1975 September 9 - 05:30 GMT - Launch Vehicle: Delta. N-1 N-1(F) Kiku 1 Mass: 85 kg (187 lb). Spacecraft: ETS. Agency: NASDA. Perigee: 975 km (605 mi). Apogee: 1,103 km (685 mi). Inclination: 47.00 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.

1976 February 29 - 03:30 GMT - Launch Vehicle: Delta. N-1 N-2(F) ISS 1 Mass: 139 kg (306 lb). Spacecraft: JISS. Agency: NASDA. Perigee: 988 km (613 mi). Apogee: 1,003 km (623 mi). Inclination: 69.70 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.

1977 February 23 - 08:50 GMT - Launch Vehicle: Delta. N-1 N-3(F) Kiku 2 Mass: 130 kg (280 lb). Spacecraft: ETS. Agency: NASDA. Perigee: 35,854 km (22,278 mi). Apogee: 35,860 km (22,280 mi). Inclination: 11.90 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.

1978 February 16 - 04:00 GMT - Launch Vehicle: Delta. N-1 N-4(F) ISS 2 Mass: 140 kg (300 lb). Spacecraft: JISS. Agency: NASDA. Perigee: 973 km (604 mi). Apogee: 1,216 km (755 mi). Inclination: 69.40 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.

1979 February 6 - 08:46 GMT - Launch Vehicle: Delta. N-1 N-5(F) FAILURE: Third stage collided with ECS a. Ayame 1 Mass: 260 kg (570 lb). Spacecraft: Ayame. Agency: NASDA. Perigee: 29,407 km (18,272 mi). Apogee: 37,278 km (23,163 mi). Inclination: 5.60 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.

1980 February 22 - 08:35 GMT - Launch Vehicle: Delta. N-1 N-6(F) Ayame 2 Mass: 260 kg (570 lb). Spacecraft: Ayame. Agency: NASDA. Perigee: 32,785 km (20,371 mi). Apogee: 36,839 km (22,890 mi). Inclination: 1.40 deg. Period: 1,386.60 min. Last known longitude (17 November 1988) 146.47 deg W drifting at 12.888 deg E per day.

1981 February 11 - 08:30 GMT - Launch Vehicle: Delta. N-2 N-7(F) Kiku 3 Mass: 640 kg (1,410 lb). Spacecraft: ETS. Agency: NASDA. Perigee: 305 km (189 mi). Apogee: 16,237 km (10,089 mi). Inclination: 28.50 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 August 10 - 20:03 GMT - Launch Vehicle: Delta. N-2 N-8(F) Himawari 2 Mass: 670 kg (1,470 lb). Spacecraft: GMS. Agency: NASDA. Perigee: 35,943 km (22,333 mi). Apogee: 36,034 km (22,390 mi). Inclination: 12.90 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 September 3 - 05:00 GMT - Launch Vehicle: Delta. N-1 N-9(F) Kiku 4 Mass: 385 kg (848 lb). Spacecraft: ETS. Agency: NASDA. Perigee: 988 km (613 mi). Apogee: 1,006 km (625 mi). Inclination: 44.60 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.

1983 February 4 - 08:37 GMT - Launch Vehicle: Delta. N-2 N-10(F) Sakura 2A Mass: 772 kg (1,701 lb). Spacecraft: CS-2. Agency: NASDA. Perigee: 35,994 km (22,365 mi). Apogee: 36,070 km (22,410 mi). Inclination: 10.60 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 Vehicle: Delta. N-2 N-11(F) Sakura 2B Mass: 670 kg (1,470 lb). Spacecraft: CS-2. Agency: NASDA. Perigee: 36,191 km (22,488 mi). Apogee: 36,210 km (22,490 mi). Inclination: 5.10 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.

1984 January 23 - 07:58 GMT - Launch Vehicle: Delta. N-2 N-12(F) Yuri 2A Mass: 670 kg (1,470 lb). Spacecraft: AS 3000. Agency: NASDA. Perigee: 36,072 km (22,414 mi). Apogee: 36,191 km (22,488 mi). Inclination: 4.90 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 Vehicle: Delta. N-2 N-13(F) Himawari 3 Mass: 303 kg (668 lb). Spacecraft: GMS. Agency: NASDA. Perigee: 35,877 km (22,292 mi). Apogee: 35,942 km (22,333 mi). Inclination: 9.80 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 Vehicle: Delta. N-2 N-14(F) Yuri 2B Mass: 677 kg (1,492 lb). Spacecraft: AS 3000. Agency: NASDA. Perigee: 35,996 km (22,366 mi). Apogee: 36,135 km (22,453 mi). Inclination: 2.70 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 Vehicle: Delta. H-1 H-15(F) EGS Mass: 685 kg (1,510 lb). Spacecraft: EGS. Agency: NASDA. Perigee: 1,479 km (919 mi). Apogee: 1,497 km (930 mi). Inclination: 50.00 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.

1987 February 19 - 01:23 GMT - Launch Vehicle: Delta. N-2 N-16(F) MOS-1 Mass: 745 kg (1,642 lb). Spacecraft: Marine Observation Satellite. Agency: NASDA. Perigee: 907 km (563 mi). Apogee: 909 km (564 mi). Inclination: 99.10 deg. Period: 103.20 min. 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 Vehicle: Delta. H-1 H-17(F) Kiku 5 Mass: 550 kg (1,210 lb). Spacecraft: ETS. Agency: NASDA. Perigee: 36,029 km (22,387 mi). Apogee: 36,072 km (22,414 mi). Inclination: 7.90 deg. Period: 1,449.60 min. Stationed at 150 deg E. ETS-V (Kiku-5). Establishment of basic technology for bus systems needed for 3-axis stabilized geostationary satellites. Accumulation of key technologies required for high performance in the next generation of applications satellites; Experiment of mobile satellite communications for the control of aircrafts over the Pacific Ocean, and for the communication, navigational aid, search and rescue of ships. H-I (3-stage) launch vehicle. Launching organization NASDA. Launch time 0920 GMT. Positioned in geosynchronous orbit at 150 deg E in 1987-1997 As of 5 September 2001 located at 92.55 deg W drifting at 3.394 deg W per day. As of 2007 Mar 10 located at 49.74W drifting at 3.380W degrees per day.

1988 February 19 - 10:05 GMT - Launch Vehicle: Delta. H-1 H-18(F) Sakura 3A Mass: 1,100 kg (2,400 lb). Spacecraft: CS-3. Agency: NASDA/TC. Perigee: 36,376 km (22,602 mi). Apogee: 36,415 km (22,627 mi). Inclination: 4.90 deg. Period: 1,467.30 min. Stationed at 132 deg E. CS-3A (Sakura 3-A). To continue communications services provided by the communications satellite 2 (CS-2). To meet increasing and diversifying demands for communications. To develop technologies for communications satellites. Launch vehicle H18F. Launchin g organization NASDA. Launch time 1005 GMT. Positioned in geosynchronous orbit at 132 deg E in 1988-1996 As of 2 September 2001 located at 85.60 deg E drifting at 7.699 deg W per day. As of 2007 Mar 10 located at 71.73E drifting at 7.700W degrees per day.

1988 September 16 - 09:59 GMT - Launch Vehicle: Delta. H-1 H-19(F) Sakura 3B Mass: 1,100 kg (2,400 lb). Spacecraft: CS-3. Agency: NASDA/TC. Perigee: 36,071 km (22,413 mi). Apogee: 36,093 km (22,427 mi). Inclination: 4.00 deg. Period: 1,451.20 min. Telephone communications; 136 deg E. CS-3B (Sakura 3-B). To continue communications services provided by the communications satellite 2 (CS-2). To meet increasing and diversifying demands for communications; to develop technologies for communications satellites. Launch vehicle H-I (H19F). La unching organization NASDA. Launch time 0959 GMT. Positioned in geosynchronous orbit at 149 deg E in 1988; 136 deg E in 1988-1997; 154 deg E in 1997 As of 28 August 2001 located at 128.96 deg W drifting at 3.783 deg W per day. As of 2007 Mar 10 located at 177.82E drifting at 3.765W degrees per day.

1989 September 5 - 19:11 GMT - Launch Vehicle: Delta. H-1-6R H-20(F) Himawari 4 Mass: 725 kg (1,598 lb). Spacecraft: GMS. Agency: NASDA. Perigee: 36,410 km (22,620 mi). Apogee: 36,807 km (22,870 mi). Inclination: 6.20 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 Vehicle: Delta. H-1 H-21(F) MOS-1b Mass: 740 kg (1,630 lb). Spacecraft: Marine Observation Satellite. Agency: NASDA. Perigee: 908 km (564 mi). Apogee: 909 km (564 mi). Inclination: 99.10 deg. Period: 103.20 min. 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 GMT - Launch Vehicle: Delta. H-1 H-22(F) Yuri 3A Mass: 1,115 kg (2,458 lb). Spacecraft: AS 3000. Agency: NASDA/TC. Perigee: 36,157 km (22,466 mi). Apogee: 36,245 km (22,521 mi). Inclination: 3.50 deg. Period: 1,457.30 min. Japanese DBS; 110 deg E. Continuation of broadcasting services by BS-2; accommodations to increasing and diversifying demands for broadcasting; establishment of common technology necessary for broadcasting satellite. Launching organization NASDA. Launch time 0905 GMT. BS-3a 'Yuri -3a'. Positioned in geosynchronous orbit at 110 deg E in 1990-1998 As of 2 September 2001 located at 84.62 deg E drifting at 5.278 deg W per day. As of 2007 Mar 10 located at 83.70W drifting at 5.275W degrees per day.

1991 August 25 - 08:40 GMT - Launch Vehicle: Delta. H-1 H-23(F) Yuri 3B Mass: 1,115 kg (2,458 lb). Spacecraft: AS 3000. Agency: NASDA/TC. Perigee: 36,171 km (22,475 mi). Apogee: 36,244 km (22,520 mi). Inclination: 3.20 deg. Period: 1,457.70 min. 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.

1992 February 11 - 01:50 GMT - Launch Vehicle: Delta. H-1 H-24(F) JERS-1 Mass: 1,340 kg (2,950 lb). Spacecraft: JERS. Agency: NASDA. Perigee: 567 km (352 mi). Apogee: 568 km (352 mi). Inclination: 97.70 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.