series of sounding rockets. More...
  • Kappa 6 Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 6 + 1 x Kappa 6 St2 More...
  • Kappa 8 Japanese sounding rocket. Two stage vehicle consisting of 1 x K420 + 1 x Kappa 8 More...
  • Kappa 6H Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 6H + 1 x Kappa 6 St2 More...
  • Kappa 9L Japanese sounding rocket. Three stage vehicle consisting of 1 x K420 + 1 x Kappa 6 + 1 x Kappa 6 St2 More...
  • Kappa 8L Japanese sounding rocket. Two stage vehicle consisting of 1 x Kappa 6H + 1 x Kappa 8L More...
  • Kappa 9M Japanese sounding rocket. Two stage vehicle consisting of 1 x K420H + 1 x K250 More...
  • S-A Japanese sounding rocket. Single stage vehicle. More...
  • S Series of Japanese single-stage sounding rockets designed for low-cost observations of the ionosphere. More...
  • Lambda Japanese all-solid orbital launch vehicle. 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...
  • LS-A Japanese test vehicle. Early suborbital test version of the Lambda rocket series. More...
  • MT-135 Japanese sounding rocket. The MT-135 was a small single-stage sounding rocket designed to collect data on the middle atmosphere, such as ozone layer depletion. More...
  • Lambda 3 Japanese test vehicle. Four stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x K420 + 1 x Kappa 8 More...
  • S-B Japanese sounding rocket. Single stage vehicle. More...
  • S-160 Japanese sounding rocket. Single stage vehicle. More...
  • HM-16 Japanese sounding rocket. Single stage vehicle. More...
  • Kappa 10S Japanese sounding rocket. Three stage vehicle consisting of 1 x K420H + 1 x K420(1/3) + 1 x K10S More...
  • Kappa 10 Japanese sounding rocket. 2-3 stage vehicle consisting of 1 x K420H + 1 x K420(1/3) More...
  • ST Japanese test vehicle. Single stage vehicle. More...
  • NAL Japanese test vehicle. Single stage vehicles. More...
  • S-250 Japanese sounding rocket. Single stage vehicle. More...
  • Lambda 3H Japanese test vehicle. Four stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500 More...
  • S-210 Japanese sounding rocket. Single stage ionospheric sounding rocket used for research from Japan's Antarctic base. More...
  • Lambda 4S Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500 + 1 x L480S 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...
  • Mu-1 Japanese test vehicle. Five stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-20 + 1 x M-30 + 1 x M-40 More...
  • S-300 ISAS Japanese sounding rocket. The the S-300, was developed for observations in Antarctica, in parallel with the S-210. 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...
  • LSC-3 Japanese test vehicle. Early suborbital test version of the Lambda rocket series. More...
  • MT-135P Japanese sounding rocket. In 1969 the MT-135P was developed; featuring a parachute-equipped recoverable motor case for maritime safety. More...
  • Kappa 10C Japanese sounding rocket. Two stage vehicle consisting of 1 x K420H + 1 x K420(1/3) More...
  • S-C Japanese sounding rocket. Single stage vehicle. More...
  • Mu-3D Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-20 + 1 x M-30 + 1 x M-40 More...
  • Lambda 4T Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500 + 1 x L480S More...
  • JCR Japanese sounding rocket. Single stage vehicle. More...
  • Mu-4S Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-20 + 1 x M-30 + 1 x M-40 More...
  • Lambda 4SC Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 2 x SB-310 + 1 x L735 + 1 x L735(1/3) + 1 x L500 + 1 x L480S More...
  • Mu-3C Japanese all-solid orbital launch vehicle. Four stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x M-22TVC + 1 x M-3A More...
  • ETV Japanese test vehicle. Three stage vehicle consisting of 8 x SB-310 + 1 x M-10 + 1 x LE-3 More...
  • S-310 Japanese sounding rocket. The S-310 was a mid-sized single-stage sounding rocket designed to reach an altitude of 200 km. 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...
  • Mu-3H Japanese all-solid orbital launch vehicle. Five stage vehicle consisting of 8 x SB-310 + 1 x M-13 + 1 x M-22TVC + 1 x M-3A + 1 x KM-H More...
  • S-520 Japanese sounding rocket. The S-520 was a larger single-stage rocket which could be equipped with a three-axis attitude control and a recovery system. It had the capability of launching a 100 kg payload above 300 km and provided more than five minutes of micro-gravity flight for experiments. More...
  • Mu-3S Japanese all-solid orbital launch vehicle. Four stage vehicle consisting of 8 x SB-310 + 1 x M-13TVC + 1 x M-22TVC + 1 x M-3A More...
  • N-2 Licensed version of Delta built in Japan using both US and Japanese components. 4 stage vehicle. More...
  • ST-735 Japanese test vehicle. Two stage vehicle consisting of 1 x ST-735 + 1 x ST-735 stage 2 More...
  • Mu-3S-II Japanese all-solid orbital launch vehicle. Four stage vehicle consisting of 2 x SB-735 + 1 x M-13 + 1 x M-23 + 1 x M-3B 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...
  • 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. More...
  • H-II (2S) Japanese orbital launch vehicle. Three stage version consisting of 2 x H-II SSB boosters + 2 x H-II SRB boosters + core vehicle. More...
  • Mu-3 The Japanese Mu launcher series provided a flexible all-solid propellant launch vehicle for access to space. More...
  • Japanese Space Plane Japanese winged orbital launch vehicle. NAL / Mitsubishi Heavy Industries, Ltd. design for a single stage to orbit spaceplane. Crew of ten, empty mass 110 tonnes. LACE / Scramjet engines, 29 m wingspan. More...
  • Kankoh Maru Japanese SSTO VTOVL orbital launch vehicle. Kawasaki design for single stage to orbit reusable booster. Would carry 50 passengers to orbiting hotels or fast intercontinental flights. More...
  • J Japanese all-solid orbital launch vehicle. 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...
  • J-1 Japanese all-solid orbital launch vehicle. Original version. More...
  • M-V All-solid Japanese satellite launch vehicle. More...
  • M-V KM Japanese all-solid orbital launch vehicle. Four stage version consisting of 1 x M-14 + 1 x M-24 + 1 x M-34 + 1 x KM-V1 More...
  • SS-520 Japanese test vehicle. The SS-520 was a two-stage rocket, the first stage consisting of the main booster of the S-520. It had a capability of launching a 140 kg payload to an altitude of about 1,000 km, and with addition of a third stage, as a satellite launch vehicle. More...
  • H-2A 212 Japanese orbital launch vehicle. This version uses two core stages side-by-side in an asymmetric configuration, supplemented by two SRB-A solid rocket boosters. More...
  • H-2A Japanese orbital launch vehicle. Low-cost version of H-2 developed for the commercial market. The two SRB-A solid rocket boosters can be supplemented by 4 smaller SSB solid boosters. 0 or 2 SSB's can be fitted for reduced 9,940 kg or 10,740 kg LEO payloads. More...
  • H-2 HIMES Japanese orbital launch vehicle. Concept of H-2 augmented with Liquid-Air Cycle Engine boosters and advanced HIMES upper stage. 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...
  • J-1 F2 Japanese all-solid orbital launch vehicle. Lower cost alternate to the original J-1 design. Uses the SRB-A of the H-2A vehicle as the first stage, the second and third stages of the J-1, with updated avionics. More...
  • Kappa 9 Japanese sounding rocket. 2-3 stage vehicle consisting of 1 x K420H + 1 x K250 + optional upper stage. 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
  • ISAS Japanese agency overseeing development of rockets, spacecraft, and rocket engines. Institute of Space and Astronautical Science, Japan. More...
  • STA Japanese agency overseeing development of rockets. Science and Technology Agency, Japan. More...
  • JMA Japanese agency. Japan Meteorological Agency, Japan. More...
  • NASDA Japanese agency overseeing development of rockets, spacecraft, and rocket engines. National Space Development Agency, Japan. More...
  • NIPR Japanese agency. National Institute of Polar Research, Japan. More...
  • JARL Japanese agency overseeing development of spacecraft. Japanese Amateur Radio League, Japan. More...
  • SCC Japanese agency. Space Communications Corporation, Tokyo, Japan. More...
  • TSCJ Japanese agency overseeing development of spacecraft. TSCJ, Japan. More...
  • NHK Japanese agency. Nippon Hoso Kyokai, Japan, Japan. More...
  • JSAT Japanese agency. Japan Satellite Systems, Japan. More...
  • NTT Japanese agency. Nippon Telephone and Telegraph, Japan. More...
  • NEC Japanese manufacturer of spacecraft. Nippon Electric Corporation, Japan. More...
  • BSAT Japanese agency. Broadcasting Satellite System Corporation, Tokyo, Japan. More...
  • Toshiba Japanese manufacturer of spacecraft. Toshiba Corp. , Tokyo, Tokyo, Japan More...
  • NAL Japanese agency. National Aerospace Laboratory, Japan. More...
  • Mitsubishi Japanese manufacturer of rockets, spacecraft, and rocket engines. Mitsubishi Electric Corp, Japan. More...
  • Chiba Japanese manufacturer of spacecraft. Chiba Institute of Technology, Chiba, Japan. More...
  • Tokyo Japanese agency. University of Tokyo, Tokyo, Japan. More...
  • TIT Japanese manufacturer of spacecraft. Tokyo Insitute of Technology, Tokyo, Japan. More...
  • MBC Japanese agency. Mobile Broadcasting Corp, Japan. More...
  • JSCC Japanese Communications Corporation, Japan. More...
  • JAXA Japanese agency overseeing development of spacecraft. JAXA, Japan. More...
  • MLIT Japanese agency. Ministry of Land, Infrastructure and Transport, Japan. More...
  • Melco Japanese manufacturer of spacecraft. Melco, Japan. More...
  • Hokkaido Japanese agency overseeing development of spacecraft. Hokkaido, Hokkaido, Japan. More...
  • ISAC Japanese agency. Telecom Information Sharing and Analysis Centre. More...
  • Kawasaki Japanese manufacturer of rockets and spacecraft. Kawasaki, Japan. More...
  • MT Japanese manufacturer. Ministry of Telecommunications, Japan. More...
  • Nissan Japanese manufacturer of rocket engines and rockets. Nissan, 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...
  • JCSAT Japanese domestic communications satellite network. More...
  • Muses Mu Space Engineering Satellites (launched on Japanes Mu series launch vehicles) pioneered new satellite technologies, including lunar flyby interplanetary injection, aerobraking, and large structure deployment. 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...

Associated Launch Sites
  • Akita Sounding rocket launch site for Kappa series, known to have been used for 81 launches from 1956 to 1990. More...
  • Obachi Location used for release and launch of balloon-launched Kappa sounding rockets in 1961. More...
  • Kagoshima Japanese launch center for solid fueled sounding rockets and satellite launchers. Limited to two months a year due to disturbance of local fisheries. More...
  • Niijima Sounding rocket and test vehicle launch site, known to have been used for 18 launches from 1963 to 1965, reaching up to 150 kilometers altitude. More...
  • Tanegashima Japan's main launch site for he larger N and H launch vehicles. In use for sounding rockets from 1967 and orbital launches from 1975. As of 2007 over 140 major launches had been made from the site. More...
  • Syowa Base Sounding rocket launch location known to have been used for 54 launches from 1970 to 1985, reaching up to 222 kilometers altitude. More...
  • Ryori Sounding rocket launch location known to have been used for 777 launches from 1970 to 2000, reaching up to 65 kilometers altitude. More...

Associated Stages
  • H-1-1 Lox/Kerosene propellant rocket stage. Loaded/empty mass 85,800/4,400 kg. Thrust 866.71 kN. Vacuum specific impulse 290 seconds. License built MB-3 ELT Thor More...
  • H-2-0 Solid propellant rocket stage. Loaded/empty mass 70,400/11,250 kg. Thrust 1,540.00 kN. Vacuum specific impulse 273 seconds. More...
  • H-2-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 98,100/11,900 kg. Thrust 1,078.00 kN. Vacuum specific impulse 446 seconds. More...
  • H-2A-1 Lox/LH2 propellant rocket stage. Loaded/empty mass 113,600/13,600 kg. Thrust 1,098.00 kN. Vacuum specific impulse 440 seconds. Lower cost version of H-2 first stage. Can be throttled to 72% thrust. More...
  • H-2A LRB Lox/LH2 propellant rocket stage. Loaded/empty mass 117,000/17,800 kg. Thrust 2,196.00 kN. Vacuum specific impulse 440 seconds. Two-engine version of H-2A-1 used as strap-on booster. More...
  • H-2A SRB-A Solid propellant rocket stage. Loaded/empty mass 76,400/10,400 kg. Thrust 2,250.00 kN. Vacuum specific impulse 280 seconds. More...
  • HIMES Lox/LH2 propellant rocket stage. Loaded/empty mass 13,600/3,100 kg. Thrust 274.00 kN. Vacuum specific impulse 452 seconds. More...
  • J-1-1 Solid propellant rocket stage. Loaded/empty mass 71,100/11,900 kg. Thrust 1,556.60 kN. Vacuum specific impulse 273 seconds. Shorter monolithic motor using filament-wound case technology from Thiokol. Version for J-1 has 1,000 kg less propellant and 1,200 kg less empty mass than later H-2 SRB. More...
  • J-1-2 Solid propellant rocket stage. Loaded/empty mass 12,800/2,400 kg. Thrust 524.80 kN. Vacuum specific impulse 282 seconds. Version for J-1 F2 has 300 kg heavier empty mass. More...
  • JCR-1 Solid propellant rocket stage. Loaded mass 700 kg. More...
  • K245-1 Solid rocket stage. 34.00 kN (7,644 lbf) thrust. Mass 100 kg (220 lb). More...
  • Kappa 5-1 Solid rocket stage. 34.00 kN (7,644 lbf) thrust. Mass 200 kg (441 lb). More...
  • Kappa 9L-1 Solid rocket stage. 110.00 kN (24,729 lbf) thrust. Mass 1,200 kg (2,646 lb). More...
  • Kappa 8-2 Solid rocket stage. 34.00 kN (7,644 lbf) thrust. Mass 300 kg (661 lb). More...
  • Kappa 9M-2 Solid rocket stage. 43.00 kN (9,667 lbf) thrust. Mass 300 kg (661 lb). More...
  • Kappa 6H-2 Solid rocket stage. 19.00 kN (4,271 lbf) thrust. Mass 100 kg (220 lb). More...
  • Kappa 10S-1 Solid rocket stage. 110.00 kN (24,729 lbf) thrust. Mass 1,200 kg (2,646 lb). More...
  • KM-H Solid rocket stage. Mass 100 kg (220 lb). More...
  • LACE Liquid Air/LH2 propellant rocket stage. Loaded/empty mass 8,000/2,000 kg. Thrust 147.00 kN. Vacuum specific impulse 1200 seconds. More...
  • Lambda 4T-4 Solid rocket stage. 7.80 kN (1,754 lbf) thrust. Mass 100 kg (220 lb). More...
  • Lambda 3-2 Solid rocket stage. 110.00 kN (24,729 lbf) thrust. Mass 1,800 kg (3,968 lb). More...
  • Lambda 3-1 Solid rocket stage. 410.00 kN (92,172 lbf) thrust. Mass 5,000 kg (11,023 lb). More...
  • Lambda 2-2 Solid rocket stage. 110.00 kN (24,729 lbf) thrust. Mass 1,400 kg (3,086 lb). More...
  • Lambda 3-3 Solid rocket stage. 110.00 kN (24,729 lbf) thrust. Mass 500 kg (1,102 lb). More...
  • LE-5 Lox/LH2 propellant rocket stage. Loaded/empty mass 10,600/1,800 kg. Thrust 102.90 kN. Vacuum specific impulse 450 seconds. More...
  • LE-5B Lox/LH2 propellant rocket stage. Loaded/empty mass 19,600/3,000 kg. Thrust 137.00 kN. Vacuum specific impulse 447 seconds. Lower cost version of H-2 second stage. More...
  • LE-5EC Lox/LH2 propellant rocket stage. Loaded/empty mass 16,700/2,700 kg. Thrust 121.50 kN. Vacuum specific impulse 452 seconds. More...
  • LS-A-1 Solid propellant rocket stage. Loaded mass 400 kg. Thrust 60.00 kN. More...
  • LS-A-2 Solid propellant rocket stage. Loaded mass 300 kg. Thrust 10.00 kN. More...
  • LS-C-1 Solid propellant rocket stage. Loaded mass 300 kg. More...
  • LS-C-2 Solid propellant rocket stage. Loaded mass 300 kg. More...
  • M-13TVC Solid rocket stage. 1020.00 kN (229,305 lbf) thrust. Mass 34,200 kg (75,398 lb). More...
  • M-20 Solid rocket stage. 285.00 kN (64,071 lbf) thrust. Mass 9,900 kg (21,826 lb). More...
  • M-22 Solid rocket stage. 285.00 kN (64,071 lbf) thrust. Mass 9,800 kg (21,605 lb). More...
  • M-3A Solid rocket stage. 61.00 kN (13,713 lbf) thrust. Mass 1,100 kg (2,425 lb). More...
  • M-3B Solid propellant rocket stage. Loaded/empty mass 3,590/310 kg. Thrust 132.12 kN. Vacuum specific impulse 294 seconds. More...
  • M-V-1 Solid propellant rocket stage. Loaded/empty mass 83,560/12,070 kg. Thrust 3,780.35 kN. Vacuum specific impulse 276 seconds. More...
  • M-V-3 Solid propellant rocket stage. Loaded/empty mass 11,000/1,000 kg. Thrust 294.00 kN. Vacuum specific impulse 301 seconds. More...
  • M-V-4 Solid propellant rocket stage. Loaded/empty mass 1,430/118 kg. Thrust 51.90 kN. Vacuum specific impulse 298 seconds. More...
  • M-V-2 Solid propellant rocket stage. Loaded/empty mass 34,470/3,410 kg. Thrust 1,245.29 kN. Vacuum specific impulse 288 seconds. More...
  • Mu-3S-2 Solid propellant rocket stage. Loaded/empty mass 13,100/2,800 kg. Thrust 524.00 kN. Vacuum specific impulse 285 seconds. More...
  • Mu-3S-0 Solid propellant rocket stage. Loaded/empty mass 5,100/1,080 kg. Thrust 327.83 kN. Vacuum specific impulse 263 seconds. More...
  • Mu-3D-3 Solid rocket stage. 128.00 kN (28,776 lbf) thrust. Mass 2,800 kg (6,173 lb). More...
  • Mu-3C-0 Solid rocket stage. 95.00 kN (21,357 lbf) thrust. Mass 500 kg (1,102 lb). More...
  • Mu-3S-1 Solid propellant rocket stage. Loaded/empty mass 34,800/7,640 kg. Thrust 1,262.42 kN. Vacuum specific impulse 263 seconds. More...
  • Mu-4S-1 Solid rocket stage. 737.00 kN (165,684 lbf) thrust. Mass 26,600 kg (58,643 lb). More...
  • Mu-4S-4 Solid rocket stage. 26.50 kN (5,957 lbf) thrust. Mass 400 kg (882 lb). More...
  • NAL-735-1 Solid propellant rocket stage. Loaded mass 4,700 kg. Thrust 250.00 kN. More...
  • NAL-16-1 Solid rocket stage. 10.00 kN (2,248 lbf) thrust. Mass 100 kg (220 lb). More...
  • S-A-1 Solid propellant rocket stage. Loaded mass 100 kg. More...
  • S-B-1 Solid propellant rocket stage. Loaded mass 100 kg. More...
  • S-C-1 Solid propellant rocket stage. Loaded mass 100 kg. More...
  • SS-520-1 Solid rocket stage. 143.10 kN (32,170 lbf) thrust. Mass 2,300 kg (5,071 lb). More...
  • TR-1A-1 Solid rocket stage. 608.00 kN (136,684 lbf) thrust. Mass 7,500 kg (16,535 lb). More...
  • TR-1-1 Solid rocket stage. 608.00 kN (136,684 lbf) thrust. Mass 10,800 kg (23,810 lb). More...
  • TT-500-1 Solid rocket stage. 116.00 kN (26,078 lbf) thrust. Mass 1,300 kg (2,866 lb). More...
  • TT-500-2 Solid rocket stage. 61.00 kN (13,713 lbf) thrust. Mass 700 kg (1,543 lb). More...
  • UM-129A Solid propellant rocket stage. Loaded/empty mass 2,200/360 kg. Thrust 77.40 kN. Vacuum specific impulse 291 seconds. More...

Japan Chronology


1942 July 22 - .
  • Birth of Tohiro Akiyama - . Nation: Japan. Summary: Japanese journalist cosmonaut. Flew on Mir Kosmoreporter. First Japanese to fly in space..

1945 August 6 - .
  • U.S. drops atomic bomb on Japanese city of Hiroshima - . Nation: Japan.

1945 August 9 - .
  • U.S. drops atomic bomb on Japanese city of Nagasaki - . Nation: Japan.

1945 September 2 - .
  • Japan signs official surrender on V-J Day - . Nation: Japan.

1948 January 29 - .
  • Birth of Mamoru Mohri - . Nation: Japan. Summary: Japanese chemist mission specialist astronaut. Flew on STS-47, STS-99. NASDA; Spacelab-J specialist..

1952 May 6 - .
  • Birth of Chiaki Mukai - . Nation: Japan. Summary: Japanese physician payload specialist astronaut. Flew on STS-65, STS-95. Surgeon, first Japanese female astronaut..

1954 September 18 - .
  • Birth of Dr Takao Doi - . Nation: Japan. Summary: Japanese engineer mission specialist astronaut 1985-2009. Flew on STS-87, STS-123..

1956 September 24 - . 00:02 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 1. LV Configuration: Kappa 1 K-1-1.
  • K-I-S-1 test - . Nation: Japan. Agency: ISAS. Apogee: 5.00 km (3.10 mi).

1956 September 28 - . 02:15 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 1. LV Configuration: Kappa 1 K-1-2.
  • K-I-S-2 test - . Nation: Japan. Agency: ISAS. Apogee: 5.00 km (3.10 mi).

1956 September 29 - . 01:50 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 1. LV Configuration: Kappa 1 K-1-3.
  • K-I-S-3 test - . Nation: Japan. Agency: ISAS. Apogee: 5.00 km (3.10 mi).

1956 December 3 - . 04:20 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 1. LV Configuration: Kappa 1 K-1-4.
  • K-I-T-1 test - . Nation: Japan. Agency: ISAS. Apogee: 5.00 km (3.10 mi).

1956 December 8 - . 03:32 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 1. LV Configuration: Kappa 1 K-1-5.
  • K-I-T-2 test - . Nation: Japan. Agency: ISAS. Apogee: 5.00 km (3.10 mi).

1956 December 11 - . 03:26 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 1. LV Configuration: Kappa 1 K-1-6.
  • K-I-T-3 test - . Nation: Japan. Agency: ISAS. Apogee: 5.00 km (3.10 mi).

1956 December 13 - . 02:10 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 1. LV Configuration: Kappa 1 K-1-7.
  • K-I-T-4 test - . Nation: Japan. Agency: ISAS. Apogee: 5.00 km (3.10 mi).

1957 April 30 - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 2. LV Configuration: Kappa 2 K-2-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 30 km (18 mi).

1957 May 2 - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 3. LV Configuration: Kappa 3 K-3-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 30 km (18 mi).

1957 June 22 - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 3. LV Configuration: Kappa 3 K-3-2.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 30 km (18 mi).

1957 July 26 - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 3. LV Configuration: Kappa 3 K-3-3.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 30 km (18 mi).

1957 September 20 - . 10:03 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 4. LV Configuration: Kappa 4 K-4-1.
  • Chemical release mission - . Nation: Japan. Agency: ISAS. Apogee: 40 km (24 mi).

1957 September 22 - . 10:00 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 4. LV Configuration: Kappa 4 K-4-2.
  • Chemical release mission - . Nation: Japan. Agency: ISAS. Apogee: 40 km (24 mi).

1958 April 8 - . 01:31 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: K150. LV Configuration: K150 K150S-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 6.00 km (3.70 mi).

1958 April 20 - . 00:00 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 5. LV Configuration: Kappa 5 K-5-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 9.00 km (5.50 mi).

1958 April 24 - . 00:30 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: K150. LV Configuration: K150 K150T-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 6.00 km (3.70 mi).

1958 April 24 - . 04:00 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: K150. LV Configuration: K150 K150T-2.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 6.00 km (3.70 mi).

1958 May 26 - . 03:41 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 5. LV Configuration: Kappa 5 K-5-L.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 15 km (9 mi).

1958 May 27 - . 03:45 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: K150. LV Configuration: K150 K150G.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 5.00 km (3.10 mi).

1958 June 14 - . 01:11 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: K245.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 1.00 km (0.60 mi).

1958 June 16 - . 02:36 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 30 km (18 mi).

1958 June 20 - . 06:15 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-2.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 45 km (27 mi).

1958 June 24 - . 01:51 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-TW-1.
  • TW-1 / S1 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 25 km (15 mi).

1958 June 30 - . 07:42 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-TW-2.
  • S2 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 45 km (27 mi).

1958 July 1 - . LV Family: Kappa. Launch Vehicle: Kappa.
  • Kappa-6tw rocket reaches 30 miles. - . Nation: Japan. Summary: Japanese Kappa-6tw two-stage rocket flown to 30-mile altitude over Michikawa Rocket Center, Japan..

1958 September 12 - . 01:31 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-3.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 4.00 km (2.40 mi).

1958 September 14 - . 02:40 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-4.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 40 km (24 mi).

1958 September 25 - . 02:55 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-TW-3.
  • S3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 44 km (27 mi).

1958 September 25 - . 05:50 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-RS-1.
  • Solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 51 km (31 mi).

1958 September 26 - . 03:50 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-TW-4.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 58 km (36 mi).

1958 November 28 - . 03:07 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-CP-1. FAILURE: Failure.
  • Chemical release / aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 36 km (22 mi).

1958 November 29 - . 03:05 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-RS-2. FAILURE: Failure.
  • Solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 40 km (24 mi).

1958 November 30 - . 04:00 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-CP-2.
  • Chemical release / aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 49 km (30 mi).

1958 December 23 - . 03:03 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-TW-5.
  • Grenade Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 60 km (37 mi).

1959 March 17 - . 01:35 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-RS-3.
  • Solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 60 km (37 mi).

1959 March 18 - . 02:45 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-TW-6.
  • Grenade Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 50 km (31 mi).

1959 March 19 - . 01:15 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-RS-4.
  • Solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 50 km (31 mi).

1959 March 20 - . 02:50 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-TW-7.
  • Grenade Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 50 km (31 mi).

1959 November 18 - . 05:03 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 7. LV Configuration: Kappa 7 K-7-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 53 km (32 mi).

1960 March 28 - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8D-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 20 km (12 mi).

1960 July 11 - . 04:24 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 150 km (90 mi).

1960 July 17 - . 04:11 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-2.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 182 km (113 mi).

1960 September 17 - . 02:47 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6. LV Configuration: Kappa 6 K-6-TW-8.
  • K-6-18 Grenade Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 46 km (28 mi).

1960 September 22 - . 06:32 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-3.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 200 km (120 mi).

1960 September 26 - . 11:25 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-4.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 185 km (114 mi).

1960 September 29 - . 02:46 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 6H. LV Configuration: Kappa 6H K-6H-TW-9.
  • K-6H-1 Grenade Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 70 km (43 mi).

1960 December 1 - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: K150. LV Configuration: K150 SP-150-2.
  • K-9L 1 / 1.6 Model test - . Nation: Japan. Agency: ISAS. Apogee: 5.00 km (3.10 mi).

1960 December 1 - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: K150. LV Configuration: K150 SP-150-1.
  • K-9L 1 / 1.6 Model test - . Nation: Japan. Agency: ISAS. Apogee: 5.00 km (3.10 mi).

1961 March 27 - . 04:08 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-5.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 172 km (106 mi).

1961 April 1 - . 03:25 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 9L. LV Configuration: Kappa 9L K-9L-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 350 km (210 mi).

1961 April 18 - . 12:27 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-6.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 150 km (90 mi).

1961 June 18 - . 04:35 GMT - . Launch Site: Obachi. LV Family: Kappa. Launch Vehicle: Kappa 4. LV Configuration: Kappa 4 K-4-2.
  • Sigma 4 Rockoon Chemical release mission - . Nation: Japan. Agency: ISAS. Apogee: 105 km (65 mi).

1961 July 21 - . 02:42 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-7 TW-10/ID-6.
  • Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 158 km (98 mi).

1961 September 2 - .
  • Japan prepares biological payload. - . Nation: Japan. Summary: Scientists at Nagoya University, Japan, were reported to be training monkey for space flight next year, hopefully in conjunction with Japanese Government-financed rocket program carried out by Tokyo University's Institute of Industrial Science..

1961 October 24 - . 03:59 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-8.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 200 km (120 mi).

1961 October 30 - . 11:13 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-9.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 175 km (108 mi).

1961 December 26 - . 05:05 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 9L. LV Configuration: Kappa 9L K-9L-2.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 343 km (213 mi).

1962 May 24 - . 10:50 GMT - . Launch Site: Akita. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-10. FAILURE: Failure.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 0 km ( mi).

1962 August 1 - . Launch Site: Kagoshima. Launch Complex: Kagoshima TMP. LV Family: Kappa. Launch Vehicle: K150. LV Configuration: K150 AT-150.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 5.00 km (3.10 mi).

1962 August 23 - . 07:15 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima TMP. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 173 km (107 mi).

1962 November 25 - . 02:01 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-1. FAILURE: Failure.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 58 km (36 mi).

1962 December 18 - . 05:03 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-11.
  • Cosmic rays mission - . Nation: Japan. Agency: ISAS. Apogee: 202 km (125 mi).

1963 May 20 - . 02:09 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-2.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 345 km (214 mi).

1963 August 1 - .
  • Birth of Koichi Wakata - . Nation: Japan. Summary: Japanese engineer mission specialist astronaut. Flew on STS-72, STS-92, STS-119..

1963 August 10 - . 03:17 GMT - . Launch Site: Niijima. LV Family: Lambda. Launch Vehicle: LS-A. LV Configuration: LS-A Sustainer.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 50 km (31 mi).

1963 August 10 - . 04:58 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: S-A. LV Configuration: S-A1.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 50 km (31 mi).

1963 August 10 - . 07:20 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: S-A. LV Configuration: S-A2.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 50 km (31 mi).

1963 August 10 - . 08:58 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: S-A. LV Configuration: S-A3.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 50 km (31 mi).

1963 August 24 - . 02:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 2. LV Configuration: Lambda 2 L-2-1. FAILURE: Failure. Failed Stage: U.
  • Ionosphere / test - . Nation: Japan. Agency: ISAS. Apogee: 51 km (31 mi).

1963 December 11 - . 05:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 2. LV Configuration: Lambda 2 L-2-2.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 410 km (250 mi).

1963 December 12 - . 08:50 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-2.
  • Aeronomy / Fields mission - . Nation: Japan. Agency: ISAS. Apogee: 103 km (64 mi).

1964 March 29 - . 02:12 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135PT-1.
  • Propellant test - . Nation: Japan. Agency: ISAS. Apogee: 51 km (31 mi).

1964 April 1 - . 03:10 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-3.
  • Aeronomy / fields mission - . Nation: Japan. Agency: ISAS. Apogee: 100 km (60 mi).

1964 April 4 - .
  • Birth of Satoshi Furukawa - . Nation: Japan. Summary: Japanese physician mission specialist astronaut, 1999-on. Underwent cosmonaut training in Russia, then Astronaut training in USA..

1964 July 11 - . 02:02 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3. LV Configuration: Lambda 3 L-3-1.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 857 km (532 mi).

1964 July 17 - . 07:20 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B S-B1.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1964 July 19 - . 03:47 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B S-B2.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1964 July 22 - . 02:50 GMT - . Launch Site: Niijima. LV Family: Lambda. Launch Vehicle: LS-A. LV Configuration: LS-A-1.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 150 km (90 mi).

1964 July 22 - . 08:55 GMT - . Launch Site: Niijima. LV Family: Lambda. Launch Vehicle: LS-A. LV Configuration: LS-A-2.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 150 km (90 mi).

1964 July 23 - . 03:37 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B S-B3.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1964 July 24 - . 02:07 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-001.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 49 km (30 mi).

1964 July 26 - . 09:07 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-4.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 124 km (77 mi).

1964 July 26 - . 10:51 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-5.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 112 km (69 mi).

1964 July 28 - . 02:08 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 PT-160-1.
  • Propellant test - . Nation: Japan. Agency: ISAS. Apogee: 44 km (27 mi).

1964 July 29 - . 10:07 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-5.
  • Chemical release mission - . Nation: Japan. Agency: ISAS. Apogee: 300 km (180 mi).

1964 September 15 - .
  • Birth of Ryoko Kikuchi - . Nation: Japan. Summary: Japanese journalist cosmonaut, 1989-1990. Graduated from the University of Tokyo in Chinese language Journalist, Tokyo Broadcasting Corporation. Reporter for world news with TBS, reporting from Moscow and then again from Tokyo..

1964 November 2 - . 09:03 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-7.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 156 km (96 mi).

1964 November 5 - . 03:01 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-4.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 356 km (221 mi).

1964 November 10 - . 02:05 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-8.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 145 km (90 mi).

1964 November 12 - . 03:05 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-6.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 100 km (60 mi).

1964 November 14 - . 02:10 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-002.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 55 km (34 mi).

1964 November 15 - . 07:10 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-003.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 55 km (34 mi).

1965 January 22 - . 05:14 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-3.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 350 km (210 mi).

1965 January 31 - . 05:01 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3. LV Configuration: Lambda 3 L-3-2.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 1,040 km (640 mi).

1965 February 6 - . 05:01 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-7.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 325 km (201 mi).

1965 February 6 - . 10:02 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-6.
  • Solar radio frequencies mission - . Nation: Japan. Agency: ISAS. Apogee: 335 km (208 mi).

1965 March 9 - . 02:10 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-004.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 53 km (32 mi).

1965 March 11 - . 02:07 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-005.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1965 March 11 - . 07:07 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-006.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 60 km (37 mi).

1965 March 18 - . 10:07 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3. LV Configuration: Lambda 3 L-3-3.
  • X-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 1,085 km (674 mi).

1965 March 25 - . 11:21 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-8.
  • Airglow Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 320 km (190 mi).

1965 March 27 - . 05:01 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-9.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 335 km (208 mi).

1965 March 28 - . 07:01 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-10.
  • Ionosphere / plasma mission - . Nation: Japan. Agency: ISAS. Apogee: 349 km (216 mi).

1965 April 15 - .
  • Birth of Soichi Noguchi - . Nation: Japan. Summary: Japanese engineer mission specialist astronaut. Flew on STS-114, ISS EO-22..

1965 June 15 - . 02:30 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B S-B4.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1965 June 16 - . 04:00 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B S-B5.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1965 June 17 - . 07:30 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: HM-16. LV Configuration: HM-16 HM-16-D.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 52 km (32 mi).

1965 June 18 - . 07:43 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: HM-16. LV Configuration: HM-16 HM-16-IT.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 38 km (23 mi).

1965 July 8 - . 02:26 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-007.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 50 km (31 mi).

1965 July 8 - . 11:10 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-008.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 50 km (31 mi).

1965 July 12 - . 02:07 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-009. FAILURE: Failure.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 50 km (31 mi).

1965 July 16 - . 10:50 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-12.
  • Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 160 km (90 mi).

1965 July 21 - . 02:23 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 ST-160-1.
  • Spin test - . Nation: Japan. Agency: ISAS. Apogee: 9.00 km (5.50 mi).

1965 July 21 - . 05:20 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 ST-160-2.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 14 km (8 mi).

1965 July 26 - . 12:01 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-12.
  • Optical astronomy / x-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 350 km (210 mi).

1965 July 27 - . 03:10 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-13.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 317 km (196 mi).

1965 August 7 - . Launch Site: Pameungpeuk. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8(L).
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 100 km (60 mi).

1965 August 11 - . 01:35 GMT - . Launch Site: Pameungpeuk. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8(L)-4.
  • SK-8-4 Aeronomy / ionosphere / Fields mission - . Nation: Japan. Agency: ISAS. Apogee: 191 km (118 mi).

1965 August 17 - . 00:05 GMT - . Launch Site: Pameungpeuk. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8(L).
  • SK-8-3 (Grenades) Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 100 km (60 mi).

1965 August 25 - . 00:15 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 BT-160-1.
  • Booster test - . Nation: Japan. Agency: ISAS. Apogee: 2.00 km (1.20 mi).

1965 August 25 - . 02:09 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 BT-160-2.
  • Booster test - . Nation: Japan. Agency: ISAS. Apogee: 9.00 km (5.50 mi).

1965 August 28 - . 02:02 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10S. LV Configuration: Kappa 10S K-10S-1.
  • Electron temp Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 742 km (461 mi).

1965 September 29 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-010.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 48 km (29 mi).

1965 September 29 - . 07:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-011.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 51 km (31 mi).

1965 October 4 - . 03:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-14.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 299 km (185 mi).

1965 October 6 - . 04:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-9.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 141 km (87 mi).

1965 November 1 - . 02:15 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 PT-160-2.
  • Propellant test - . Nation: Japan. Agency: ISAS. Apogee: 93 km (57 mi).

1965 November 4 - . 07:25 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 DS-160-1.
  • Despin test - . Nation: Japan. Agency: ISAS. Apogee: 35 km (21 mi).

1965 November 8 - . 05:05 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-1.
  • Test / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 228 km (141 mi).

1965 November 16 - . 02:09 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: ST. LV Configuration: ST ST-I F1.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 20 km (12 mi).

1965 November 17 - . 06:34 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: NAL-16. LV Configuration: NAL-16 NAL-16TR.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 45 km (27 mi).

1965 November 18 - . 06:42 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B SB-II F6.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1965 November 19 - . 01:44 GMT - . Launch Site: Niijima. LV Family: S. Launch Vehicle: S-B. LV Configuration: S-B SB-II F7.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 75 km (46 mi).

1965 November 22 - . 06:35 GMT - . Launch Site: Niijima. LV Family: Lambda. Launch Vehicle: LS-A. LV Configuration: LS-A-3.
  • Test mission - . Nation: Japan. Agency: STA. Apogee: 150 km (90 mi).

1965 December 13 - . 06:20 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-16.
  • Ozone profile Ionosphere / aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 318 km (197 mi).

1965 December 18 - . 06:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-17.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 316 km (196 mi).

1966 January 18 - . 02:10 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-012.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 54 km (33 mi).

1966 January 19 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-013.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 59 km (36 mi).

1966 January 19 - . 10:30 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-014.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 49 km (30 mi).

1966 January 26 - . 02:10 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: S-250. LV Configuration: S-250 BT-250-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 6.00 km (3.70 mi).

1966 March 5 - . 04:50 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3H. LV Configuration: Lambda 3H L-3H-1.
  • X-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 1,829 km (1,136 mi).

1966 March 20 - . 12:15 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-15.
  • XRA? / Airglow X-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 300 km (180 mi).

1966 April 20 - . 12:05 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-13.
  • Aeronomy / plasma / fields mission - . Nation: Japan. Agency: ISAS. Apogee: 155 km (96 mi).

1966 April 25 - . 04:15 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 IT-160-1.
  • Instrument test - . Nation: Japan. Agency: ISAS. Apogee: 68 km (42 mi).

1966 April 28 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: BT-310. LV Configuration: BT-310 BT-310-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 1.00 km (0.60 mi).

1966 April 29 - . 00:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: BT-310. LV Configuration: BT-310 BT-310-2.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 1.00 km (0.60 mi).

1966 April 30 - . 02:20 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-015.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 53 km (32 mi).

1966 April 30 - . 10:40 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-016.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 54 km (33 mi).

1966 May 2 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-017.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 55 km (34 mi).

1966 July 17 - . 02:10 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-18.
  • Ionosphere / solar / solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 326 km (202 mi).

1966 July 23 - . 06:35 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3H. LV Configuration: Lambda 3H L-3H-2.
  • Gyro-plasma probe Ionosphere / aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 1,800 km (1,100 mi).

1966 August 3 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-11.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 328 km (203 mi).

1966 August 6 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: BT-310. LV Configuration: BT-310 MM-310-1.
  • Mu Scale Model test - . Nation: Japan. Agency: ISAS. Apogee: 2.00 km (1.20 mi).

1966 August 6 - . 06:30 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210 PT-210-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 1.00 km (0.60 mi).

1966 August 10 - . 12:37 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-19.
  • VLF Doppler Ionosphere / aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 330 km (200 mi).

1966 August 11 - . 05:30 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135 IT-135-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 45 km (27 mi).

1966 August 11 - . 12:05 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-10.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 130 km (80 mi).

1966 August 18 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-018.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 52 km (32 mi).

1966 September 21 - . 02:10 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135 DT-135-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 56 km (34 mi).

1966 September 26 - . 02:58 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. LV Configuration: Lambda 4S L-4S-1. FAILURE: Fourth stage attitude control failed.. Failed Stage: 4.
  • Ohsumi 1 - . Payload: L-4S-1. Mass: 26 kg (57 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Ohsumi. Decay Date: 1966-09-26 . COSPAR: F660926A. Apogee: 400 km (240 mi).

1966 October 13 - . 02:25 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-019.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 44 km (27 mi).

1966 October 13 - . 04:20 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135A-020.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 65 km (40 mi).

1966 October 18 - . 09:17 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-11.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 150 km (90 mi).

1966 October 20 - . 02:20 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-14.
  • Ionosphere / fields / solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 191 km (118 mi).

1966 October 20 - . 08:25 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-20.
  • Gyro-plasma probe Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 353 km (219 mi).

1966 October 31 - . 05:04 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-1. LV Configuration: Mu-1 M-1-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 34 km (21 mi).

1966 November 4 - . 02:05 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-300 ISAS. LV Configuration: S-300 PT-300-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 160 km (90 mi).

1966 December 5 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-21.
  • Gyro-plasma probe Aeronomy / ionosphere / solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 326 km (202 mi).

1966 December 10 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8L. LV Configuration: Kappa 8L K-8L-12.
  • Aeronomy / ionosphere / solar mission - . Nation: Japan. Agency: ISAS. Apogee: 147 km (91 mi).

1966 December 10 - . 11:30 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-2.
  • Aeronomy / solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 253 km (157 mi).

1966 December 20 - . 02:20 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. LV Configuration: Lambda 4S L-4S-2. FAILURE: Fourth stage failed to ignite.. Failed Stage: 4.
  • Ohsumi 2 - . Payload: L-4S-2. Mass: 26 kg (57 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Ohsumi. Decay Date: 1966-12-19 . COSPAR: F661220A. Apogee: 400 km (240 mi).

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).

1967 January 19 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-021.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 60 km (37 mi).

1967 January 22 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-022.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 63 km (39 mi).

1967 January 22 - . 05:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-023.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 62 km (38 mi).

1967 January 22 - . 08:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-024.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 59 km (36 mi).

1967 January 24 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-025.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 59 km (36 mi).

1967 January 24 - . 08:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 MT-160-001.
  • Meteorological Test Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 86 km (53 mi).

1967 January 27 - . 02:15 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 IT-160-2.
  • Instrument test - . Nation: Japan. Agency: ISAS. Apogee: 86 km (53 mi).

1967 January 31 - . 02:05 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-22.
  • Ionosphere / solar radio frequencies mission - . Nation: Japan. Agency: ISAS. Apogee: 327 km (203 mi).

1967 February 6 - . 02:10 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3H. LV Configuration: Lambda 3H L-3H-3.
  • Ionosphere / chemical release / x-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 2,150 km (1,330 mi).

1967 March 7 - . 11:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-3.
  • Far ultraviolet Stellar photometer Ultraviolet astronomy / solar x-ray mission - . Nation: Japan. Agency: ISAS. Apogee: 248 km (154 mi).

1967 March 11 - . 06:30 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210 PT-210-2.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 1.00 km (0.60 mi).

1967 March 31 - . 18:28 GMT - . Launch Site: Wallops Island. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-026?.
  • Aeronomy mission - . Nation: Japan. Agency: NASA; JMA. Apogee: 54 km (33 mi).

1967 April 1 - . Launch Site: Wallops Island. LV Family: Arcas. Launch Vehicle: Boosted Arcas.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS; NASA. Apogee: 90 km (55 mi).

1967 April 1 - . Launch Site: Wallops Island. LV Family: Arcas. Launch Vehicle: Boosted Arcas.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS; NASA. Apogee: 90 km (55 mi).

1967 April 1 - . Launch Site: Wallops Island. LV Family: Arcas. Launch Vehicle: Boosted Arcas.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS; NASA. Apogee: 90 km (55 mi).

1967 April 1 - . Launch Site: Wallops Island. LV Family: Arcas. Launch Vehicle: Boosted Arcas.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS; NASA. Apogee: 90 km (55 mi).

1967 April 1 - . Launch Site: Wallops Island. LV Family: Arcas. Launch Vehicle: Boosted Arcas.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS; NASA. Apogee: 90 km (55 mi).

1967 April 1 - . Launch Site: Wallops Island. LV Family: Arcas. Launch Vehicle: Boosted Arcas.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS; NASA. Apogee: 90 km (55 mi).

1967 April 1 - . Launch Site: Wallops Island. LV Family: Arcas. Launch Vehicle: Boosted Arcas.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS; NASA. Apogee: 90 km (55 mi).

1967 April 1 - . Launch Site: Wallops Island. LV Family: Arcas. Launch Vehicle: Boosted Arcas.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS; NASA. Apogee: 90 km (55 mi).

1967 April 1 - . Launch Site: Wallops Island. LV Family: Arcas. Launch Vehicle: Boosted Arcas.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS; NASA. Apogee: 90 km (55 mi).

1967 April 1 - . Launch Site: Wallops Island. LV Family: Arcas. Launch Vehicle: Boosted Arcas.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS; NASA. Apogee: 90 km (55 mi).

1967 April 4 - . 09:10 GMT - . Launch Site: Wallops Island. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-027?.
  • Aeronomy mission - . Nation: Japan. Agency: NASA; JMA. Apogee: 54 km (33 mi).

1967 April 4 - . 09:55 GMT - . Launch Site: Wallops Island. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-028?.
  • Aeronomy mission - . Nation: Japan. Agency: NASA; JMA. Apogee: 57 km (35 mi).

1967 April 4 - . 11:07 GMT - . Launch Site: Wallops Island. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-029?.
  • Aeronomy mission - . Nation: Japan. Agency: NASA; JMA. Apogee: 54 km (33 mi).

1967 April 4 - . 11:56 GMT - . Launch Site: Wallops Island. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-030?.
  • Aeronomy mission - . Nation: Japan. Agency: NASA; JMA. Apogee: 57 km (35 mi).

1967 April 4 - . 16:28 GMT - . Launch Site: Wallops Island. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-031?.
  • Aeronomy mission - . Nation: Japan. Agency: NASA; JMA. Apogee: 55 km (34 mi).

1967 April 4 - . 22:44 GMT - . Launch Site: Wallops Island. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-032?.
  • Aeronomy mission - . Nation: Japan. Agency: NASA; JMA. Apogee: 56 km (34 mi).

1967 April 5 - . 00:15 GMT - . Launch Site: Wallops Island. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-033?.
  • Aeronomy mission - . Nation: Japan. Agency: NASA; JMA. Apogee: 56 km (34 mi).

1967 April 5 - . 01:01 GMT - . Launch Site: Wallops Island. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-034?.
  • Aeronomy mission - . Nation: Japan. Agency: NASA; JMA. Apogee: 54 km (33 mi).

1967 April 5 - . 03:33 GMT - . Launch Site: Wallops Island. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-035?.
  • Aeronomy mission - . Nation: Japan. Agency: NASA; JMA. Apogee: 56 km (34 mi).

1967 April 13 - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. LV Configuration: Lambda 4S L-4S-3. FAILURE: Fourth stage failed to ignite.. Failed Stage: 4.
  • Ohsumi 3 - . Payload: L-4S-3. Mass: 26 kg (57 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Ohsumi. Decay Date: 1967-04-13 . COSPAR: F670413A. Apogee: 200 km (120 mi).

1968 September 10 - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 ST-160-F-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 80 km (49 mi).

1968 September 10 - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 ST-160-F-2.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 80 km (49 mi).

1968 September 12 - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 SO-160-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 80 km (49 mi).

1968 September 14 - . 01:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160-1.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 82 km (50 mi).

1968 September 14 - . 04:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160-2.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 82 km (50 mi).

1968 September 15 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-036.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1968 September 15 - . 05:18 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-037.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 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).

1968 December 28 - .
  • Birth of Akihito Hoshide - . Nation: Japan. Summary: Japanese engineer mission specialist astronaut. Flew on STS-124. Underwent cosmonaut training in Russia, then Astronaut training in USA..

1969 January 4 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-038.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1969 January 4 - . 05:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-039.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1969 January 5 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-40.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 59 km (36 mi).

1969 January 5 - . 05:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-1.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 44 km (27 mi).

1969 January 8 - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: S-250. LV Configuration: S-250 SO-250-B.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 100 km (60 mi).

1969 January 8 - . 02:10 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-25.
  • Gyro-plasma probe Ionosphere / chemical release / fields mission - . Nation: Japan. Agency: ISAS. Apogee: 343 km (213 mi).

1969 January 9 - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-300 ISAS. LV Configuration: S-300-1. FAILURE: Failure.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 0 km ( mi).

1969 January 9 - . 07:40 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-15.
  • E field antenna Ionosphere / fields mission - . Nation: Japan. Agency: ISAS. Apogee: 188 km (116 mi).

1969 January 12 - . 05:10 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10C. LV Configuration: Kappa 10C K-10C-1.
  • Stability test Aeronomy / solar ultraviolet / test - . Nation: Japan. Agency: ISAS. Apogee: 229 km (142 mi).

1969 January 14 - . 10:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-4.
  • Langmuir probe Infrared / x-ray astronomy / solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 229 km (142 mi).

1969 January 16 - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3H. LV Configuration: Lambda 3H L-3H-4.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 1,800 km (1,100 mi).

1969 January 19 - . 12:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-24.
  • Gryo-plasma probe Aeronomy / ionosphere / fields / mission - . Nation: Japan. Agency: ISAS. Apogee: 340 km (210 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 February 13 - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 PT-420-001.
  • TVC test (1-stage) test - . Nation: Japan. Agency: ISAS. Apogee: 100 km (60 mi).

1969 February 13 - . 02:05 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-23.
  • Fields/Ultraviolet Astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 310 km (190 mi).

1969 August 7 - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-1.
  • Plasma / fields / x-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 101 km (62 mi).

1969 August 7 - . 12:15 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-27.
  • X-ray sources Ionosphere / plasma / x-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 340 km (210 mi).

1969 August 8 - . 12:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-2.
  • X-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 108 km (67 mi).

1969 August 17 - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3D. LV Configuration: Mu-3D M-3D-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 160 km (90 mi).

1969 August 24 - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-300 ISAS. LV Configuration: S-300-2.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 160 km (90 mi).

1969 August 24 - . 08:04 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-26.
  • Radio noise Ionosphere / fields mission - . Nation: Japan. Agency: ISAS. Apogee: 341 km (211 mi).

1969 August 25 - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 IT-160-3.
  • Instrumentation Test Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 78 km (48 mi).

1969 September 3 - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4T. LV Configuration: Lambda 4T L-4T-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 400 km (240 mi).

1969 September 6 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-041.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1969 September 6 - . 11:35 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-5.
  • Zodiacal light Ionosphere / astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 247 km (153 mi).

1969 September 7 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P MT-135-P -002.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1969 September 7 - . 05:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-042.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1969 September 8 - . 10:20 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-300 ISAS. LV Configuration: S-300-3. FAILURE: Failure.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 10 km (6 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).

1969 September 22 - . 02:10 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. LV Configuration: Lambda 4S L-4S-4. FAILURE: Fourth stage control system malfunction after third stage collided with fourth stage.. Failed Stage: 4.
  • Ohsumi 4 - . Payload: L-4S-4. Mass: 25 kg (55 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Ohsumi. Decay Date: 1969-09-22 . COSPAR: F690922A. Apogee: 400 km (240 mi).

1969 September 26 - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10C. LV Configuration: Kappa 10C K-10C-2. FAILURE: Failure.
  • TVC test - . Nation: Japan. Agency: ISAS. Apogee: 300 km (180 mi).

1969 September 27 - . 02:05 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P MT-135-P -003.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1969 September 27 - . 05:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-043.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 49 km (30 mi).

1970 January 17 - . 01:20 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-3.
  • X-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 119 km (73 mi).

1970 January 21 - . 02:10 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3H. LV Configuration: Lambda 3H L-3H-6.
  • Ionosphere / plasma mission - . Nation: Japan. Agency: ISAS. Apogee: 1,848 km (1,148 mi).

1970 January 22 - . 05:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P MT-135-P -004.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1970 January 23 - . 02:20 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P MT-135-P -005.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1970 January 23 - . 05:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160 MT-160-2.
  • Meteorological Test Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 75 km (46 mi).

1970 January 25 - . 05:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-28.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 369 km (229 mi).

1970 January 27 - . 10:20 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-29.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 357 km (221 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 February 10 - . 12:30 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160JA-1.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 87 km (54 mi).

1970 February 11 - . 04:25 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4S. LV Configuration: Lambda 4S L-4S-5.
  • Ohsumi 5 - . Payload: L-4S-5. Mass: 12 kg (26 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Osumi. Decay Date: 2003-08-02 . USAF Sat Cat: 4330 . COSPAR: 1970-011A. Apogee: 2,440 km (1,510 mi). Perigee: 323 km (200 mi). Inclination: 31.0000 deg. Period: 113.40 min. Summary: Engineering tests. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E .

1970 February 17 - . 12:10 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160JA-2.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 88 km (54 mi).

1970 July 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R1. FAILURE: Failure.
  • Range Test Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 44 km (27 mi).

1970 August 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R2.
  • Range Test / Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1970 August 19 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R3.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 47 km (29 mi).

1970 September 2 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R4.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 47 km (29 mi).

1970 September 2 - . 10:14 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 8. LV Configuration: Kappa 8 K-8-16.
  • Ionosphere / release mission - . Nation: Japan. Agency: ISAS. Apogee: 174 km (108 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).

1970 September 13 - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10C. LV Configuration: Kappa 10C K-10C-3.
  • TVC test - . Nation: Japan. Agency: ISAS. Apogee: 300 km (180 mi).

1970 September 19 - . 11:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3H. LV Configuration: Lambda 3H L-3H-5.
  • X-ray / ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 2,017 km (1,253 mi).

1970 September 25 - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-4S. LV Configuration: Mu-4S M-4S-1. FAILURE: Fourth stage failed to ignite.. Failed Stage: 4.
  • SS - . Payload: MS-F1. Nation: Japan. Agency: ISAS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SS. Decay Date: 1970-09-25 . COSPAR: F700925A. Apogee: 712 km (442 mi).

1970 September 27 - . 06:42 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-32.
  • B field Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 346 km (214 mi).

1970 September 28 - . 01:20 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-5.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 108 km (67 mi).

1970 October 1 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R5.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 49 km (30 mi).

1970 October 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R7.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 47 km (29 mi).

1970 October 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R8.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 50 km (31 mi).

1970 November 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R6.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 50 km (31 mi).

1970 November 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R9.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 48 km (29 mi).

1970 December 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R10.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 49 km (30 mi).

1970 December 23 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R11.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1970 December 27 - .
  • Birth of Naoko Yamazaki - . Nation: Japan. Summary: Japanese engineer mission specialist astronaut, 1999-on. Underwent cosmonaut training in Russia, then Astronaut training in USA. NASDA.

1971 January 6 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R12.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1971 January 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R13.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 43 km (26 mi).

1971 January 16 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-4.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 115 km (71 mi).

1971 January 16 - . 07:15 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-30.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 357 km (221 mi).

1971 January 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R14.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 50 km (31 mi).

1971 January 23 - . 13:20 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-35.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 338 km (210 mi).

1971 January 24 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-34.
  • Sco X-1 X-ray astronomy / solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 328 km (203 mi).

1971 January 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R15.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 48 km (29 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 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R16.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 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 February 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R17.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1971 February 16 - . 04:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-4S. LV Configuration: Mu-4S M-4S-2.
  • Tansei 1 - . Payload: MS T1. Mass: 62 kg (136 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Tansei. USAF Sat Cat: 4952 . COSPAR: 1971-011A. Apogee: 1,106 km (687 mi). Perigee: 986 km (612 mi). Inclination: 29.7000 deg. Period: 106.10 min. Summary: Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E .

1971 February 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R18.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1971 March 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R19. FAILURE: Failure.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 0 km ( mi).

1971 March 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R20.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1971 March 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R21.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1971 April 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R22.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1971 April 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R23.
  • Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1971 April 22 - .
1971 April 30 - . 10:00 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160JA-3.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 83 km (51 mi).

1971 May 6 - . 02:00 GMT - . Launch Site: Ryori. Launch Vehicle: MT-135P. LV Configuration: MT-135P MT135P-R24.
  • - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1971 May 12 - . 02:00 GMT - . Launch Site: Ryori. Launch Vehicle: MT-135P. LV Configuration: MT-135P MT135P-R25.
  • - . Nation: Japan. Agency: JMA. Apogee: 49 km (30 mi).

1971 May 26 - . 10:10 GMT - . Launch Site: Barking Sands. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk.
  • LEINAX I X-ray astronomy mission - . Nation: Japan. Agency: Sandia. Apogee: 209 km (129 mi).

1971 June 24 - . 01:05 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-4.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 130 km (80 mi).

1971 July 21 - . 21:52 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-3.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 131 km (81 mi).

1971 August 10 - . 02:24 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-1.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 139 km (86 mi).

1971 August 18 - . 12:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-31.
  • X-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 330 km (200 mi).

1971 August 20 - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4SC. LV Configuration: Lambda 4SC L-4SC-1. FAILURE: Failure. Failed Stage: U.
  • TVC test - . Nation: Japan. Agency: ISAS. Apogee: 1,500 km (900 mi).

1971 August 20 - . 12:10 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-7.
  • Optical astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 274 km (170 mi).

1971 August 25 - . 05:40 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-36. FAILURE: Failure.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 0 km ( mi).

1971 August 26 - . 10:35 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-33.
  • Cs / Ba Release Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 340 km (210 mi).

1971 September 1 - . 02:10 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-6.
  • Solar ultraviolet Solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 228 km (141 mi).

1971 September 3 - . 12:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3H. LV Configuration: Lambda 3H L-3H-7.
  • Aeronomy / ionosphere / x-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 1,718 km (1,067 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 13 - . 21:50 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-5.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 115 km (71 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).

1971 September 24 - . 21:08 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-2.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 138 km (85 mi).

1971 September 28 - . 04:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-4S. LV Configuration: Mu-4S M-4S-3.
  • SS-01 Shinsei - . Payload: MS-F2. Mass: 65 kg (143 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SS. USAF Sat Cat: 5485 . COSPAR: 1971-080A. Apogee: 1,866 km (1,159 mi). Perigee: 872 km (541 mi). Inclination: 32.0000 deg. Period: 113.10 min. Summary: Scientific observations in outer space. Injection point 29 deg 7 min N, 145 deg 8 min E. .

1971 September 29 - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160-3.
  • Parachute test - . Nation: Japan. Agency: ISAS. Apogee: 80 km (49 mi).

1971 December 3 - . 12:00 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-6.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 131 km (81 mi).

1972 January 21 - . 02:24 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-6.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 112 km (69 mi).

1972 January 23 - . 11:22 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-37.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 340 km (210 mi).

1972 January 29 - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210 DT-210-1.
  • Structural Dynamics test - . Nation: Japan. Agency: ISAS. Apogee: 100 km (60 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 February 11 - . 12:00 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-12.
  • Mass spectrometer Ionosphere mission - . Nation: Japan. Agency: NIPR. Apogee: 108 km (67 mi).

1972 February 17 - . 08:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-7.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 118 km (73 mi).

1972 February 18 - . 09:28 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-39.
  • Cesium Release Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 310 km (190 mi).

1972 February 21 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160-4.
  • Fields mission - . Nation: Japan. Agency: ISAS. Apogee: 81 km (50 mi).

1972 February 22 - . 06:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-38.
  • Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 352 km (218 mi).

1972 April 16 - . 23:42 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-160. LV Configuration: S-160JA-4.
  • Ionosphere mission - . Nation: Japan. Agency: NIPR. Apogee: 86 km (53 mi).

1972 May 13 - . 23:13 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-9.
  • Aurora / ionosphere / fields mission - . Nation: Japan. Agency: NIPR. Apogee: 129 km (80 mi).

1972 May 15 - . 23:02 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-10.
  • Aurora / ionosphere / fields mission - . Nation: Japan. Agency: NIPR. Apogee: 115 km (71 mi).

1972 May 22 - . 12:00 GMT - . Launch Site: Barking Sands. LV Family: Tomahawk Sandia. Launch Vehicle: Nike Tomahawk. LV Configuration: Nike Tomahawk LEINAX II.
  • X-ray astronomy mission - . Nation: Japan. Agency: Sandia. Apogee: 270 km (160 mi).

1972 August 7 - . 01:45 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-11.
  • Aurora / ionosphere / fields mission - . Nation: Japan. Agency: NIPR. Apogee: 126 km (78 mi).

1972 August 11 - . 01:01 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-8.
  • Ionosphere / fields mission - . Nation: Japan. Agency: NIPR. Apogee: 127 km (78 mi).

1972 August 19 - . 02:40 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-4S. LV Configuration: Mu-4S M-4S-4.
  • SS-02 Denpa - . Payload: REXS. Mass: 75 kg (165 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SS. Decay Date: 1980-05-19 . USAF Sat Cat: 6152 . COSPAR: 1972-064A. Apogee: 6,322 km (3,928 mi). Perigee: 238 km (147 mi). Inclination: 31.0000 deg. Period: 157.40 min. Summary: Ionospheric experiments. Scientific observations in the ionosphere and magnetosphere. Interjection point 31 deg 15' N 11 deg 05' E. .

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 12 - . 11:10 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-8.
  • Fiberglass Casing Infrared astronomy / x-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 259 km (160 mi).

1972 September 20 - . 05:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-40.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 326 km (202 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).

1972 December 13 - . 21:23 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-7.
  • Aurora / ionosphere / fields mission - . Nation: Japan. Agency: NIPR. Apogee: 126 km (78 mi).

1973 January 15 - . 23:40 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-8.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 122 km (75 mi).

1973 January 19 - . 09:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-41.
  • VLF Ionosphere / active plasma mission - . Nation: Japan. Agency: ISAS. Apogee: 330 km (200 mi).

1973 January 28 - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4SC. LV Configuration: Lambda 4SC L-4SC-2.
  • TVC test - . Nation: Japan. Agency: ISAS. Apogee: 1,500 km (900 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 February 14 - . 20:45 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-16.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 103 km (64 mi).

1973 February 19 - . 00:22 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-9.
  • Aeronomy / ionosphere / solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 236 km (146 mi).

1973 February 23 - . 09:38 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-42.
  • Cesium Release Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 306 km (190 mi).

1973 March 25 - . 17:47 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-14.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 114 km (70 mi).

1973 April 22 - . 18:25 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-17.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 124 km (77 mi).

1973 June 10 - . 17:20 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-13.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 123 km (76 mi).

1973 June 11 - . 18:10 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-15.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 125 km (77 mi).

1973 July 15 - . 16:09 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-19.
  • Auroral mission - . Nation: Japan. Agency: NIPR. Apogee: 131 km (81 mi).

1973 August 19 - . 09:55 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-9.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 115 km (71 mi).

1973 August 21 - . 07:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-43.
  • Plasma / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 355 km (220 mi).

1973 August 22 - . 21:53 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-18.
  • Auroral arc Aurora mission - . Nation: Japan. Agency: NIPR. Apogee: 129 km (80 mi).

1973 August 27 - . 12:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-44.
  • X-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 341 km (211 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).

1973 September 22 - . 09:20 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-10.
  • X-ray astronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 242 km (150 mi).

1974 January 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R144.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 January 16 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-45.
  • Ionosphere-solar mission Ionosphere-solar mission - . Nation: Japan. Agency: ISAS. Apogee: 360 km (220 mi).

1974 January 22 - . 11:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3H. LV Configuration: Lambda 3H L-3H-8.
  • St 2: 329 km X-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 1,571 km (976 mi).

1974 January 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R145.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 January 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R139.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 January 31 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R146.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 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 6 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R147.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 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 February 16 - . 05:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3C. LV Configuration: Mu-3C M-3C-1.
  • Tansei 2 - . Payload: MS T2. Mass: 65 kg (143 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Tansei. Decay Date: 1983-01-22 . USAF Sat Cat: 7122 . COSPAR: 1974-008A. Apogee: 3,231 km (2,007 mi). Perigee: 284 km (176 mi). Inclination: 31.2000 deg. Period: 121.70 min. Summary: Attitude control satellite (performance test of launch vehicle). .

1974 February 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R148.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 February 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R149.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 March 13 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R150.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 March 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R160.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 March 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R151.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 April 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R152.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 April 10 - . 02:09 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R153.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 April 17 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R154.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 April 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R155.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 May 1 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R156.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 May 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R158.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 May 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R157.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 May 22 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R159.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 June 13 - . 02:30 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R161.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 June 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R162.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 July 17 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R163.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 July 24 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R164.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 August 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R165.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 August 20 - . 09:55 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-10.
  • NNP / NEL / TEL Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 112 km (69 mi).

1974 August 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R166.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 August 28 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R167.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 September 1 - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 4SC. LV Configuration: Lambda 4SC L-4SC-3.
  • TVC test - . Nation: Japan. Agency: ISAS. Apogee: 1,500 km (900 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).

1974 September 4 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R169.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 September 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R170.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 September 16 - . 15:40 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-46.
  • Plasma gun M / D Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 336 km (208 mi).

1974 September 18 - . 02:30 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R168.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 September 19 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-47.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 328 km (203 mi).

1974 September 20 - . 11:32 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-48.
  • Precipitate Electrons Ionosphere / x-ray / ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 348 km (216 mi).

1974 October 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R171.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 October 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R172.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 October 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R173.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 October 30 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R174.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 November 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R175.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 November 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R176.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 November 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R177.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 November 27 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R178.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 December 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R179.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 December 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R180.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1974 December 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R181.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1975 January 1 - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-1.
  • Test mission - . Nation: Japan. Agency: ISAS. Apogee: 200 km (120 mi).

1975 January 17 - . 09:35 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-49.
  • Airglow Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 363 km (225 mi).

1975 January 23 - . 11:05 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-50.
  • X-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 353 km (219 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 February 24 - . 05:25 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3C. LV Configuration: Mu-3C M-3C-2.
  • SS-03 Taiyo - . Payload: SRATS. Mass: 86 kg (189 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SS. Decay Date: 1980-06-29 . USAF Sat Cat: 7671 . COSPAR: 1975-014A. Apogee: 3,125 km (1,941 mi). Perigee: 254 km (157 mi). Inclination: 31.5000 deg. Period: 120.20 min. Examined solar radiation, thermospheric structure. SRATS (Solar and Thermospheric Radiation Satellite) is the third Japanese scientific satellite, to study the intereffects of solar radiation and the thermosphere of the earth. National name: Taiyo. Launch time 0525 GMT.

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 August 26 - . 10:40 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-53.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 351 km (218 mi).

1975 August 30 - . 04:10 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-2.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 191 km (118 mi).

1975 September 2 - . 12:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-51.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 311 km (193 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).

1975 September 23 - . 12:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-52.
  • Soft X-ray X-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 336 km (208 mi).

1975 September 24 - . 05:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-11.
  • X-ray astronomy / solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 196 km (121 mi).

1976 January 16 - . 21:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-54.
  • Magnetospheric mission - . Nation: Japan. Agency: ISAS. Apogee: 367 km (228 mi).

1976 January 18 - . 05:20 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-12.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 350 km (210 mi).

1976 January 25 - . 23:20 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-22.
  • NO / Ne Aeronomy / ionosphere mission - . Nation: Japan. Agency: NIPR. Apogee: 127 km (78 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 4 - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3C. LV Configuration: Mu-3C M-3C-3. FAILURE: Stage 2 thrust vector control failure.. Failed Stage: 2.
  • Corsa A - . Mass: 92 kg (202 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Corsa A. Decay Date: 1976-02-04 . COSPAR: F760204A.

1976 February 13 - . 09:45 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310JA-1.
  • VLF / HF Ionosphere mission - . Nation: Japan. Agency: NIPR. Apogee: 216 km (134 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 May 29 - . 09:49 GMT - . Launch Site: Barking Sands. LV Family: Sandhawk. Launch Vehicle: Terrier Sandhawk. LV Configuration: Terrier Sandhawk Sandia.
  • LEINAX IV X-ray astronomy mission - . Nation: Japan. Agency: Sandia. Apogee: 271 km (168 mi).

1976 June 24 - . 23:40 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-20.
  • VLF / HF / ne Aurora mission - . Nation: Japan. Agency: NIPR. Apogee: 118 km (73 mi).

1976 July 26 - . 00:23 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-21.
  • VLF / HF / ne / ISIS-2 Aurora mission - . Nation: Japan. Agency: NIPR. Apogee: 116 km (72 mi).

1976 August 16 - . 23:54 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-24.
  • E / B / ne Aurora mission - . Nation: Japan. Agency: NIPR. Apogee: 118 km (73 mi).

1976 August 17 - . 10:15 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-11.
  • Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 112 km (69 mi).

1976 August 21 - . 12:10 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-3.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 195 km (121 mi).

1976 August 30 - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Vehicle: Lambda 4SC. LV Configuration: Lambda 4SC L-4SC-4.
  • Radar transponder - . Nation: Japan. Agency: ISAS. Apogee: 1,500 km (900 mi).

1976 August 30 - . 19:55 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-57.
  • Ionosphere / fields mission - . Nation: Japan. Agency: ISAS. Apogee: 288 km (178 mi).

1976 September 1 - . 00:00 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-25.
  • E / B / ne Aurora mission - . Nation: Japan. Agency: NIPR. Apogee: 125 km (77 mi).

1976 September 13 - . 04:31 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-23.
  • NO / Ne / ISIS-2 Aurora mission - . Nation: Japan. Agency: NIPR. Apogee: 120 km (70 mi).

1976 September 16 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-55.
  • Ionosphere / fields mission - . Nation: Japan. Agency: ISAS. Apogee: 359 km (223 mi).

1976 September 18 - . 10:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-56.
  • Ionosphere / fields mission - . Nation: Japan. Agency: ISAS. Apogee: 300 km (180 mi).

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 16 - . 12:45 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-58.
  • Near infrared Galactic Plane Infrared astronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 324 km (201 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 10 - . 00:22 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310JA-2.
  • VLF / HF Ionosphere mission - . Nation: Japan. Agency: NIPR. Apogee: 212 km (131 mi).

1977 February 19 - . 05:15 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3H. LV Configuration: Mu-3H M-3H-1.
  • Tansei 3 - . Payload: MS T3. Mass: 230 kg (500 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Tansei. USAF Sat Cat: 9841 . COSPAR: 1977-012A. Apogee: 3,802 km (2,362 mi). Perigee: 799 km (496 mi). Inclination: 65.8000 deg. Period: 134.10 min. Tentative name before launching: MS-T3. Launching organization: Institute of Space and Aeronautical Science, University of Tokyo. Radio frequencies: 136.725 MHz, tracking; 400.500 MHz, telemetry. Active life: two weeks. Function: (1) Test of the overall p erformance of the newly developed launch vehicle, M-3H-1. (2) Experiment of magnetic stabilization. (3) Observation of ultraviolet radiation.

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 March 27 - . 03:55 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-28.
  • NO / O3 / Ne Aeronomy mission - . Nation: Japan. Agency: NIPR. Apogee: 106 km (65 mi).

1977 April 11 - . 05:00 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-26.
  • NO / O3 / Ne Aeronomy mission - . Nation: Japan. Agency: NIPR. Apogee: 105 km (65 mi).

1977 July 12 - . 16:15 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-29.
  • E / B / ne / ISIS-2 Aurora mission - . Nation: Japan. Agency: NIPR. Apogee: 118 km (73 mi).

1977 July 14 - . 10:39 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Delta. Launch Vehicle: Delta 2914. LV Configuration: Delta 2914 618/D132.
  • Himawari 1 - . Payload: GMS 1. Mass: 670 kg (1,470 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: GMS. Completed Operations Date: 1989-09-17 . USAF Sat Cat: 10143 . COSPAR: 1977-065A. Apogee: 36,148 km (22,461 mi). Perigee: 36,005 km (22,372 mi). Inclination: 11.1000 deg. Period: 1,451.00 min. Geostationary meteorological satellite. Positioned in geosynchronous orbit over the Pacific Ocean at 140 deg E in 1977-1981; over the Pacific Ocean 160 deg E in 1981-1984; over the Pacific Ocean 140 deg E in 1984; over the Pacific Ocean160 deg E in 1984-1989 As of 29 August 2001 located at 10.47 deg W drifting at 3.675 deg W per day. As of 2007 Mar 10 located at 112.63E drifting at 3.690W degrees per day.

1977 July 26 - . 15:35 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310JA-3.
  • VLF / plasma / B Ionosphere mission - . Nation: Japan. Agency: NIPR. Apogee: 221 km (137 mi).

1977 August 10 - . 12:47 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-27.
  • NO airglow Aurora mission - . Nation: Japan. Agency: NIPR. Apogee: 120 km (70 mi).

1977 August 16 - . 11:15 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: Lambda. Launch Vehicle: Lambda 3H. LV Configuration: Lambda 3H L-3H-9.
  • Aeronomy / ionosphere / plasma mission - . Nation: Japan. Agency: ISAS. Apogee: 1,294 km (804 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).

1977 September 3 - . 10:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-59.
  • Aeronomy / ionosphere / solar extreme ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 376 km (233 mi).

1977 September 14 - . 12:22 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-13.
  • Ultraviolet astronomy / extreme ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 204 km (126 mi).

1977 September 15 - . 09:30 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-12.
  • Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 114 km (70 mi).

1977 September 21 - . 08:35 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-4.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 188 km (116 mi).

1977 December 15 - . 00:47 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Delta. Launch Vehicle: Delta 2914. LV Configuration: Delta 2914 624/D137.
  • Sakura - . Payload: CS-1A. Mass: 676 kg (1,490 lb). Nation: Japan. Agency: NASDA. Program: CS. Class: Communications. Type: Civilian communications satellite. Spacecraft: CS-1. Completed Operations Date: 1985-11-19 . USAF Sat Cat: 10516 . COSPAR: 1977-118A. Apogee: 36,176 km (22,478 mi). Perigee: 36,169 km (22,474 mi). Inclination: 10.5000 deg. Period: 1,455.90 min. Medium-capacity Communications Satellite for Experimental Purposes . Launch vehicle Delta 2914-137. Launch time 0047 UT. Geographical longitude on geostationary orbit: 135 deg E. CS is a spin stabilized geostationary communications satellite. Characteris tics of satellite: Weight approx 340 kg at an early stage in orbit, configuration: cylindrical, height 3.48 m, diameter 2.18m, Expected life more than three years. Positioned in geosynchronous orbit over the Pacific Ocean at 135 deg E in 1977-1983 over the Pacific Ocean 150 deg E in 1984-1985 As of 25 August 2001 located at 78.79 deg E drifting at 4.904 deg W per day. As of 2007 Mar 10 located at 94.72W drifting at 4.901W degrees per day.

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 January 22 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-62.
  • Ionosphere / fields / solar mission - . Nation: Japan. Agency: ISAS. Apogee: 369 km (229 mi).

1978 January 27 - . 11:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-61.
  • Aeronomy / ionosphere / plasma mission - . Nation: Japan. Agency: ISAS. Apogee: 292 km (181 mi).

1978 January 28 - . 20:20 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-30.
  • Aurora mission - . Nation: Japan. Agency: NIPR. Apogee: 125 km (77 mi).

1978 February 4 - . 07:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3H. LV Configuration: Mu-3H M-3H-2.
  • SS-05 Kyokko - . Payload: Exos A. Mass: 103 kg (227 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Ionosphere satellite. Spacecraft: EXOS. USAF Sat Cat: 10664 . COSPAR: 1978-014A. Apogee: 3,952 km (2,455 mi). Perigee: 639 km (397 mi). Inclination: 65.4000 deg. Period: 134.00 min. Auroral studies. Active life - two years. Function: 1) Observation of wide angle global auroral pictures using UV television camera. 2) Spectrophotometry of ultraviolet air glow. 3) Observation of the energy spectrum of photoelectrons and auroral electrons. 4) Mass spect rometry of the ionized atmospheric species in the thermosphere. 5) Measurements of density and temperature of ambient electrons in the thermosphere. 6) Observation of electromagnetic and plasma waves and the emission associated with auroral phenomena.

1978 February 6 - . 18:55 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210JA-31.
  • Aurora mission - . Nation: Japan. Agency: NIPR. Apogee: 116 km (72 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 February 26 - . 11:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-60.
  • Ultraviolet astronomy / extreme ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 340 km (210 mi).

1978 April 7 - . 22:01 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17B. LV Family: Delta. Launch Vehicle: Delta 2914. LV Configuration: Delta 2914 626/D140.
  • Yuri 1 - . Payload: BSE-1. Mass: 678 kg (1,494 lb). Nation: Japan. Agency: NASDA. Program: BS. Class: Technology. Type: Communications technology satellite. Spacecraft: Yuri. Completed Operations Date: 1982-01-28 . USAF Sat Cat: 10792 . COSPAR: 1978-039A. Apogee: 35,868 km (22,287 mi). Perigee: 35,736 km (22,205 mi). Inclination: 11.7000 deg. Period: 1,436.90 min. Experimental comsat. Medium-scale broadcasting satellite for experimental purposes (BSE). Launch vehicle Delta 2914-140. Launch time 2201 GMT. Location 110 deg E. Characteristics of satellite: Weight approx 355 kg in an early stage in orbit. Configuration - box shaped satelli te with 2 solar array panels with overall span of 8.95m. Height 3.09m, width 1.32m, length 1.19m. 3-axis stabilized attitude control. Expected life 3 years. Positioned in geosynchronous orbit over the Indian Ocean at 110 deg E in 1978-1982 As of 4 September 2001 located at 44.59 deg E drifting at 0.116 deg E per day. As of 2007 Mar 11 located at 108.19E drifting at 0.031E degrees per day.

1978 August 20 - . 11:30 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-64.
  • Near infrared Galactic Plane Test / infrared astronomy / ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 319 km (198 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).

1978 September 16 - . 05:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3H. LV Configuration: Mu-3H M-3H-3.
  • SS-06 Jikiken - . Payload: Exos B. Mass: 100 kg (220 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Ionosphere satellite. Spacecraft: EXOS. USAF Sat Cat: 11027 . COSPAR: 1978-087A. Apogee: 21,192 km (13,168 mi). Perigee: 251 km (155 mi). Inclination: 31.3000 deg. Period: 370.90 min. Launching organization: Institute of Space and Aeronautical Science, University of Tokyo. Stimulated plasma wave experiment, natural plasma wave measurement, plasma parameter measurement by VLF Doppler technique, electric field probe and plasma density me asurement, energetic particle analysis, and controlled electron beam emission experiment. Characteristics: weight 90.5 kg, configuration - polyhedron with 38 faces, height 0.6m , diameter 0.75m, attitude control spin stabilization, life two years.

1979 January 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R336.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 63 km (39 mi).

1979 January 16 - . 20:50 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-65.
  • Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 353 km (219 mi).

1979 January 17 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R337.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 64 km (39 mi).

1979 January 19 - . 08:50 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-6.
  • Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 212 km (131 mi).

1979 January 21 - . 09:06 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-66.
  • Test / aeronomy / ionosphere / plasma mission - . Nation: Japan. Agency: ISAS. Apogee: 336 km (208 mi).

1979 January 24 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R338.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 62 km (38 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 January 31 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-5.
  • Ionosphere / fields mission - . Nation: Japan. Agency: ISAS. Apogee: 185 km (114 mi).

1979 January 31 - . 02:07 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R339.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 63 km (39 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 February 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R340.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1979 February 14 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R341.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1979 February 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R342.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 63 km (39 mi).

1979 February 21 - . 05:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3C. LV Configuration: Mu-3C M-3C-4.
  • SS-04 Hakucho - . Payload: Corsa B. Mass: 100 kg (220 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SS. Decay Date: 1985-04-15 . USAF Sat Cat: 11272 . COSPAR: 1979-014A. Apogee: 566 km (351 mi). Perigee: 543 km (337 mi). Inclination: 29.8000 deg. Period: 95.70 min. Soft X-ray telescope. Launching organization: Institute of Space and Aeronautical Science, University of Tokyo. Function: Observation of X-ray radiation of celestial bodies with good time resolution over a wide spectrum range. Characterstics: weight 96 kg, configuration regula r octagonal prism, height 0.66 m, diameter 0.76m, spin stabilized. Expected life 2 years.

1979 March 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R343.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 61 km (37 mi).

1979 March 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R344.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 64 km (39 mi).

1979 March 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R345.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1979 April 11 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R346.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 64 km (39 mi).

1979 April 18 - . 02:11 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R347.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 65 km (40 mi).

1979 April 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R348.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 65 km (40 mi).

1979 May 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R349.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 61 km (37 mi).

1979 May 16 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R350.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1979 May 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R351.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 65 km (40 mi).

1979 May 30 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R352.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 61 km (37 mi).

1979 June 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R353.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 62 km (38 mi).

1979 June 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R354.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 64 km (39 mi).

1979 July 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R355.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 64 km (39 mi).

1979 July 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R356.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1979 August 1 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R357.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 62 km (38 mi).

1979 August 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R358.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 61 km (37 mi).

1979 August 18 - . 07:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-67.
  • TED / TPI / NEL / PWN Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 365 km (226 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).

1979 September 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R359.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 64 km (39 mi).

1979 September 11 - . 01:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-68.
  • SUV / AUV / NEL / EPA Ionosphere / solar ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 353 km (219 mi).

1979 September 12 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R360.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1979 September 15 - . 11:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-7.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 166 km (103 mi).

1979 September 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R361.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1979 October 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R362.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1979 October 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R363.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1979 October 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R364.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1979 November 7 - . 02:14 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R365.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1979 November 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R366.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1979 November 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R367.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1979 December 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R369.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1979 December 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R368.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1979 December 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R370.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1979 December 26 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R371.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1980 January 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R372.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1980 January 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R373.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1980 January 16 - . 03:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-69.
  • TPE-1 Ionosphere / tether mission - . Nation: Japan. Agency: ISAS. Apogee: 328 km (203 mi).

1980 January 18 - . 06:20 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-1.
  • Heat Pipe Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 329 km (204 mi).

1980 January 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R374.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 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 2 - . 08:47 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-8.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 179 km (111 mi).

1980 February 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R375.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1980 February 17 - . 00:40 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3S. LV Configuration: Mu-3S M-3S-1.
  • Tansei 4 - . Payload: MS T4. Mass: 134 kg (295 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Tansei. Decay Date: 1983-05-12 . USAF Sat Cat: 11706 . COSPAR: 1980-015A. Apogee: 608 km (377 mi). Perigee: 517 km (321 mi). Inclination: 38.7000 deg. Period: 95.90 min.

1980 February 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R376.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 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 February 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R377.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1980 March 5 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R378.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1980 March 13 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R379.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1980 March 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R380.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1980 March 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R381.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1980 April 9 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R382.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1980 April 16 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R383.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1980 April 30 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R384.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1980 May 8 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R385.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1980 May 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R386.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1980 May 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R387.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1980 May 28 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R388.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1980 June 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R389.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1980 June 11 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R390.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1980 June 25 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R391.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1980 July 9 - . 02:28 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R392.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1980 July 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R393.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1980 August 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R394.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1980 August 20 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R395.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1980 August 26 - . 11:40 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 10. LV Configuration: Kappa 10 K-10-14.
  • GIR / GXV / STS X-ray astronomy / infrared astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 219 km (136 mi).

1980 September 2 - . 10:40 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-70.
  • Test / aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 230 km (140 mi).

1980 September 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R396.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1980 September 4 - . 12:45 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-71.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 308 km (191 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).

1980 September 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R397.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1980 October 1 - . 02:13 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R398.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1980 October 8 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R399.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1980 October 22 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R400.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1980 October 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R401.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 50 km (31 mi).

1980 November 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R402.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1980 November 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R403.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1980 November 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R404.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1980 December 3 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R405.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1980 December 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R406.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1980 December 17 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R407.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1981 January 7 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R408.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1981 January 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R409.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 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 January 21 - . 21:46 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-9.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 174 km (108 mi).

1981 January 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R410.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1981 January 28 - . 02:29 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R411.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1981 January 29 - . 07:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-2.
  • TPE-2 Ionosphere / tether mission - . Nation: Japan. Agency: ISAS. Apogee: 323 km (200 mi).

1981 February 4 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R412.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 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 February 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R413.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1981 February 21 - . 00:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. LV Family: Mu. Launch Vehicle: Mu-3S. LV Configuration: Mu-3S M-3S-2.
  • SS-07 Hinotori - . Payload: Astro A. Mass: 185 kg (407 lb). Nation: Japan. Agency: ISAS. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Astro. Decay Date: 1991-07-11 . USAF Sat Cat: 12307 . COSPAR: 1981-017A. Apogee: 279 km (173 mi). Perigee: 274 km (170 mi). Inclination: 31.3000 deg. Period: 90.10 min. Summary: Hinotori (ASTRO-A). Launching organisation: Institute of Space and Aeronautical Science, University of Tokyo. Investigation of solar flare by X-ray telescope and spectrograph. .

1981 February 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R414.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 61 km (37 mi).

1981 March 11 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R415.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1981 March 18 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R416.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1981 March 26 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R417.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1981 April 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R418.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1981 April 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R419.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1981 April 22 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R420.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1981 April 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R421.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1981 May 13 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R422.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1981 May 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R423.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1981 May 27 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R424.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1981 June 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R425.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1981 June 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R426.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1981 July 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R427.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1981 July 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R428.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 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 6 - . 02:07 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R429.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 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.

1981 August 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R430.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1981 August 24 - . 12:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-10.
  • Test / aurora / aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 187 km (116 mi).

1981 September 2 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R431.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1981 September 5 - . 01:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-4.
  • Payload recovery rest / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 224 km (139 mi).

1981 September 7 - . 09:38 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-11.
  • Submillimeter atmospheric spectra Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 193 km (119 mi).

1981 September 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R432.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1981 September 30 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R433.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1981 October 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R434.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1981 October 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R435.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1981 October 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R436.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1981 November 11 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R437.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1981 November 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R438.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1981 November 25 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R439.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1981 December 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R440.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1981 December 9 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R441.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1981 December 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R442.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1981 December 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R443.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1982 January 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R444.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1982 January 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R445.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1982 January 15 - . 09:20 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-73.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 303 km (188 mi).

1982 January 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R446.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1982 January 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R447.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

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 February 3 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R448.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1982 February 13 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-72.
  • Test / ionosphere / plasma / fields mission - . Nation: Japan. Agency: ISAS. Apogee: 328 km (203 mi).

1982 February 14 - . 10:50 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-3.
  • 0.3m telescope test Ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 266 km (165 mi).

1982 February 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R449.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1982 February 18 - . 12:40 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-74.
  • Ultraviolet / x-ray astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 315 km (195 mi).

1982 February 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R450.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 45 km (27 mi).

1982 March 10 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R451.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 24 km (14 mi).

1982 March 17 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R452.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 49 km (30 mi).

1982 March 24 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R453.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1982 April 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R454.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1982 April 14 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R455.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1982 April 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R456.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1982 April 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R457.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1982 May 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R458.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1982 May 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R459.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 43 km (26 mi).

1982 May 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R460.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1982 June 2 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R461.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1982 June 9 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R462.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1982 June 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R463.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1982 July 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R464.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1982 July 21 - . 02:25 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R465.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1982 August 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R466.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 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 August 18 - . 02:12 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R467.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1982 September 1 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R468.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 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).

1982 September 6 - . 02:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-5.
  • 0.1m telescope Solar extreme ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 237 km (147 mi).

1982 September 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R469.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1982 September 12 - . 12:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-210. LV Configuration: S-210-13.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 97 km (60 mi).

1982 September 13 - . 12:30 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-75.
  • Near infrared Background Infrared astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 320 km (190 mi).

1982 September 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R470.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1982 September 25 - . 09:15 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-12.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 200 km (120 mi).

1982 September 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R471.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1982 October 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R472.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1982 October 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R473.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1982 October 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R474.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1982 November 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R475.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1982 November 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R476.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1982 December 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R477.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1982 December 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R478.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1982 December 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R479.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1982 December 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R480.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1983 January 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R481.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1983 January 14 - . 20:40 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-76.
  • Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 349 km (216 mi).

1983 January 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R482.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1983 January 26 - . 02:18 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R483.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 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 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R484.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 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 February 16 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R485.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1983 February 20 - . 05:10 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S. LV Configuration: Mu-3S M-3S-3.
  • SS-08 Tenma - . Payload: Astro B. Mass: 185 kg (407 lb). Nation: Japan. Agency: ISAS. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Astro. Decay Date: 1988-12-17 . USAF Sat Cat: 13829 . COSPAR: 1983-011A. Apogee: 438 km (272 mi). Perigee: 431 km (267 mi). Inclination: 31.5000 deg. Period: 93.30 min. X-ray experiments. Astro-B (Tenma). Launch 0510 GMT. Launching organization: ISAS (Institute of Space and Astronautical Science). X-ray observation of X-ray stars in our galaxy as well as X-ray galaxies using a scintillating proportional counter, a transient X-ray source mo nitor, an X-ray foucsing collector, a radiation belt monitor, a gamma ray burst detector and a star sensor.

1983 February 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R486.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1983 March 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R487.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1983 March 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R488.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1983 March 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R489.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1983 April 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R490.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1983 April 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R491.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1983 April 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R492.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1983 April 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R493.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1983 May 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R494.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1983 May 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R495.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1983 May 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R496.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1983 June 1 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R497.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1983 June 15 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R498.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1983 June 29 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R499.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1983 July 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R500.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1983 July 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R501.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

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 8 - . 06:00 GMT - . Launch Site: White Sands. LV Family: Black Brant. Launch Vehicle: Black Brant 9B.
  • CHARGE-1 (TPE-3) Tether / ionosphere mission - . Nation: Japan. Agency: NASA; ISAS. Apogee: 218 km (135 mi).

1983 August 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R502.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

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).

1983 August 25 - . 02:30 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R503.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1983 August 29 - . 10:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-6.
  • MINIX Plasma physics mission - . Nation: Japan. Agency: ISAS. Apogee: 238 km (147 mi).

1983 September 7 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R504.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1983 September 12 - . 22:00 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-13.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 227 km (141 mi).

1983 September 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R505.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 50 km (31 mi).

1983 September 16 - . 18:16 GMT - . Launch Site: Kagoshima. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-14.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 218 km (135 mi).

1983 September 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R506.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1983 October 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R507.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1983 October 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R508.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1983 October 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R509.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1983 November 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R510.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1983 November 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R511.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1983 November 30 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R512.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1983 December 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R513.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1983 December 14 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R514.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1983 December 21 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R515.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1983 December 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R516.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1984 January 11 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R517.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1984 January 13 - . 19:30 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-77.
  • CIR Infrared astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 317 km (196 mi).

1984 January 17 - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K?. LV Family: SB-735. Launch Vehicle: ST-735. LV Configuration: ST-735-1 ST-735-1.
  • SRB Sep test - . Nation: Japan. Agency: ISAS. Apogee: 50 km (31 mi).

1984 January 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R518.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 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 January 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R519.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1984 February 8 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R520.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1984 February 14 - . 08:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S. LV Configuration: Mu-3S M-3S-4.
  • SS-09 Onzora - . Payload: Exos C. Mass: 180 kg (390 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Ionosphere satellite. Spacecraft: EXOS. Decay Date: 1988-12-26 . USAF Sat Cat: 14722 . COSPAR: 1984-015A. Apogee: 331 km (205 mi). Perigee: 247 km (153 mi). Inclination: 74.6000 deg. Period: 90.30 min. Optical investigations of ionosphere. EXOS-C (OHZORA). Optical study of the stratosphere and middle atmosphere. Study of the specific phenomena of the ionospheric plasma over the southern Atlantic geomagnetic anomaly zone which was discovered by the third scientific satellite 'TAIYO'. Launch vehicle Mu-3S-4, launching organization ISAS (Institute of Space and Astronautical Science). Launch time 0800 GMT.

1984 February 15 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R521.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1984 February 22 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R522.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1984 March 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R523.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1984 March 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R524.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1984 March 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R525.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1984 April 4 - . 19:27 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310JA-8.
  • Ionosphere mission - . Nation: Japan. Agency: NIPR. Apogee: 201 km (124 mi).

1984 April 11 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R526.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1984 April 18 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R527.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 49 km (30 mi).

1984 April 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R528.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1984 May 3 - . 22:14 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310JA-9.
  • Ionosphere mission - . Nation: Japan. Agency: NIPR. Apogee: 204 km (126 mi).

1984 May 9 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R529.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1984 May 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R530.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1984 May 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R531.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1984 May 28 - . 23:17 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310JA-10.
  • Ionosphere mission - . Nation: Japan. Agency: NIPR. Apogee: 209 km (129 mi).

1984 May 30 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R532.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1984 June 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R533.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1984 June 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R534.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1984 July 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R535.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1984 July 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R536.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1984 August 1 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R537.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

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.

1984 August 15 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R538.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1984 August 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R539.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1984 September 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R540.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1984 September 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R541.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1984 October 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R542.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1984 October 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R543.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1984 October 24 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R544.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1984 October 31 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R545.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1984 November 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R546.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1984 November 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R547.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1984 November 21 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R548.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1984 December 5 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R549.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1984 December 12 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R550.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1984 December 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R551.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1985 January 7 - . 19:26 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-1.
  • SS-10 Sagikake - . Payload: MS T5. Mass: 141 kg (310 lb). Nation: Japan. Agency: ISAS. Class: Technology. Type: Navigation technology satellite. Spacecraft: Tansei. USAF Sat Cat: 15464 . COSPAR: 1985-001A. Sakigake ('Pioneer') was a test spacecraft similar to Suisei (Planet-A). Objectives were :verification of fundamental technology related to interplanetary missions, including deep-space communication, attitude control, attitude determination; study and observation of solar wind and plasma waves and interplanetary magnetic field. It carried three instruments to measure plasma wave spectra, solar wind ions, and interplanetary magnetic fields. The spacecraft was spin-stabilized at two different rates (5 and 0.2 rpm). It was equipped with hydrazine thrusters for attitude and velocity control, star and sun sensors for attitude determination, and a mechanically despun off-set parabolic dish for long-range communication. Launched into an initial heliocentric orbit with a period of 318.8 days, at 151.4 x 121.9 million km (0.815 x 1.012 AU), 1.439 degree inclination. Flew by Comet Halley on its sunward side at a distance of about 7 million kilometers on March 11, 1986. It later made an Earth swingby on January 8, 1992 with a closest approach of 88,997 km. This was the first planet-swingby for a Japanese spacecraft. During the approach, Sakigake observed the geotail, with passage occurring at 290 Re on 14 June 1993 before ISTP's multi-spacecraft investigation of that region. The second Earth swingby was on June 14, 1993 at 40 Re, and the third on October 28, 1994 at 86 Re. Almost no hydrazine remained so no further maneuvers were accomplished. Telemetry contact was lost on 15 November 1995 at a distance of 106 million km. Future mission planning had included a 23.6 km/s, 10,000 km flyby of Comet Honda-Mrkos-Pajdusakova on Feb 3, 1996 (approaching the nucleus along the tail) some 0.17 AU from the Sun, and a 14 million km passage of Comet Giacobini-Zinner on Nov 29, 1998.

1985 January 9 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R552.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1985 January 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R553.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1985 January 23 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R554.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1985 January 30 - . 14:00 GMT - . Launch Site: Syowa Base. LV Family: MT-135. Launch Vehicle: MT-135JA. LV Configuration: MT-135JA-1.
  • Meteorological mission - . Nation: Japan. Agency: NIPR. Apogee: 60 km (37 mi).

1985 February 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R555.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1985 February 7 - . 09:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-15.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 213 km (132 mi).

1985 February 11 - . 10:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-7.
  • Aeronomy / ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 362 km (224 mi).

1985 February 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R556.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1985 February 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R557.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1985 February 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R558.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1985 March 6 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R559.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1985 March 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R560.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1985 March 26 - . 14:30 GMT - . Launch Site: Syowa Base. LV Family: MT-135. Launch Vehicle: MT-135JA. LV Configuration: MT-135JA-2.
  • Meteorological mission - . Nation: Japan. Agency: NIPR. Apogee: 60 km (37 mi).

1985 March 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R561.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1985 April 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R562.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1985 April 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R563.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1985 April 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R564.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1985 May 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R565.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1985 May 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R566.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1985 May 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R567.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1985 May 29 - . 00:59 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310JA-11.
  • Ionosphere mission - . Nation: Japan. Agency: NIPR. Apogee: 212 km (131 mi).

1985 May 30 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R568.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1985 June 12 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R569.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1985 June 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R570.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1985 June 28 - . 13:35 GMT - . Launch Site: Syowa Base. LV Family: MT-135. Launch Vehicle: MT-135JA. LV Configuration: MT-135JA-3.
  • Meteorological mission - . Nation: Japan. Agency: NIPR. Apogee: 61 km (37 mi).

1985 June 28 - . 16:16 GMT - . Launch Site: Syowa Base. LV Family: MT-135. Launch Vehicle: MT-135JA. LV Configuration: MT-135JA-5.
  • Meteorological mission - . Nation: Japan. Agency: NIPR. Apogee: 71 km (44 mi).

1985 June 28 - . 18:10 GMT - . Launch Site: Syowa Base. LV Family: MT-135. Launch Vehicle: MT-135JA. LV Configuration: MT-135JA-6.
  • Meteorological mission - . Nation: Japan. Agency: NIPR. Apogee: 73 km (45 mi).

1985 June 28 - . 20:02 GMT - . Launch Site: Syowa Base. LV Family: MT-135. Launch Vehicle: MT-135JA. LV Configuration: MT-135JA-7.
  • Meteorological mission - . Nation: Japan. Agency: NIPR. Apogee: 69 km (42 mi).

1985 June 28 - . 21:58 GMT - . Launch Site: Syowa Base. LV Family: MT-135. Launch Vehicle: MT-135JA. LV Configuration: MT-135JA-4.
  • Meteorological mission - . Nation: Japan. Agency: NIPR. Apogee: 69 km (42 mi).

1985 July 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R571.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1985 July 12 - . 19:35 GMT - . Launch Site: Syowa Base. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310JA-12.
  • Ionosphere mission - . Nation: Japan. Agency: NIPR. Apogee: 222 km (137 mi).

1985 July 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R572.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 61 km (37 mi).

1985 July 31 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R573.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1985 August 14 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R574.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1985 August 18 - . 23:33 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-2.
  • SS-11 Suisei - . Payload: Planet A. Mass: 141 kg (310 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: SS. USAF Sat Cat: 15967 . COSPAR: 1985-073A. Rendezvoused with comet Halley 3/8/86. Solar Orbit (Heliocentric). PLANET-A (SUISEI). Launch time 2333 GMT. Imaging of the hydrogen coma of Halley's comet by the hydrogen Lyman alpha line. Measurement of the solar wind in the cruising phase and in the vicinity of the comet. Launching organiza tion ISAS. Heliocentric orbit parameters 282 days, inclination 0.888 deg, 151.42 x 100.5 million km (1.0122 x 0.6718 AU).

1985 August 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R575.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1985 August 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R576.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1985 September 11 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R577.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1985 September 11 - . 02:25 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-44.
  • SONDE Meteorological mission - . Nation: Japan. Agency: ISAS. Apogee: 63 km (39 mi).

1985 September 14 - . 14:40 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-78.
  • CBR Submillimeter radio astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 297 km (184 mi).

1985 September 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R578.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1985 September 25 - . 14:00 GMT - . Launch Site: Syowa Base. LV Family: MT-135. Launch Vehicle: MT-135JA. LV Configuration: MT-135JA-9.
  • Meteorological mission - . Nation: Japan. Agency: NIPR. Apogee: 71 km (44 mi).

1985 September 25 - . 16:00 GMT - . Launch Site: Syowa Base. LV Family: MT-135. Launch Vehicle: MT-135JA. LV Configuration: MT-135JA-8.
  • Meteorological mission - . Nation: Japan. Agency: NIPR. Apogee: 71 km (44 mi).

1985 September 25 - . 18:00 GMT - . Launch Site: Syowa Base. LV Family: MT-135. Launch Vehicle: MT-135JA. LV Configuration: MT-135JA-11.
  • Meteorological mission - . Nation: Japan. Agency: NIPR. Apogee: 72 km (44 mi).

1985 September 25 - . 20:00 GMT - . Launch Site: Syowa Base. LV Family: MT-135. Launch Vehicle: MT-135JA. LV Configuration: MT-135JA-10.
  • Meteorological mission - . Nation: Japan. Agency: NIPR. Apogee: 73 km (45 mi).

1985 October 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R579.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1985 October 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R580.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1985 October 31 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R581.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1985 November 6 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R582.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 46 km (28 mi).

1985 November 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R583.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1985 November 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R584.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1985 December 5 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R585.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1985 December 11 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R586.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1985 December 18 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R587.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1985 December 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R588.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1986 January 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R589.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1986 January 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R590.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1986 January 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R591.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1986 January 31 - . 08:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-79.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 319 km (198 mi).

1986 February 1 - . 12:40 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-16.
  • E-region Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 201 km (124 mi).

1986 February 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R592.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1986 February 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R593.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

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 February 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R594.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1986 March 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R595.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1986 March 8 - .
  • Susei, Comet Halley Flyby - . Nation: Japan.

1986 March 10 - .
  • Sakigake, Comet Halley Flyby - . Nation: Japan.

1986 March 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R596.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1986 March 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R597.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1986 April 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R598.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1986 April 17 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R599.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1986 April 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R600.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1986 May 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R601.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1986 May 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R602.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1986 May 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R603.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1986 May 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R604.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1986 June 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R605.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1986 June 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R606.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1986 July 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R607.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1986 July 16 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R608.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1986 July 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R609.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1986 August 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R610.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

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. .

1986 August 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R611.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1986 August 20 - . 02:20 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-45.
  • SONDE Meteorological mission - . Nation: Japan. Agency: ISAS. Apogee: 58 km (36 mi).

1986 August 20 - . 04:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-46.
  • SONDE Meteorological mission - . Nation: Japan. Agency: ISAS. Apogee: 60 km (37 mi).

1986 August 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R612.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1986 September 6 - . 13:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-17.
  • Airglow Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 202 km (125 mi).

1986 September 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R613.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1986 September 24 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R614.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1986 October 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R615.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1986 October 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R616.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1986 October 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R617.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1986 October 29 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R618.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1986 November 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R619.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1986 November 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R620.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1986 December 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R621.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1986 December 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R622.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1986 December 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R623.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1986 December 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R624.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1987 January 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R625.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1987 January 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R626.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1987 January 15 - . 08:10 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-9.
  • E field Ionosphere / aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 365 km (226 mi).

1987 January 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R627.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1987 February 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R628.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1987 February 5 - . 06:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-3.
  • Ginga - . Payload: Astro C. Mass: 420 kg (920 lb). Nation: Japan. Agency: ISAS. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Astro. Decay Date: 1991-11-01 . USAF Sat Cat: 17480 . COSPAR: 1987-012A. Apogee: 450 km (270 mi). Perigee: 395 km (245 mi). Inclination: 31.0000 deg. Period: 93.00 min. Summary: Studyied galactic gamma ray, X-ray sources. ASTRO-C (Ginga). Observation of variabilities of X-rays from active galactic nuclei and galactic compact sources. Launching organization ISAS. Launch time 0630 GMT. .

1987 February 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R629.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

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 February 21 - . 16:15 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-8.
  • GUV Ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 286 km (177 mi).

1987 February 22 - . 15:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-80.
  • CBR Submillimeter radio astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 317 km (196 mi).

1987 February 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R630.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 March 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R631.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 March 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R632.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 March 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R633.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 April 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R634.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 April 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R635.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 April 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R636.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1987 May 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R637.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1987 May 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R638.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 61 km (37 mi).

1987 May 27 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R639.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1987 June 10 - . 02:30 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R640.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 June 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R641.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 June 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R642.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1987 July 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R643.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 July 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R644.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1987 August 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R645.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1987 August 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R646.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

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.

1987 September 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R647.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 September 9 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-47.
  • SONDE Meteorological mission - . Nation: Japan. Agency: ISAS. Apogee: 58 km (36 mi).

1987 September 9 - . 02:12 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R648.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1987 September 9 - . 04:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-48.
  • SONDE Meteorological mission - . Nation: Japan. Agency: ISAS. Apogee: 58 km (36 mi).

1987 September 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R649.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1987 September 30 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R650.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1987 October 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R651.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 October 21 - . 02:17 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R652.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1987 October 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R653.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1987 November 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R654.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1987 November 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R655.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1987 November 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R656.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1987 December 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R657.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1987 December 16 - . 02:13 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R658.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1987 December 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R659.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1988 January 6 - . 02:24 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R660.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1988 January 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R661.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1988 January 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R662.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1988 January 25 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: Kappa. Launch Vehicle: Kappa 9M. LV Configuration: Kappa 9M K-9M-81.
  • COREX Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 359 km (223 mi).

1988 January 28 - . 02:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-18.
  • D-region Ionosphere / aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 202 km (125 mi).

1988 February 10 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R663.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1988 February 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R664.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

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 February 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R665.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1988 March 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R666.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1988 March 9 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R667.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1988 March 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R668.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1988 March 30 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R669.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1988 April 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R670.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1988 April 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R671.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1988 April 27 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R672.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1988 May 11 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R673.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1988 May 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R674.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1988 June 1 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R675.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1988 June 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R676.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1988 June 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R677.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1988 June 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R678.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1988 July 13 - . 02:14 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R679.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1988 July 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R680.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1988 August 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R681.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1988 August 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R682.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1988 August 31 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R683.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

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 11 - . 02:25 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-49.
  • NNP Meteorological mission - . Nation: Japan. Agency: ISAS. Apogee: 58 km (36 mi).

1988 September 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R684.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 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.

1988 September 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R685.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1988 October 12 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R686.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1988 October 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R687.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1988 November 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R688.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1988 November 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R689.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1988 November 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R690.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1988 November 30 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R691.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1988 December 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R692.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1988 December 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R693.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1988 December 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R694.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1988 December 28 - . 02:12 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R695.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1989 January 11 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R696.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1989 January 18 - . 01:50 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R697.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 January 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R698.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

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 February 1 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R699.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 February 1 - . 12:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-19.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 230 km (140 mi).

1989 February 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R700.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 February 21 - . 23:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-4.
  • Akebono - . Payload: Exos D. Mass: 295 kg (650 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Ionosphere satellite. Spacecraft: EXOS. USAF Sat Cat: 19822 . COSPAR: 1989-016A. Apogee: 8,554 km (5,315 mi). Perigee: 272 km (169 mi). Inclination: 75.1000 deg. Period: 185.90 min. Summary: Studied aurora borealis, auroral australis. EXOS-D (Akebono). Observation in high precision of behaviour and acceleration mechanism of aurora particles in Earth magnetosphere. Launching organization ISAS. Launch time 2330 GMT. .

1989 February 22 - . 02:06 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R701.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 March 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R702.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 March 6 - . 23:29 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44LP. LV Configuration: Ariane 44LP V29.
  • JCSAT 1 - . Mass: 2,280 kg (5,020 lb). Nation: Japan. Agency: JCSAT. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 393. Completed Operations Date: 1998-08-17 . USAF Sat Cat: 19874 . COSPAR: 1989-020A. Apogee: 36,018 km (22,380 mi). Perigee: 35,971 km (22,351 mi). Inclination: 4.1000 deg. Period: 1,446.80 min. Japanese domestic communications; 150 deg E. Domestic communication. Launching states: Japan, France, USA. Launch vehicle Ariane 29 (Ariane IV). Launching organization ARIANE SPACE. Launch time 1129 GMT. Positioned in geosynchronous orbit at 150 deg E in 1989-1997; 148 deg E in 1997; 111 deg E in 1998 As of 31 August 2001 located at 19.12 deg E drifting at 2.653 deg W per day. As of 2007 Mar 11 located at 63.05E drifting at 2.678W degrees per day.

1989 March 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R703.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 March 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R704.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 March 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R705.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 April 13 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R706.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 April 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R707.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 April 26 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R708.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 May 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R709.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 May 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R710.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 May 31 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R711.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 June 5 - . 22:37 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44L. LV Configuration: Ariane 44L V31.
  • Superbird A - . Payload: Superbird A / DFS-Kopernikus 1. Mass: 2,489 kg (5,487 lb). Nation: Japan. Agency: SCC. Program: Superbird. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. Completed Operations Date: 1991-02-01 . USAF Sat Cat: 20040 . COSPAR: 1989-041A. Apogee: 35,944 km (22,334 mi). Perigee: 35,931 km (22,326 mi). Inclination: 2.5000 deg. Period: 1,443.80 min. Japanese domestic business communications; 158 deg E. Positioned in geosynchronous orbit at 158 deg E in 1989-1990 As of 6 September 2001 located at 41.59 deg E drifting at 1.921 deg W per day. As of 2007 Mar 11 located at 166.35W drifting at 1.878W degrees per day.

1989 June 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R712.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 June 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R713.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 June 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R714.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 July 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R715.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 August 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R716.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 August 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R717.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 August 17 - .
  • Japanese Commercial Cosmonaut Training Group selected. - . Nation: Japan. Related Persons: Akiyama; Kikuchi. Summary: Japanese journalists trained for a commercial flight to the Mir space station..

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 August 30 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R718.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 September 4 - . 16:15 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-10.
  • CIR Cosmic infrared Infrared astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 288 km (178 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.

1989 September 6 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-50.
  • NNP-O3 Meteorological mission - . Nation: Japan. Agency: ISAS. Apogee: 54 km (33 mi).

1989 September 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R719.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 September 20 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R720.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 October 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R721.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 October 18 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R722.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 November 1 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R723.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 November 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R724.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 November 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R725.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 December 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R726.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 December 13 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R727.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 December 21 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R728.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1989 December 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R729.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 January 1 - . 00:07 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC40. LV Family: Titan. Launch Vehicle: Commercial Titan 3. LV Configuration: Commercial Titan 3 CT-1.
  • JCSAT 2 - . Payload: JCSat 2 / Orbus-7S. Mass: 2,280 kg (5,020 lb). Nation: Japan. Agency: JCSAT. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 393. USAF Sat Cat: 20402 . COSPAR: 1990-001B. Apogee: 35,877 km (22,292 mi). Perigee: 35,868 km (22,287 mi). Inclination: 0.1000 deg. Period: 1,440.50 min. Japanese domestic communications; 154 deg E. Domestic communications. Launching organization Martin Marietta. Launch time 0007 GMT. Positioned in geosynchronous orbit at 154 deg E in 1990-1999 As of 5 September 2001 located at 154.04 deg E drifting at 0.006 deg W per day. As of 2007 Mar 10 located at 116.78W drifting at 6.255W degrees per day.

1990 January 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R730.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 January 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R731.
  • DYANA Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1990 January 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R732.
  • DYANA Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1990 January 24 - . 11:46 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-5.
  • Hiten - . Payload: Muses A. Mass: 185 kg (407 lb). Nation: Japan. Agency: ISAS. Program: Muses. Class: Moon. Type: Lunar probe. Spacecraft: Hiten. Decay Date: 1993-04-11 . USAF Sat Cat: 20448 . COSPAR: 1990-007A. Apogee: 286,183 km (177,825 mi). Perigee: 262 km (162 mi). Inclination: 30.6000 deg. Period: 9,597.60 min. MUSES-A was renamed Hiten after launch. It developed of lunar swingby techniques for future missions and ejected a lunar orbiter. Launching organization ISAS. On 1990 Jan 25: Period 6.665 days, inclination 30.63 deg, 262.49 x 286182.72 km. On 1992 Feb 17: Period 4.53 days, inclination 38.90 deg, perilune 2289.67 km, apolune 49013.93 km.
  • Hagoromo - . Payload: Muses A. Mass: 12 kg (26 lb). Nation: Japan. Agency: ISAS. Program: Muses. Class: Moon. Type: Lunar probe. Spacecraft: Hagoromo. USAF Sat Cat: 20618 . COSPAR: 1990-007B. Summary: Lunar orbiter ejected from Muses A 3/19/90; contact lost after release; engineering test. Lunar Orbit (Selenocentric). .

1990 January 27 - . 19:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-20.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 185 km (114 mi).

1990 January 31 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R733.
  • DYANA Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

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 February 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R734.
  • DYANA Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1990 February 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R735.
  • DYANA Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1990 February 21 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-51.
  • DYANA parachute Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 58 km (36 mi).

1990 February 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R736.
  • DYANA Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1990 February 21 - . 16:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-11.
  • CIR Infrared astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 317 km (196 mi).

1990 February 22 - . 23:17 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44L. LV Configuration: Ariane 44L V36. FAILURE: Exploded 100 seconds after liftoff due to water line blockage. This was caused by a piece of cloth found in the first stage Viking engine water cooling system.. Failed Stage: 1.
  • Superbird B - . Nation: Japan. Agency: SCC. Program: Superbird. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. Decay Date: 1990-02-23 . COSPAR: F900222A. Apogee: 9.00 km (5.50 mi). Summary: Launched with BS-2X. Targeted for Geosynch orbit..

1990 February 26 - . 02:06 GMT - . Launch Site: Andoya. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-12.
  • Auroral mission - . Nation: Japan. Agency: ISAS. Apogee: 369 km (229 mi).

1990 February 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R737.
  • DYANA Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1990 March 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R738.
  • DYANA Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1990 March 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R739.
  • DYANA Aeronomy mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1990 March 19 - .
  • Hiten, Moon Flyby (Japan) - . Nation: Japan. Spacecraft: Hiten.

1990 March 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R740.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 March 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R741.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 April 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R742.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 April 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R743.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 April 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R744.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 May 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R745.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 May 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R746.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 May 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R747.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 June 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R748.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 June 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R749.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 June 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R750.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 July 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R751.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 July 25 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R752.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 August 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R753.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 August 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R754.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 August 27 - . 02:10 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-52.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 57 km (35 mi).

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.

1990 September 5 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R755.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 September 19 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R756.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 October 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R757.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 October 17 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R758.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 November 1 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R759.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 November 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R760.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 November 14 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R761.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 November 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R762.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 December 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R763.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 December 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R764.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 December 19 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R765.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1990 December 27 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R766.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 January 9 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R767.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 January 16 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R768.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 January 23 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R769.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 January 30 - . 02:08 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R770.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 February 6 - . 02:25 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R771.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 February 9 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-53.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 57 km (35 mi).

1991 February 11 - . 02:10 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-54.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 62 km (38 mi).

1991 February 12 - . 03:29 GMT - . Launch Site: Andoya. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-14.
  • Auroral mission - . Nation: Japan. Agency: ISAS. Apogee: 353 km (219 mi).

1991 February 13 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R772.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 February 16 - . 13:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-13.
  • Extreme ultraviolet Telescopes Extreme ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 337 km (209 mi).

1991 February 20 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R773.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 February 27 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R774.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 March 13 - . 02:13 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R775.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 March 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R776.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 March 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R777.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 April 10 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R778.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 April 17 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R779.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 April 18 - . 23:30 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36B. LV Family: Atlas. Launch Vehicle: Atlas I. LV Configuration: Atlas I AC-70. FAILURE: RL-10 Centaur engine turbopump failed at T+361 seconds; destroyed by range safety.. Failed Stage: 2.
  • Yuri 3H - . Payload: BS-3H. Mass: 600 kg (1,320 lb). Nation: Japan. Agency: TSCJ. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. Decay Date: 1991-04-18 . COSPAR: F910418A. Apogee: 175 km (108 mi).

1991 April 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R780.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 May 8 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R781.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 May 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R782.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 May 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R783.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 June 5 - . 02:25 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R784.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 June 19 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R785.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 June 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R786.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 July 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R787.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 July 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R788.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 August 1 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R789.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 August 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R790.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

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 August 28 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R791.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 August 30 - . 02:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-6.
  • Solar-A - . Payload: Yohkoh. Mass: 420 kg (920 lb). Nation: Japan. Agency: ISAS. Class: Astronomy. Type: Solar astronomy satellite. Spacecraft: Solar. Decay Date: 2005-09-12 . USAF Sat Cat: 21694 . COSPAR: 1991-062A. Apogee: 754 km (468 mi). Perigee: 516 km (320 mi). Inclination: 31.3000 deg. Period: 97.40 min. Summary: X-ray imaging of Sun..

1991 September 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R792.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 September 11 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-55.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 56 km (34 mi).

1991 September 12 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-56.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 57 km (35 mi).

1991 September 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R793.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

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).

1991 September 25 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R794.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 October 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R795.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 October 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R796.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 October 23 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R797.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 November 6 - . 02:14 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R798.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 November 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R799.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 November 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R800.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 December 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R801.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 December 11 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R802.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 December 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R803.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1991 December 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R804.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1992 January 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R805.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1992 January 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R806.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1992 January 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R807.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1992 January 28 - . 12:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-21.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 223 km (138 mi).

1992 February 1 - . 16:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-15.
  • CIR Infrared astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 338 km (210 mi).

1992 February 5 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R808.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 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 February 14 - . 23:00 GMT - . Launch Site: Kagoshima. LV Family: Rockoon. Launch Vehicle: HIMES Rockoon. LV Configuration: HIMES Rockoon RFT-2.
  • HIMES RFT-2 - . Nation: Japan. Agency: ISAS. Apogee: 67 km (41 mi).

1992 February 19 - . 02:11 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R809.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1992 February 26 - . 02:08 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R810.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1992 February 26 - . 23:58 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44L. LV Configuration: Ariane 44L V49.
  • Superbird B1 - . Mass: 2,560 kg (5,640 lb). Nation: Japan. Agency: SCC. Program: Superbird. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 21893 . COSPAR: 1992-010A. Apogee: 36,206 km (22,497 mi). Perigee: 36,057 km (22,404 mi). Inclination: 0.9000 deg. Period: 1,453.80 min. Stationed at 162 deg E. Domestic communications. Launching organization Arianespace. Launch time 2358 GMT. Positioned in geosynchronous orbit at 162 deg E in 1992-1999 As of 4 September 2001 located at 19.90 deg W drifting at 4.382 deg W per day. As of 2007 Mar 9 located at 164.51E drifting at 4.378W degrees per day.

1992 March 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R811.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1992 March 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R812.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1992 March 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R813.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1992 April 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R814.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1992 April 15 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R815.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1992 April 22 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R816.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1992 April 30 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R817.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1992 May 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R818.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1992 May 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R819.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1992 May 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R820.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1992 June 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R821.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1992 June 17 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R822.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1992 June 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R823.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1992 July 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R824.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1992 July 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R825.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1992 July 24 - . 14:26 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC17A. LV Family: Delta. Launch Vehicle: Delta 6925. LV Configuration: Delta 6925 D212.
  • Geotail - . Payload: Geotail. Mass: 1,008 kg (2,222 lb). Nation: Japan. Agency: ISAS. Class: Earth. Type: Magnetosphere satellite. Spacecraft: Geotail. USAF Sat Cat: 22049 . COSPAR: 1992-044A. Apogee: 399,941 km (248,511 mi). Perigee: 57,448 km (35,696 mi). Inclination: 18.0000 deg. Period: 18,904.40 min. Measured magnetosphere and Earth's geomagnetic tail. To investigate the structure and dynamics of the geomagnetic tail that extends on the nightside of the Earth. Launch time 1426 GMT. Launching states Japan and the United States of America. Launching organization NASA.
  • DUVE - . Payload: DUVE. Nation: Japan. Agency: MDAC. Class: Earth. Type: Seismology satellite. Spacecraft: DUVE. Decay Date: 1993-03-16 . USAF Sat Cat: 22050 . COSPAR: 1992-044B. Apogee: 1,413 km (877 mi). Perigee: 215 km (133 mi). Inclination: 27.4000 deg. Period: 101.17 min. Summary: Diffuse Ultraviolet Explorer package bolted to Delta 2 2nd stage..

1992 August 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R826.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1992 August 19 - . 02:30 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R827.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

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).

1992 September 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R828.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1992 September 9 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-57.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 57 km (35 mi).

1992 September 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R829.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1992 September 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R830.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1992 October 7 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R831.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1992 October 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R832.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1992 October 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R833.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1992 November 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R834.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1992 November 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R835.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1992 November 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R836.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1992 December 1 - . 22:48 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 42P. LV Configuration: Ariane 42P+ V55.
  • Superbird A1 - . Mass: 2,780 kg (6,120 lb). Nation: Japan. Agency: SCC. Program: Superbird. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 22253 . COSPAR: 1992-084A. Apogee: 35,800 km (22,200 mi). Perigee: 35,774 km (22,228 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Stationed at 158 deg E. Domestic communications. Launching states: Japan and France. Launch time 2248 GMT. Positioned in geosynchronous orbit at 158 deg E in 1993-1999 As of 31 August 2001 located at 157.95 deg E drifting at 0.011 deg W per day. As of 2007 Mar 9 located at 158.03E drifting at 0.006W degrees per day.

1992 December 2 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R837.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1992 December 10 - .
  • Mihonoseki Meteor Fall (Fell Through Roof of A House In Japan) - . Nation: Japan.

1992 December 16 - . 02:09 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R838.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1992 December 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R839.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1992 December 31 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R840.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1993 January 6 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R841.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1993 January 20 - . 02:01 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R842.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1993 January 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R843.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1993 February 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R844.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1993 February 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R845.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1993 February 18 - . 07:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-16.
  • METS Ionosphere / active plasma mission - . Nation: Japan. Agency: ISAS. Apogee: 272 km (169 mi).

1993 February 20 - . 02:20 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-7.
  • Asuka - . Payload: Astro D. Mass: 420 kg (920 lb). Nation: Japan. Agency: ISAS. Program: Astro. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Astro. Decay Date: 2001-03-02 . USAF Sat Cat: 22521 . COSPAR: 1993-011A. Apogee: 646 km (401 mi). Perigee: 539 km (334 mi). Inclination: 31.1000 deg. Period: 96.50 min. Summary: X-ray imaging and astronomy. Imaging and spectroscopic observations of various astronomical objects (stars and galaxies) in the X-ray band. Launching organization ISAS. Launch time 0200 GMT. Astro-D 'ASCA'..

1993 February 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R846.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1993 March 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R847.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1993 March 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R848.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1993 March 24 - . 02:07 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R849.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1993 April 7 - . 02:07 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R850.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1993 April 21 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R851.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1993 April 28 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R852.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 58 km (36 mi).

1993 May 12 - . 02:02 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R853.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1993 May 19 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R854.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1993 May 26 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R855.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 59 km (36 mi).

1993 June 9 - . 02:26 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R856.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1993 June 16 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R857.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1993 June 30 - . 02:21 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R858.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1993 July 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R859.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1993 July 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R860.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1993 August 4 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R861.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1993 August 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R862.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1993 September 1 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R863.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1993 September 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R864.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 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).

1993 September 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R865.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1993 September 23 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-58.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 57 km (35 mi).

1993 September 24 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-59.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 56 km (34 mi).

1993 September 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R866.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1993 October 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R867.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1993 October 20 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R868.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1993 October 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R869.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1993 November 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R870.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1993 November 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R871.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1993 December 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R872.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1993 December 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R873.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1993 December 15 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R874.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1993 December 22 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R875.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1994 January 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R876.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 49 km (30 mi).

1994 January 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R877.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 50 km (31 mi).

1994 January 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R878.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 February 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R879.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 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 February 15 - . 23:52 GMT - . Launch Site: Andoya. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-22.
  • NNP / AIR / NID / NEL Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 192 km (119 mi).

1994 February 16 - . 02:07 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R880.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 March 2 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R881.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 March 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R882.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 March 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R883.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 March 24 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R884.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 March 30 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R885.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 April 13 - . 02:28 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R886.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 April 20 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R887.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 April 27 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R888.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 May 11 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R889.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 May 25 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R890.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 June 8 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R891.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 June 15 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R892.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 June 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R893.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 July 8 - . 23:05 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44L. LV Configuration: Ariane 44L V65.
  • Yuri 3N - . Payload: BS-3N. Mass: 1,210 kg (2,660 lb). Nation: Japan. Agency: NHK. Manufacturer: Lockheed. Program: BS. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 3000. USAF Sat Cat: 23176 . COSPAR: 1994-040B. Apogee: 35,797 km (22,243 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.0500 deg. Period: 1,436.15 min. Summary: Stationed at 109.67 deg E. Positioned in geosynchronous orbit at 109 deg E in 1994-1999 As of 5 September 2001 located at 109.71 deg E drifting at 0.013 deg W per day. As of 2007 Mar 11 located at 109.92E drifting at 0.008W degrees per day..

1994 July 13 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R894.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 July 20 - . 02:08 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R895.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 August 3 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R896.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 August 17 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R897.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 August 24 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R898.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

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..

1994 September 6 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-60.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 56 km (34 mi).

1994 September 7 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-61.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 56 km (34 mi).

1994 September 8 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R899.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 September 15 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-62.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 55 km (34 mi).

1994 September 16 - . 04:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K?. LV Family: SB-735. Launch Vehicle: ST-735. LV Configuration: ST-735 ST-735-2.
  • FIH test - . Nation: Japan. Agency: ISAS. Apogee: 118 km (73 mi).

1994 September 18 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-63.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 53 km (32 mi).

1994 September 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R900.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 September 28 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R901.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 October 5 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R902.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 October 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R903.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 October 19 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R904.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 October 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R905.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 November 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R906.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 November 16 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R907.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 November 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R908.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 November 24 - . 10:20 GMT - . Launch Site: Andoya. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-23.
  • NNP / AIR / NID / NEL Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 200 km (120 mi).

1994 December 1 - . 21:39 GMT - . Launch Site: Andoya. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-21.
  • Auroral mission - . Nation: Japan. Agency: ISAS. Apogee: 344 km (213 mi).

1994 December 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R909.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 December 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R910.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 December 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R911.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1994 December 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R912.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 January 12 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R913.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 January 15 - . 13:45 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M. Launch Pad: M1. LV Family: Mu. Launch Vehicle: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-8. FAILURE: Failure of second stage attitude control system.. Failed Stage: 2.
  • Express 1 - . Nation: Japan. Agency: ISAS. Class: Materials. Type: Materials science satellite. Spacecraft: Express 1. Decay Date: 1995-01-15 . COSPAR: F950115A. At first thought not to have reached orbit. Later the re-entry vehicle was discovered in Ghana having reentered and deployed its parachute on January 15. At T+103 sec, during the second stage burn, the vehicle veered off course. The payload service module entered a 110 x 250 km x 33 degree orbit, instead of the intended 270 x 380 km and re-entered on its second orbit. The re-entry capsule was found later in Ghana. A failure of the second stage attitude control system was blamed, although it was considered likely that the payload was too heavy for the vehicle, being twice the mass of earlier MU-3S payloads.

1995 January 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R914.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 January 23 - . 12:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-17.
  • Submillimeter radio astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 346 km (214 mi).

1995 January 25 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R915.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 January 28 - . 16:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-19.
  • Extreme ultraviolet Telescopes Extreme ultraviolet astronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 330 km (200 mi).

1995 February 9 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R916.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 February 15 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R917.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 February 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R918.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 March 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R919.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

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 March 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R920.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 March 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R921.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 April 26 - . 02:20 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R922.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 May 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R923.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 May 17 - . 02:08 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R924.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 May 24 - . 02:17 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R925.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 May 31 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R926.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 June 7 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R927.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 June 21 - . 02:07 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R928.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 June 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R929.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 July 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R930.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 July 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R931.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 July 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R932.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 August 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R933.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 August 9 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R934.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 August 23 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R935.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

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).

1995 August 29 - . 00:53 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36B. LV Family: Atlas. Launch Vehicle: Atlas IIAS. LV Configuration: Atlas IIAS AC-117.
  • JCSAT 3 - . Mass: 1,841 kg (4,058 lb). Nation: Japan. Agency: JSAT. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 23649 . COSPAR: 1995-043A. Apogee: 35,794 km (22,241 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.0000 deg. Period: 1,436.20 min. 8 transponders for digital TV. Stationed at 128.1 deg E. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 128 deg E in 1995-1999 As of 5 September 2001 located at 128.05 deg E drifting at 0.005 deg E per day. As of 2007 Feb 20 located at 126.99E drifting at 0.144W degrees per day.

1995 August 29 - . 06:41 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44P. LV Configuration: Ariane 44P-3 V77.
  • N-Star a - . Mass: 3,100 kg (6,800 lb). Nation: Japan. Agency: NTT. Program: N-STAR. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 23651 . COSPAR: 1995-044A. Apogee: 35,791 km (22,239 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Summary: Stationed at 131.9 deg E. Positioned in geosynchronous orbit at 132 deg E in 1995-1999 As of 1 September 2001 located at 131.99 deg E drifting at 0.017 deg W per day. As of 2007 Mar 11 located at 25.96E drifting at 4.123W degrees per day..

1995 September 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R936.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 September 17 - . 07:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-20. FAILURE: Failure.
  • Lunar Penetrator test technology mission - . Nation: Japan. Agency: ISAS. Apogee: 1.00 km (0.60 mi).

1995 September 20 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R937.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 October 4 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R938.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 October 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R939.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 October 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R940.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 October 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R941.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 November 9 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R942.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 November 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R943.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 November 22 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R944.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 November 29 - . 02:05 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R945.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 mi).

1995 December 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R946.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1995 December 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R947.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1995 December 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R948.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1996 January 11 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R949.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1996 January 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R950.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1996 January 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R951.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1996 January 31 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R952.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1996 February 5 - . 07:19 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44P. LV Configuration: Ariane 44P-3 V83.
  • N-STAR b - . Mass: 3,400 kg (7,400 lb). Nation: Japan. Agency: NTT. Program: N-STAR. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 23781 . COSPAR: 1996-007A. Apogee: 35,801 km (22,245 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.1000 deg. Period: 1,436.20 min. Summary: Geostationary at 128.9E. Positioned in geosynchronous orbit at 136 deg E in 1996-1999 As of 1 September 2001 located at 136.01 deg E drifting at 0.012 deg W per day. As of 2007 Mar 9 located at 136.04E drifting at 0.012W degrees per day..

1996 February 11 - . 11:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-24.
  • NTV-1 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 199 km (123 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 February 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P-R953.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 60 km (37 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 August 20 - . 15:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-26.
  • SEEK-1 Plasma mission - . Nation: Japan. Agency: ISAS. Apogee: 177 km (109 mi).

1996 August 26 - . 14:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-25.
  • SEEK-1 Plasma mission - . Nation: Japan. Agency: ISAS. Apogee: 180 km (110 mi).

1996 September 15 - . 02:30 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-64.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 56 km (34 mi).

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).

1996 December 4 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1996 December 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1996 December 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1996 December 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1997 January 8 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1997 January 13 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-65.
  • NNP-O3 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 55 km (34 mi).

1997 January 14 - . 12:00 GMT - . Launch Site: Kagoshima. LV Family: Viper. Launch Vehicle: Viper 3A.
  • Chaff Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 100 km (60 mi).

1997 January 14 - . 13:15 GMT - . Launch Site: Kagoshima. LV Family: Viper. Launch Vehicle: Viper 3A.
  • Chaff Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 100 km (60 mi).

1997 January 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1997 January 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1997 January 29 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1997 January 30 - . 07:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-18.
  • Lunar Penetrator test technology mission - . Nation: Japan. Agency: ISAS. Apogee: 309 km (192 mi).

1997 February 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1997 February 12 - . 04:50 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M-V. LV Family: M-V. Launch Vehicle: M-V. LV Configuration: M-V M-V-1.
  • Haruka - . Payload: MUSES B. Nation: Japan. Agency: ISAS. Manufacturer: NEC. Program: Muses. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: Haruka. USAF Sat Cat: 24720 . COSPAR: 1997-005A. Apogee: 21,415 km (13,306 mi). Perigee: 569 km (353 mi). Inclination: 31.4000 deg. Period: 379.30 min.

1997 February 17 - . 01:42 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36B. LV Family: Atlas. Launch Vehicle: Atlas IIAS. LV Configuration: Atlas IIAS AC-127.
  • JCSAT 4 - . Nation: Japan. Agency: JSAT. Manufacturer: El Segundo. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 24732 . COSPAR: 1997-007A. Apogee: 35,793 km (22,240 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 150.0E Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 150 deg E in 1997-1998; 124 deg E in 1998-1999; 127 deg E in 1999. As of 5 September 2001 located at 127.02 deg E drifting at 0.015 deg W per day. As of 2007 Mar 7 located at 150.01E drifting at 0.008W degrees per day.

1997 February 19 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1997 March 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1997 March 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1997 March 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1997 April 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1997 April 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1997 April 16 - . 23:08 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44LP. LV Configuration: Ariane 44LP V95.
  • BSAT 1a - . Nation: Japan. Agency: BSAT. Manufacturer: El Segundo. Program: BSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 24769 . COSPAR: 1997-016B. Apogee: 35,787 km (22,236 mi). Perigee: 35,786 km (22,236 mi). Inclination: 0.0000 deg. Period: 1,436.20 min. Summary: Geosynchronous. Stationed over 110.0E Positioned in geosynchronous orbit at 110 deg E in 1997-1999 As of 4 September 2001 located at 109.56 deg E drifting at 0.018 deg W per day. As of 2007 Mar 10 located at 109.63E drifting at 0.008W degrees per day..

1997 April 30 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1997 May 22 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1997 May 28 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1997 June 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1997 June 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1997 June 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1997 June 30 - .
  • ADEOS spacecraft fails - . Nation: Japan. Spacecraft: ADEOS. Summary: The polar orbiting ADEOS spacecraft performed Earth, atmospheric, and oceanographic remote sensing. Initially put on August 20 1996 into a wrong orbit, it achieved an acceptable orbit in September 1996..

1997 July 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1997 July 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1997 July 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1997 July 28 - . 01:15 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36B. LV Family: Atlas. Launch Vehicle: Atlas IIAS. LV Configuration: Atlas IIAS AC-133.
  • Superbird C - . Nation: Japan. Agency: SCC. Manufacturer: El Segundo. Program: Superbird. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 24880 . COSPAR: 1997-036A. Apogee: 35,793 km (22,240 mi). Perigee: 35,780 km (22,230 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Geosynchronous. Stationed over 144.0E Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 144 deg E in 1997-1999 As of 5 September 2001 located at 144.00 deg E drifting at 0.014 deg W per day. As of 2007 Mar 9 located at 143.94E drifting at 0.009W degrees per day.

1997 August 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1997 August 13 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1997 August 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1997 September 8 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-66.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 50 km (31 mi).

1997 September 9 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-67.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 52 km (32 mi).

1997 September 10 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1997 September 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 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 October 1 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1997 October 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1997 October 22 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1997 November 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1997 November 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1997 November 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 42 km (26 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-6F.
  • 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.
  • 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..

1997 December 2 - . 22:52 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44P. LV Configuration: Ariane 44P-3 V103.
  • JCSAT 5 - . Nation: Japan. Agency: JSAT. Manufacturer: El Segundo. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 25067 . COSPAR: 1997-075A. Apogee: 35,790 km (22,230 mi). Perigee: 35,784 km (22,235 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Summary: Geosynchronous. Stationed over 139.4E Positioned in geosynchronous orbit at 150 deg E in 1998-1999 As of 4 September 2001 located at 150.00 deg E drifting at 0.012 deg W per day. As of 2007 Mar 8 located at 127.98E drifting at 0.014W degrees per day..

1997 December 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1997 December 10 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1997 December 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1997 December 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1998 January 8 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1998 January 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1998 January 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1998 January 25 - . 08:35 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-27.
  • SEEK Ozone Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 183 km (113 mi).

1998 January 31 - . 04:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520-22.
  • SOLAR-B XDT Solar x-ray / ultraviolet mission - . Nation: Japan. Agency: ISAS. Apogee: 270 km (160 mi).

1998 February 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1998 February 5 - . 08:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: SS-520. LV Configuration: SS-520 SS-520-1.
  • ENA / EPS / LAP Test / plasma mission - . Nation: Japan. Agency: ISAS. Apogee: 750 km (460 mi).

1998 February 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1998 February 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

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 March 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1998 March 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1998 March 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1998 April 8 - . 02:07 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1998 April 16 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1998 April 28 - . 22:53 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44P. LV Configuration: Ariane 44P V108.
  • BSAT 1B - . Nation: Japan. Agency: BSAT. Manufacturer: El Segundo. Program: BSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 376. USAF Sat Cat: 25312 . COSPAR: 1998-024B. Apogee: 35,788 km (22,237 mi). Perigee: 35,787 km (22,236 mi). Inclination: 0.0000 deg. Period: 1,436.20 min. Summary: Geostationary at 109.9 degrees E. Positioned in geosynchronous orbit at 110 deg E in 1998-1999 As of 5 September 2001 located at 109.63 deg E drifting at 0.019 deg W per day. As of 2007 Mar 10 located at 109.75E drifting at 0.009W degrees per day..

1998 April 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1998 May 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

1998 May 27 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1998 June 11 - . 02:04 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1998 June 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1998 June 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1998 July 3 - . 18:12 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M-V. LV Family: M-V. Launch Vehicle: M-V. LV Configuration: M-V M-V-3.
  • Nozomi - . Mass: 258 kg (568 lb). Nation: Japan. Agency: ISAS. Manufacturer: NEC. Class: Mars. Type: Mars probe. Spacecraft: Nozomi. USAF Sat Cat: 25383 . COSPAR: 1998-041A. Apogee: 489,381 km (304,086 mi). Perigee: 703 km (436 mi). Inclination: 27.3000 deg. Period: 20,910.00 min. Originally known as Planet-B; renamed Nozomi ('Hope') after launch. The third stage and payload entered a 146 x 417 km x 31.1 deg parking orbit. The KM-V1 kick (fourth) stage then fired to place the spacecraft into a circumlunar 359 x 401491 km x 28.6 deg orbit. Nozomi made multiple lunar and Earth gravity assist passes to increase its energy for solar orbit insertion and the cruise to Mars.. The spacecraft used a lunar swingby on 24 September and another on 18 December 1998 to increase the apogee of its orbit. It swung by Earth on 20 December at a perigee of about 1000 km. The gravitational assist from the swingby coupled with a 7 minute burn of the bipropellant engine put Nozomi into an escape trajectory towards Mars. It was scheduled to arrive at Mars on 11 October 1999 at 7:45:14 GMT, but the Earth swingby left the spacecraft with insufficient acceleration and two course correction burns on 21 December used more propellant than planned, leaving the spacecraft short of fuel. The new plan is for Nozomi to remain in heliocentric orbit for an additional four years and encounter Mars at a slower relative velocity in December 2003.

1998 July 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1998 July 15 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1998 July 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1998 August 5 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

1998 August 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1998 August 31 - .
  • North Korea fires missile across Japan - . Nation: Japan.

1998 September 7 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-68.
  • Ozone Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 57 km (35 mi).

1998 September 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1998 September 9 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-69.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 57 km (35 mi).

1998 September 17 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1998 September 23 - . 02:03 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1998 October 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

1998 October 14 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1998 October 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1998 November 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

1998 November 11 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

1998 November 18 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

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).

1998 December 2 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

1998 December 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

1999 February 2 - . 01:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-28.
  • SELENE RF / X-ray test Ionosphere / x-ray mission - . Nation: Japan. Agency: ISAS. Apogee: 184 km (114 mi).

1999 February 16 - . 01:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. Launch Pad: SLC36A. LV Family: Atlas. Launch Vehicle: Atlas IIAS. LV Configuration: Atlas IIAS AC-152.
  • JCSAT-6 - . Mass: 2,900 kg (6,300 lb). Nation: Japan. Agency: JSAT. Manufacturer: El Segundo. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 25630 . COSPAR: 1999-006A. Apogee: 35,791 km (22,239 mi). Perigee: 35,784 km (22,235 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. JCSAT-6 carried a Ku-band relay system. It was operated by Japan Satellite Systems, Inc., Tokyo, provided communications and data relay for Japan and the Pacific Rim. Two burns of the Centaur upper stage placed it into a supersynchronous transfer orbit of 258 km x 96736 km x 24.1 degrees. JCSAT-6's on-board R-4D engine would maneuver it into its final geostationary location. Dry mass of the spacecraft was 1230 kg. Stationed at 124 deg E Positioned in geosynchronous orbit at 123 deg E in 1999. As of 5 September 2001 located at 124.00 deg E drifting at 0.014 deg W per day. As of 2007 Mar 10 located at 124.01E drifting at 0.011W degrees per day.

1999 September 7 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-70.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 55 km (34 mi).

1999 September 11 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-71.
  • Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 55 km (34 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.

2000 January 9 - . 20:50 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-29.
  • WAVE2000 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 179 km (111 mi).

2000 January 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

2000 January 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

2000 January 26 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

2000 February 9 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 57 km (35 mi).

2000 February 10 - . 01:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M-V. LV Family: M-V. Launch Vehicle: M-V. LV Configuration: M-V M-V-4. FAILURE: First stage failure. An anomalous vibration was detected 25 seconds after launch. At 41 seconds ceramic heat shields in the first stage nozzle broke and fell off, and thrust vector control on the nozzle was lost.. Failed Stage: 1.
  • Astro E - . Mass: 1,680 kg (3,700 lb). Nation: Japan. Agency: ISAS. Program: Astro. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: ASTRO E. COSPAR: F000210A. Apogee: 200 km (120 mi). Spacecraft was injected in very low perigee orbit and reentered. X-ray astronomy satellite. Stage 1 lost control, and separated with the rocket off-course at 75 seconds in the flight. Stage 2 burned correctly and separated at 218 seconds, followed by the third stage burn at 621 seconds. Last signals were received at 20 minutes after launch. ASTRO-E was to have separated from the third stage at 23 minutes, but ended in an orbit with a perigee of only 80 km and an apogee of 410 km. It probably reentered on the first orbit at around 0230 - 0300 GMT somewhere between East Africa and western China.

2000 February 18 - . 01:04 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44LP. LV Configuration: Ariane 44LP-3 V127.
  • Superbird 4 - . Mass: 4,057 kg (8,944 lb). Nation: Japan. Agency: SCC. Manufacturer: El Segundo. Program: Superbird. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 26095 . COSPAR: 2000-012A. Apogee: 35,796 km (22,242 mi). Perigee: 35,777 km (22,230 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Provided geosynchronous communications services for the Space Communications Corporation of Japan. Carried 23 Ku-band and 6 Ka-band transponders, and was equipped with a Marquardt R4D apogee engine and XIPS ion propulsion stationkeeping system. Stationed at 162 deg E. Positioned in geosynchronous orbit at 162 deg E in 2000. As of 4 September 2001 located at 162.01 deg E drifting at 0.003 deg W per day. As of 2007 Mar 9 located at 161.98E drifting at 0.004W degrees per day.

2000 February 24 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

2000 March 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

2000 April 12 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

2000 April 19 - . 02:10 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

2000 May 25 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

2000 May 31 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

2000 June 21 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 56 km (34 mi).

2000 June 29 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

2000 July 6 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

2000 July 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

2000 August 3 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 50 km (31 mi).

2000 August 23 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

2000 September 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

2000 September 18 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-72.
  • Ozone Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 55 km (34 mi).

2000 September 19 - . 02:00 GMT - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135-73.
  • Ozone Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 53 km (32 mi).

2000 September 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 54 km (33 mi).

2000 October 4 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 55 km (34 mi).

2000 October 6 - . 23:00 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 42L. LV Configuration: Ariane 42L-3 V133.
  • N-SAT-110 - . Mass: 3,531 kg (7,784 lb). Nation: Japan. Agency: SCC. Manufacturer: Lockheed. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 26559 . COSPAR: 2000-060A. Apogee: 35,792 km (22,240 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. N-SAT-110, also known as Superbird 5, was jointly owned by SCC (Space Communications Corporation of Tokyo) and JSat (Japan Satellite Systems). SCC controlled the vehicle on orbit. The satellite carried 24 Ku-band transponders. By October 15 N-SAT-110 was in a 35610 x 35752 km x 0.1 deg orbit drifting past 109 deg E. Stationed at 110 deg E. Positioned in geosynchronous orbit at 110 deg E in 2000. As of 4 September 2001 located at 110.06 deg E drifting at 0.012 deg W per day. As of 2007 Mar 11 located at 110.07E drifting at 0.007W degrees per day.

2000 October 19 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 51 km (31 mi).

2000 November 1 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

2000 November 15 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

2000 November 22 - . 02:15 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

2000 November 29 - .
  • Discovery of Y000593 Meteorite (Mars Meteorite) - . Nation: Japan.

2000 December 3 - .
  • Discovery of Y000749 Meteorite (Mars Meteorite) - . Nation: Japan.

2000 December 4 - . 09:16 GMT - . Launch Site: SvalRak. LV Family: S. Launch Vehicle: SS-520. LV Configuration: SS-520 SS-520-2.
  • Ionosphere mission - . Nation: Japan. Agency: ISAS. Apogee: 1,108 km (688 mi).

2000 December 7 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 53 km (32 mi).

2000 December 20 - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G. LV Configuration: Ariane 5G V138 508.
  • LDREX - . Mass: 1,414 kg (3,117 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: LDREX. Decay Date: 2010-03-21 . USAF Sat Cat: 26640 . COSPAR: 2000-081C. Apogee: 30,257 km (18,800 mi). Perigee: 241 km (149 mi). Inclination: 2.4000 deg. Period: 527.50 min. Ariane V138's EPS upper stage carried an ASAP5 small payload attachment ring with a special camera system and the LDREX experimental antenna for Japan's NASDA space agency. LDREX (Large-scale Deployable Reflector EXperiment) was a 6-m diameter antenna which was to have deployed 40 minutes after launch, to test the deployment mechanism for the larger antenna to be used on the ETS-8 satellite. After the test the antenna was to have been jettisoned. However the experiment failed and no deployment or jettison took place.

2000 December 20 - . 02:00 GMT - . Launch Site: Ryori. LV Family: MT-135. Launch Vehicle: MT-135P.
  • Meteorological mission - . Nation: Japan. Agency: JMA. Apogee: 52 km (32 mi).

2001 March 8 - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G. LV Configuration: Ariane 5G V140 509.
  • BSAT-2a - . Mass: 3,050 kg (6,720 lb). Nation: Japan. Agency: BSAT. Manufacturer: Cannes. Program: BSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: Star bus. USAF Sat Cat: 26720 . COSPAR: 2001-011B. Apogee: 35,807 km (22,249 mi). Perigee: 35,764 km (22,222 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. BSAT-2a was a Japanese geosynchronous communications spacecraft and the second Orbital STAR-class television broadcasting satellite. Its launch mass was 1317 kg; dry mass was 535 kg. The satellite had a Thiokol Star 30CBP solid apogee motor. The new BSTAR STAR-class satellites are a new design replacing the earlier Starbus type satellite of which only one (Cakrawarta 1) was launched. BSAT Corp. (Broadcasting Satellite System Corp.) earlier launched HS-376 satellites BSAT 1a and 1b, replacing the government's BS series which began Japanese direct broadcast services in 1978. The satellite was to be parked over 110 deg-E longitude to provide direct-to-home voice, video and internet communications. Positioned in geosynchronous orbit at 110 deg E in 2001 As of 5 September 2001 located at 109.82 deg E drifting at 0.018 deg W per day. As of 2007 Mar 11 located at 109.92E drifting at 0.009W degrees per day.

2001 March 21 - . Launch Site: Kagoshima. LV Family: MT-135. Launch Vehicle: MT-135. LV Configuration: MT-135 R1119.
  • Last flight Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 55 km (34 mi). The Japan Meteorological Agency launched the 1119th MT-135P meteorological sounding rocket from the meteorological observation station in Sanriku-cho, Iwate-ken. This was the final launch of the type. The MT-135P had served for more than thirty years gathering meteorological data in the upper atmosphere since the first launching on July 15, 1970. IHI Aerospace Co., Ltd. has been responsible for design, development and manufacture of the MT-135P.

2001 July 12 - . 21:58 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G. LV Configuration: Ariane 5G V142 510.
  • BSAT-2b - . Mass: 3,105 kg (6,845 lb). Nation: Japan. Agency: BSAT. Manufacturer: Alenia. Program: BSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: Star bus. USAF Sat Cat: 26864 . COSPAR: 2001-029B. Apogee: 17,400 km (10,800 mi). Perigee: 659 km (409 mi). Inclination: 2.9000 deg. Period: 317.20 min. BSAT-2b was planned as a geosynchronous television broadcast satellite for the Japanese B-SAT company. It used Orbital's Star 1 bus and had a launch mass of 1298 kg. It carried a Thiokol Star 30 solid apogee motor and a set of station-keeping thrusters with 200 kg of propellant. A propulsion problem in the final stage of rocket stranded the satellite at a much lower altitude than planned. Since BSAT 2B carried only a soild propellant apogee kick motor, it was unable to maneuver itself to a useful orbit.

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 February 6 - . 10:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-30.
  • NTV-2 Thermosphere Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 150 km (90 mi).

2002 March 29 - . 01:29 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA2. LV Family: Ariane. Launch Vehicle: Ariane 44L. LV Configuration: Ariane 44L V149.
  • JCSAT 8 - . Payload: JC-Sat 2A. Mass: 3,800 kg (8,300 lb). Nation: Japan. Agency: JSAT. Manufacturer: El Segundo. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 27400 . COSPAR: 2002-015B. Apogee: 35,802 km (22,246 mi). Perigee: 35,770 km (22,220 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Communications satellite. Launch delayed from mid-March. JCSAT 8 was a Boeing BSS-601 with a launch mass of 2600 kg and a dry mass around 1200 kg. It was to be used by Japan Satellite to replace JCSAT 2. As of 2007 Mar 10 located at 24.29E drifting at 0.020W degrees per day.

2002 April 10 - .
  • Yuji Hyakutake Dies At 51 - . Nation: Japan.

2002 July 5 - . 23:22 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G. LV Configuration: Ariane 5G s/n V153 "Ville de Charleroi".
  • NStar c - . Mass: 4,050 kg (8,920 lb). Nation: Japan. Agency: Stellat. Manufacturer: Cannes. Program: N-STAR. Class: Communications. Type: Civilian communications satellite. Spacecraft: Star bus. USAF Sat Cat: 27461 . COSPAR: 2002-035B. Apogee: 35,801 km (22,245 mi). Perigee: 35,772 km (22,227 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Launch delayed from late June. The N-Star c satellite was an S-band satellite for mobile telephone communications for NTT DoCoMo of Japan. N-Star c had a communications payload built by Lockheed Martin and used the Star 2 bus from Orbital. The small Star 2 satellite had a dry mass around 800 kg and was the first flight of a new Orbital hydrazine/nitrogen tetroxide liquid apogee propulsion system with a 500N thrust apogee engine developed by Japan's IHI. As of 2007 Mar 9 located at 135.92E drifting at 0.012W degrees per day.

2002 July 14 - . 01:34 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA1. LV Family: S. Launch Vehicle: NAL-735. FAILURE: Failure.
  • National Experimental Supersonic Transport NEXST-1 test - . Nation: Japan. Agency: NAL. Apogee: 0 km ( mi). Summary: The intention was that an 11.5-m-long, one tenth scale model of the aircraft would be propelled by the NAL-735 solid rocket booster to Mach 2 at 18 km altitude. Instead the vehicle lost stability and crashed near the launch point..

2002 August 3 - . 14:24 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-31.
  • SEEK-2 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 152 km (94 mi).

2002 August 3 - . 14:39 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-32.
  • SEEK-2 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 117 km (72 mi).

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..
  • 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
  • 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..

2002 December 20 - .
  • Nozomi, Earth Flyby - . Nation: Japan. Spacecraft: Nozomi.

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 May 9 - . Launch Site: Kagoshima. Launch Complex: Kagoshima M-V. LV Family: M-V. Launch Vehicle: M-V. LV Configuration: M-V-1 M-V-5.
  • Hayabusa - . Payload: MUSES-C. Mass: 500 kg (1,100 lb). Nation: Japan. Agency: ISAS. Class: Asteroids. Type: Asteroid probe. Spacecraft: Hayabusa. Decay Date: 2010-06-13 . USAF Sat Cat: 27809 . COSPAR: 2003-019A. Summary: Asteroid sample return probe launched toward asteroid 1998 SF36. Launch delayed from Nov. 24, 2002, then May 5, 2003..

2003 June 11 - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5G. LV Configuration: Ariane 5G V161.
  • BSAT-2c - . Payload: Star 1. Mass: 1,298 kg (2,861 lb). Nation: Japan. Agency: BSAT. Manufacturer: OSC. Program: BSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: Star bus. USAF Sat Cat: 27831 . COSPAR: 2003-028B. Apogee: 35,802 km (22,246 mi). Perigee: 35,771 km (22,227 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: As of 2007 Mar 9 located at 155.98E drifting at 0.008W degrees per day..

2003 June 19 - .
  • Nozomi, Earth Flyby, Successful - . Nation: Japan. Spacecraft: Nozomi.

2003 June 30 - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot / Briz-KM.
  • CubeSat XI-IV - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Tokyo. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 27848 . COSPAR: 2003-031J. Apogee: 833 km (517 mi). Perigee: 818 km (508 mi). Inclination: 98.7000 deg. Period: 101.40 min. Summary: Cubesat XI carried technology tests for the University of Tokyo..
  • Cute-1 - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: TIT. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 27844 . COSPAR: 2003-031E. Apogee: 833 km (517 mi). Perigee: 817 km (507 mi). Inclination: 98.7000 deg. Period: 101.40 min. Summary: CUTE-I carried engineering test equipment and was built by the Tokyo Institute of Technology..

2003 October 30 - . 13:43 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot. LV Configuration: Rokot 4921921121.
  • Servis-1 - . Mass: 840 kg (1,850 lb). Nation: Japan. Agency: USEF. Class: Technology. Type: Navigation technology satellite. Spacecraft: SERVIS. USAF Sat Cat: 28060 . COSPAR: 2003-050A. Apogee: 1,016 km (631 mi). Perigee: 984 km (611 mi). Inclination: 99.5000 deg. Period: 105.10 min. The mission of the 'Space Environment Reliability Verification of Integrated System' was to flight test a range of commerical-grade spacecraft components including a computer, star tracker, battery, and laser gyro. The objective was to lower the cost of future satellites.

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.

2003 December 14 - .
  • Nozomi, Mars Flyby - . Nation: Japan. Spacecraft: Nozomi. The Japanese Mars probe, Nozomi, flew past the planet at a height of 1000 km. Attempts to operate the spacecraft's main propulsion system failed, and small thrusters were used to increase the flyby distance by about 100 km to ensure a clean miss. The mission was abandoned, and Nozomi entered a new orbit around the Sun.

2004 January 17 - . 15:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-33.
  • WAVE2004 Aeronomy mission - . Nation: Japan. Agency: ISAS. Apogee: 141 km (87 mi).

2004 March 13 - . 05:40 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36B. Launch Pad: SLC36B. LV Family: Atlas V. Launch Vehicle: Atlas IIIA. LV Configuration: Atlas 3A AC-202.
  • MBSAT - . Mass: 4,143 kg (9,133 lb). Nation: Japan. Agency: MBC. Manufacturer: Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300. USAF Sat Cat: 28184 . COSPAR: 2004-007A. Apogee: 35,795 km (22,241 mi). Perigee: 35,779 km (22,231 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Mobile S-band digital broadcasting services for home and automobile users in Japan. As of 2007 Mar 9 located at 144.03E drifting at 0.009W degrees per day..

2004 April 16 - . 00:45 GMT - . Launch Site: Cape Canaveral. Launch Complex: Cape Canaveral LC36A. Launch Pad: SLC36A. LV Family: Atlas. Launch Vehicle: Atlas IIAS. LV Configuration: Atlas IIAS AC-163.
  • Superbird 6 - . Nation: Japan. Agency: JSCC. Program: Superbird. Class: Communications. Type: Civilian communications satellite. Spacecraft: HS 601. USAF Sat Cat: 28218 . COSPAR: 2004-011A. Apogee: 35,797 km (22,243 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: The satellite was to provide Ka and Ku band communications for Japan's Space Communications Corporation..

2004 May 19 - .
  • Hayabusa (MUSES-C), Earth Gravity Assist, Successful - . Nation: Japan. Spacecraft: Hayabusa.

2004 August 9 - . 08:15 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-34.
  • Solar Sails Technology mission - . Nation: Japan. Agency: ISAS. Apogee: 170 km (100 mi).

2004 December 13 - . 00:33 GMT - . Launch Site: Andoya. Launch Complex: Andoya U3. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-35.
  • DELTA 2004 Aeronomy mission - . Nation: Japan. Agency: JAXA. Apogee: 140 km (80 mi).

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.

2005 July 10 - . 03:30 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M-V. LV Family: M-V. Launch Vehicle: M-V. LV Configuration: M-V-1 M-V-6.
  • Suzaku - . Payload: Astro E2. Mass: 1,680 kg (3,700 lb). Nation: Japan. Agency: JAXA. Manufacturer: Toshiba. Class: Astronomy. Type: X-ray astronomy satellite. Spacecraft: ASTRO E. USAF Sat Cat: 28773 . COSPAR: 2005-025A. Apogee: 573 km (356 mi). Perigee: 562 km (349 mi). Inclination: 31.4000 deg. Period: 96.00 min. Delayed from February, June 26, July 6 and 8, 2005. CUTE-1.7 nanosat mistakenly reported on this flight. Astro-E2 was renamed Suzaku (after a legendary red bird) after launch. It replaced the Astro-E, which never reached orbit due to an M-V-4 launch failure in 2000. The satellite had five 0.4-meter diameter X-ray telescopes, one with an XRS microcalorimeter and the other four with X-ray CCD cameras. However it was revealed that the XRS failed on 9 August due to leaking of helium coolant.

2005 August 23 - . 21:10 GMT - . Launch Site: Baikonur. Launch Complex: Baikonur LC109. Launch Pad: LC109/95. LV Family: R-36M. Launch Vehicle: Dnepr.
  • Kirari - . Mass: 570 kg (1,250 lb). Nation: Japan. Agency: JAXA. Manufacturer: Toshiba. Class: Technology. Type: Navigation technology satellite. Spacecraft: Kirari. USAF Sat Cat: 28809 . COSPAR: 2005-031A. Apogee: 614 km (381 mi). Perigee: 596 km (370 mi). Inclination: 97.8000 deg. Period: 96.80 min. Moved from J-1A . Delayed from August 15. Optical Inter-Orbit Communications Engineering Test Satellite. Its laser communications experiment was be used in with ESA's Artemis geostationary satellite. The satellite was renamed Kirari (twinkle) after launch.
  • Reimei - . Payload: Index. Mass: 60 kg (132 lb). Nation: Japan. Agency: JAXA. Manufacturer: Mitsubishi. Class: Technology. Type: Navigation technology satellite. Spacecraft: Reimei. USAF Sat Cat: 28810 . COSPAR: 2005-031B. Apogee: 650 km (400 mi). Perigee: 601 km (373 mi). Inclination: 97.8000 deg. Period: 97.20 min. Summary: Plasma Science Technology. INDEX, renamed Reimei ("Dawn") after launch, was a test satellite with new lightweight satellite components, and a demonstration auroral imager payload..

2005 September 12 - .
  • Hayabusa (MUSES-C), Asteroid 25143 Itokawa Arrival, Successful - . Nation: Japan. Spacecraft: Hayabusa.

2005 September 12 - .
  • Yohkoh Reenters Into Earth's Atmosphere - . Nation: Japan.

2005 October 9 - . 21:36 GMT - . Launch Site: Woomera. Launch Complex: Woomera LA1. LV Family: S. Launch Vehicle: NAL-735.
  • NEXST-1 F2 - . Nation: Japan. Agency: NAL. Apogee: 20 km (12 mi).

2005 October 27 - . 06:52 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC132/1. LV Family: Kosmos 3. Launch Vehicle: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 104.
  • Cubesat XI-V - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: Tokyo. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 28895 . COSPAR: 2005-043F. Apogee: 708 km (439 mi). Perigee: 682 km (423 mi). Inclination: 98.2000 deg. Period: 98.70 min. Summary: University of Tokyo cubesat. Released from SSETI Express..

2005 November 9 - .
  • Hayabusa releases target marker. - . Nation: Japan. Summary: Hayabusa released the first of three 10-cm target markers towards the surface of asteroid Itokawa. It missed the surface and floated off into deep space..

2005 November 12 - .
  • Hayabusa releases Minerva nano-lander. - . Nation: Japan. Hayabusa probe skimmed at an altitude of 55 m over asteroid Itokawa. The Minerva nano-lander was released, but missed the asteroid and floated out into deep space. Hayabusa was then moved to a safe position 5 km from the surface and the control team considered its next move.

2005 November 12 - .
  • Hayabusa, MINERVA Landing, Failed - . Nation: Japan. Spacecraft: Hayabusa.

2005 November 19 - .
  • Hayabusa lands on Itokawa. - . Nation: Japan. Hayabusa released the second target marker at 20:30 GMT and this marker stayed on the surface, arriving at 20:36. Hayabusa then homed on the target and bounced off the surface at 21:10, followed by a firm landing at 21:30. It stayed on the surface until 21:58 - it was uncertain whether the planned surface sample had been obtained. A safe-mode command sent it Hayabusa to a distance of 100 km from the asteroid as the team considered their next move.

2005 November 20 - .
  • Hayabusa (MUSES-C), first Asteroid 25143 Itokawa Sample Collection, Failed - . Nation: Japan. Spacecraft: Hayabusa.

2005 November 25 - .
  • Hayabusa (MUSES-C), second Asteroid 25143 Itokawa Sample Collection - . Nation: Japan. Spacecraft: Hayabusa.

2005 November 27 - .
  • Hayabusa returns to Itokawa. - . Nation: Japan. The spacecraft grazed the surface again at 22:07. However it was again uncertain if any surface material was obtained. Control of the spacecraft was lost again due to orientation jet failures which prevented the satellite from pointing its high gain antenna toward earth.

2005 December 1 - .
  • Hayabusa (MUSES-C), Asteroid 25143 Itokawa Departure - . Nation: Japan. Spacecraft: Hayabusa.

2006 January 22 - . 04:00 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-36.
  • Furoshiki Technology test - . Nation: Japan. Agency: JAXA. Apogee: 130 km (80 mi).

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 February 21 - . 21:28 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M-V. LV Family: M-V. Launch Vehicle: M-V. LV Configuration: M-V-1 M-V-8.
  • Astro F (Akari) - . Mass: 960 kg (2,110 lb). Nation: Japan. Agency: JAXA. Manufacturer: Toshiba. Program: Astro. Class: Astronomy. Type: Infrared astronomy satellite. Spacecraft: Akari. USAF Sat Cat: 28939 . COSPAR: 2006-005A. Apogee: 719 km (446 mi). Perigee: 705 km (438 mi). Inclination: 98.2000 deg. Period: 99.00 min. Summary: Carried a 0.67m-diameter liquid-helium-cooled infrared telescope with detectors ranging from the near infrared to 60 and 170 micron channels in the far IR. It was to carry out the first far infrared sky survey since IRAS in 1983..
  • Cute 1.7 - . Mass: 3.00 kg (6.60 lb). Nation: Japan. Agency: ISAS. Manufacturer: TIT. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cute. Decay Date: 2009-10-25 . USAF Sat Cat: 28941 . COSPAR: 2006-005C. Apogee: 685 km (425 mi). Perigee: 297 km (184 mi). Inclination: 98.2000 deg. Period: 94.40 min. Summary: Student subsatellite ejected from the M-V-8 third stage at 21:45 GMT..

2006 April 12 - . 23:30 GMT - . Launch Site: Kiritimati. Launch Pad: 0.0 N x 154.0 W. Launch Platform: ODYSSEY. LV Family: Zenit. Launch Vehicle: Zenit-3SL. LV Configuration: Zenit-3SL 21.
  • JCSAT 9 - . Payload: A2100AX. Mass: 4,401 kg (9,702 lb). Nation: Japan. Agency: JSAT. Manufacturer: Lockheed. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 29045 . COSPAR: 2006-010A. Apogee: 35,790 km (22,230 mi). Perigee: 35,785 km (22,235 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: As of 2007 Mar 8 located at 132.01E drifting at 0.014W degrees per day..

2006 August 11 - . 22:15 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA. LV Configuration: Ariane 5ECA V172 (531).
  • JCSAT 10 - . Payload: AS2100AX. Mass: 4,048 kg (8,924 lb). Nation: Japan. Agency: JSAT. Manufacturer: Lockheed. Program: JCSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 29272 . COSPAR: 2006-033A. Apogee: 35,793 km (22,240 mi). Perigee: 35,781 km (22,233 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Ku/C-band television broadcasting satellite for the Japanese market; mass 1858 kg dry. As of 2007 Mar 11 located at 128.01E drifting at 0.012W 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 September 22 - . 21:36 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima M-V. LV Family: M-V. Launch Vehicle: M-V. LV Configuration: M-V-1 M-V-7.
  • Hinode (Solar B) - . Mass: 870 kg (1,910 lb). Nation: Japan. Agency: JAXA. Manufacturer: Melco. Class: Astronomy. Type: Solar astronomy satellite. Spacecraft: Hinode. USAF Sat Cat: 29479 . COSPAR: 2006-041A. Apogee: 695 km (431 mi). Perigee: 674 km (418 mi). Inclination: 98.1000 deg. Period: 98.50 min. Summary: Solar satellite with a large optical telescope and an X-ray telescope built by the Smithsonian Observatory..
  • Hitsat - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Manufacturer: Hokkaido. Class: Technology. Type: Navigation technology satellite. Spacecraft: Hitsat. Decay Date: 2008-06-18 . USAF Sat Cat: 29484 . COSPAR: 2006-041F. Apogee: 659 km (409 mi). Perigee: 279 km (173 mi). Inclination: 98.3000 deg. Period: 94.00 min.
  • SSSat - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Agency: JAXA. Class: Technology. Type: Navigation technology satellite. Spacecraft: SSSat. Decay Date: 2008-06-18 . USAF Sat Cat: 29484 . COSPAR: 2006-041D. Apogee: 659 km (409 mi). Perigee: 279 km (173 mi). Inclination: 98.3000 deg. Period: 94.00 min. Summary: Solar sail experiment..

2006 October 13 - . 20:56 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA. LV Configuration: Ariane 5ECA V173 (533).
  • LDREX 2 - . Nation: Japan. Agency: JAXA. Class: Technology. Type: Navigation technology satellite. Spacecraft: LDREX. Decay Date: 2010-09-30 . USAF Sat Cat: 29496 . COSPAR: 2006-043C. Apogee: 26,980 km (16,760 mi). Perigee: 227 km (141 mi). Inclination: 7.2000 deg. Period: 468.50 min. Summary: LDREX-2 was attached to the upper stage. It deployed a 6.5-meter antenna design planned for the later ETS-8 satellite.

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 January 16 - . 02:20 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. Launch Pad: K. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310-37.
  • Ionosphere mission - . Nation: Japan. Agency: JAXA. Apogee: 130 km (80 mi).

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 August 14 - . 23:44 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA. LV Configuration: Ariane 5ECA V177 (537).
  • BSAT-3A - . Payload: A2100A. Mass: 1,967 kg (4,336 lb). Nation: Japan. Agency: BSAT. Manufacturer: Lockheed. Program: BSAT. Class: Communications. Type: Civilian communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 32019 . COSPAR: 2007-036B. Apogee: 35,826 km (22,261 mi). Perigee: 35,746 km (22,211 mi). Inclination: 0.1000 deg. Period: 1,436.00 min. Summary: Satllite launched for the Japan Broadcasting Satellite Systems Corp. (BSAT) with a Ku-band television payload. Mass 930 kg dry..

2007 September 2 - . 10:20 GMT - . Launch Site: Uchinoura. Launch Complex: Uchinoura LCK. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520 S-520-23.
  • WIND - . Nation: Japan. Agency: JAXA. Apogee: 300 km (180 mi).

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 6 - . 11:14 GMT - . Launch Site: Kagoshima. Launch Complex: Kagoshima L. LV Family: S. Launch Vehicle: S-310. LV Configuration: S-310 S-310-38.
  • VLF/Chaff - . Nation: Japan. Agency: JAXA. Apogee: 157 km (97 mi).

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.

2008 April 28 - . 03:53 GMT - . Launch Site: Sriharikota. LV Family: PSLV. Launch Vehicle: PSLV.
  • Cute-1.7-APD-II - . Mass: 4.00 kg (8.80 lb). Nation: Japan. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 32785 . COSPAR: 2008-021C. Apogee: 635 km (394 mi). Perigee: 615 km (382 mi). Inclination: 98.0000 deg. Period: 97.20 min. Summary: Tokyo Institute of Technology nanosat..
  • SEEDS 2 - . Nation: Japan. Agency: ISRO. Class: Technology. Type: Navigation technology satellite. Spacecraft: Cubesat. USAF Sat Cat: 32791 . COSPAR: 2008-021J. Apogee: 637 km (395 mi). Perigee: 614 km (381 mi). Inclination: 98.0000 deg. Period: 97.20 min. Summary: Nihon University at Tokyo nanosat..

2008 August 2 - . 08:30 GMT - . Launch Site: Uchinoura. Launch Complex: Uchinoura LCK. LV Family: S. Launch Vehicle: S-520. LV Configuration: S-520 S-520-24.
  • Microgravity - . Nation: Japan. Agency: JAXA. Apogee: 293 km (182 mi).

2008 August 14 - . 20:44 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA.
  • Superbird 7 - . Nation: Japan. Agency: Arianespace. Program: Superbird. Class: Communications. Type: Military communications satellite. Spacecraft: DS2000. USAF Sat Cat: 33274 . COSPAR: 2008-038A. Apogee: 35,804 km (22,247 mi). Perigee: 35,770 km (22,220 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Summary: Ku-band Mitsubishi Electric DS2000 class satellite for Japanese television broadcasting..

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.

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 June 2 - . 01:58 GMT - . Launch Site: Plesetsk. Launch Complex: Plesetsk LC133/3. LV Family: UR-100N. Launch Vehicle: Rokot.
  • Servis 2 - . Mass: 900 kg (1,980 lb). Nation: Japan. Agency: KVR. Class: Technology. Type: Technology satellite. Spacecraft: Servis. USAF Sat Cat: 36588 . COSPAR: 2010-023A. Apogee: 1,212 km (753 mi). Perigee: 1,185 km (736 mi). Inclination: 100.4000 deg. Period: 109.40 min. Summary: Space Environment Reliability Verification Integrated System to test usability of off-the-shelf commercial components in place of space-qualified hardware..

2010 August 30 - . 20:00 GMT - . Launch Site: Uchinoura. LV Family: S. Launch Vehicle: S-520.
  • S-520-25 - . Nation: Japan. Agency: JAXA. Apogee: 309 km (192 mi). T-REX Tether Technology Rocket Experiment. The 580 kg payload consisted of three parts: 'mother' and 'daughter' spacecraft connected by a 300-meter-long electrodynamic tether; and the small Tethered Space Robot connected to the daughter. Fell into Pacific Ocean after a ten-minute zero-G flight.

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.

2010 October 28 - . 21:51 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA.
  • Bsat 3B - . Payload: A2100A. Mass: 2,060 kg (4,540 lb). Nation: Japan. Program: BSAT. Class: Communications. Type: Communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 37207 . COSPAR: 2010-056B. Apogee: 35,801 km (22,245 mi). Perigee: 35,774 km (22,228 mi). Inclination: 0.1000 deg. Period: 1,436.10 min.

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 May 20 - . 20:38 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA.
  • ST-2 - . Mass: 5,090 kg (11,220 lb). Nation: Japan. Program: ST. Class: Communications. Type: Communications satellite. Spacecraft: DS2000. COSPAR: 2011-022B. Apogee: 35,793 km (22,240 mi). Perigee: 35,781 km (22,233 mi). Inclination: 0.0000 deg. Period: 1,436.10 min. Summary: Singapore-Taiwan 2 communications satellite with both C and Ku band transmitters..

2011 August 6 - . 22:52 GMT - . Launch Site: Kourou. Launch Complex: Kourou ELA3. LV Family: Ariane 5. Launch Vehicle: Ariane 5ECA.
  • BSAT-3C - . Payload: A2100A. Nation: Japan. Program: BSAT. Class: Communications. Type: Communications satellite. Spacecraft: AS 2100. USAF Sat Cat: 37776 . COSPAR: 2011-041B. Apogee: 35,791 km (22,239 mi). Perigee: 35,782 km (22,233 mi). Inclination: 0.1000 deg. Period: 1,436.10 min. Summary: Japan's Broadcast Satellite Systems Corporation communications satellite..

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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