Encyclopedia Astronautica
NASDA


Japanese agency overseeing development of rockets, spacecraft, and rocket engines. National Space Development Agency, Japan.

More... - Chronology...


Associated People
  • 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...
  • 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...

Associated Countries
Associated Spacecraft
  • 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...
  • Yuri Japanese communications technology satellite. One launch, 1978.04.07. Medium-scale broadcasting satellite for experimental purposes. 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...
  • 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...
  • 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...
  • SFU Japanese materials science satellite. One launch, 1995.03.18. Carried materials, astronomy, biological experiments; released and later retrieved by space shuttle. More...
  • ADEOS Japanese earth atmosphere satellite. 2 launches, 1996.08.17 (ADEOS) and 2002.12.14 (Adeos 2). The polar orbiting ADEOS spacecraft was to perform Earth, atmospheric, and oceanographic remote sensing. More...
  • TRMM American earth atmosphere satellite. One launch, 1997.11.27. TRMM was an international mission dedicated to measuring tropical and subtropical rainfall. More...
  • ETS-7 Japanese rendezvous technology satellite. One launch, 1997.11.27, Hikoboshi. Technology satellite, to accomplish remote automatic rendezvous and docking. More...
  • ETS-7 Target Japanese rendezvous technology satellite. One launch, 1997.11.27, Orihime. Attached to Hikoboshi. Docking target for ETS-7. More...
  • Kakehashi Japanese communications satellite. One launch, 1998.02.21. Name means 'Bridge', was called Communications and Broadcasting Experimental Test Satellite (COMETS) before launch. It contained Ka-band communications and inter-satellite data relay payloads. More...
  • 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...
  • MDS Japanese technology satellite. One launch, 2002.02.04. MDS (Mission Demonstration Satellite) was a technology demonstrator to flight-qualify commercial subsystems. 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...
  • 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...

Associated Engines
See also
  • Agency Agencies or institutions overseeing design, development, construction, or operation of space-related systems. More...

Associated Launch Vehicles
  • JCR Japanese sounding rocket. Single stage vehicle. More...
  • TT-500 Japanese sounding rocket. Small, half-meter diameter, two stage suborbital rocket used for tracking system and microgravity tests. 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...

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

Associated Stages
  • NAL-735-1 Solid propellant rocket stage. Loaded mass 4,700 kg. Thrust 250.00 kN. 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...

NASDA Chronology


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 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).

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

1977 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 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 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 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 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 24 - . 01:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima T. LV Family: MT-135. Launch Vehicle: MT-135P. LV Configuration: MT-135P T22.
  • Aeronomy mission - . Nation: Japan. Agency: NASDA. Apogee: 50 km (31 mi).

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

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

1986 August 12 - . 20:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-15(F).
  • EGS - . Payload: EGP. Mass: 685 kg (1,510 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Geodetic satellite. Spacecraft: EGS. USAF Sat Cat: 16908 . COSPAR: 1986-061A. Apogee: 1,497 km (930 mi). Perigee: 1,479 km (919 mi). Inclination: 50.0000 deg. Period: 115.70 min. Experimental Geophysical Payload; new launch vehicle test flight. EGS (Ajisai). Improvement of the accuracy of domestic geodetic triangulation network. Determination of accurate location of remote islands. Clarification of the relationship between Japanese geodetic system network and those of other areas of the world. L aunch vehicle H-I (two-stage) test flight no. 1. Launch time 2045 GMT. Launching organization NASDA.
  • MABES - . Payload: Jindai/LE-5. Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: MABES. USAF Sat Cat: 16910 . COSPAR: 1986-061C. Apogee: 1,604 km (996 mi). Perigee: 1,483 km (921 mi). Inclination: 50.0000 deg. Period: 117.00 min. Summary: MABES (Jindai). Experiment on the levitation of the magnetic bearing flywheel under zero-g condition. .

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

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

1988 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).

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

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

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

1990 February 7 - . 01:33 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Delta. Launch Vehicle: H-1. LV Configuration: H-1 H-21(F).
  • MOS-1b - . Payload: Momo 1B. Mass: 740 kg (1,630 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Sea satellite. Spacecraft: Marine Observation Satellite. USAF Sat Cat: 20478 . COSPAR: 1990-013A. Apogee: 909 km (564 mi). Perigee: 908 km (564 mi). Inclination: 99.1000 deg. Period: 103.20 min. Summary: Marine observation. Continuation of Earth observation functions of MOS-1; establishment of common technology necessary for Earth-observation satellites. Launching organization NASDA. Name MOS-1b 'Momo-1b'. Launch time 0133 UT..
  • 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..

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

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

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

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

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

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

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

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

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

1996 August 17 - . 01:53 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. LV Configuration: H-II H-II-4F.
  • ADEOS - . Nation: Japan. Agency: NASDA. Class: Earth. Type: Atmosphere satellite. Spacecraft: ADEOS. USAF Sat Cat: 24277 . COSPAR: 1996-046A. Apogee: 800 km (490 mi). Perigee: 799 km (496 mi). Inclination: 98.6000 deg. Period: 100.90 min.

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

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

1997 November 27 - . 21:27 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. LV Configuration: H-II-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..

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

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

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

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.

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

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

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

2002 December 14 - . 23:04 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202. LV Configuration: H-IIA 202 H-IIA-4F.
  • Adeos 2 - . Payload: Midori 2. Mass: 3,730 kg (8,220 lb). Nation: Japan. Agency: NASDA. Manufacturer: Mitsubishi. Class: Earth. Type: Earth resources satellite. Spacecraft: Adeos. USAF Sat Cat: 27597 . COSPAR: 2002-056A. Apogee: 806 km (500 mi). Perigee: 804 km (499 mi). Inclination: 98.7000 deg. Period: 101.00 min. Summary: Environment Monitoring, Aeronomy..
  • WEOS Kanta-Kun - . Mass: 50 kg (110 lb). Nation: Japan. Agency: NASDA. Manufacturer: Chiba. Class: Earth. Type: Earth resources satellite. Spacecraft: WEOS Kanta-Kun. USAF Sat Cat: 27600 . COSPAR: 2002-056D. Apogee: 804 km (499 mi). Perigee: 789 km (490 mi). Inclination: 98.7000 deg. Period: 100.80 min. Summary: Ecology..
  • Mu-Labsat - . Mass: 65 kg (143 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: Mu-Labsat. USAF Sat Cat: 27598 . COSPAR: 2002-056B. Apogee: 806 km (500 mi). Perigee: 793 km (492 mi). Inclination: 98.7000 deg. Period: 100.90 min. Technology. In 2003 the satellite released two tiny subsatellites in an experiment to test an onboard tracking imager for inspector satellites. The RITE (Remote Inspection Technology Experiment) targets are disks about 0.1m in diameter. They were released from Micro-LabSat on 2003 Mar 14 at 0140 UTC and 2003 May 14 at 0150 UTC

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

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

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