Tanegashima Credit - © Mark Wade

Japan's main launch site for he larger N and H launch vehicles. In use for sounding rockets from 1967 and orbital launches from 1975.

• Name: N Launch Complex. Latitude: 30.3958 N. Longitude: 130.9728 E. Launch Pads: 1. H-1, J-1, N, N-2.

• Name: Q Launch Complex. Latitude: 30.3943 N. Longitude: 130.9713 E. Launch Pads: 1. ETV.

• Name: Takesaki Launch Site. Latitude: 30.3736 N. Longitude: 130.9655 E. Launch Pads: 1. JCR, LS-C, MT-135, NAL, S, SA-II, TR-1, TT-200, TT-500.

• Name: Yoshinobu Launch Complex. Latitude: 30.3972 N. Longitude: 130.9797 E. Launch Pads: 1. H-2, H-2A.

Tanegashima Credit - © Mark Wade

• 1967 - Test mission Launch Vehicle: NAL. NAL-16 NAL-16TR LC: T. Apogee: 45 km (27 mi).

• 1968 September 17 07:10 - Test mission Launch Vehicle: SA-II. SA-II SA-II A9 LC: T. Apogee: 20 km (12 mi).

• 1968 September 19 01:58 - Test mission Launch Vehicle: LS-C. LS-C LS-C-D LC: T. Apogee: 100 km (60 mi).

• 1968 September 19 07:01 - Test mission Launch Vehicle: NAL. NAL-16 NAL-16H F1 LC: T. Apogee: 100 km (60 mi).

• 1969 January 30 01:31 - Test mission Launch Vehicle: NAL. NAL-16 NAL-16 31D LC: T. Apogee: 50 km (31 mi).

• 1969 February 1 01:40 - Test mission Launch Vehicle: NAL. NAL-25 NAL-25 31 LC: T. Apogee: 50 km (31 mi).

• 1969 February 6 06:31 - Test mission Launch Vehicle: LS-C. LS-C LS-C-1 LC: T. Apogee: 100 km (60 mi).

• 1969 February 7 06:30 - Test mission Launch Vehicle: S. S-C SC-3 LC: T. Apogee: 85 km (52 mi).

• 1969 February 8 06:30 - Test mission Launch Vehicle: S. S-C SC-1 LC: T. Apogee: 85 km (52 mi).

• 1969 February 8 01:30 - Test mission Launch Vehicle: S. S-C SC-4 LC: T. Apogee: 85 km (52 mi).

• 1969 September 9 06:30 - Test mission Launch Vehicle: S. S-B SB-III F11 LC: T. Apogee: 75 km (46 mi).

• 1969 September 10 06:30 - Test mission Launch Vehicle: LS-C. LS-C LS-C-2 LC: T. Apogee: 100 km (60 mi).

• 1969 September 15 01:40 - Test mission Launch Vehicle: JCR. JCR JCR-1 LC: T. Apogee: 200 km (120 mi).

• 1969 September 16 06:40 - Test mission Launch Vehicle: JCR. JCR JCR-2 LC: T. Apogee: 200 km (120 mi).

• 1969 September 20 01:55 - Test mission Launch Vehicle: NAL. NAL-16 NAL-16H F2 LC: T. Apogee: 100 km (60 mi).

• 1969 September 20 06:30 - Test mission Launch Vehicle: NAL. NAL-7 NAL-7 F7 LC: T. Apogee: 20 km (12 mi).

• 1970 February 1 01:00 - Test mission Launch Vehicle: JCR. JCR JCR-3 LC: T. Apogee: 200 km (120 mi).

• 1970 February 3 06:03 - Test mission Launch Vehicle: LS-C. LS-C LS-C-3 LC: T. Apogee: 100 km (60 mi).

• 1970 February 4 - Test mission Launch Vehicle: JCR. JCR JCR-4 LC: T. Apogee: 200 km (120 mi).

• 1970 September 7 06:30 - Test mission Launch Vehicle: NAL. NAL-7 NAL-7 BS9 LC: T. Apogee: 20 km (12 mi).

• 1970 September 9 06:40 - Test mission Launch Vehicle: LS-C. LS-C LS-C-4 LC: T. Apogee: 100 km (60 mi).

• 1971 February 1 01:30 - Test mission Launch Vehicle: JCR. JCR JCR-5 LC: T. Apogee: 200 km (120 mi).

• 1971 February 3 01:35 - Test mission Launch Vehicle: S. S-B SB-III A12 LC: T. Apogee: 75 km (46 mi).

• 1971 February 3 06:30 - Test mission Launch Vehicle: S. S-B SB-III A13 LC: T. Apogee: 75 km (46 mi).

• 1971 September 6 01:35 - Test mission Launch Vehicle: S. S-B SB-III A14 LC: T. Apogee: 75 km (46 mi).

• 1971 September 10 06:47 - Test mission Launch Vehicle: LS-C. LS-C LS-C-5 LC: T. Apogee: 100 km (60 mi).

• 1971 September 11 01:45 - Test mission Launch Vehicle: S. S-B SB-III A15 LC: T. Apogee: 75 km (46 mi).

• 1971 September 17 06:40 - Test mission Launch Vehicle: JCR. JCR JCR-6 LC: T. Apogee: 200 km (120 mi).

• 1972 February 2 06:56 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T1 LC: T. Apogee: 50 km (31 mi).

• 1972 February 6 06:35 - Test mission Launch Vehicle: JCR. JCR JCR-7 LC: T. Apogee: 200 km (120 mi).

• 1972 February 7 06:45 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T2 LC: T. Apogee: 50 km (31 mi).

• 1972 August 30 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T3 LC: T. Apogee: 50 km (31 mi).

• 1972 August 30 06:15 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T4 LC: T. Apogee: 50 km (31 mi).

• 1972 September 25 06:05 - Test mission Launch Vehicle: LS-C. LS-C LS-C-6 LC: T. Apogee: 100 km (60 mi).

• 1973 February 5 01:52 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T5 LC: T. Apogee: 50 km (31 mi).

• 1973 February 7 01:50 - Test mission Launch Vehicle: JCR. JCR JCR-8 LC: T. Apogee: 200 km (120 mi).

• 1973 February 8 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T6 LC: T. Apogee: 50 km (31 mi).

• 1973 September 5 06:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T8 LC: T. Apogee: 50 km (31 mi).

• 1973 September 5 01:57 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T7 LC: T. Apogee: 50 km (31 mi).

• 1973 September 7 01:40 - Test mission Launch Vehicle: JCR. JCR JCR-9 LC: T. Apogee: 200 km (120 mi).

• 1974 February 1 06:30 - Test mission Launch Vehicle: JCR. JCR JCR-10 LC: T. Apogee: 200 km (120 mi).

• 1974 February 2 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T9 LC: T. Apogee: 50 km (31 mi).

• 1974 February 9 06:30 - LE-3 test mission Launch Vehicle: LS-C. LS-C LS-C-7 LC: T. Apogee: 100 km (60 mi).

• 1974 February 10 06:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T10 LC: T. Apogee: 50 km (31 mi).

• 1974 September 2 06:00 - Test mission Launch Vehicle: ETV. ETV ETV-1 LC: Q. Apogee: 128 km (79 mi).

• 1974 September 3 06:00 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T12 LC: T. Apogee: 50 km (31 mi).

• 1974 September 3 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T11 LC: T. Apogee: 50 km (31 mi).

• 1975 January 30 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T13 LC: T. Apogee: 50 km (31 mi).

• 1975 February 5 06:00 - Test mission Launch Vehicle: ETV. ETV ETV-2 LC: Q. Apogee: 167 km (103 mi).

• 1975 February 7 01:00 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T14 LC: T. Apogee: 50 km (31 mi).

• 1975 August 17 06:00 - Test mission Launch Vehicle: TT-200. TT-210 TT-210-1F LC: T. Apogee: 100 km (60 mi).

• 1975 September 9 05:30 - Kiku 1 Launch Vehicle: N. N-1 N-1(F) LC: N. Apogee: 1,103 km (685 mi). 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 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T15 LC: T. Apogee: 50 km (31 mi).

• 1976 January 27 06:00 - Test mission Launch Vehicle: TT-200. TT-210 TT-210-2F LC: T. Apogee: 100 km (60 mi).

• 1976 February 29 03:30 - ISS 1 Launch Vehicle: N. N-1 N-2(F) LC: N. Apogee: 1,003 km (623 mi). 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 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T16 LC: T. Apogee: 50 km (31 mi).

• 1976 September 24 01:30 - Test mission Launch Vehicle: TT-200. TT-210 TT-210-3F LC: T. Apogee: 100 km (60 mi).

• 1976 September 25 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T17 LC: T. Apogee: 50 km (31 mi).

• 1977 January 25 01:30 - Test mission Launch Vehicle: TT-500. TT-500 TT-500-1F LC: T. Apogee: 300 km (180 mi).

• 1977 February 23 08:50 - Kiku 2 Launch Vehicle: N. N-1 N-3(F) LC: N. Apogee: 35,860 km (22,280 mi). 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 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T18 LC: T. Apogee: 50 km (31 mi).

• 1977 August 23 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T19 LC: T. Apogee: 50 km (31 mi).

• 1977 August 25 01:30 - Test mission Launch Vehicle: TT-500. TT-500 TT-500-2F LC: T. Apogee: 300 km (180 mi).

• 1977 August 26 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T20 LC: T. Apogee: 50 km (31 mi).

• 1978 January 16 01:30 - Test mission Launch Vehicle: TT-500. TT-500 TT-500-3F LC: T. Apogee: 300 km (180 mi).

• 1978 February 16 04:00 - ISS 2 Launch Vehicle: N. N-1 N-4(F) LC: N. Apogee: 1,216 km (755 mi). 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 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T21 LC: T. Apogee: 50 km (31 mi).

• 1978 August 24 01:45 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T22 LC: T. Apogee: 50 km (31 mi).

• 1978 August 25 01:30 - Test mission Launch Vehicle: TT-500. TT-500 TT-500-4F LC: T. Apogee: 300 km (180 mi).

• 1978 August 26 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T23 LC: T. Apogee: 50 km (31 mi).

• 1979 January 27 01:30 - Test mission Launch Vehicle: TT-500. TT-500 TT-500-5F LC: T. Apogee: 300 km (180 mi).

• 1979 February 6 08:46 - Ayame 1 Launch Vehicle: N. Third stage collided with ECS a.. N-1 N-5(F) LC: N. Apogee: 37,278 km (23,163 mi). 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 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T24 LC: T. Apogee: 50 km (31 mi).

• 1979 August 25 01:40 - Test mission Launch Vehicle: TT-500. TT-500 TT-500-6F LC: T. Apogee: 300 km (180 mi).

• 1979 August 27 06:00 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T26 LC: T. Apogee: 50 km (31 mi).

• 1979 August 27 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T25 LC: T. Apogee: 50 km (31 mi).

• 1980 January 28 01:30 - Test mission Launch Vehicle: TT-500. TT-500 TT-500-7F LC: T. Apogee: 300 km (180 mi).

• 1980 February 22 08:35 - Ayame 2 Launch Vehicle: N. N-1 N-6(F) LC: N. Apogee: 36,839 km (22,890 mi). Last known longitude (17 November 1988) 146.47 deg W drifting at 12.888 deg E per day.

• 1980 February 23 01:55 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T27 LC: T. Apogee: 50 km (31 mi).

• 1980 September 13 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T28 LC: T. Apogee: 50 km (31 mi).

• 1980 September 13 22:00 - Test mission Launch Vehicle: TT-500. TT-500A TT-500A-8F LC: T. Apogee: 300 km (180 mi).

• 1980 September 15 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T29 LC: T. Apogee: 50 km (31 mi).

• 1981 January 14 22:00 - Test mission Launch Vehicle: TT-500. TT-500A TT-500A-9F LC: T. Apogee: 300 km (180 mi).

• 1981 February 11 08:30 - Kiku 3 Launch Vehicle: N-2. N-2 N-7(F) LC: N. Apogee: 16,237 km (10,089 mi). 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 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T30 LC: T. Apogee: 50 km (31 mi).

• 1981 August 1 22:00 - Test mission Launch Vehicle: TT-500. TT-500A TT-500A-10F LC: T. Apogee: 300 km (180 mi).

• 1981 August 10 20:03 - Himawari 2 Launch Vehicle: N-2. N-2 N-8(F) LC: N. Apogee: 36,034 km (22,390 mi). 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 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T31 LC: T. Apogee: 50 km (31 mi).

• 1982 February 3 01:30 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T32 LC: T. Apogee: 50 km (31 mi).

• 1982 August 15 23:15 - Test mission Launch Vehicle: TT-500. TT-500A TT-500A-11F LC: T. Apogee: 300 km (180 mi).

• 1982 September 3 05:00 - Kiku 4 Launch Vehicle: N. N-1 N-9(F) LC: N. Apogee: 1,006 km (625 mi). 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 - Aeronomy mission? Launch Vehicle: MT-135. MT-135P MT135P T33 LC: T. Apogee: 50 km (31 mi).

• 1983 January 26 23:00 - Microgravity mission Launch Vehicle: TT-500. TT-500A TT-500A-12F LC: T. Apogee: 300 km (180 mi).

• 1983 February 4 08:37 - Sakura 2A Launch Vehicle: N-2. N-2 N-10(F) LC: N. Apogee: 36,070 km (22,410 mi). 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 - Sakura 2B Launch Vehicle: N-2. N-2 N-11(F) LC: N. Apogee: 36,210 km (22,490 mi). 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 - Microgravity mission Launch Vehicle: TT-500. TT-500A TT-500A-13F LC: T. Apogee: 300 km (180 mi).

• 1984 January 23 07:58 - Yuri 2A Launch Vehicle: N-2. N-2 N-12(F) LC: N. Apogee: 36,191 km (22,488 mi). 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 - Himawari 3 Launch Vehicle: N-2. N-2 N-13(F) LC: N. Apogee: 35,942 km (22,333 mi). 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 - Yuri 2B Launch Vehicle: N-2. N-2 N-14(F) LC: N. Apogee: 36,135 km (22,453 mi). 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 - EGS Launch Vehicle: H-1. H-1 H-15(F) LC: N. Apogee: 1,497 km (930 mi). 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.

• 1987 February 19 01:23 - MOS-1 Launch Vehicle: N-2. N-2 N-16(F) LC: N. Apogee: 909 km (564 mi). 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 - Kiku 5 Launch Vehicle: H-1. H-1 H-17(F) LC: N. Apogee: 36,072 km (22,414 mi). Stationed at 150 deg E. ETS-V (Kiku-5). Establishment of basic technology for bus systems needed for 3-axis stabilized geostationary satellites. Accumulation of key technologies required for high performance in the next generation of applications satellites; Experiment of mobile satellite communications for the control of aircrafts over the Pacific Ocean, and for the communication, navigational aid, search and rescue of ships. H-I (3-stage) launch vehicle. Launching organization NASDA. Launch time 0920 GMT. Positioned in geosynchronous orbit at 150 deg E in 1987-1997 As of 5 September 2001 located at 92.55 deg W drifting at 3.394 deg W per day. As of 2007 Mar 10 located at 49.74W drifting at 3.380W degrees per day.

• 1988 February 19 10:05 - Sakura 3A Launch Vehicle: H-1. H-1 H-18(F) LC: N. Apogee: 36,415 km (22,627 mi). Stationed at 132 deg E. CS-3A (Sakura 3-A). To continue communications services provided by the communications satellite 2 (CS-2). To meet increasing and diversifying demands for communications. To develop technologies for communications satellites. Launch vehicle H18F. Launchin g organization NASDA. Launch time 1005 GMT. Positioned in geosynchronous orbit at 132 deg E in 1988-1996 As of 2 September 2001 located at 85.60 deg E drifting at 7.699 deg W per day. As of 2007 Mar 10 located at 71.73E drifting at 7.700W degrees per day.

• 1988 September 5 23:00 - H-II 1/4 Scale model test flight Launch Vehicle: TR-1. TR-1 TR-1-1 LC: T. Apogee: 80 km (49 mi).

• 1988 September 16 09:59 - Sakura 3B Launch Vehicle: H-1. H-1 H-19(F) LC: N. Apogee: 36,093 km (22,427 mi). Telephone communications; 136 deg E. CS-3B (Sakura 3-B). To continue communications services provided by the communications satellite 2 (CS-2). To meet increasing and diversifying demands for communications; to develop technologies for communications satellites. Launch vehicle H-I (H19F). La unching organization NASDA. Launch time 0959 GMT. Positioned in geosynchronous orbit at 149 deg E in 1988; 136 deg E in 1988-1997; 154 deg E in 1997 As of 28 August 2001 located at 128.96 deg W drifting at 3.783 deg W per day. As of 2007 Mar 10 located at 177.82E drifting at 3.765W degrees per day.

• 1989 January 26 23:00 - H-II 1/4 Scale model test flight Launch Vehicle: TR-1. TR-1 TR-1-2 LC: T. Apogee: 80 km (49 mi).

• 1989 August 19 23:00 - H-II 1/4 Scale model test flight Launch Vehicle: TR-1. TR-1 TR-1-3 LC: T. Apogee: 80 km (49 mi).

• 1989 September 5 19:11 - Himawari 4 Launch Vehicle: H-1. H-1 H-20(F) LC: N. Apogee: 36,807 km (22,870 mi). 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 - MOS-1b Launch Vehicle: H-1. H-1 H-21(F) LC: N. Apogee: 909 km (564 mi). 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.

• 1990 August 28 09:05 - Yuri 3A Launch Vehicle: H-1. H-1 H-22(F) LC: N. Apogee: 36,245 km (22,521 mi). Japanese DBS; 110 deg E. Continuation of broadcasting services by BS-2; accommodations to increasing and diversifying demands for broadcasting; establishment of common technology necessary for broadcasting satellite. Launching organization NASDA. Launch time 0905 GMT. BS-3a 'Yuri -3a'. Positioned in geosynchronous orbit at 110 deg E in 1990-1998 As of 2 September 2001 located at 84.62 deg E drifting at 5.278 deg W per day. As of 2007 Mar 10 located at 83.70W drifting at 5.275W degrees per day.

• 1991 August 25 08:40 - Yuri 3B Launch Vehicle: H-1. H-1 H-23(F) LC: N. Apogee: 36,244 km (22,520 mi). TV; 110 deg E. Positioned in geosynchronous orbit at 110 deg E in 1991-1999 As of 3 September 2001 located at 91.59 deg E drifting at 5.350 deg W per day. As of 2007 Mar 9 located at 152.69E drifting at 5.334W degrees per day.

• 1991 September 15 23:00 - Microgravity mission Launch Vehicle: TR-1. TR-1A TR-1A-1 LC: T. Apogee: 270 km (160 mi).

• 1992 February 11 01:50 - JERS-1 Launch Vehicle: H-1. H-1 H-24(F) LC: N. Apogee: 568 km (352 mi). 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 - Microgravity mission Launch Vehicle: TR-1. TR-1A TR-1A-2 LC: T. Apogee: 290 km (180 mi).

• 1993 September 16 23:00 - Microgravity mission Launch Vehicle: TR-1. TR-1A TR-1A-3 LC: T. Apogee: 264 km (164 mi).

• 1994 February 3 22:20 - OREX Launch Vehicle: H-2. H-II-1F LC: Y. Apogee: 451 km (280 mi). 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.

• 1994 August 28 07:50 - Kiku 6 Launch Vehicle: H-2. LAPS apogee kick motor failed to ignite. Partial Failure.. H-II-2F LC: Y. Apogee: 38,677 km (24,032 mi). Failed to reach geostationary orbit; Engineering Test Satellite; partial mission success. Also tested ion engines for NSSK.

• 1995 March 18 08:01 - SFU Launch Vehicle: H-2. H-II-3F LC: Y. Apogee: 483 km (300 mi). Space Flyer Unit; carried materials, astronomy, biological experiments; retrieved by STS-72 1/20/96.

• 1995 August 24 22:00 - Microgravity mission Launch Vehicle: TR-1. TR-1A TR-1A-4 LC: T. Apogee: 270 km (160 mi).

• 1996 February 11 23:00 - Spacecraft Test mission Launch Vehicle: J-1. J-1 J-1-1F LC: N. Apogee: 110 km (60 mi).

• 1996 August 17 01:53 - ADEOS Launch Vehicle: H-2. H-II-4F LC: Y. Apogee: 800 km (490 mi).

• 1996 September 24 22:00 - Microgravity mission Launch Vehicle: TR-1. TR-1A TR-1A-5 LC: T. Apogee: 100 km (60 mi).

• 1997 September 25 00:30 - Microgravity mission Launch Vehicle: TR-1. TR-1A TR-1A-6 LC: T. Apogee: 100 km (60 mi).

• 1997 November 27 21:27 - TRMM Launch Vehicle: H-2. H-II-6F LC: Y. Apogee: 403 km (250 mi). TRMM was an international mission dedicated to measuring tropical and subtropical rainfall. The spacecraft and four instruments were provided by the USA, while Japan provided one instrument and launch services.

• 1998 February 21 07:55 - Kakehashi Launch Vehicle: H-2. H-II-5F LC: Y. Apogee: 17,727 km (11,015 mi). 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 - Microgravity mission Launch Vehicle: TR-1. TR-1A TR-1A-7 LC: T. Apogee: 100 km (60 mi).

• 1999 November 15 07:29 - MTSAT Launch Vehicle: H-2. Failure during first stage burn.. H-II-8F LC: Y. Multi-functional Transportation Satellite intended to provide communications and air traffic control for the Japanese transportation ministry and a meteorological data for the Japanese Meteorological Agency. The spacecraft had a mass of 1223 kg dry and was a follow-on to the GMS (Himawari) weather satellite series.

• 2001 August 29 07:00 - LRE Launch Vehicle: H-2A. H-IIA 202 H-IIA-1F LC: Y. Apogee: 36,214 km (22,502 mi). 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.

• 2002 February 4 02:45 - MDS-1 Launch Vehicle: H-2A. H-IIA 2024 H-IIA-2F LC: Y. Apogee: 35,753 km (22,215 mi). 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.

• 2002 September 10 08:20 - USERS Launch Vehicle: H-2A. H-2A/2024 s/n F3 LC: Y. Apogee: 508 km (315 mi). 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.

• 2002 December 14 23:04 - Adeos 2 Launch Vehicle: H-2A. H-2A-202 s/n 3F LC: Y. Apogee: 806 km (500 mi). Environment Monitoring, Aeronomy.

• 2003 March 28 01:27 - IGS-1a Launch Vehicle: H-2A. H-2A/2024 (F5) LC: Y. Apogee: 495 km (307 mi). 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.

• 2003 November 29 04:33 - IGS-2a Launch Vehicle: H-2A. Destroyed by range safety after solid booster nozzle burn-through resulted in motor not seperating from core.. H-IIA 2024 F6 LC: Y. 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.

• 2005 February 26 09:25 - Himawari 6 Launch Vehicle: H-2A. H-2A 2022 F7 LC: Y. Apogee: 35,798 km (22,243 mi). Return to flight after earlier failure; first commercial mission for H-2A. Delayed from August 2003, January 2004, and February 24, 2005. The dual-purpose satellite was to provide weather data for the Japanese Meteorological Agency (as with others in the Himawari-GMS series), and air traffic control support (airplane-ATC voice/data links, GPS augmentation and airplane position tracking) for the Japanese Civil Aviation Bureau. As of 2007 Mar 11 located at 140.26E drifting at 0.000E degrees per day.

• 2006 January 24 01:33 - Daichi Launch Vehicle: H-2A. H-2A 2022 F8 LC: Y. Apogee: 697 km (433 mi). 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 - MTSAT-2 Launch Vehicle: H-2A. LC: Y. Apogee: 35,803 km (22,246 mi). Multifunctional Transport Satellite. An aeronautical payload provided communications relay between aircraft and air traffic control; GPS augmentation navigation for aircraft; and transmitted the location of aircraft to air traffic control. A Japan Advanced Meteorological Imager weather camera had one visible and four infrared channels. MTSAT-2 was built by Mitsubishi using the new DS2000 bus. As of 2007 Mar 8 located at 144.93E drifting at 0.016W degrees per day.

• 2006 September 11 04:35 - IGS-3A Launch Vehicle: H-2A. H-2A/202 LC: Y. Apogee: 491 km (305 mi). Information Gathering Satellite / Optical-2 military surveillance satellite, launched to replace IGS O-1 launched in 2003, which demonstrated technical problems. The first replacement, IGS-O-2, was lost in a launch failure in 2003.

• 2006 December 16 06:32 - Kiku 8 Launch Vehicle: H-2A. H-2A/204 Apogee: 35,798 km (22,243 mi). Engineering Test Satellite-8 was a Japanese prototype/operational demonstration for a number of new technologies: a large satellite bus, large-scale deployable 40-m-span antennae, mobile satellite communications system, mobile satellite digital multimedia broadcasting, and basic positioning using high-accuracy time standard devices. It will be positioned in geosynchronous orbit at 146 degrees East. JAXA developed two portable terrestrial systems to communicate directly with the satellite - a tiny telephone and a portable laptop computer. The satellite was to have a lifetime of ten years. As of 2007 Mar 11 located at 145.97E drifting at 0.010W degrees per day.

• 2007 February 24 04:41 - IGS-2 Launch Vehicle: H-2A. H-IIA 2024 F-12 LC: YLP1. Information Gathering Satellite Radar-2. Japanese military satellite using a synthetic aperture radar for all-weather, 24-hour, high-resolution surveillance of the earth.

• 2007 September 14 01:31 - Okina Launch Vehicle: H-2A. H-IIA 2022 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.

• 2007 September 14 01:31 - Kaguya Launch Vehicle: H-2A. H-IIA 2022 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.

• 2007 September 14 01:31 - Ouna Launch Vehicle: H-2A. H-IIA 2022 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.

• McDowell, Jonathan, Jonathan's Space Home Page, Harvard University, 1997-present. Jonathan McDowell's complete on-line listing of all objects orbited and over 20,000 rocket launches Accessed at: http://www.planet4589.org/jsr.html.