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Japan
Credit - © Mark Wade

Launch Sites in Japan

Akita. Agency: ISAS. Type: Suborbital Launch Site. Location: Akita Rocket Range (ATC), Honshu. Latitude: 39.5715. Longitude: 140.0579.

Kadena AB. Agency: USAF. Operating Country: USA. Type: IRCM Base. Location: Okinawa. Latitude: 26.5000. Longitude: 127.8000.

Kagoshima. Agency: ISAS. Type: Orbital Launch Site. Location: Kagoshima Space Center, Kyushu. Latitude: 31.2519. Longitude: 131.0791.

Niijima. Agency: STA. Type: Suborbital Launch Site. Latitude: 34.3377. Longitude: 139.2658.

Obachi. Agency: ISAS. Type: Suborbital Launch Site. Location: Honshu. Latitude: 40.7034. Longitude: 141.3694.

Ryori. Type: Suborbital Launch Site. Location: Japan. Latitude: 39.0300. Longitude: 141.8300.

Sendai. Type: Suborbital Launch Site. Location: Miyagi. Latitude: 38.3309. Longitude: 140.8832.

Syowa Base. Type: Suborbital Launch Site. Location: Syowa Base, East Ongul Island, Queen Maud Land, Antarctica. Latitude: -69.0000. Longitude: 39.5800.

Tanegashima. Agency: NASDA. Type: Orbital Launch Site. Location: Tanegashima Space Center. Latitude: 30.3910. Longitude: 130.9681.

Rockets Developed in Japan

H-2. - orbital launch vehicle - Status: Active. Heavy lift Japanese indigenous launch vehicle. The original H-2 version was cancelled due to high costs and poor reliability and replaced by the substantially redesigned H-2A.

J. - all-solid orbital launch vehicle - Status: Retired 1996. All-solid rocket motor launch vehicle. Because of the high cost, the original J-1 design was superseded by an alternate J-1 F2 with a different booster stage.

Japanese Space Plane. - winged orbital launch vehicle - Status: Design 1995. NAL / Mitsubishi Heavy Industries, Ltd. design for a single stage to orbit spaceplane. Crew of ten, empty mass 110 tonnes. LACE / Scramjet engines, 29 m wingspan.

Kankoh Maru. - SSTO orbital launch vehicle - Status: Design 1995. Kawasaki design for single stage to orbit reusable booster. Would carry 50 passengers to orbiting hotels or fast intercontinental flights.

Kappa. - sounding rocket - Status: Retired 1988. The Kappa series represented Japan's first large post-war indigenously-developed sounding rockets. They led eventually to the Lambda and Mu solid rocket satellite launchers.

Lambda. - all-solid orbital launch vehicle - Status: Retired 1977. All solid-propellant vehicle, Japan's first satellite launcher. The L-4S project simulated the procedures and demonstrated the capabilities required for orbital satellite launch essential to the follow-on Mu project.

M-V. - all-solid orbital launch vehicle - Status: Active. All-solid Japanese satellite launch vehicle.

MT-135. - sounding rocket - Status: Retired 2001. The MT-135 was a small single-stage sounding rocket designed to collect data on the middle atmosphere, such as ozone layer depletion.

Mu. - all-solid orbital launch vehicle - Status: Retired 1995. The Japanese Mu launcher series provided a flexible all-solid propellant launch vehicle for access to space. It was the first Japanese launch vehicle designed from the start as an orbital launch vehicle.

NAL. - test vehicle - Status: Retired. Single stage vehicles.

S. - sounding rocket - Status: Active. Series of Japanese single-stage sounding rockets designed for low-cost observations of the ionosphere.

SB-735. - sounding rocket - Status: Retired 1994.

TR-1. - test vehicle - Status: Retired 1998. Single stage vehicle.

Spacecraft Designed in Japan

ADEOS. - Earth Atmosphere

Akari. - Astronomy Gamma Ray

Alflex. - Spaceplane

Alpex. - Spaceplane

ASCA. - Astronomy X-ray

Astro. - Astronomy X-ray

ASTRO E. - Astronomy X-Ray

Ayame. - Technology Communications

Corsa A. - Technology

CS-1. - Communications

CS-2. - Communications

CS-3. - Communications

Daichi. - Surveillance Radarsat

DASH 2002. - Technology RV

Debut. - Technology Communications

DRTS. - Communications

DS2000. - Communications

DUVE. - Earth Atmosphere

EGS. - Earth Geodetic

ETS. - Technology

ETS-7. - Technology Rendezvous

ETS-7 Target. - Technology Rendezvous

EXOS. - Earth Ionosphere

Express 1. - Materials

Fuji. - Communications

Geotail. - Earth Magnetosphere

GMS. - Earth Weather

Hagoromo. - Planetary Lunar Orbiter

Haruka. - Astronomy Radio

Hayabusa. - Planetary Asteroid

Hinode. - Astronomy Solar

Hiten. - Planetary Lunar Orbiter

HOPE. - Spaceplane

Hyflex. - Spaceplane

IGS. - Surveillance Military

Japanese Space Plane. - Manned Spacecraft

JERS. - Earth Landsat

JISS. - Earth Ionosphere

Kaguya. - Planetary Lunar Orbiter

Kakehashi. - Communications

Kankoh Maru. - Manned Spacecraft

Kirari. - Communications

Kizuna. - Communications

LDREX. - Technology Communications

LRE. - Earth Geodetic

MABES. - Technology

Marine Observation Satellite. - Earth Seasat

MDS. - Technology

NASDA H-2 Transfer Vehicle. - Tug

NASDA Japanese Experiment Module. - Manned Space Station Module

Nozomi. - Planetary Mars Orbiter

Ohsumi. - Technology

OREX. - Technology RV

Osumi. - Technology

SERVIS. - Technology

SFU. - Materials

Solar. - Solar

SS. - Earth Magnetosphere

Tansei. - Technology

USERS. - Materials

VEP. - Technology

Yuri. - Technology Communications

Space-related People born in Japan

Akiyama. - Tohiro Akiyama Japanese Journalist Cosmonaut. Born 22 July 1942. Number of Flights: 1.00. Total Time: 7.91 days.

Doi. - Dr Takao Doi Japanese Mission Specialist Astronaut. Born 18 September 1954. Number of Flights: 2.00. Total Time: 31.45 days.

Enomoto. - Daisuke Enomoto Japanese Engineer Cosmonaut. Born 22 April 1971.

Furukawa. - Satoshi Furukawa Japanese Physician Astronaut. Born 4 April 1964.

Hoshide. - Akihito Hoshide Japanese Engineer Astronaut. Born 28 December 1968. Number of Flights: 1.00. Total Time: 13.76 days.

Kikuchi. - Ryoko Kikuchi Japanese Journalist Cosmonaut. Born 15 September 1964.

Mohri. - Mamoru Mohri Japanese Mission Specialist Astronaut. Born 29 January 1948. Number of Flights: 2.00. Total Time: 19.17 days.

Mukai. - Chiaki Mukai Japanese Medical Doctor Astronaut. Born 6 May 1952. Number of Flights: 2.00. Total Time: 23.65 days.

Noguchi. - Soichi Noguchi Japanese Mission Specialist Astronaut. Born 15 April 1965. Number of Flights: 1.00. Total Time: 13.90 days.

Wakata. - Koichi Wakata Japanese Mission Specialist Astronaut. Born 1 August 1963. Number of Flights: 2.00. Total Time: 21.82 days.

Yamazaki. - Naoko Yamazaki (nee Sumino) Japanese Engineer Astronaut. Born 27 December 1970.

Chronology of Events for Japan

1945 August 6 -

U.S. drops atomic bomb on Japanese city of Hiroshima Level: 1.

1945 August 9 -

U.S. drops atomic bomb on Japanese city of Nagasaki Level: 1.

1945 September 2 -

Japan signs official surrender on V-J Day Level: 1.

1956 September 24 - 00:02 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 1. LV Configuration: Kappa 1 K-1-1.

K-I-S-1 test Agency: ISAS. Apogee: 5.00 km (3.10 mi). References: 2. Level: 1.

1956 December 13 - 02:10 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 1. LV Configuration: Kappa 1 K-1-7.

K-I-T-4 test Agency: ISAS. Apogee: 5.00 km (3.10 mi). References: 2. Level: 1.

1957 April 30 - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 2. LV Configuration: Kappa 2 K-2-1.

Test mission Agency: ISAS. Apogee: 30 km (18 mi). References: 2. Level: 1.

1957 July 26 - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 3. LV Configuration: Kappa 3 K-3-3.

Test mission Agency: ISAS. Apogee: 30 km (18 mi). References: 2. Level: 1.

1957 September 20 - 10:03 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 4. LV Configuration: Kappa 4 K-4-1.

Chemical release mission Agency: ISAS. Apogee: 40 km (24 mi). References: 2. Level: 1.

1958 April 8 - 01:31 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: K150. LV Configuration: K150 K150S-1.

Test mission Agency: ISAS. Apogee: 6.00 km (3.70 mi). References: 2. Level: 1.

1958 June 14 - 01:11 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: K245.

Test mission Agency: ISAS. Apogee: 1.00 km (0.60 mi). References: 2. Level: 1.

1958 June 16 - 02:36 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 6. LV Configuration: Kappa 6 K-6-1.

Test mission Agency: ISAS. Apogee: 30 km (18 mi). References: 2. Level: 1.

1958 July 1 - Launch Vehicle: Kappa.

Kappa-6tw rocket reaches 30 miles. Japanese Kappa-6tw two-stage rocket flown to 30-mile altitude over Michikawa Rocket Center, Japan. References: 17. Level: 1.

1959 November 18 - 05:03 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 7. LV Configuration: Kappa 7 K-7-1.

Test mission Agency: ISAS. Apogee: 53 km (32 mi). References: 2. Level: 1.

1960 March 28 - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8D-1.

Test mission Agency: ISAS. Apogee: 20 km (12 mi). References: 2. Level: 1.

1960 July 11 - 04:24 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-1.

Test mission Agency: ISAS. Apogee: 150 km (90 mi). References: 2. Level: 1.

1960 July 17 - 04:11 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-2.

Test mission Agency: ISAS. Apogee: 182 km (113 mi). References: 2. Level: 1.

1960 September 22 - 06:32 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-3.

Ionosphere mission Agency: ISAS. Apogee: 200 km (120 mi). References: 2. Level: 1.

1960 September 26 - 11:25 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-4.

Ionosphere mission Agency: ISAS. Apogee: 185 km (114 mi). References: 2. Level: 1.

1960 September 29 - 02:46 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 6H. LV Configuration: Kappa 6H K-6H-TW-9.

K-6H-1 Grenade Aeronomy mission Agency: ISAS. Apogee: 70 km (43 mi). References: 2. Level: 1.

1961 March 27 - 04:08 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-5.

Ionosphere mission Agency: ISAS. Apogee: 172 km (106 mi). References: 2. Level: 1.

1961 April 1 - 03:25 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9L. LV Configuration: Kappa 9L K-9L-1.

Test mission Agency: ISAS. Apogee: 350 km (210 mi). References: 2. Level: 1.

1961 April 18 - 12:27 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-6.

Ionosphere mission Agency: ISAS. Apogee: 150 km (90 mi). References: 2. Level: 1.

1961 June 18 - 04:35 GMT - Launch Site: Obachi. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 4. LV Configuration: Kappa 4 K-4-2.

Sigma 4 Rockoon Chemical release mission Agency: ISAS. Apogee: 105 km (65 mi). References: 2. Level: 1.

1961 July 21 - 02:42 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-7 TW-10/ID-6.

Aeronomy / ionosphere mission Agency: ISAS. Apogee: 158 km (98 mi). References: 2. Level: 1.

1961 September 2 -

Japan prepares biological payload. Scientists at Nagoya University, Japan, were reported to be training monkey for space flight next year, hopefully in conjunction with Japanese Government-financed rocket program carried out by Tokyo University's Institute of Industrial Science. References: 18. Level: 1.

1961 October 24 - 03:59 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-8.

Ionosphere mission Agency: ISAS. Apogee: 200 km (120 mi). References: 2. Level: 1.

1961 October 30 - 11:13 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-9.

Ionosphere mission Agency: ISAS. Apogee: 175 km (108 mi). References: 2. Level: 1.

1961 December 26 - 05:05 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9L. LV Configuration: Kappa 9L K-9L-2.

Test mission Agency: ISAS. Apogee: 343 km (213 mi). References: 2. Level: 1.

1962 May 24 - 10:50 GMT - Launch Site: Akita. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-10. FAILURE: Failure.

Ionosphere mission Agency: ISAS. Apogee: 0 km ( mi). References: 2. Level: 1.

1962 August 1 - Launch Site: Kagoshima. Launch Complex: TMP. Launch Pad: -. Launch Vehicle: Kappa. Model: K150. LV Configuration: K150 AT-150.

Test mission Agency: ISAS. Apogee: 5.00 km (3.10 mi). References: 2. Level: 1.

1962 August 23 - 07:15 GMT - Launch Site: Kagoshima. Launch Complex: TMP. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-1.

Test mission Agency: ISAS. Apogee: 173 km (107 mi). References: 2. Level: 1.

1962 December 18 - 05:03 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-11.

Cosmic rays mission Agency: ISAS. Apogee: 202 km (125 mi). References: 2. Level: 1.

1963 May 20 - 02:09 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-2.

Ionosphere mission Agency: ISAS. Apogee: 345 km (214 mi). References: 2. Level: 1.

1963 August 10 - 04:58 GMT - Launch Site: Niijima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-A. LV Configuration: S-A1.

Test mission Agency: STA. Apogee: 50 km (31 mi). References: 2. Level: 1.

1963 August 10 - 03:17 GMT - Launch Site: Niijima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-A. LV Configuration: LS-A Sustainer.

Test mission Agency: STA. Apogee: 50 km (31 mi). References: 2. Level: 1.

1963 August 24 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 2. LV Configuration: Lambda 2 L-2-1. FAILURE: Failure.

Ionosphere / test Agency: ISAS. Apogee: 51 km (31 mi). References: 2. Level: 1.

1963 December 11 - 05:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 2. LV Configuration: Lambda 2 L-2-2.

Ionosphere mission Agency: ISAS. Apogee: 410 km (250 mi). References: 2. Level: 1.

1963 December 12 - 08:50 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-2.

Aeronomy / Fields mission Agency: ISAS. Apogee: 103 km (64 mi). References: 2. Level: 1.

1964 March 29 - 02:12 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: MT-135. Model: MT-135. LV Configuration: MT-135PT-1.

Propellant test Agency: ISAS. Apogee: 51 km (31 mi). References: 2. Level: 1.

1964 April 1 - 03:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-3.

Aeronomy / fields mission Agency: ISAS. Apogee: 100 km (60 mi). References: 2. Level: 1.

1964 July 11 - 02:02 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3. LV Configuration: Lambda 3 L-3-1.

Ionosphere mission Agency: ISAS. Apogee: 857 km (532 mi). References: 2. Level: 1.

1964 July 22 - 02:50 GMT - Launch Site: Niijima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-A. LV Configuration: LS-A-1.

Test mission Agency: STA. Apogee: 150 km (90 mi). References: 2. Level: 1.

1964 July 22 - 08:55 GMT - Launch Site: Niijima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-A. LV Configuration: LS-A-2.

Test mission Agency: STA. Apogee: 150 km (90 mi). References: 2. Level: 1.

1964 July 26 - 10:51 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-5.

Aeronomy mission Agency: ISAS. Apogee: 112 km (69 mi). References: 2. Level: 1.

1964 July 26 - 09:07 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-4.

Aeronomy mission Agency: ISAS. Apogee: 124 km (77 mi). References: 2. Level: 1.

1964 July 28 - 02:08 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-160. LV Configuration: S-160 PT-160-1.

Propellant test Agency: ISAS. Apogee: 44 km (27 mi). References: 2. Level: 1.

1964 July 29 - 10:07 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-5.

Chemical release mission Agency: ISAS. Apogee: 300 km (180 mi). References: 2. Level: 1.

1964 November 2 - 09:03 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-7.

Aeronomy mission Agency: ISAS. Apogee: 156 km (96 mi). References: 2. Level: 1.

1964 November 5 - 03:01 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-4.

Ionosphere mission Agency: ISAS. Apogee: 356 km (221 mi). References: 2. Level: 1.

1964 November 10 - 02:05 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-8.

Ionosphere mission Agency: ISAS. Apogee: 145 km (90 mi). References: 2. Level: 1.

1964 November 12 - 03:05 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-6.

Aeronomy mission Agency: ISAS. Apogee: 100 km (60 mi). References: 2. Level: 1.

1965 January 22 - 05:14 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-3.

Ionosphere mission Agency: ISAS. Apogee: 350 km (210 mi). References: 2. Level: 1.

1965 January 31 - 05:01 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3. LV Configuration: Lambda 3 L-3-2.

Ionosphere mission Agency: ISAS. Apogee: 1,040 km (640 mi). References: 2. Level: 1.

1965 February 6 - 05:01 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-7.

Ionosphere mission Agency: ISAS. Apogee: 325 km (201 mi). References: 2. Level: 1.

1965 February 6 - 10:02 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-6.

Solar radio frequencies mission Agency: ISAS. Apogee: 335 km (208 mi). References: 2. Level: 1.

1965 March 18 - 10:07 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3. LV Configuration: Lambda 3 L-3-3.

X-ray astronomy mission Agency: ISAS. Apogee: 1,085 km (674 mi). References: 2. Level: 1.

1965 March 25 - 11:21 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-8.

Airglow Aeronomy / ionosphere mission Agency: ISAS. Apogee: 320 km (190 mi). References: 2. Level: 1.

1965 March 27 - 05:01 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-9.

Ionosphere mission Agency: ISAS. Apogee: 335 km (208 mi). References: 2. Level: 1.

1965 March 28 - 07:01 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-10.

Ionosphere / plasma mission Agency: ISAS. Apogee: 349 km (216 mi). References: 2. Level: 1.

1965 June 17 - 07:30 GMT - Launch Site: Niijima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: HM-16. LV Configuration: HM-16 HM-16-D.

Test mission Agency: STA. Apogee: 52 km (32 mi). References: 2. Level: 1.

1965 June 18 - 07:43 GMT - Launch Site: Niijima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: HM-16. LV Configuration: HM-16 HM-16-IT.

Test mission Agency: STA. Apogee: 38 km (23 mi). References: 2. Level: 1.

1965 July 16 - 10:50 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-12.

Aeronomy / ionosphere mission Agency: ISAS. Apogee: 160 km (90 mi). References: 2. Level: 1.

1965 July 26 - 12:01 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-12.

Optical astronomy / x-ray astronomy mission Agency: ISAS. Apogee: 350 km (210 mi). References: 2. Level: 1.

1965 July 27 - 03:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-13.

Ionosphere mission Agency: ISAS. Apogee: 317 km (196 mi). References: 2. Level: 1.

1965 August 7 - Launch Site: Pameungpeuk. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8(L).

Aeronomy mission Agency: ISAS. Apogee: 100 km (60 mi). References: 2. Level: 1.

1965 August 11 - 01:35 GMT - Launch Site: Pameungpeuk. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8(L)-4.

SK-8-4 Aeronomy / ionosphere / Fields mission Agency: ISAS. Apogee: 191 km (118 mi). References: 2. Level: 1.

1965 August 17 - 00:05 GMT - Launch Site: Pameungpeuk. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8(L).

SK-8-3 (Grenades) Aeronomy mission Agency: ISAS. Apogee: 100 km (60 mi). References: 2. Level: 1.

1965 August 28 - 02:02 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10S. LV Configuration: Kappa 10S K-10S-1.

Electron temp Ionosphere mission Agency: ISAS. Apogee: 742 km (461 mi). References: 2. Level: 1.

1965 October 4 - 03:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-14.

Ionosphere mission Agency: ISAS. Apogee: 299 km (185 mi). References: 2. Level: 1.

1965 October 6 - 04:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-9.

Aeronomy mission Agency: ISAS. Apogee: 141 km (87 mi). References: 2. Level: 1.

1965 November 8 - 05:05 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-1.

Test / ionosphere mission Agency: ISAS. Apogee: 228 km (141 mi). References: 2. Level: 1.

1965 November 16 - 02:09 GMT - Launch Site: Niijima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: ST. LV Configuration: ST ST-I F1.

Test mission Agency: STA. Apogee: 20 km (12 mi). References: 2. Level: 1.

1965 November 17 - 06:34 GMT - Launch Site: Niijima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: NAL-16. LV Configuration: NAL-16 NAL-16TR.

Test mission Agency: STA. Apogee: 45 km (27 mi). References: 2. Level: 1.

1965 November 22 - 06:35 GMT - Launch Site: Niijima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-A. LV Configuration: LS-A-3.

Test mission Agency: STA. Apogee: 150 km (90 mi). References: 2. Level: 1.

1965 December 13 - 06:20 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-16.

Ozone profile Ionosphere / aeronomy mission Agency: ISAS. Apogee: 318 km (197 mi). References: 2. Level: 1.

1965 December 18 - 06:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-17.

Ionosphere mission Agency: ISAS. Apogee: 316 km (196 mi). References: 2. Level: 1.

1966 January 26 - 02:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: S-250. LV Configuration: S-250 BT-250-1.

Test mission Agency: ISAS. Apogee: 6.00 km (3.70 mi). References: 2. Level: 1.

1966 March 5 - 04:50 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3H. LV Configuration: Lambda 3H L-3H-1.

X-ray astronomy mission Agency: ISAS. Apogee: 1,829 km (1,136 mi). References: 2. Level: 1.

1966 March 20 - 12:15 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-15.

XRA? / Airglow X-ray astronomy mission Agency: ISAS. Apogee: 300 km (180 mi). References: 2. Level: 1.

1966 April 20 - 12:05 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-13.

Aeronomy / plasma / fields mission Agency: ISAS. Apogee: 155 km (96 mi). References: 2. Level: 1.

1966 April 28 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: BT-310. LV Configuration: BT-310 BT-310-1.

Test mission Agency: ISAS. Apogee: 1.00 km (0.60 mi). References: 2. Level: 1.

1966 July 17 - 02:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-18.

Ionosphere / solar / solar ultraviolet mission Agency: ISAS. Apogee: 326 km (202 mi). References: 2. Level: 1.

1966 July 23 - 06:35 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3H. LV Configuration: Lambda 3H L-3H-2.

Gyro-plasma probe Ionosphere / aeronomy mission Agency: ISAS. Apogee: 1,800 km (1,100 mi). References: 2. Level: 1.

1966 August 3 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-11.

Ionosphere mission Agency: ISAS. Apogee: 328 km (203 mi). References: 2. Level: 1.

1966 August 6 - 06:30 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210 PT-210-1.

Test mission Agency: ISAS. Apogee: 1.00 km (0.60 mi). References: 2. Level: 1.

1966 August 10 - 12:37 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-19.

VLF Doppler Ionosphere / aeronomy mission Agency: ISAS. Apogee: 330 km (200 mi). References: 2. Level: 1.

1966 August 11 - 12:05 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-10.

Aeronomy mission Agency: ISAS. Apogee: 130 km (80 mi). References: 2. Level: 1.

1966 September 26 - 02:58 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 4S. LV Configuration: Lambda 4S L-4S-1. FAILURE: Fourth stage attitude control failed.

Ohsumi 1 Payload: L-4S-1. Mass: 26 kg (57 lb). Class: Technology. Spacecraft: Ohsumi. Agency: ISAS. Apogee: 400 km (240 mi). COSPAR: F660926A. Decay Date: 1966-09-26. References: 126. Level: 1.

1966 October 18 - 09:17 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-11.

Aeronomy mission Agency: ISAS. Apogee: 150 km (90 mi). References: 2. Level: 1.

1966 October 20 - 08:25 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-20.

Gyro-plasma probe Ionosphere mission Agency: ISAS. Apogee: 353 km (219 mi). References: 2. Level: 1.

1966 October 20 - 02:20 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-14.

Ionosphere / fields / solar ultraviolet mission Agency: ISAS. Apogee: 191 km (118 mi). References: 2. Level: 1.

1966 October 31 - 05:04 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-1. LV Configuration: Mu-1 M-1-1.

Test mission Agency: ISAS. Apogee: 34 km (21 mi). References: 2. Level: 1.

1966 November 4 - 02:05 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-300 ISAS. LV Configuration: S-300 PT-300-1.

Test mission Agency: ISAS. Apogee: 160 km (90 mi). References: 2. Level: 1.

1966 December 5 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-21.

Gyro-plasma probe Aeronomy / ionosphere / solar ultraviolet mission Agency: ISAS. Apogee: 326 km (202 mi). References: 2. Level: 1.

1966 December 10 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8L. LV Configuration: Kappa 8L K-8L-12.

Aeronomy / ionosphere / solar mission Agency: ISAS. Apogee: 147 km (91 mi). References: 2. Level: 1.

1966 December 10 - 11:30 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-2.

Aeronomy / solar ultraviolet mission Agency: ISAS. Apogee: 253 km (157 mi). References: 2. Level: 1.

1966 December 20 - 02:20 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 4S. LV Configuration: Lambda 4S L-4S-2. FAILURE: Fourth stage failed to ignite.

Ohsumi 2 Payload: L-4S-2. Mass: 26 kg (57 lb). Class: Technology. Spacecraft: Ohsumi. Agency: ISAS. Apogee: 400 km (240 mi). COSPAR: F661220A. Decay Date: 1966-12-19. References: 126. Level: 1.

1967 January 31 - 02:05 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-22.

Ionosphere / solar radio frequencies mission Agency: ISAS. Apogee: 327 km (203 mi). References: 2. Level: 1.

1967 February 6 - 02:10 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3H. LV Configuration: Lambda 3H L-3H-3.

Ionosphere / chemical release / x-ray astronomy mission Agency: ISAS. Apogee: 2,150 km (1,330 mi). References: 2. Level: 1.

1967 March 7 - 11:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-3.

Far ultraviolet Stellar photometer Ultraviolet astronomy / solar x-ray mission Agency: ISAS. Apogee: 248 km (154 mi). References: 2. Level: 1.

1967 April 13 - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 4S. LV Configuration: Lambda 4S L-4S-3. FAILURE: Fourth stage failed to ignite.

Ohsumi 3 Payload: L-4S-3. Mass: 26 kg (57 lb). Class: Technology. Spacecraft: Ohsumi. Agency: ISAS. Apogee: 200 km (120 mi). COSPAR: F670413A. Decay Date: 1967-04-13. References: 126. Level: 1.

1968 September 17 - 07:10 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: SA-II. LV Configuration: SA-II SA-II A9.

Test mission Agency: STA. Apogee: 20 km (12 mi). References: 2. Level: 1.

1968 September 19 - 01:58 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-C. LV Configuration: LS-C-D.

Test mission Agency: STA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1969 January 8 - 02:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-25.

Gyro-plasma probe Ionosphere / chemical release / fields mission Agency: ISAS. Apogee: 343 km (213 mi). References: 2. Level: 1.

1969 January 8 - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: S-250. LV Configuration: S-250 SO-250-B.

Test mission Agency: ISAS. Apogee: 100 km (60 mi). References: 2. Level: 1.

1969 January 9 - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-300 ISAS. LV Configuration: S-300-1. FAILURE: Failure.

Aeronomy mission Agency: ISAS. Apogee: 0 km ( mi). References: 2. Level: 1.

1969 January 9 - 07:40 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-15.

E field antenna Ionosphere / fields mission Agency: ISAS. Apogee: 188 km (116 mi). References: 2. Level: 1.

1969 January 12 - 05:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10C. LV Configuration: Kappa 10C K-10C-1.

Stability test Aeronomy / solar ultraviolet / test Agency: ISAS. Apogee: 229 km (142 mi). References: 2. Level: 1.

1969 January 14 - 10:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-4.

Langmuir probe Infrared / x-ray astronomy / solar ultraviolet mission Agency: ISAS. Apogee: 229 km (142 mi). References: 2. Level: 1.

1969 January 16 - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3H. LV Configuration: Lambda 3H L-3H-4.

Ionosphere mission Agency: ISAS. Apogee: 1,800 km (1,100 mi). References: 2. Level: 1.

1969 January 19 - 12:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-24.

Gryo-plasma probe Aeronomy / ionosphere / fields / mission Agency: ISAS. Apogee: 340 km (210 mi). References: 2. Level: 1.

1969 February 6 - 06:31 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-C. LV Configuration: LS-C-1.

Test mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1969 February 13 - 02:05 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-23.

Fields/Ultraviolet Astronomy mission Agency: ISAS. Apogee: 310 km (190 mi). References: 2. Level: 1.

1969 February 13 - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 PT-420-001.

TVC test (1-stage) test Agency: ISAS. Apogee: 100 km (60 mi). References: 2. Level: 1.

1969 August 7 - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-1.

Plasma / fields / x-ray astronomy mission Agency: ISAS. Apogee: 101 km (62 mi). References: 2. Level: 1.

1969 August 7 - 12:15 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-27.

X-ray sources Ionosphere / plasma / x-ray astronomy mission Agency: ISAS. Apogee: 340 km (210 mi). References: 2. Level: 1.

1969 August 8 - 12:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-2.

X-ray astronomy mission Agency: ISAS. Apogee: 108 km (67 mi). References: 2. Level: 1.

1969 August 17 - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-3D. LV Configuration: Mu-3D M-3D-1.

Test mission Agency: ISAS. Apogee: 160 km (90 mi). References: 2. Level: 1.

1969 August 24 - 08:04 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-26.

Radio noise Ionosphere / fields mission Agency: ISAS. Apogee: 341 km (211 mi). References: 2. Level: 1.

1969 August 24 - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-300 ISAS. LV Configuration: S-300-2.

Test mission Agency: ISAS. Apogee: 160 km (90 mi). References: 2. Level: 1.

1969 September 3 - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 4T. LV Configuration: Lambda 4T L-4T-1.

Test mission Agency: ISAS. Apogee: 400 km (240 mi). References: 2. Level: 1.

1969 September 6 - 11:35 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-5.

Zodiacal light Ionosphere / astronomy mission Agency: ISAS. Apogee: 247 km (153 mi). References: 2. Level: 1.

1969 September 10 - 06:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-C. LV Configuration: LS-C-2.

Test mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1969 September 15 - 01:40 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: JCR. LV Configuration: JCR-1.

Test mission Agency: NASDA. Apogee: 200 km (120 mi). References: 2. Level: 1.

1969 September 16 - 06:40 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: JCR. LV Configuration: JCR-2.

Test mission Agency: NASDA. Apogee: 200 km (120 mi). References: 2. Level: 1.

1969 September 22 - 02:10 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 4S. LV Configuration: Lambda 4S L-4S-4. FAILURE: Fourth stage control system malfunction after third stage collided with fourth stage.

Ohsumi 4 Payload: L-4S-4. Mass: 25 kg (55 lb). Class: Technology. Spacecraft: Ohsumi. Agency: ISAS. Apogee: 400 km (240 mi). COSPAR: F690922A. Decay Date: 1969-09-22. References: 126. Level: 1.

1969 September 26 - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10C. LV Configuration: Kappa 10C K-10C-2. FAILURE: Failure.

TVC test Agency: ISAS. Apogee: 300 km (180 mi). References: 2. Level: 1.

1970 January 17 - 01:20 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-3.

X-ray astronomy mission Agency: ISAS. Apogee: 119 km (73 mi). References: 2. Level: 1.

1970 January 21 - 02:10 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3H. LV Configuration: Lambda 3H L-3H-6.

Ionosphere / plasma mission Agency: ISAS. Apogee: 1,848 km (1,148 mi). References: 2. Level: 1.

1970 January 25 - 05:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-28.

Ionosphere mission Agency: ISAS. Apogee: 369 km (229 mi). References: 2. Level: 1.

1970 January 27 - 10:20 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-29.

Ionosphere mission Agency: ISAS. Apogee: 357 km (221 mi). References: 2. Level: 1.

1970 February 1 - 01:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: JCR. LV Configuration: JCR-3.

Test mission Agency: NASDA. Apogee: 200 km (120 mi). References: 2. Level: 1.

1970 February 3 - 06:03 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-C. LV Configuration: LS-C-3.

Test mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1970 February 4 - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: JCR. LV Configuration: JCR-4.

Test mission Agency: NASDA. Apogee: 200 km (120 mi). References: 2. Level: 1.

1970 February 11 - 04:25 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 4S. LV Configuration: Lambda 4S L-4S-5.

Ohsumi 5 Payload: L-4S-5. Mass: 12 kg (26 lb). Class: Technology. Spacecraft: Osumi. Agency: ISAS. Perigee: 323 km (200 mi). Apogee: 2,440 km (1,510 mi). Inclination: 31.00 deg. Period: 113.40 min. COSPAR: 1970-011A. USAF Sat Cat: 4330. Decay Date: 2003-08-02. Engineering tests. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E References: 2, 6. Level: 1.

1970 September 2 - 10:14 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 8. LV Configuration: Kappa 8 K-8-16.

Ionosphere / release mission Agency: ISAS. Apogee: 174 km (108 mi). References: 2. Level: 1.

1970 September 9 - 06:40 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-C. LV Configuration: LS-C-4.

Test mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1970 September 13 - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10C. LV Configuration: Kappa 10C K-10C-3.

TVC test Agency: ISAS. Apogee: 300 km (180 mi). References: 2. Level: 1.

1970 September 19 - 11:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3H. LV Configuration: Lambda 3H L-3H-5.

X-ray / ultraviolet astronomy mission Agency: ISAS. Apogee: 2,017 km (1,253 mi). References: 2. Level: 1.

1970 September 25 - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-4S. LV Configuration: Mu-4S M-4S-1. FAILURE: Fourth stage failed to ignite.

SS Payload: MS-F1. Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. Apogee: 712 km (442 mi). COSPAR: F700925A. Decay Date: 1970-09-25. References: 126. Level: 1.

1970 September 27 - 06:42 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-32.

B field Ionosphere mission Agency: ISAS. Apogee: 346 km (214 mi). References: 2. Level: 1.

1970 September 28 - 01:20 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-5.

Ionosphere mission Agency: ISAS. Apogee: 108 km (67 mi). References: 2. Level: 1.

1971 January 16 - 07:15 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-30.

Ionosphere mission Agency: ISAS. Apogee: 357 km (221 mi). References: 2. Level: 1.

1971 January 16 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-4.

Ionosphere mission Agency: ISAS. Apogee: 115 km (71 mi). References: 2. Level: 1.

1971 January 23 - 13:20 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-35.

Ionosphere mission Agency: ISAS. Apogee: 338 km (210 mi). References: 2. Level: 1.

1971 January 24 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-34.

Sco X-1 X-ray astronomy / solar ultraviolet mission Agency: ISAS. Apogee: 328 km (203 mi). References: 2. Level: 1.

1971 February 1 - 01:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: JCR. LV Configuration: JCR-5.

Test mission Agency: NASDA. Apogee: 200 km (120 mi). References: 2. Level: 1.

1971 February 16 - 04:00 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-4S. LV Configuration: Mu-4S M-4S-2.

Tansei 1 Payload: MS T1. Mass: 62 kg (136 lb). Class: Technology. Spacecraft: Tansei. Agency: ISAS. Perigee: 986 km (612 mi). Apogee: 1,106 km (687 mi). Inclination: 29.70 deg. Period: 106.10 min. COSPAR: 1971-011A. USAF Sat Cat: 4952. Engineering test for the launching of scientific satellites. Injection point 29.7 N, 145.8 E References: 2, 6. Level: 1.

1971 May 26 - 10:10 GMT - Launch Site: Barking Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. Model: Nike Tomahawk.

LEINAX I X-ray astronomy mission Agency: Sandia. Apogee: 209 km (129 mi). References: 2. Level: 1.

1971 June 24 - 01:05 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-4.

Auroral mission Agency: NIPR. Apogee: 130 km (80 mi). References: 2. Level: 1.

1971 July 21 - 21:52 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-3.

Auroral mission Agency: NIPR. Apogee: 131 km (81 mi). References: 2. Level: 1.

1971 August 10 - 02:24 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-1.

Auroral mission Agency: NIPR. Apogee: 139 km (86 mi). References: 2. Level: 1.

1971 August 18 - 12:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-31.

X-ray astronomy mission Agency: ISAS. Apogee: 330 km (200 mi). References: 2. Level: 1.

1971 August 20 - 12:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-7.

Optical astronomy mission Agency: ISAS. Apogee: 274 km (170 mi). References: 2. Level: 1.

1971 August 20 - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 4SC. LV Configuration: Lambda 4SC L-4SC-1. FAILURE: Failure.

TVC test Agency: ISAS. Apogee: 1,500 km (900 mi). References: 2. Level: 1.

1971 August 25 - 05:40 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-36. FAILURE: Failure.

Ionosphere mission Agency: ISAS. Apogee: 0 km ( mi). References: 2. Level: 1.

1971 August 26 - 10:35 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-33.

Cs / Ba Release Ionosphere mission Agency: ISAS. Apogee: 340 km (210 mi). References: 2. Level: 1.

1971 September 1 - 02:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-6.

Solar ultraviolet Solar ultraviolet mission Agency: ISAS. Apogee: 228 km (141 mi). References: 2. Level: 1.

1971 September 3 - 12:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3H. LV Configuration: Lambda 3H L-3H-7.

Aeronomy / ionosphere / x-ray astronomy mission Agency: ISAS. Apogee: 1,718 km (1,067 mi). References: 2. Level: 1.

1971 September 10 - 06:47 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-C. LV Configuration: LS-C-5.

Test mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1971 September 11 - 01:45 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: S-B. LV Configuration: S-B SB-III A15.

Test mission Agency: STA. Apogee: 75 km (46 mi). References: 2. Level: 1.

1971 September 13 - 21:50 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-5.

Auroral mission Agency: NIPR. Apogee: 115 km (71 mi). References: 2. Level: 1.

1971 September 17 - 06:40 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: JCR. LV Configuration: JCR-6.

Test mission Agency: NASDA. Apogee: 200 km (120 mi). References: 2. Level: 1.

1971 September 24 - 21:08 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-2.

Auroral mission Agency: NIPR. Apogee: 138 km (85 mi). References: 2. Level: 1.

1971 September 28 - 04:00 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-4S. LV Configuration: Mu-4S M-4S-3.

SS-01 Shinsei Payload: MS-F2. Mass: 65 kg (143 lb). Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. Perigee: 872 km (541 mi). Apogee: 1,866 km (1,159 mi). Inclination: 32.00 deg. Period: 113.10 min. COSPAR: 1971-080A. USAF Sat Cat: 5485. Scientific observations in outer space. Injection point 29 deg 7 min N, 145 deg 8 min E. References: 2, 6. Level: 1.

1971 December 3 - 12:00 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-6.

Auroral mission Agency: NIPR. Apogee: 131 km (81 mi). References: 2. Level: 1.

1972 January 21 - 02:24 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-6.

Ionosphere mission Agency: ISAS. Apogee: 112 km (69 mi). References: 2. Level: 1.

1972 January 23 - 11:22 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-37.

Ionosphere mission Agency: ISAS. Apogee: 340 km (210 mi). References: 2. Level: 1.

1972 January 29 - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210 DT-210-1.

Structural Dynamics test Agency: ISAS. Apogee: 100 km (60 mi). References: 2. Level: 1.

1972 February 6 - 06:35 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: JCR. LV Configuration: JCR-7.

Test mission Agency: NASDA. Apogee: 200 km (120 mi). References: 2. Level: 1.

1972 February 11 - 12:00 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-12.

Mass spectrometer Ionosphere mission Agency: NIPR. Apogee: 108 km (67 mi). References: 2. Level: 1.

1972 February 17 - 08:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-7.

Ionosphere mission Agency: ISAS. Apogee: 118 km (73 mi). References: 2. Level: 1.

1972 February 18 - 09:28 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-39.

Cesium Release Ionosphere mission Agency: ISAS. Apogee: 310 km (190 mi). References: 2. Level: 1.

1972 February 22 - 06:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-38.

Aeronomy / ionosphere mission Agency: ISAS. Apogee: 352 km (218 mi). References: 2. Level: 1.

1972 April 16 - 23:42 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-160. LV Configuration: S-160JA-4.

Ionosphere mission Agency: NIPR. Apogee: 86 km (53 mi). References: 2. Level: 1.

1972 May 13 - 23:13 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-9.

Aurora / ionosphere / fields mission Agency: NIPR. Apogee: 129 km (80 mi). References: 2. Level: 1.

1972 May 15 - 23:02 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-10.

Aurora / ionosphere / fields mission Agency: NIPR. Apogee: 115 km (71 mi). References: 2. Level: 1.

1972 May 22 - 12:00 GMT - Launch Site: Barking Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Tomahawk Sandia. Model: Nike Tomahawk. LV Configuration: Nike Tomahawk LEINAX II.

X-ray astronomy mission Agency: Sandia. Apogee: 270 km (160 mi). References: 2. Level: 1.

1972 August 7 - 01:45 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-11.

Aurora / ionosphere / fields mission Agency: NIPR. Apogee: 126 km (78 mi). References: 2. Level: 1.

1972 August 11 - 01:01 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-8.

Ionosphere / fields mission Agency: NIPR. Apogee: 127 km (78 mi). References: 2. Level: 1.

1972 August 19 - 02:40 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-4S. LV Configuration: Mu-4S M-4S-4.

SS-02 Denpa Payload: REXS. Mass: 75 kg (165 lb). Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. Perigee: 238 km (147 mi). Apogee: 6,322 km (3,928 mi). Inclination: 31.00 deg. Period: 157.40 min. COSPAR: 1972-064A. USAF Sat Cat: 6152. Decay Date: 1980-05-19. Ionospheric experiments. Scientific observations in the ionosphere and magnetosphere. Interjection point 31 deg 15' N 11 deg 05' E. References: 2, 6. Level: 1.

1972 September 12 - 11:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-8.

Fiberglass Casing Infrared astronomy / x-ray astronomy mission Agency: ISAS. Apogee: 259 km (160 mi). References: 2. Level: 1.

1972 September 20 - 05:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-40.

Ionosphere mission Agency: ISAS. Apogee: 326 km (202 mi). References: 2. Level: 1.

1972 September 25 - 06:05 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-C. LV Configuration: LS-C-6.

Test mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1972 December 13 - 21:23 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-7.

Aurora / ionosphere / fields mission Agency: NIPR. Apogee: 126 km (78 mi). References: 2. Level: 1.

1973 January 15 - 23:40 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-8.

Ionosphere mission Agency: ISAS. Apogee: 122 km (75 mi). References: 2. Level: 1.

1973 January 19 - 09:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-41.

VLF Ionosphere / active plasma mission Agency: ISAS. Apogee: 330 km (200 mi). References: 2. Level: 1.

1973 January 28 - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 4SC. LV Configuration: Lambda 4SC L-4SC-2.

TVC test Agency: ISAS. Apogee: 1,500 km (900 mi). References: 2. Level: 1.

1973 February 7 - 01:50 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: JCR. LV Configuration: JCR-8.

Test mission Agency: NASDA. Apogee: 200 km (120 mi). References: 2. Level: 1.

1973 February 14 - 20:45 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-16.

Auroral mission Agency: NIPR. Apogee: 103 km (64 mi). References: 2. Level: 1.

1973 February 19 - 00:22 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-9.

Aeronomy / ionosphere / solar ultraviolet mission Agency: ISAS. Apogee: 236 km (146 mi). References: 2. Level: 1.

1973 February 23 - 09:38 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-42.

Cesium Release Ionosphere mission Agency: ISAS. Apogee: 306 km (190 mi). References: 2. Level: 1.

1973 March 25 - 17:47 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-14.

Auroral mission Agency: NIPR. Apogee: 114 km (70 mi). References: 2. Level: 1.

1973 April 22 - 18:25 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-17.

Auroral mission Agency: NIPR. Apogee: 124 km (77 mi). References: 2. Level: 1.

1973 June 10 - 17:20 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-13.

Auroral mission Agency: NIPR. Apogee: 123 km (76 mi). References: 2. Level: 1.

1973 June 11 - 18:10 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-15.

Auroral mission Agency: NIPR. Apogee: 125 km (77 mi). References: 2. Level: 1.

1973 July 15 - 16:09 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-19.

Auroral mission Agency: NIPR. Apogee: 131 km (81 mi). References: 2. Level: 1.

1973 August 19 - 09:55 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-9.

Aeronomy mission Agency: ISAS. Apogee: 115 km (71 mi). References: 2. Level: 1.

1973 August 21 - 07:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-43.

Plasma / ionosphere mission Agency: ISAS. Apogee: 355 km (220 mi). References: 2. Level: 1.

1973 August 22 - 21:53 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-18.

Auroral arc Aurora mission Agency: NIPR. Apogee: 129 km (80 mi). References: 2. Level: 1.

1973 August 27 - 12:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-44.

X-ray astronomy mission Agency: ISAS. Apogee: 341 km (211 mi). References: 2. Level: 1.

1973 September 7 - 01:40 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: JCR. LV Configuration: JCR-9.

Test mission Agency: NASDA. Apogee: 200 km (120 mi). References: 2. Level: 1.

1973 September 22 - 09:20 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-10.

X-ray astronomy / ionosphere mission Agency: ISAS. Apogee: 242 km (150 mi). References: 2. Level: 1.

1974 January 16 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-45.

Ionosphere-solar mission Ionosphere-solar mission Agency: ISAS. Apogee: 360 km (220 mi). References: 2. Level: 1.

1974 January 22 - 11:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3H. LV Configuration: Lambda 3H L-3H-8.

St 2: 329 km X-ray astronomy mission Agency: ISAS. Apogee: 1,571 km (976 mi). References: 2. Level: 1.

1974 February 1 - 06:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: JCR. LV Configuration: JCR-10.

Test mission Agency: NASDA. Apogee: 200 km (120 mi). References: 2. Level: 1.

1974 February 9 - 06:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: Lambda. Model: LS-C. LV Configuration: LS-C-7.

LE-3 test Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1974 February 16 - 05:00 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-3C. LV Configuration: Mu-3C M-3C-1.

Tansei 2 Payload: MS T2. Mass: 65 kg (143 lb). Class: Technology. Spacecraft: Tansei. Agency: ISAS. Perigee: 284 km (176 mi). Apogee: 3,231 km (2,007 mi). Inclination: 31.20 deg. Period: 121.70 min. COSPAR: 1974-008A. USAF Sat Cat: 7122. Decay Date: 1983-01-22. Attitude control satellite (performance test of launch vehicle). References: 2, 6. Level: 1.

1974 August 20 - 09:55 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-10.

NNP / NEL / TEL Aeronomy / ionosphere mission Agency: ISAS. Apogee: 112 km (69 mi). References: 2. Level: 1.

1974 September 1 - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 4SC. LV Configuration: Lambda 4SC L-4SC-3.

TVC test Agency: ISAS. Apogee: 1,500 km (900 mi). References: 2. Level: 1.

1974 September 2 - 06:00 GMT - Launch Site: Tanegashima. Launch Complex: Q. Launch Pad: -. Launch Vehicle: Mu. Model: ETV. LV Configuration: ETV-1.

Test mission Agency: NASDA. Apogee: 128 km (79 mi). References: 2. Level: 1.

1974 September 16 - 15:40 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-46.

Plasma gun M / D Ionosphere mission Agency: ISAS. Apogee: 336 km (208 mi). References: 2. Level: 1.

1974 September 19 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-47.

Ionosphere mission Agency: ISAS. Apogee: 328 km (203 mi). References: 2. Level: 1.

1974 September 20 - 11:32 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-48.

Precipitate Electrons Ionosphere / x-ray / ultraviolet mission Agency: ISAS. Apogee: 348 km (216 mi). References: 2. Level: 1.

1975 January 1 - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-1.

Test mission Agency: ISAS. Apogee: 200 km (120 mi). References: 2. Level: 1.

1975 January 17 - 09:35 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-49.

Airglow Aeronomy / ionosphere mission Agency: ISAS. Apogee: 363 km (225 mi). References: 2. Level: 1.

1975 January 23 - 11:05 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-50.

X-ray astronomy mission Agency: ISAS. Apogee: 353 km (219 mi). References: 2. Level: 1.

1975 February 5 - 06:00 GMT - Launch Site: Tanegashima. Launch Complex: Q. Launch Pad: -. Launch Vehicle: Mu. Model: ETV. LV Configuration: ETV-2.

Test mission Agency: NASDA. Apogee: 167 km (103 mi). References: 2. Level: 1.

1975 February 24 - 05:25 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-3C. LV Configuration: Mu-3C M-3C-2.

SS-03 Taiyo Payload: SRATS. Mass: 86 kg (189 lb). Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. Perigee: 254 km (157 mi). Apogee: 3,125 km (1,941 mi). Inclination: 31.50 deg. Period: 120.20 min. COSPAR: 1975-014A. USAF Sat Cat: 7671. Decay Date: 1980-06-29. Examined solar radiation, thermospheric structure. SRATS (Solar and Thermospheric Radiation Satellite) is the third Japanese scientific satellite, to study the intereffects of solar radiation and the thermosphere of the earth. National name: Taiyo. Launch time 0525 GMT. References: 2, 6. Level: 1.

1975 August 17 - 06:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-210. LV Configuration: TT-210 TT-210-1F.

Test mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1975 August 26 - 10:40 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-53.

Ionosphere mission Agency: ISAS. Apogee: 351 km (218 mi). References: 2. Level: 1.

1975 August 30 - 04:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-2.

Ionosphere mission Agency: ISAS. Apogee: 191 km (118 mi). References: 2. Level: 1.

1975 September 2 - 12:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-51.

Ionosphere mission Agency: ISAS. Apogee: 311 km (193 mi). References: 2. Level: 1.

1975 September 9 - 05:30 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-1. LV Configuration: N-1 N-1(F).

Kiku 1 Payload: ETS 1 (JETS). Mass: 85 kg (187 lb). Class: Technology. Spacecraft: ETS. Agency: NASDA. Perigee: 975 km (605 mi). Apogee: 1,103 km (685 mi). Inclination: 47.00 deg. Period: 106.00 min. COSPAR: 1975-082A. USAF Sat Cat: 8197. 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. References: 2, 6. Level: 1.

1975 September 23 - 12:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-52.

Soft X-ray X-ray astronomy mission Agency: ISAS. Apogee: 336 km (208 mi). References: 2. Level: 1.

1975 September 24 - 05:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-11.

X-ray astronomy / solar ultraviolet mission Agency: ISAS. Apogee: 196 km (121 mi). References: 2. Level: 1.

1976 January 16 - 21:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-54.

Magnetospheric mission Agency: ISAS. Apogee: 367 km (228 mi). References: 2. Level: 1.

1976 January 18 - 05:20 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-12.

Ionosphere mission Agency: ISAS. Apogee: 350 km (210 mi). References: 2. Level: 1.

1976 January 25 - 23:20 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-22.

NO / Ne Aeronomy / ionosphere mission Agency: NIPR. Apogee: 127 km (78 mi). References: 2. Level: 1.

1976 January 27 - 06:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-210. LV Configuration: TT-210 TT-210-2F.

Test mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1976 February 4 - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-3C. LV Configuration: Mu-3C M-3C-3. FAILURE: Stage 2 thrust vector control failure.

Corsa A Mass: 92 kg (202 lb). Class: Technology. Spacecraft: Corsa A. Agency: ISAS. COSPAR: F760204A. Decay Date: 1976-02-04. References: 126. Level: 1.

1976 February 13 - 09:45 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310JA-1.

VLF / HF Ionosphere mission Agency: NIPR. Apogee: 216 km (134 mi). References: 2. Level: 1.

1976 February 29 - 03:30 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-1. LV Configuration: N-1 N-2(F).

ISS 1 Payload: ISS a. Mass: 139 kg (306 lb). Class: Earth. Type: Ionosphere. Spacecraft: JISS. Agency: NASDA. Perigee: 988 km (613 mi). Apogee: 1,003 km (623 mi). Inclination: 69.70 deg. Period: 105.00 min. COSPAR: 1976-019A. USAF Sat Cat: 8709. 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. References: 2, 6. Level: 1.

1976 May 29 - 09:49 GMT - Launch Site: Barking Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Sandhawk. Model: Terrier Sandhawk. LV Configuration: Terrier Sandhawk Sandia.

LEINAX IV X-ray astronomy mission Agency: Sandia. Apogee: 271 km (168 mi). References: 2. Level: 1.

1976 June 24 - 23:40 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-20.

VLF / HF / ne Aurora mission Agency: NIPR. Apogee: 118 km (73 mi). References: 2. Level: 1.

1976 July 26 - 00:23 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-21.

VLF / HF / ne / ISIS-2 Aurora mission Agency: NIPR. Apogee: 116 km (72 mi). References: 2. Level: 1.

1976 August 16 - 23:54 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-24.

E / B / ne Aurora mission Agency: NIPR. Apogee: 118 km (73 mi). References: 2. Level: 1.

1976 August 17 - 10:15 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-11.

Aeronomy / ionosphere mission Agency: ISAS. Apogee: 112 km (69 mi). References: 2. Level: 1.

1976 August 21 - 12:10 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-3.

Ionosphere mission Agency: ISAS. Apogee: 195 km (121 mi). References: 2. Level: 1.

1976 August 30 - 19:55 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-57.

Ionosphere / fields mission Agency: ISAS. Apogee: 288 km (178 mi). References: 2. Level: 1.

1976 September 1 - 00:00 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-25.

E / B / ne Aurora mission Agency: NIPR. Apogee: 125 km (77 mi). References: 2. Level: 1.

1976 September 13 - 04:31 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-23.

NO / Ne / ISIS-2 Aurora mission Agency: NIPR. Apogee: 120 km (70 mi). References: 2. Level: 1.

1976 September 16 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-55.

Ionosphere / fields mission Agency: ISAS. Apogee: 359 km (223 mi). References: 2. Level: 1.

1976 September 18 - 10:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-56.

Ionosphere / fields mission Agency: ISAS. Apogee: 300 km (180 mi). References: 2. Level: 1.

1976 September 24 - 01:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-210. LV Configuration: TT-210 TT-210-3F.

Test mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1977 January 16 - 12:45 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-58.

Near infrared Galactic Plane Infrared astronomy / ionosphere mission Agency: ISAS. Apogee: 324 km (201 mi). References: 2. Level: 1.

1977 January 25 - 01:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500. LV Configuration: TT-500 TT-500-1F.

Test mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1977 February 10 - 00:22 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310JA-2.

VLF / HF Ionosphere mission Agency: NIPR. Apogee: 212 km (131 mi). References: 2. Level: 1.

1977 February 19 - 05:15 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-3H. LV Configuration: Mu-3H M-3H-1.

Tansei 3 Payload: MS T3. Mass: 230 kg (500 lb). Class: Technology. Spacecraft: Tansei. Agency: ISAS. Perigee: 799 km (496 mi). Apogee: 3,802 km (2,362 mi). Inclination: 65.80 deg. Period: 134.10 min. COSPAR: 1977-012A. USAF Sat Cat: 9841. Tentative name before launching: MS-T3. Launching organization: Institute of Space and Aeronautical Science, University of Tokyo. Radio frequencies: 136.725 MHz, tracking; 400.500 MHz, telemetry. Active life: two weeks. Function: (1) Test of the overall p erformance of the newly developed launch vehicle, M-3H-1. (2) Experiment of magnetic stabilization. (3) Observation of ultraviolet radiation. References: 2, 6. Level: 1.

1977 February 23 - 08:50 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-1. LV Configuration: N-1 N-3(F).

Kiku 2 Payload: ETS 2. Mass: 130 kg (280 lb). Class: Technology. 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. COSPAR: 1977-014A. USAF Sat Cat: 9852. Completed Operations Date: 1990-12-01. 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. References: 2, 6. Level: 1.

1977 March 27 - 03:55 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-28.

NO / O3 / Ne Aeronomy mission Agency: NIPR. Apogee: 106 km (65 mi). References: 2. Level: 1.

1977 April 11 - 05:00 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-26.

NO / O3 / Ne Aeronomy mission Agency: NIPR. Apogee: 105 km (65 mi). References: 2. Level: 1.

1977 July 12 - 16:15 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-29.

E / B / ne / ISIS-2 Aurora mission Agency: NIPR. Apogee: 118 km (73 mi). References: 2. Level: 1.

1977 July 14 - 10:39 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17B. Launch Pad: -. Launch Vehicle: Delta. Model: Delta 2914. LV Configuration: Delta 2914 618/D132.

Himawari 1 Payload: GMS 1. Mass: 670 kg (1,470 lb). Class: Earth. Type: Weather. Spacecraft: GMS. Agency: NASDA. Perigee: 36,005 km (22,372 mi). Apogee: 36,148 km (22,461 mi). Inclination: 11.10 deg. Period: 1,451.00 min. COSPAR: 1977-065A. USAF Sat Cat: 10143. Completed Operations Date: 1989-09-17. 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. References: 2, 6. Level: 1.

1977 July 26 - 15:35 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310JA-3.

VLF / plasma / B Ionosphere mission Agency: NIPR. Apogee: 221 km (137 mi). References: 2. Level: 1.

1977 August 10 - 12:47 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-27.

NO airglow Aurora mission Agency: NIPR. Apogee: 120 km (70 mi). References: 2. Level: 1.

1977 August 16 - 11:15 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: -. Launch Vehicle: Lambda. Model: Lambda 3H. LV Configuration: Lambda 3H L-3H-9.

Aeronomy / ionosphere / plasma mission Agency: ISAS. Apogee: 1,294 km (804 mi). References: 2. Level: 1.

1977 August 25 - 01:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500. LV Configuration: TT-500 TT-500-2F.

Test mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1977 September 3 - 10:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-59.

Aeronomy / ionosphere / solar extreme ultraviolet mission Agency: ISAS. Apogee: 376 km (233 mi). References: 2. Level: 1.

1977 September 14 - 12:22 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-13.

Ultraviolet astronomy / extreme ultraviolet astronomy mission Agency: ISAS. Apogee: 204 km (126 mi). References: 2. Level: 1.

1977 September 15 - 09:30 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210-12.

Aeronomy / ionosphere mission Agency: ISAS. Apogee: 114 km (70 mi). References: 2. Level: 1.

1977 September 21 - 08:35 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-4.

Ionosphere mission Agency: ISAS. Apogee: 188 km (116 mi). References: 2. Level: 1.

1977 December 15 - 00:47 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17B. Launch Pad: -. Launch Vehicle: Delta. Model: Delta 2914. LV Configuration: Delta 2914 624/D137.

Sakura Program: CS. Payload: CS-1A. Mass: 676 kg (1,490 lb). Class: Communications. Spacecraft: CS-1. Agency: NASDA. Perigee: 36,169 km (22,474 mi). Apogee: 36,176 km (22,478 mi). Inclination: 10.50 deg. Period: 1,455.90 min. COSPAR: 1977-118A. USAF Sat Cat: 10516. Completed Operations Date: 1985-11-19. 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. References: 2, 6. Level: 1.

1978 January 16 - 01:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500. LV Configuration: TT-500 TT-500-3F.

Test mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1978 January 22 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-62.

Ionosphere / fields / solar mission Agency: ISAS. Apogee: 369 km (229 mi). References: 2. Level: 1.

1978 January 27 - 11:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-61.

Aeronomy / ionosphere / plasma mission Agency: ISAS. Apogee: 292 km (181 mi). References: 2. Level: 1.

1978 January 28 - 20:20 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-30.

Aurora mission Agency: NIPR. Apogee: 125 km (77 mi). References: 2. Level: 1.

1978 February 4 - 07:00 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-3H. LV Configuration: Mu-3H M-3H-2.

SS-05 Kyokko Payload: Exos A. Mass: 103 kg (227 lb). Class: Earth. Type: Ionosphere. Spacecraft: EXOS. Agency: ISAS. Perigee: 639 km (397 mi). Apogee: 3,952 km (2,455 mi). Inclination: 65.40 deg. Period: 134.00 min. COSPAR: 1978-014A. USAF Sat Cat: 10664. Auroral studies. Active life - two years. Function: 1) Observation of wide angle global auroral pictures using UV television camera. 2) Spectrophotometry of ultraviolet air glow. 3) Observation of the energy spectrum of photoelectrons and auroral electrons. 4) Mass spect rometry of the ionized atmospheric species in the thermosphere. 5) Measurements of density and temperature of ambient electrons in the thermosphere. 6) Observation of electromagnetic and plasma waves and the emission associated with auroral phenomena. References: 2, 6. Level: 1.

1978 February 6 - 18:55 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-210. LV Configuration: S-210JA-31.

Aurora mission Agency: NIPR. Apogee: 116 km (72 mi). References: 2. Level: 1.

1978 February 16 - 04:00 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-1. LV Configuration: N-1 N-4(F).

ISS 2 Payload: ISS b. Mass: 140 kg (300 lb). Class: Earth. Type: Ionosphere. Spacecraft: JISS. Agency: NASDA. Perigee: 973 km (604 mi). Apogee: 1,216 km (755 mi). Inclination: 69.40 deg. Period: 107.20 min. COSPAR: 1978-018A. USAF Sat Cat: 10674. 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. References: 2, 6. Level: 1.

1978 February 26 - 11:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-60.

Ultraviolet astronomy / extreme ultraviolet astronomy mission Agency: ISAS. Apogee: 340 km (210 mi). References: 2. Level: 1.

1978 April 7 - 22:01 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17B. Launch Pad: -. Launch Vehicle: Delta. Model: Delta 2914. LV Configuration: Delta 2914 626/D140.

Yuri 1 Program: BS. Payload: BSE-1. Mass: 678 kg (1,494 lb). Class: Technology. Type: Comsat. Spacecraft: Yuri. Agency: NASDA. Perigee: 35,736 km (22,205 mi). Apogee: 35,868 km (22,287 mi). Inclination: 11.70 deg. Period: 1,436.90 min. COSPAR: 1978-039A. USAF Sat Cat: 10792. Completed Operations Date: 1982-01-28. 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. References: 2, 6. Level: 1.

1978 August 20 - 11:30 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-64.

Near infrared Galactic Plane Test / infrared astronomy / ultraviolet astronomy mission Agency: ISAS. Apogee: 319 km (198 mi). References: 2. Level: 1.

1978 August 25 - 01:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500. LV Configuration: TT-500 TT-500-4F.

Test mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1978 September 16 - 05:00 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-3H. LV Configuration: Mu-3H M-3H-3.

SS-06 Jikiken Payload: Exos B. Mass: 100 kg (220 lb). Class: Earth. Type: Ionosphere. Spacecraft: EXOS. Agency: ISAS. Perigee: 251 km (155 mi). Apogee: 21,192 km (13,168 mi). Inclination: 31.30 deg. Period: 370.90 min. COSPAR: 1978-087A. USAF Sat Cat: 11027. Launching organization: Institute of Space and Aeronautical Science, University of Tokyo. Stimulated plasma wave experiment, natural plasma wave measurement, plasma parameter measurement by VLF Doppler technique, electric field probe and plasma density me asurement, energetic particle analysis, and controlled electron beam emission experiment. Characteristics: weight 90.5 kg, configuration - polyhedron with 38 faces, height 0.6m , diameter 0.75m, attitude control spin stabilization, life two years. References: 2, 6. Level: 1.

1979 January 16 - 20:50 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-65.

Aeronomy / ionosphere mission Agency: ISAS. Apogee: 353 km (219 mi). References: 2. Level: 1.

1979 January 19 - 08:50 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-6.

Aeronomy / ionosphere mission Agency: ISAS. Apogee: 212 km (131 mi). References: 2. Level: 1.

1979 January 21 - 09:06 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-66.

Test / aeronomy / ionosphere / plasma mission Agency: ISAS. Apogee: 336 km (208 mi). References: 2. Level: 1.

1979 January 27 - 01:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500. LV Configuration: TT-500 TT-500-5F.

Test mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1979 January 31 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-5.

Ionosphere / fields mission Agency: ISAS. Apogee: 185 km (114 mi). References: 2. Level: 1.

1979 February 6 - 08:46 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-1. LV Configuration: N-1 N-5(F). FAILURE: Third stage collided with ECS a.

Ayame 1 Payload: ECS a; ECS 1. Mass: 260 kg (570 lb). Class: Technology. Type: Comsat. 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. COSPAR: 1979-009A. USAF Sat Cat: 11261. Completed Operations Date: 1979-02-09. 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. References: 2, 6. Level: 1.

1979 February 21 - 05:00 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-3C. LV Configuration: Mu-3C M-3C-4.

SS-04 Hakucho Payload: Corsa B. Mass: 100 kg (220 lb). Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. Perigee: 543 km (337 mi). Apogee: 566 km (351 mi). Inclination: 29.80 deg. Period: 95.70 min. COSPAR: 1979-014A. USAF Sat Cat: 11272. Decay Date: 1985-04-15. Soft X-ray telescope. Launching organization: Institute of Space and Aeronautical Science, University of Tokyo. Function: Observation of X-ray radiation of celestial bodies with good time resolution over a wide spectrum range. Characterstics: weight 96 kg, configuration regula r octagonal prism, height 0.66 m, diameter 0.76m, spin stabilized. Expected life 2 years. References: 2, 6. Level: 1.

1979 August 18 - 07:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-67.

TED / TPI / NEL / PWN Ionosphere mission Agency: ISAS. Apogee: 365 km (226 mi). References: 2. Level: 1.

1979 August 25 - 01:40 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500. LV Configuration: TT-500 TT-500-6F.

Test mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1979 September 11 - 01:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-68.

SUV / AUV / NEL / EPA Ionosphere / solar ultraviolet mission Agency: ISAS. Apogee: 353 km (219 mi). References: 2. Level: 1.

1979 September 15 - 11:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-7.

Aeronomy mission Agency: ISAS. Apogee: 166 km (103 mi). References: 2. Level: 1.

1980 January 16 - 03:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-69.

TPE-1 Ionosphere / tether mission Agency: ISAS. Apogee: 328 km (203 mi). References: 2. Level: 1.

1980 January 18 - 06:20 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-1.

Heat Pipe Aeronomy / ionosphere mission Agency: ISAS. Apogee: 329 km (204 mi). References: 2. Level: 1.

1980 January 28 - 01:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500. LV Configuration: TT-500 TT-500-7F.

Test mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1980 February 2 - 08:47 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-8.

Aeronomy mission Agency: ISAS. Apogee: 179 km (111 mi). References: 2. Level: 1.

1980 February 17 - 00:40 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-3S. LV Configuration: Mu-3S M-3S-1.

Tansei 4 Payload: MS T4. Mass: 134 kg (295 lb). Class: Technology. Spacecraft: Tansei. Agency: ISAS. Perigee: 517 km (321 mi). Apogee: 608 km (377 mi). Inclination: 38.70 deg. Period: 95.90 min. COSPAR: 1980-015A. USAF Sat Cat: 11706. Decay Date: 1983-05-12. References: 2, 6. Level: 1.

1980 February 22 - 08:35 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-1. LV Configuration: N-1 N-6(F).

Ayame 2 Payload: ECS b; ECS 2. Mass: 260 kg (570 lb). Class: Technology. Type: Comsat. 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. COSPAR: 1980-018A. USAF Sat Cat: 11715. Completed Operations Date: 1980-02-24. Last known longitude (17 November 1988) 146.47 deg W drifting at 12.888 deg E per day. References: 2, 6. Level: 1.

1980 August 26 - 11:40 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 10. LV Configuration: Kappa 10 K-10-14.

GIR / GXV / STS X-ray astronomy / infrared astronomy mission Agency: ISAS. Apogee: 219 km (136 mi). References: 2. Level: 1.

1980 September 2 - 10:40 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-70.

Test / aeronomy / ionosphere mission Agency: ISAS. Apogee: 230 km (140 mi). References: 2. Level: 1.

1980 September 4 - 12:45 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-71.

Aeronomy mission Agency: ISAS. Apogee: 308 km (191 mi). References: 2. Level: 1.

1980 September 13 - 22:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500A. LV Configuration: TT-500A TT-500A-8F.

Test mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1981 January 14 - 22:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500A. LV Configuration: TT-500A TT-500A-9F.

Test mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1981 January 21 - 21:46 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-9.

Aeronomy mission Agency: ISAS. Apogee: 174 km (108 mi). References: 2. Level: 1.

1981 January 29 - 07:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-2.

TPE-2 Ionosphere / tether mission Agency: ISAS. Apogee: 323 km (200 mi). References: 2. Level: 1.

1981 February 11 - 08:30 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-2. LV Configuration: N-2 N-7(F).

Kiku 3 Payload: ETS 4. Mass: 640 kg (1,410 lb). Class: Technology. Spacecraft: ETS. Agency: NASDA. Perigee: 305 km (189 mi). Apogee: 16,237 km (10,089 mi). Inclination: 28.50 deg. Period: 294.10 min. COSPAR: 1981-012A. USAF Sat Cat: 12295. 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. References: 2, 6. Level: 1.

1981 February 21 - 00:30 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: -. Launch Vehicle: Mu. Model: Mu-3S. LV Configuration: Mu-3S M-3S-2.

SS-07 Hinotori Payload: Astro A. Mass: 185 kg (407 lb). Class: Astronomy. Spacecraft: Astro. Agency: ISAS. Perigee: 274 km (170 mi). Apogee: 279 km (173 mi). Inclination: 31.30 deg. Period: 90.10 min. COSPAR: 1981-017A. USAF Sat Cat: 12307. Decay Date: 1991-07-11. Hinotori (ASTRO-A). Launching organisation: Institute of Space and Aeronautical Science, University of Tokyo. Investigation of solar flare by X-ray telescope and spectrograph. References: 2, 6. Level: 1.

1981 August 1 - 22:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500A. LV Configuration: TT-500A TT-500A-10F.

Test mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1981 August 10 - 20:03 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-2. LV Configuration: N-2 N-8(F).

Himawari 2 Payload: GMS 2. Mass: 670 kg (1,470 lb). Class: Earth. Type: Weather. 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. COSPAR: 1981-076A. USAF Sat Cat: 12677. Completed Operations Date: 1988-02-01. 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. References: 2, 6. Level: 1.

1981 August 24 - 12:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-10.

Test / aurora / aeronomy mission Agency: ISAS. Apogee: 187 km (116 mi). References: 2. Level: 1.

1981 September 5 - 01:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-4.

Payload recovery rest / ionosphere mission Agency: ISAS. Apogee: 224 km (139 mi). References: 2. Level: 1.

1981 September 7 - 09:38 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-11.

Submillimeter atmospheric spectra Aeronomy mission Agency: ISAS. Apogee: 193 km (119 mi). References: 2. Level: 1.

1982 January 15 - 09:20 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-73.

Ionosphere mission Agency: ISAS. Apogee: 303 km (188 mi). References: 2. Level: 1.

1982 February 13 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-72.

Test / ionosphere / plasma / fields mission Agency: ISAS. Apogee: 328 km (203 mi). References: 2. Level: 1.

1982 February 14 - 10:50 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-3.

0.3m telescope test Ultraviolet astronomy mission Agency: ISAS. Apogee: 266 km (165 mi). References: 2. Level: 1.

1982 February 18 - 12:40 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-74.

Ultraviolet / x-ray astronomy mission Agency: ISAS. Apogee: 315 km (195 mi). References: 2. Level: 1.

1982 August 15 - 23:15 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500A. LV Configuration: TT-500A TT-500A-11F.

Test mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1982 September 3 - 05:00 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-1. LV Configuration: N-1 N-9(F).

Kiku 4 Payload: ETS 3. Mass: 385 kg (848 lb). Class: Technology. Spacecraft: ETS. Agency: NASDA. Perigee: 988 km (613 mi). Apogee: 1,006 km (625 mi). Inclination: 44.60 deg. Period: 105.10 min. COSPAR: 1982-087A. USAF Sat Cat: 13492. 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. References: 2, 6. Level: 1.

1982 September 6 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-5.

0.1m telescope Solar extreme ultraviolet mission Agency: ISAS. Apogee: 237 km (147 mi). References: 2. Level: 1.

1982 September 13 - 12:30 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-75.

Near infrared Background Infrared astronomy mission Agency: ISAS. Apogee: 320 km (190 mi). References: 2. Level: 1.

1982 September 25 - 09:15 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-12.

Aeronomy mission Agency: ISAS. Apogee: 200 km (120 mi). References: 2. Level: 1.

1983 January 14 - 20:40 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-76.

Aeronomy / ionosphere mission Agency: ISAS. Apogee: 349 km (216 mi). References: 2. Level: 1.

1983 January 26 - 23:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500A. LV Configuration: TT-500A TT-500A-12F.

Microgravity mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1983 February 4 - 08:37 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-2. LV Configuration: N-2 N-10(F).

Sakura 2A Program: CS. Payload: CS-2A. Mass: 772 kg (1,701 lb). Class: Communications. 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. COSPAR: 1983-006A. USAF Sat Cat: 13782. Completed Operations Date: 1990-12-04. 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. References: 2, 6. Level: 1.

1983 February 20 - 05:10 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: M1. Launch Vehicle: Mu. Model: Mu-3S. LV Configuration: Mu-3S M-3S-3.

SS-08 Tenma Payload: Astro B. Mass: 185 kg (407 lb). Class: Astronomy. Spacecraft: Astro. Agency: ISAS. Perigee: 431 km (267 mi). Apogee: 438 km (272 mi). Inclination: 31.50 deg. Period: 93.30 min. COSPAR: 1983-011A. USAF Sat Cat: 13829. Decay Date: 1988-12-17. X-ray experiments. Astro-B (Tenma). Launch 0510 GMT. Launching organization: ISAS (Institute of Space and Astronautical Science). X-ray observation of X-ray stars in our galaxy as well as X-ray galaxies using a scintillating proportional counter, a transient X-ray source mo nitor, an X-ray foucsing collector, a radiation belt monitor, a gamma ray burst detector and a star sensor. References: 2, 6. Level: 1.

1983 August 5 - 20:29 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-2. LV Configuration: N-2 N-11(F).

Sakura 2B Program: CS. Payload: CS-2B. Mass: 670 kg (1,470 lb). Class: Communications. 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. COSPAR: 1983-081A. USAF Sat Cat: 14248. Completed Operations Date: 1990-01-01. 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. References: 2, 6. Level: 1.

1983 August 8 - 06:00 GMT - Launch Site: White Sands. Launch Complex: -. Launch Pad: -. Launch Vehicle: Black Brant. Model: Black Brant 9B.

CHARGE-1 (TPE-3) Tether / ionosphere mission Agency: NASA/ISAS. Apogee: 218 km (135 mi). References: 2. Level: 1.

1983 August 18 - 23:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: S. Model: TT-500A. LV Configuration: TT-500A TT-500A-13F.

Microgravity mission Agency: NASDA. Apogee: 300 km (180 mi). References: 2. Level: 1.

1983 August 29 - 10:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-6.

MINIX Plasma physics mission Agency: ISAS. Apogee: 238 km (147 mi). References: 2. Level: 1.

1983 September 12 - 22:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-13.

Ionosphere mission Agency: ISAS. Apogee: 227 km (141 mi). References: 2. Level: 1.

1983 September 16 - 18:16 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-14.

Aeronomy mission Agency: ISAS. Apogee: 218 km (135 mi). References: 2. Level: 1.

1984 January 13 - 19:30 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-77.

CIR Infrared astronomy mission Agency: ISAS. Apogee: 317 km (196 mi). References: 2. Level: 1.

1984 January 17 - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K?. Launch Vehicle: SB-735. Model: ST-735. LV Configuration: ST-735-1 ST-735-1.

SRB Sep test Agency: ISAS. Apogee: 50 km (31 mi). References: 2. Level: 1.

1984 January 23 - 07:58 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-2. LV Configuration: N-2 N-12(F).

Yuri 2A Program: BS. Payload: BS-2a. Mass: 670 kg (1,470 lb). Class: Communications. Spacecraft: AS 3000. Manufacturer: Lockheed Martin. 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. COSPAR: 1984-005A. USAF Sat Cat: 14659. Completed Operations Date: 1989-07-01. 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. References: 2, 6. Level: 1.

1984 February 14 - 08:00 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: M1. Launch Vehicle: Mu. Model: Mu-3S. LV Configuration: Mu-3S M-3S-4.

SS-09 Onzora Payload: Exos C. Mass: 180 kg (390 lb). Class: Earth. Type: Ionosphere. Spacecraft: EXOS. Agency: ISAS. Perigee: 247 km (153 mi). Apogee: 331 km (205 mi). Inclination: 74.60 deg. Period: 90.30 min. COSPAR: 1984-015A. USAF Sat Cat: 14722. Decay Date: 1988-12-26. Optical investigations of ionosphere. EXOS-C (OHZORA). Optical study of the stratosphere and middle atmosphere. Study of the specific phenomena of the ionospheric plasma over the southern Atlantic geomagnetic anomaly zone which was discovered by the third scientific satellite 'TAIYO'. Launch vehicle Mu-3S-4, launching organization ISAS (Institute of Space and Astronautical Science). Launch time 0800 GMT. References: 2, 6. Level: 1.

1984 April 4 - 19:27 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310JA-8.

Ionosphere mission Agency: NIPR. Apogee: 201 km (124 mi). References: 2. Level: 1.

1984 May 3 - 22:14 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310JA-9.

Ionosphere mission Agency: NIPR. Apogee: 204 km (126 mi). References: 2. Level: 1.

1984 May 28 - 23:17 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310JA-10.

Ionosphere mission Agency: NIPR. Apogee: 209 km (129 mi). References: 2. Level: 1.

1984 August 2 - 20:30 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-2. LV Configuration: N-2 N-13(F).

Himawari 3 Payload: GMS 3. Mass: 303 kg (668 lb). Class: Earth. Type: Weather. 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. COSPAR: 1984-080A. USAF Sat Cat: 15152. Completed Operations Date: 1995-06-22. 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. References: 2, 6. Level: 1.

1985 January 7 - 19:26 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: M1. Launch Vehicle: Mu. Model: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-1.

SS-10 Sagikake Payload: MS T5. Mass: 141 kg (310 lb). Class: Technology. Spacecraft: Tansei. Agency: ISAS. COSPAR: 1985-001A. USAF Sat Cat: 15464. Sakigake ('Pioneer') was a test spacecraft similar to Suisei (Planet-A). Objectives were :verification of fundamental technology related to interplanetary missions, including deep-space communication, attitude control, attitude determination; study and observation of solar wind and plasma waves and interplanetary magnetic field. It carried three instruments to measure plasma wave spectra, solar wind ions, and interplanetary magnetic fields. The spacecraft was spin-stabilized at two different rates (5 and 0.2 rpm). It was equipped with hydrazine thrusters for attitude and velocity control, star and sun sensors for attitude determination, and a mechanically despun off-set parabolic dish for long-range communication. Launched into an initial heliocentric orbit with a period of 318.8 days, at 151.4 x 121.9 million km (0.815 x 1.012 AU), 1.439 degree inclination. Flew by Comet Halley on its sunward side at a distance of about 7 million kilometers on March 11, 1986. It later made an Earth swingby on January 8, 1992 with a closest approach of 88,997 km. This was the first planet-swingby for a Japanese spacecraft. During the approach, Sakigake observed the geotail, with passage occurring at 290 Re on 14 June 1993 before ISTP's multi-spacecraft investigation of that region. The second Earth swingby was on June 14, 1993 at 40 Re, and the third on October 28, 1994 at 86 Re. Almost no hydrazine remained so no further maneuvers were accomplished. Telemetry contact was lost on 15 November 1995 at a distance of 106 million km. Future mission planning had included a 23.6 km/s, 10,000 km flyby of Comet Honda-Mrkos-Pajdusakova on Feb 3, 1996 (approaching the nucleus along the tail) some 0.17 AU from the Sun, and a 14 million km passage of Comet Giacobini-Zinner on Nov 29, 1998. References: 2, 6, 296. Level: 1.

1985 February 7 - 09:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-15.

Aeronomy mission Agency: ISAS. Apogee: 213 km (132 mi). References: 2. Level: 1.

1985 February 11 - 10:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-7.

Aeronomy / ionosphere mission Agency: ISAS. Apogee: 362 km (224 mi). References: 2. Level: 1.

1985 May 29 - 00:59 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310JA-11.

Ionosphere mission Agency: NIPR. Apogee: 212 km (131 mi). References: 2. Level: 1.

1985 July 12 - 19:35 GMT - Launch Site: Syowa Base. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310JA-12.

Ionosphere mission Agency: NIPR. Apogee: 222 km (137 mi). References: 2. Level: 1.

1985 August 18 - 23:33 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: M1. Launch Vehicle: Mu. Model: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-2.

SS-11 Suisei Payload: Planet A. Mass: 141 kg (310 lb). Class: Earth. Type: Magnetosphere. Spacecraft: SS. Agency: ISAS. COSPAR: 1985-073A. USAF Sat Cat: 15967. Rendezvoused with comet Halley 3/8/86. Solar Orbit (Heliocentric). PLANET-A (SUISEI). Launch time 2333 GMT. Imaging of the hydrogen coma of Halley's comet by the hydrogen Lyman alpha line. Measurement of the solar wind in the cruising phase and in the vicinity of the comet. Launching organiza tion ISAS. Heliocentric orbit parameters 282 days, inclination 0.888 deg, 151.42 x 100.5 million km (1.0122 x 0.6718 AU). References: 2, 6. Level: 1.

1985 September 14 - 14:40 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-78.

CBR Submillimeter radio astronomy mission Agency: ISAS. Apogee: 297 km (184 mi). References: 2. Level: 1.

1986 January 31 - 08:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-79.

Ionosphere mission Agency: ISAS. Apogee: 319 km (198 mi). References: 2. Level: 1.

1986 February 1 - 12:40 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-16.

E-region Ionosphere mission Agency: ISAS. Apogee: 201 km (124 mi). References: 2. Level: 1.

1986 February 12 - 07:55 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-2. LV Configuration: N-2 N-14(F).

Yuri 2B Program: BS. Payload: BS-2b. Mass: 677 kg (1,492 lb). Class: Communications. Spacecraft: AS 3000. Manufacturer: Lockheed Martin. 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. COSPAR: 1986-016A. USAF Sat Cat: 16597. Completed Operations Date: 1991-10-24. 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. References: 2, 6. Level: 1.

1986 March 8 -

Susei, Comet Halley Flyby Level: 1.

1986 March 10 -

Sakigake, Comet Halley Flyby Level: 1.

1986 August 12 - 20:45 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: H-1. LV Configuration: H-1 H-15(F).

EGS Payload: EGP. Mass: 685 kg (1,510 lb). Class: Earth. Type: Geodetic. Spacecraft: EGS. Agency: NASDA. Perigee: 1,479 km (919 mi). Apogee: 1,497 km (930 mi). Inclination: 50.00 deg. Period: 115.70 min. COSPAR: 1986-061A. USAF Sat Cat: 16908. 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. References: 2, 6. Level: 1.

Oscar 12 Program: Oscar. Payload: JAS-1. Mass: 50 kg (110 lb). Class: Communications. Type: Amateur Radio. Spacecraft: Oscar. Agency: JARL. Perigee: 1,479 km (919 mi). Apogee: 1,497 km (930 mi). Inclination: 50.00 deg. Period: 115.70 min. COSPAR: 1986-061B. USAF Sat Cat: 16909. Japanese Amateur Satellite. JAS-1 (Fuji). Amateur satellite communications. Development of amateur satellite technology. Launch vehicle H-I (two-stage) test flight no. 1. Launch time 2045 GMT. Launching organization NASDA. Fuji-OSCAR 12 was launched piggyback with a Japanese experimental geodetic satellite Ajisai (EGS). Weight 50 kg. 26-sided polyhedron, 40 x 40 x 47 cm. FO-12 was the first Japanese amateur satellite developed by the Japan Amateur Radio League (English version) with system design and integration performed at NEC. FO-12 was taken out of service November 5, 1989 because of battery failure. References: 2, 6. Level: 1.

MABES Payload: Jindai/LE-5. Class: Technology. Spacecraft: MABES. Agency: NASDA. Perigee: 1,483 km (921 mi). Apogee: 1,604 km (996 mi). Inclination: 50.00 deg. Period: 117.00 min. COSPAR: 1986-061C. USAF Sat Cat: 16910. MABES (Jindai). Experiment on the levitation of the magnetic bearing flywheel under zero-g condition. References: 2, 6. Level: 1.

1986 September 6 - 13:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-17.

Airglow Aeronomy mission Agency: ISAS. Apogee: 202 km (125 mi). References: 2. Level: 1.

1987 January 15 - 08:10 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-9.

E field Ionosphere / aeronomy mission Agency: ISAS. Apogee: 365 km (226 mi). References: 2. Level: 1.

1987 February 5 - 06:30 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: M1. Launch Vehicle: Mu. Model: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-3.

Ginga Payload: Astro C. Mass: 420 kg (920 lb). Class: Astronomy. Spacecraft: Astro. Agency: ISAS. Perigee: 395 km (245 mi). Apogee: 450 km (270 mi). Inclination: 31.00 deg. Period: 93.00 min. COSPAR: 1987-012A. USAF Sat Cat: 17480. Decay Date: 1991-11-01. Studyied galactic gamma ray, X-ray sources. ASTRO-C (Ginga). Observation of variabilities of X-rays from active galactic nuclei and galactic compact sources. Launching organization ISAS. Launch time 0630 GMT. References: 2, 6. Level: 1.

1987 February 19 - 01:23 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: N-2. LV Configuration: N-2 N-16(F).

MOS-1 Payload: Momo 1. Mass: 745 kg (1,642 lb). Class: Earth. Type: Seasat. Spacecraft: Marine Observation Satellite. Agency: NASDA. Perigee: 907 km (563 mi). Apogee: 909 km (564 mi). Inclination: 99.10 deg. Period: 103.20 min. COSPAR: 1987-018A. USAF Sat Cat: 17527. 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. References: 2, 6. Level: 1.

1987 February 21 - 16:15 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-8.

GUV Ultraviolet astronomy mission Agency: ISAS. Apogee: 286 km (177 mi). References: 2. Level: 1.

1987 February 22 - 15:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-80.

CBR Submillimeter radio astronomy mission Agency: ISAS. Apogee: 317 km (196 mi). References: 2. Level: 1.

1987 August 27 - 09:20 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: H-1. LV Configuration: H-1 H-17(F).

Kiku 5 Payload: ETS 5. Mass: 550 kg (1,210 lb). Class: Technology. 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. COSPAR: 1987-070A. USAF Sat Cat: 18316. Completed Operations Date: 1997-09-10. 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. References: 2, 6. Level: 1.

1988 January 25 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: Kappa. Model: Kappa 9M. LV Configuration: Kappa 9M K-9M-81.

COREX Ionosphere mission Agency: ISAS. Apogee: 359 km (223 mi). References: 2. Level: 1.

1988 January 28 - 02:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-18.

D-region Ionosphere / aeronomy mission Agency: ISAS. Apogee: 202 km (125 mi). References: 2. Level: 1.

1988 February 19 - 10:05 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: H-1. LV Configuration: H-1 H-18(F).

Sakura 3A Program: CS. Payload: CS-3A. Mass: 1,100 kg (2,400 lb). Class: Communications. 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. COSPAR: 1988-012A. USAF Sat Cat: 18877. Completed Operations Date: 1996-09-28. 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. References: 2, 6. Level: 1.

1988 September 5 - 23:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: TR-1. Model: TR-1. LV Configuration: TR-1 TR-1-1.

H-II 1/4 Scale model test flight Agency: NASDA. Apogee: 85 km (52 mi). References: 2. Level: 1.

1988 September 16 - 09:59 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: H-1. LV Configuration: H-1 H-19(F).

Sakura 3B Program: CS. Payload: CS-3B. Mass: 1,100 kg (2,400 lb). Class: Communications. 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. COSPAR: 1988-086A. USAF Sat Cat: 19508. Completed Operations Date: 1997-11-10. 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. References: 2, 6. Level: 1.

1989 February 1 - 12:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-19.

Aeronomy mission Agency: ISAS. Apogee: 230 km (140 mi). References: 2. Level: 1.

1989 February 21 - 23:30 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: M1. Launch Vehicle: Mu. Model: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-4.

Akebono Payload: Exos D. Mass: 295 kg (650 lb). Class: Earth. Type: Ionosphere. Spacecraft: EXOS. Agency: ISAS. Perigee: 272 km (169 mi). Apogee: 8,554 km (5,315 mi). Inclination: 75.10 deg. Period: 185.90 min. COSPAR: 1989-016A. USAF Sat Cat: 19822. Studied aurora borealis, auroral australis. EXOS-D (Akebono). Observation in high precision of behaviour and acceleration mechanism of aurora particles in Earth magnetosphere. Launching organization ISAS. Launch time 2330 GMT. References: 2, 6. Level: 1.

1989 March 6 - 23:29 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44LP. LV Configuration: Ariane 44LP V29.

JCSAT 1 Program: JCSAT. Mass: 2,280 kg (5,020 lb). Class: Communications. Spacecraft: HS 393. Agency: JCSAT. Perigee: 35,971 km (22,351 mi). Apogee: 36,018 km (22,380 mi). Inclination: 4.10 deg. Period: 1,446.80 min. COSPAR: 1989-020A. USAF Sat Cat: 19874. Completed Operations Date: 1998-08-17. Japanese domestic communications; 150 deg E. Domestic communication. Launching states: Japan, France, USA. Launch vehicle Ariane 29 (Ariane IV). Launching organization ARIANE SPACE. Launch time 1129 GMT. Positioned in geosynchronous orbit at 150 deg E in 1989-1997; 148 deg E in 1997; 111 deg E in 1998 As of 31 August 2001 located at 19.12 deg E drifting at 2.653 deg W per day. As of 2007 Mar 11 located at 63.05E drifting at 2.678W degrees per day. References: 2, 6. Level: 1.

1989 June 5 - 22:37 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44L. LV Configuration: Ariane 44L V31.

Superbird A Program: Superbird. Payload: Superbird A / DFS-Kopernikus 1. Mass: 2,489 kg (5,487 lb). Class: Communications. Spacecraft: FS-1300. Agency: SCC. Perigee: 35,931 km (22,326 mi). Apogee: 35,944 km (22,334 mi). Inclination: 2.50 deg. Period: 1,443.80 min. COSPAR: 1989-041A. USAF Sat Cat: 20040. Completed Operations Date: 1991-02-01. Japanese domestic business communications; 158 deg E. Positioned in geosynchronous orbit at 158 deg E in 1989-1990 As of 6 September 2001 located at 41.59 deg E drifting at 1.921 deg W per day. As of 2007 Mar 11 located at 166.35W drifting at 1.878W degrees per day. References: 2, 6. Level: 1.

1989 August 17 -

Japanese Commercial Cosmonaut Training Group selected. Japanese journalists trained for a commercial flight to the Mir space station. Level: 1.

1989 September 4 - 16:15 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-10.

CIR Cosmic infrared Infrared astronomy mission Agency: ISAS. Apogee: 288 km (178 mi). References: 2. Level: 1.

1989 September 5 - 19:11 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: H-1. LV Configuration: H-1-6R H-20(F).

Himawari 4 Payload: GMS 4. Mass: 725 kg (1,598 lb). Class: Earth. Type: Weather. 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. COSPAR: 1989-070A. USAF Sat Cat: 20217. Completed Operations Date: 2000-02-24. 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. References: 2, 6. Level: 1.

1990 January 1 - 00:07 GMT - Launch Site: Cape Canaveral. Launch Complex: LC40. Launch Pad: -. Launch Vehicle: Titan. Model: Commercial Titan 3. LV Configuration: Commercial Titan 3 CT-1.

JCSAT 2 Program: JCSAT. Payload: JCSat 2 / Orbus-7S. Mass: 2,280 kg (5,020 lb). Class: Communications. Spacecraft: HS 393. Agency: JCSAT. Perigee: 35,868 km (22,287 mi). Apogee: 35,877 km (22,292 mi). Inclination: 0.10 deg. Period: 1,440.50 min. COSPAR: 1990-001B. USAF Sat Cat: 20402. Japanese domestic communications; 154 deg E. Domestic communications. Launching organization Martin Marietta. Launch time 0007 GMT. Positioned in geosynchronous orbit at 154 deg E in 1990-1999 As of 5 September 2001 located at 154.04 deg E drifting at 0.006 deg W per day. As of 2007 Mar 10 located at 116.78W drifting at 6.255W degrees per day. References: 2, 6. Level: 1.

1990 January 24 - 11:46 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: M1. Launch Vehicle: Mu. Model: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-5.

Hiten Program: Muses. Payload: Muses A. Mass: 185 kg (407 lb). Class: Planetary. Type: Lunar. Spacecraft: Hiten. Agency: ISAS. Perigee: 262 km (162 mi). Apogee: 286,183 km (177,825 mi). Inclination: 30.60 deg. Period: 9,597.60 min. COSPAR: 1990-007A. USAF Sat Cat: 20448. Decay Date: 1993-04-11. MUSES-A was renamed Hiten after launch. It developed of lunar swingby techniques for future missions and ejected a lunar orbiter. Launching organization ISAS. On 1990 Jan 25: Period 6.665 days, inclination 30.63 deg, 262.49 x 286182.72 km. On 1992 Feb 17: Period 4.53 days, inclination 38.90 deg, perilune 2289.67 km, apolune 49013.93 km. References: 2, 6. Level: 1.

Hagoromo Program: Muses. Payload: Muses A. Mass: 12 kg (26 lb). Class: Planetary. Type: Lunar. Spacecraft: Hagoromo. Agency: ISAS. COSPAR: 1990-007B. USAF Sat Cat: 20618. Lunar orbiter ejected from Muses A 3/19/90; contact lost after release; engineering test. Lunar Orbit (Selenocentric). References: 2, 6. Level: 1.

1990 January 27 - 19:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-20.

Aeronomy mission Agency: ISAS. Apogee: 185 km (114 mi). References: 2. Level: 1.

1990 February 7 - 01:33 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: H-1. LV Configuration: H-1 H-21(F).

MOS-1b Payload: Momo 1B. Mass: 740 kg (1,630 lb). Class: Earth. Type: Seasat. Spacecraft: Marine Observation Satellite. Agency: NASDA. Perigee: 908 km (564 mi). Apogee: 909 km (564 mi). Inclination: 99.10 deg. Period: 103.20 min. COSPAR: 1990-013A. USAF Sat Cat: 20478. 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. References: 2, 6. Level: 1.

Debut Payload: Orizuru. Mass: 50 kg (110 lb). Class: Technology. Spacecraft: Debut. Agency: NASDA. Perigee: 911 km (566 mi). Apogee: 1,743 km (1,083 mi). Inclination: 99.00 deg. Period: 112.20 min. COSPAR: 1990-013B. USAF Sat Cat: 20479. 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. References: 2, 6. Level: 1.

Oscar 20 Program: Oscar. Payload: JAS 1b. Mass: 50 kg (110 lb). Class: Communications. Type: Amateur Radio. Spacecraft: Oscar. Agency: JARL. Perigee: 912 km (566 mi). Apogee: 1,745 km (1,084 mi). Inclination: 99.00 deg. Period: 112.20 min. COSPAR: 1990-013C. USAF Sat Cat: 20480. JAS-1b 'Fuji-2'. Continuation of amateurradio services of JAS-1; extension of amateur radio communications area; advancement of amateur radio technology. Launching organization NASDA. Launch time 0133 UT. References: 2, 6. Level: 1.

1990 February 21 - 16:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-11.

CIR Infrared astronomy mission Agency: ISAS. Apogee: 317 km (196 mi). References: 2. Level: 1.

1990 February 22 - 23:17 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44L. LV Configuration: Ariane 44L V36. FAILURE: Exploded 100 seconds after liftoff due to water line blockage. This was caused by a piece of cloth found in the first stage Viking engine water cooling system.

Superbird B Program: Superbird. Class: Communications. Spacecraft: FS-1300. Agency: SCCJ. Apogee: 9.00 km (5.50 mi). COSPAR: F900222A. Decay Date: 1990-02-23. Launched with BS-2X. Targeted for Geosynch orbit. References: 5. Level: 1.

1990 February 26 - 02:06 GMT - Launch Site: Andoya. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-12.

Auroral mission Agency: ISAS. Apogee: 369 km (229 mi). References: 2. Level: 1.

1990 March 19 -

Hiten, Moon Flyby (Japan) Spacecraft: Hiten. Level: 1.

1990 August 28 - 09:05 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: H-1. LV Configuration: H-1 H-22(F).

Yuri 3A Program: BS. Payload: BS-3a. Mass: 1,115 kg (2,458 lb). Class: Communications. Spacecraft: AS 3000. Manufacturer: Lockheed Martin. 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. COSPAR: 1990-077A. USAF Sat Cat: 20771. Completed Operations Date: 1998-04-20. 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. References: 2, 6. Level: 1.

1991 February 12 - 03:29 GMT - Launch Site: Andoya. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-14.

Auroral mission Agency: ISAS. Apogee: 353 km (219 mi). References: 2. Level: 1.

1991 February 16 - 13:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-13.

Extreme ultraviolet Telescopes Extreme ultraviolet astronomy mission Agency: ISAS. Apogee: 337 km (209 mi). References: 2. Level: 1.

1991 April 18 - 23:30 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36B. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas I. LV Configuration: Atlas I AC-70. FAILURE: RL-10 Centaur engine turbopump failed at T+361 seconds; destroyed by range safety.

Yuri 3H Program: BS. Payload: BS-3H. Mass: 600 kg (1,320 lb). Class: Communications. Spacecraft: AS 3000. Manufacturer: Lockheed Martin. Agency: TSCJ. Apogee: 175 km (108 mi). COSPAR: F910418A. Decay Date: 1991-04-18. References: 278. Level: 1.

1991 August 25 - 08:40 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: H-1. LV Configuration: H-1 H-23(F).

Yuri 3B Program: BS. Payload: BS-3b. Mass: 1,115 kg (2,458 lb). Class: Communications. Spacecraft: AS 3000. Manufacturer: Lockheed Martin. 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. COSPAR: 1991-060A. USAF Sat Cat: 21668. Completed Operations Date: 1999-04-05. 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. References: 2, 6. Level: 1.

1991 August 30 - 02:30 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: M1. Launch Vehicle: Mu. Model: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-6.

Solar-A Payload: Yohkoh. Mass: 420 kg (920 lb). Class: Solar. Spacecraft: Solar. Agency: ISAS. Perigee: 516 km (320 mi). Apogee: 754 km (468 mi). Inclination: 31.30 deg. Period: 97.40 min. COSPAR: 1991-062A. USAF Sat Cat: 21694. Decay Date: 2005-09-12. X-ray imaging of Sun. References: 2, 6. Level: 1.

1991 September 15 - 23:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: TR-1. Model: TR-1A. LV Configuration: TR-1A TR-1A-1.

Microgravity mission Agency: NASDA. Apogee: 270 km (160 mi). References: 2. Level: 1.

1992 January 28 - 12:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-21.

Aeronomy mission Agency: ISAS. Apogee: 223 km (138 mi). References: 2. Level: 1.

1992 February 1 - 16:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-15.

CIR Infrared astronomy mission Agency: ISAS. Apogee: 338 km (210 mi). References: 2. Level: 1.

1992 February 11 - 01:50 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: Delta. Model: H-1. LV Configuration: H-1 H-24(F).

JERS-1 Payload: ERS-1. Mass: 1,340 kg (2,950 lb). Class: Earth. Type: Landsat. Spacecraft: JERS. Agency: NASDA. Perigee: 567 km (352 mi). Apogee: 568 km (352 mi). Inclination: 97.70 deg. Period: 96.00 min. COSPAR: 1992-007A. USAF Sat Cat: 21867. Completed Operations Date: 1998-10-12. Decay Date: 2001-12-03. 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. References: 2, 6. Level: 1.

1992 February 26 - 23:58 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44L. LV Configuration: Ariane 44L V49.

Superbird B1 Program: Superbird. Mass: 2,560 kg (5,640 lb). Class: Communications. Spacecraft: FS-1300. Agency: SCC. Perigee: 36,057 km (22,404 mi). Apogee: 36,206 km (22,497 mi). Inclination: 0.90 deg. Period: 1,453.80 min. COSPAR: 1992-010A. USAF Sat Cat: 21893. Stationed at 162 deg E. Domestic communications. Launching organization Arianespace. Launch time 2358 GMT. Positioned in geosynchronous orbit at 162 deg E in 1992-1999 As of 4 September 2001 located at 19.90 deg W drifting at 4.382 deg W per day. As of 2007 Mar 9 located at 164.51E drifting at 4.378W degrees per day. References: 2, 6. Level: 1.

1992 July 24 - 14:26 GMT - Launch Site: Cape Canaveral. Launch Complex: LC17A. Launch Pad: -. Launch Vehicle: Delta. Model: Delta 6925. LV Configuration: Delta 6925 D212.

Geotail Payload: Geotail. Mass: 1,008 kg (2,222 lb). Class: Earth. Type: Magnetosphere. Spacecraft: Geotail. Agency: ISAS. Perigee: 57,448 km (35,696 mi). Apogee: 399,941 km (248,511 mi). Inclination: 18.00 deg. Period: 18,904.40 min. COSPAR: 1992-044A. USAF Sat Cat: 22049. Measured magnetosphere and Earth's geomagnetic tail. To investigate the structure and dynamics of the geomagnetic tail that extends on the nightside of the Earth. Launch time 1426 GMT. Launching states Japan and the United States of America. Launching organization NASA. References: 2, 6. Level: 1.

DUVE Payload: DUVE. Class: Earth. Spacecraft: DUVE. Agency: MDAC. Perigee: 215 km (133 mi). Apogee: 1,413 km (877 mi). Inclination: 27.40 deg. Period: 101.17 min. COSPAR: 1992-044B. USAF Sat Cat: 22050. Decay Date: 1993-03-16. Diffuse Ultraviolet Explorer package bolted to Delta 2 2nd stage. References: 2, 279. Level: 1.

1992 August 19 - 23:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: TR-1. Model: TR-1A. LV Configuration: TR-1A TR-1A-2.

Microgravity mission Agency: NASDA. Apogee: 290 km (180 mi). References: 2. Level: 1.

1992 December 1 - 22:48 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 42P. LV Configuration: Ariane 42P+ V55.

Superbird A1 Program: Superbird. Mass: 2,780 kg (6,120 lb). Class: Communications. Spacecraft: FS-1300. Agency: SCC. Perigee: 35,774 km (22,228 mi). Apogee: 35,800 km (22,200 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1992-084A. USAF Sat Cat: 22253. Stationed at 158 deg E. Domestic communications. Launching states: Japan and France. Launch time 2248 GMT. Positioned in geosynchronous orbit at 158 deg E in 1993-1999 As of 31 August 2001 located at 157.95 deg E drifting at 0.011 deg W per day. As of 2007 Mar 9 located at 158.03E drifting at 0.006W degrees per day. References: 2, 6. Level: 1.

1992 December 10 -

Mihonoseki Meteor Fall (Fell Through Roof of A House In Japan) Level: 1.

1993 February 18 - 07:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-16.

METS Ionosphere / active plasma mission Agency: ISAS. Apogee: 272 km (169 mi). References: 2. Level: 1.

1993 February 20 - 02:20 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: M1. Launch Vehicle: Mu. Model: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-7.

Asuka Payload: Astro D. Mass: 420 kg (920 lb). Class: Astronomy. Spacecraft: Astro. Agency: ISAS. Perigee: 539 km (334 mi). Apogee: 646 km (401 mi). Inclination: 31.10 deg. Period: 96.50 min. COSPAR: 1993-011A. USAF Sat Cat: 22521. Decay Date: 2001-03-02. X-ray imaging and astronomy. Imaging and spectroscopic observations of various astronomical objects (stars and galaxies) in the X-ray band. Launching organization ISAS. Launch time 0200 GMT. Astro-D 'ASCA'. References: 2, 6. Level: 1.

1993 September 16 - 23:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: TR-1. Model: TR-1A. LV Configuration: TR-1A TR-1A-3.

Microgravity mission Agency: NASDA. Apogee: 264 km (164 mi). References: 2. Level: 1.

1994 February 3 - 22:20 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-II. LV Configuration: H-II H-II-1F.

OREX Payload: Ryusei. Mass: 865 kg (1,906 lb). Class: Technology. Type: RV. Spacecraft: OREX. Agency: NASDA/NA. Perigee: 450 km (270 mi). Apogee: 451 km (280 mi). Inclination: 30.50 deg. Period: 93.50 min. COSPAR: 1994-007A. USAF Sat Cat: 22978. Decay Date: 1994-02-03. 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. References: 2, 6. Level: 1.

VEP Payload: Myojo / LAPS. Mass: 2,391 kg (5,271 lb). Class: Technology. Spacecraft: VEP. Agency: NASDA. Perigee: 449 km (278 mi). Apogee: 36,261 km (22,531 mi). Inclination: 28.60 deg. Period: 645.00 min. COSPAR: 1994-007B. USAF Sat Cat: 22979. 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. References: 2, 6. Level: 1.

1994 February 15 - 23:52 GMT - Launch Site: Andoya. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-22.

NNP / AIR / NID / NEL Aeronomy mission Agency: ISAS. Apogee: 192 km (119 mi). References: 2. Level: 1.

1994 July 8 - 23:05 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44L. LV Configuration: Ariane 44L V65.

Yuri 3N Program: BS. Payload: BS-3N. Mass: 1,210 kg (2,660 lb). Class: Communications. Spacecraft: AS 3000. Manufacturer: Lockheed Martin. Agency: NHK. Perigee: 35,777 km (22,230 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.0500 deg. Period: 1,436.15 min. COSPAR: 1994-040B. USAF Sat Cat: 23176. Stationed at 109.67 deg E. Positioned in geosynchronous orbit at 109 deg E in 1994-1999 As of 5 September 2001 located at 109.71 deg E drifting at 0.013 deg W per day. As of 2007 Mar 11 located at 109.92E drifting at 0.008W degrees per day. References: 2, 6. Level: 1.

1994 August 28 - 07:50 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-II. LV Configuration: H-II H-II-2F. FAILURE: LAPS apogee kick motor failed to ignite. Partial Failure.

Kiku 6 Payload: ETS 6. Mass: 3,800 kg (8,300 lb). Class: Technology. Spacecraft: ETS. Agency: NASDA. Perigee: 8,565 km (5,322 mi). Apogee: 38,677 km (24,032 mi). Inclination: 13.23 deg. Period: 861.84 min. COSPAR: 1994-056A. USAF Sat Cat: 23230. Failed to reach geostationary orbit; Engineering Test Satellite; partial mission success. Also tested ion engines for NSSK. References: 2, 6. Level: 1.

1994 September 16 - 04:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K?. Launch Vehicle: SB-735. Model: ST-735. LV Configuration: ST-735 ST-735-2.

FIH test Agency: ISAS. Apogee: 118 km (73 mi). References: 2. Level: 1.

1994 November 24 - 10:20 GMT - Launch Site: Andoya. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-23.

NNP / AIR / NID / NEL Aeronomy mission Agency: ISAS. Apogee: 200 km (120 mi). References: 2. Level: 1.

1994 December 1 - 21:39 GMT - Launch Site: Andoya. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-21.

Auroral mission Agency: ISAS. Apogee: 344 km (213 mi). References: 2. Level: 1.

1995 January 15 - 13:45 GMT - Launch Site: Kagoshima. Launch Complex: M. Launch Pad: M1. Launch Vehicle: Mu. Model: Mu-3S-II. LV Configuration: Mu-3S-II M-3S2-8. FAILURE: Failure of second stage attitude control system.

Express 1 Class: Materials. Spacecraft: Express 1. Agency: ISAS. COSPAR: F950115A. Decay Date: 1995-01-15. At first thought not to have reached orbit. Later the re-entry vehicle was discovered in Ghana having reentered and deployed its parachute on January 15. At T+103 sec, during the second stage burn, the vehicle veered off course. The payload service module entered a 110 x 250 km x 33 degree orbit, instead of the intended 270 x 380 km and re-entered on its second orbit. The re-entry capsule was found later in Ghana. A failure of the second stage attitude control system was blamed, although it was considered likely that the payload was too heavy for the vehicle, being twice the mass of earlier MU-3S payloads. References: 2, 5. Level: 1.

1995 January 23 - 12:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-17.

Submillimeter radio astronomy mission Agency: ISAS. Apogee: 346 km (214 mi). References: 2. Level: 1.

1995 January 28 - 16:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-19.

Extreme ultraviolet Telescopes Extreme ultraviolet astronomy mission Agency: ISAS. Apogee: 330 km (200 mi). References: 2. Level: 1.

1995 March 18 - 08:01 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-II. LV Configuration: H-II H-II-3F.

SFU Mass: 4,000 kg (8,800 lb). Class: Materials. Spacecraft: SFU. Agency: NASDA. Perigee: 471 km (292 mi). Apogee: 483 km (300 mi). Inclination: 28.50 deg. Period: 94.10 min. COSPAR: 1995-011A. USAF Sat Cat: 23521. Decay Date: 1996-01-20. Space Flyer Unit; carried materials, astronomy, biological experiments; retrieved by STS-72 1/20/96. References: 2, 6. Level: 1.

Himawari 5 Payload: GMS 5. Mass: 746 kg (1,644 lb). Class: Earth. Type: Weather. Spacecraft: GMS. Agency: NASDA. Perigee: 35,784 km (22,235 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.60 deg. Period: 1,436.00 min. COSPAR: 1995-011B. USAF Sat Cat: 23522. 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. References: 2, 6. Level: 1.

1995 August 24 - 22:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: TR-1. Model: TR-1A. LV Configuration: TR-1A TR-1A-4.

Microgravity mission Agency: NASDA. Apogee: 270 km (160 mi). References: 2. Level: 1.

1995 August 29 - 00:53 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36B. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas IIAS. LV Configuration: Atlas IIAS AC-117.

JCSAT 3 Program: JCSAT. Mass: 1,841 kg (4,058 lb). Class: Communications. Spacecraft: HS 601. Agency: JSAT. Perigee: 35,779 km (22,231 mi). Apogee: 35,794 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.20 min. COSPAR: 1995-043A. USAF Sat Cat: 23649. 8 transponders for digital TV. Stationed at 128.1 deg E. Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 128 deg E in 1995-1999 As of 5 September 2001 located at 128.05 deg E drifting at 0.005 deg E per day. As of 2007 Feb 20 located at 126.99E drifting at 0.144W degrees per day. References: 2, 6, 278. Level: 1.

1995 August 29 - 06:41 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44P. LV Configuration: Ariane 44P-3 V77.

N-Star a Program: N-STAR. Mass: 3,100 kg (6,800 lb). Class: Communications. Spacecraft: FS-1300. Agency: NTT. Perigee: 35,782 km (22,233 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.10 deg. Period: 1,436.10 min. COSPAR: 1995-044A. USAF Sat Cat: 23651. Stationed at 131.9 deg E. Positioned in geosynchronous orbit at 132 deg E in 1995-1999 As of 1 September 2001 located at 131.99 deg E drifting at 0.017 deg W per day. As of 2007 Mar 11 located at 25.96E drifting at 4.123W degrees per day. References: 2, 6. Level: 1.

1996 February 5 - 07:19 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44P. LV Configuration: Ariane 44P-3 V83.

N-STAR b Program: N-STAR. Mass: 3,400 kg (7,400 lb). Class: Communications. Spacecraft: FS-1300. Agency: NTT. Perigee: 35,775 km (22,229 mi). Apogee: 35,801 km (22,245 mi). Inclination: 0.10 deg. Period: 1,436.20 min. COSPAR: 1996-007A. USAF Sat Cat: 23781. Geostationary at 128.9E. Positioned in geosynchronous orbit at 136 deg E in 1996-1999 As of 1 September 2001 located at 136.01 deg E drifting at 0.012 deg W per day. As of 2007 Mar 9 located at 136.04E drifting at 0.012W degrees per day. References: 2, 6. Level: 1.

1996 February 11 - 23:00 GMT - Launch Site: Tanegashima. Launch Complex: N. Launch Pad: -. Launch Vehicle: J. Model: J-1. LV Configuration: J-1 J-1-1F.

Hyflex Spacecraft test Agency: NASDA. Apogee: 110 km (60 mi). References: 2. Level: 1.

1996 February 11 - 11:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-24.

NTV-1 Aeronomy mission Agency: ISAS. Apogee: 199 km (123 mi). References: 2. Level: 1.

1996 August 17 - 01:53 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-II. LV Configuration: H-II H-II-4F.

ADEOS Class: Earth. Type: Atmosphere. Spacecraft: ADEOS. Agency: NASDA. Perigee: 799 km (496 mi). Apogee: 800 km (490 mi). Inclination: 98.60 deg. Period: 100.90 min. COSPAR: 1996-046A. USAF Sat Cat: 24277. References: 2. Level: 1.

JAS-2 Class: Communications. Spacecraft: Fuji. Agency: JARL. Perigee: 801 km (497 mi). Apogee: 1,323 km (822 mi). Inclination: 98.60 deg. Period: 106.50 min. COSPAR: 1996-046B. USAF Sat Cat: 24278. Japanese amateur radio satellite. References: 2. Level: 1.

1996 August 20 - 15:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-26.

SEEK-1 Plasma mission Agency: ISAS. Apogee: 177 km (109 mi). References: 2. Level: 1.

1996 August 26 - 14:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-25.

SEEK-1 Plasma mission Agency: ISAS. Apogee: 180 km (110 mi). References: 2. Level: 1.

1996 September 24 - 22:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: TR-1. Model: TR-1A. LV Configuration: TR-1A TR-1A-5.

Microgravity mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1997 January 30 - 07:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-18.

Lunar Penetrator test technology mission Agency: ISAS. Apogee: 309 km (192 mi). References: 2. Level: 1.

1997 February 12 - 04:50 GMT - Launch Site: Kagoshima. Launch Complex: M-V. Launch Pad: -. Launch Vehicle: M-V. Model: M-V. LV Configuration: M-V M-V-1.

Haruka Program: Muses. Payload: MUSES B. Class: Astronomy. Spacecraft: Haruka. Manufacturer: Nippon Electric Corp, Tokyo. Agency: ISAS. Perigee: 569 km (353 mi). Apogee: 21,415 km (13,306 mi). Inclination: 31.40 deg. Period: 379.30 min. COSPAR: 1997-005A. USAF Sat Cat: 24720. References: 2. Level: 1.

1997 February 17 - 01:42 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36B. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas IIAS. LV Configuration: Atlas IIAS AC-127.

JCSAT 4 Program: JCSAT. Class: Communications. Spacecraft: HS 601. Manufacturer: Hughes Space and Communications, El Segundo. Agency: JSAT. Perigee: 35,780 km (22,230 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1997-007A. USAF Sat Cat: 24732. Geosynchronous. Stationed over 150.0E Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 150 deg E in 1997-1998; 124 deg E in 1998-1999; 127 deg E in 1999. As of 5 September 2001 located at 127.02 deg E drifting at 0.015 deg W per day. As of 2007 Mar 7 located at 150.01E drifting at 0.008W degrees per day. References: 2, 278. Level: 1.

1997 April 16 - 23:08 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44LP. LV Configuration: Ariane 44LP V95.

BSAT 1a Program: BSAT. Class: Communications. Spacecraft: HS 376. Manufacturer: Hughes Space and Communications, El Segundo. Agency: BSAT. Perigee: 35,786 km (22,236 mi). Apogee: 35,787 km (22,236 mi). Inclination: 0.00 deg. Period: 1,436.20 min. COSPAR: 1997-016B. USAF Sat Cat: 24769. Geosynchronous. Stationed over 110.0E Positioned in geosynchronous orbit at 110 deg E in 1997-1999 As of 4 September 2001 located at 109.56 deg E drifting at 0.018 deg W per day. As of 2007 Mar 10 located at 109.63E drifting at 0.008W degrees per day. References: 2. Level: 1.

1997 June 30 -

ADEOS spacecraft fails Spacecraft: ADEOS. The polar orbiting ADEOS spacecraft performed Earth, atmospheric, and oceanographic remote sensing. Initially put on August 20 1996 into a wrong orbit, it achieved an acceptable orbit in September 1996. Level: 1.

1997 July 28 - 01:15 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36B. Launch Pad: -. Launch Vehicle: Atlas. Model: Atlas IIAS. LV Configuration: Atlas IIAS AC-133.

Superbird C Program: Superbird. Class: Communications. Spacecraft: HS 601. Manufacturer: Hughes Space and Communications, El Segundo. Agency: SCC. Perigee: 35,780 km (22,230 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1997-036A. USAF Sat Cat: 24880. Geosynchronous. Stationed over 144.0E Launch vehicle put payload into supersynchronous earth orbit with IFR/MRS trajectory option. Positioned in geosynchronous orbit at 144 deg E in 1997-1999 As of 5 September 2001 located at 144.00 deg E drifting at 0.014 deg W per day. As of 2007 Mar 9 located at 143.94E drifting at 0.009W degrees per day. References: 2, 278. Level: 1.

1997 September 25 - 00:30 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: TR-1. Model: TR-1A. LV Configuration: TR-1A TR-1A-6.

Microgravity mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1997 November 27 - 21:27 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-II. LV Configuration: H-II-6F.

Hikoboshi Payload: ETS-7. Class: Technology. Spacecraft: ETS-7. Manufacturer: Toshiba Corp., Tokyo. Agency: NASDA. Perigee: 545 km (338 mi). Apogee: 548 km (340 mi). Inclination: 35.00 deg. Period: 95.50 min. COSPAR: 1997-074B. USAF Sat Cat: 25064. 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. References: 2. Level: 1.

Orihime Payload: ETS-7 Target. Class: Technology. Spacecraft: ETS-7 Target. Manufacturer: Toshiba Corp., Tokyo. Agency: NASDA. Perigee: 346 km (214 mi). Apogee: 458 km (284 mi). Inclination: 34.50 deg. Period: 92.60 min. COSPAR: 1997-074E. USAF Sat Cat: 25424. Decay Date: 1999-01-27. Attached to Hikoboshi. It would later separate and serve as a passive docking target for the Hikobishi active automatic docking technology spacecraft. References: 2, 276. Level: 1.

1997 December 2 - 22:52 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44P. LV Configuration: Ariane 44P-3 V103.

JCSAT 5 Program: JCSAT. Class: Communications. Spacecraft: HS 601. Manufacturer: Hughes Space and Communications, El Segundo. Agency: JSAT. Perigee: 35,784 km (22,235 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.10 deg. Period: 1,436.10 min. COSPAR: 1997-075A. USAF Sat Cat: 25067. Geosynchronous. Stationed over 139.4E Positioned in geosynchronous orbit at 150 deg E in 1998-1999 As of 4 September 2001 located at 150.00 deg E drifting at 0.012 deg W per day. As of 2007 Mar 8 located at 127.98E drifting at 0.014W degrees per day. References: 2. Level: 1.

1998 January 25 - 08:35 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-27.

SEEK Ozone Aeronomy mission Agency: ISAS. Apogee: 183 km (113 mi). References: 2. Level: 1.

1998 January 31 - 04:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-520. LV Configuration: S-520-22.

SOLAR-B XDT Solar x-ray / ultraviolet mission Agency: ISAS. Apogee: 270 km (160 mi). References: 2. Level: 1.

1998 February 5 - 08:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: SS-520. LV Configuration: SS-520 SS-520-1.

ENA / EPS / LAP Test / plasma mission Agency: ISAS. Apogee: 750 km (460 mi). References: 2. Level: 1.

1998 February 21 - 07:55 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-II. LV Configuration: H-II H-II-5F.

Kakehashi Payload: COMETS. Class: Communications. Spacecraft: Kakehashi. Manufacturer: Toshiba/NEC. Agency: NASDA. Perigee: 1,033 km (641 mi). Apogee: 17,727 km (11,015 mi). Inclination: 30.10 deg. Period: 328.10 min. COSPAR: 1998-011A. USAF Sat Cat: 25175. 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. References: 2, 276. Level: 1.

1998 April 28 - 22:53 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44P. LV Configuration: Ariane 44P V108.

BSAT 1B Program: BSAT. Class: Communications. Spacecraft: HS 376. Manufacturer: Hughes Space and Communications, El Segundo. Agency: BSAT. Perigee: 35,787 km (22,236 mi). Apogee: 35,788 km (22,237 mi). Inclination: 0.00 deg. Period: 1,436.20 min. COSPAR: 1998-024B. USAF Sat Cat: 25312. Geostationary at 109.9 degrees E. Positioned in geosynchronous orbit at 110 deg E in 1998-1999 As of 5 September 2001 located at 109.63 deg E drifting at 0.019 deg W per day. As of 2007 Mar 10 located at 109.75E drifting at 0.009W degrees per day. References: 2. Level: 1.

1998 July 3 - 18:12 GMT - Launch Site: Kagoshima. Launch Complex: M-V. Launch Pad: -. Launch Vehicle: M-V. Model: M-V. LV Configuration: M-V M-V-3.

Nozomi Mass: 258 kg (568 lb). Class: Planetary. Type: Mars. Spacecraft: Nozomi. Manufacturer: Nippon Electric Corp, Tokyo. Agency: ISAS. Perigee: 703 km (436 mi). Apogee: 489,381 km (304,086 mi). Inclination: 27.30 deg. Period: 20,910.00 min. COSPAR: 1998-041A. USAF Sat Cat: 25383. Originally known as Planet-B; renamed Nozomi ('Hope') after launch. The third stage and payload entered a 146 x 417 km x 31.1 deg parking orbit. The KM-V1 kick (fourth) stage then fired to place the spacecraft into a circumlunar 359 x 401491 km x 28.6 deg orbit. Nozomi made multiple lunar and Earth gravity assist passes to increase its energy for solar orbit insertion and the cruise to Mars.. The spacecraft used a lunar swingby on 24 September and another on 18 December 1998 to increase the apogee of its orbit. It swung by Earth on 20 December at a perigee of about 1000 km. The gravitational assist from the swingby coupled with a 7 minute burn of the bipropellant engine put Nozomi into an escape trajectory towards Mars. It was scheduled to arrive at Mars on 11 October 1999 at 7:45:14 GMT, but the Earth swingby left the spacecraft with insufficient acceleration and two course correction burns on 21 December used more propellant than planned, leaving the spacecraft short of fuel. The new plan is for Nozomi to remain in heliocentric orbit for an additional four years and encounter Mars at a slower relative velocity in December 2003. References: 2, 296. Level: 1.

1998 August 31 -

North Korea fires missile across Japan Level: 1.

1998 November 18 - 23:00 GMT - Launch Site: Tanegashima. Launch Complex: T. Launch Pad: -. Launch Vehicle: TR-1. Model: TR-1A. LV Configuration: TR-1A TR-1A-7.

Microgravity mission Agency: NASDA. Apogee: 100 km (60 mi). References: 2. Level: 1.

1999 February 2 - 01:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-28.

SELENE RF / X-ray test Ionosphere / x-ray mission Agency: ISAS. Apogee: 184 km (114 mi). References: 2. Level: 1.

1999 February 16 - 01:45 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36A. Launch Pad: SLC36A. Launch Vehicle: Atlas. Model: Atlas IIAS. LV Configuration: Atlas IIAS AC-152.

JCSAT-6 Program: JCSAT. Mass: 2,900 kg (6,300 lb). Class: Communications. Spacecraft: HS 601. Manufacturer: Hughes Space and Communications, El Segundo. Agency: JSAT. Perigee: 35,784 km (22,235 mi). Apogee: 35,791 km (22,239 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 1999-006A. USAF Sat Cat: 25630. JCSAT-6 carried a Ku-band relay system. It was operated by Japan Satellite Systems, Inc., Tokyo, provided communications and data relay for Japan and the Pacific Rim. Two burns of the Centaur upper stage placed it into a supersynchronous transfer orbit of 258 km x 96736 km x 24.1 degrees. JCSAT-6's on-board R-4D engine would maneuver it into its final geostationary location. Dry mass of the spacecraft was 1230 kg. Stationed at 124 deg E Positioned in geosynchronous orbit at 123 deg E in 1999. As of 5 September 2001 located at 124.00 deg E drifting at 0.014 deg W per day. As of 2007 Mar 10 located at 124.01E drifting at 0.011W degrees per day. References: 2. Level: 1.

1999 November 15 - 07:29 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-II. LV Configuration: H-II H-II-8F. FAILURE: Failure during first stage burn.

MTSAT Class: Communications. Spacecraft: FS-1300. Manufacturer: Space Systems/Loral, Palo Alto. Agency: National Space Development Agency, Japan. 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. References: 2. Level: 1.

2000 January 9 - 20:50 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-29.

WAVE2000 Aeronomy mission Agency: ISAS. Apogee: 179 km (111 mi). References: 2. Level: 1.

2000 February 10 - 01:30 GMT - Launch Site: Kagoshima. Launch Complex: M-V. Launch Pad: -. Launch Vehicle: M-V. Model: M-V. LV Configuration: M-V M-V-4. FAILURE: First stage failure. An anomalous vibration was detected 25 seconds after launch. At 41 seconds ceramic heat shields in the first stage nozzle broke and fell off, and thrust vector control on the nozzle was lost.

ASTRO E Mass: 1,680 kg (3,700 lb). Class: Astronomy. Spacecraft: ASTRO E. Manufacturer: ISAS. Agency: ISAS. Apogee: 200 km (120 mi). COSPAR: F000210A. Spacecraft was injected in very low perigee orbit and reentered.. X-ray astronomy satellite. Stage 1 lost control, and separated with the rocket off-course at 75 seconds in the flight. Stage 2 burned correctly and separated at 218 seconds, followed by the third stage burn at 621 seconds. Last signals were received at 20 minutes after launch. ASTRO-E was to have separated from the third stage at 23 minutes, but ended in an orbit with a perigee of only 80 km and an apogee of 410 km. It probably reentered on the first orbit at around 0230 - 0300 GMT somewhere between East Africa and western China. References: 2, 552, 554. Level: 1.

2000 February 18 - 01:04 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44LP. LV Configuration: Ariane 44LP-3 V127.

Superbird 4 Mass: 4,057 kg (8,944 lb). Class: Communications. Spacecraft: HS 601. Manufacturer: Hughes Space and Communications, El Segundo. Agency: SCC. Perigee: 35,779 km (22,231 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. COSPAR: 2000-012A. USAF Sat Cat: 26095. Provided geosynchronous communications services for the Space Communications Corporation of Japan. Carried 23 Ku-band and 6 Ka-band transponders, and was equipped with a Marquardt R4D apogee engine and XIPS ion propulsion stationkeeping system. Stationed at 162 deg E. Positioned in geosynchronous orbit at 162 deg E in 2000. As of 4 September 2001 located at 162.01 deg E drifting at 0.003 deg W per day. As of 2007 Mar 9 located at 161.98E drifting at 0.004W degrees per day. References: 2, 552, 554. Level: 1.

2000 October 6 - 23:00 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 42L. LV Configuration: Ariane 42L-3 V133.

N-SAT-110 Mass: 3,531 kg (7,784 lb). Class: Communications. Spacecraft: AS 2100. Manufacturer: Lockheed Martin, Sunnyvale. Agency: SCC. Perigee: 35,782 km (22,233 mi). Apogee: 35,792 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2000-060A. USAF Sat Cat: 26559. N-SAT-110, also known as Superbird 5, was jointly owned by SCC (Space Communications Corporation of Tokyo) and JSat (Japan Satellite Systems). SCC controlled the vehicle on orbit. The satellite carried 24 Ku-band transponders. By October 15 N-SAT-110 was in a 35610 x 35752 km x 0.1 deg orbit drifting past 109 deg E. Stationed at 110 deg E. Positioned in geosynchronous orbit at 110 deg E in 2000. As of 4 September 2001 located at 110.06 deg E drifting at 0.012 deg W per day. As of 2007 Mar 11 located at 110.07E drifting at 0.007W degrees per day. References: 2, 552, 554. Level: 1.

2000 November 29 -

Discovery of Y000593 Meteorite (Mars Meteorite) Level: 1.

2000 December 3 -

Discovery of Y000749 Meteorite (Mars Meteorite) Level: 1.

2000 December 4 - 09:16 GMT - Launch Site: SvalRak. Launch Complex: -. Launch Pad: -. Launch Vehicle: S. Model: SS-520. LV Configuration: SS-520 SS-520-2.

Ionosphere mission Agency: ISAS. Apogee: 1,108 km (688 mi). References: 2. Level: 1.

2000 December 20 - Launch Site: Kourou. Launch Complex: ELA3. Launch Pad: -. Launch Vehicle: Ariane 5. Model: Ariane 5G. LV Configuration: Ariane 5G V138 508.

LDREX Mass: 1,414 kg (3,117 lb). Class: Technology. Spacecraft: LDREX. Manufacturer: National Space Development Agency, Japan. Agency: NASDA. Perigee: 241 km (149 mi). Apogee: 30,257 km (18,800 mi). Inclination: 2.40 deg. Period: 527.50 min. COSPAR: 2000-081C. USAF Sat Cat: 26640. 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. References: 2, 552, 554. Level: 1.

2001 March 8 - Launch Site: Kourou. Launch Complex: ELA3. Launch Pad: -. Launch Vehicle: Ariane 5. Model: Ariane 5G. LV Configuration: Ariane 5G V140 509.

BSAT-2a Program: BSAT. Mass: 3,050 kg (6,720 lb). Class: Communications. Spacecraft: Star bus. Manufacturer: Alcatel Space. Agency: BSAT. Perigee: 35,764 km (22,222 mi). Apogee: 35,807 km (22,249 mi). Inclination: 0.10 deg. Period: 1,436.10 min. COSPAR: 2001-011B. USAF Sat Cat: 26720. BSAT-2a was a Japanese geosynchronous communications spacecraft and the second Orbital STAR-class television broadcasting satellite. Its launch mass was 1317 kg; dry mass was 535 kg. The satellite had a Thiokol Star 30CBP solid apogee motor. The new BSTAR STAR-class satellites are a new design replacing the earlier Starbus type satellite of which only one (Cakrawarta 1) was launched. BSAT Corp. (Broadcasting Satellite System Corp.) earlier launched HS-376 satellites BSAT 1a and 1b, replacing the government's BS series which began Japanese direct broadcast services in 1978. The satellite was to be parked over 110 deg-E longitude to provide direct-to-home voice, video and internet communications. Positioned in geosynchronous orbit at 110 deg E in 2001 As of 5 September 2001 located at 109.82 deg E drifting at 0.018 deg W per day. As of 2007 Mar 11 located at 109.92E drifting at 0.009W degrees per day. References: 2, 552, 554. Level: 1.

2001 March 21 - Launch Site: Kagoshima. Launch Complex: -. Launch Pad: -. Launch Vehicle: MT-135. Model: MT-135. LV Configuration: MT-135 R1119.

Last flight Aeronomy mission Agency: ISAS. Apogee: 55 km (34 mi). The Japan Meteorological Agency launched the 1119th MT-135P meteorological sounding rocket from the meteorological observation station in Sanriku-cho, Iwate-ken. This was the final launch of the type. The MT-135P had served for more than thirty years gathering meteorological data in the upper atmosphere since the first launching on July 15, 1970. IHI Aerospace Co., Ltd. has been responsible for design, development and manufacture of the MT-135P. References: 2. Level: 1.

2001 July 12 - 21:58 GMT - Launch Site: Kourou. Launch Complex: ELA3. Launch Pad: -. Launch Vehicle: Ariane 5. Model: Ariane 5G. LV Configuration: Ariane 5G V142 510.

BSAT-2b Program: BSAT. Mass: 3,105 kg (6,845 lb). Class: Communications. Spacecraft: Star bus. Manufacturer: Alenia Aerospazio. Agency: BSAT. Perigee: 659 km (409 mi). Apogee: 17,400 km (10,800 mi). Inclination: 2.90 deg. Period: 317.20 min. COSPAR: 2001-029B. USAF Sat Cat: 26864. BSAT-2b was planned as a geosynchronous television broadcast satellite for the Japanese B-SAT company. It used Orbital's Star 1 bus and had a launch mass of 1298 kg. It carried a Thiokol Star 30 solid apogee motor and a set of station-keeping thrusters with 200 kg of propellant. A propulsion problem in the final stage of rocket stranded the satellite at a much lower altitude than planned. Since BSAT 2B carried only a soild propellant apogee kick motor, it was unable to maneuver itself to a useful orbit. References: 2, 296. Level: 1.

2001 August 29 - 07:00 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 202. LV Configuration: H-IIA 202 H-IIA-1F.

LRE Mass: 3,500 kg (7,700 lb). Class: Earth. Type: Geodesy. Spacecraft: LRE. Agency: NASDA (Japan). Perigee: 271 km (168 mi). Apogee: 36,214 km (22,502 mi). Inclination: 28.00 deg. COSPAR: 2001-038A. USAF Sat Cat: 26898. 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. References: 2, 296. Level: 1.

VEP-2 Mass: 3,500 kg (7,700 lb). Class: Technology. Spacecraft: VEP. Agency: NASDA (Japan). Perigee: 291 km (180 mi). Apogee: 35,979 km (22,356 mi). Inclination: 28.60 deg. Period: 636.60 min. COSPAR: 2001-038B. USAF Sat Cat: 26899. 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. References: 2, 296, 552, 554. Level: 1.

2002 February 4 - 02:45 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-2F.

MDS-1 Mass: 304 kg (670 lb). Class: Technology. Spacecraft: MDS. Agency: NASDA (Japan). Perigee: 373 km (231 mi). Apogee: 35,753 km (22,215 mi). Inclination: 28.30 deg. Period: 633.80 min. COSPAR: 2002-003A. USAF Sat Cat: 27367. 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. References: 2, 552, 554. Level: 1.

DASH Mass: 70 kg (154 lb). Class: Technology. Spacecraft: DASH 2002. Agency: NASDA (Japan). Perigee: 357 km (221 mi). Apogee: 35,778 km (22,231 mi). Inclination: 28.30 deg. Period: 634.00 min. COSPAR: 2002-003B. USAF Sat Cat: 27368. 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. References: 2, 552, 554. Level: 1.

2002 February 6 - 10:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-30.

NTV-2 Thermosphere Aeronomy mission Agency: ISAS. Apogee: 150 km (90 mi). References: 2. Level: 1.

2002 March 29 - 01:29 GMT - Launch Site: Kourou. Launch Complex: ELA2. Launch Pad: -. Launch Vehicle: Ariane. Model: Ariane 44L. LV Configuration: Ariane 44L V149.

JCSAT 8 Program: JCSAT. Payload: JC-Sat 2A. Mass: 3,800 kg (8,300 lb). Class: Communications. Spacecraft: HS 601. Manufacturer: Boeing Satellite Systems. Agency: JSAT. Perigee: 35,770 km (22,220 mi). Apogee: 35,802 km (22,246 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2002-015B. USAF Sat Cat: 27400. Communications satellite. Launch delayed from mid-March. JCSAT 8 was a Boeing BSS-601 with a launch mass of 2600 kg and a dry mass around 1200 kg. It was to be used by Japan Satellite to replace JCSAT 2. As of 2007 Mar 10 located at 24.29E drifting at 0.020W degrees per day. References: 2, 552, 554. Level: 1.

2002 April 10 -

Yuji Hyakutake Dies At 51 Level: 1.

2002 July 5 - 23:22 GMT - Launch Site: Kourou. Launch Complex: ELA3. Launch Pad: -. Launch Vehicle: Ariane 5. Model: Ariane 5G. LV Configuration: Ariane 5G s/n V153 "Ville de Charleroi".

NStar c Mass: 4,050 kg (8,920 lb). Class: Communications. Spacecraft: Star bus. Manufacturer: Alcatel Space. Agency: Stellat (France). Perigee: 35,772 km (22,227 mi). Apogee: 35,801 km (22,245 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2002-035B. USAF Sat Cat: 27461. Launch delayed from late June. The N-Star c satellite was an S-band satellite for mobile telephone communications for NTT DoCoMo of Japan. N-Star c had a communications payload built by Lockheed Martin and used the Star 2 bus from Orbital. The small Star 2 satellite had a dry mass around 800 kg and was the first flight of a new Orbital hydrazine/nitrogen tetroxide liquid apogee propulsion system with a 500N thrust apogee engine developed by Japan's IHI. As of 2007 Mar 9 located at 135.92E drifting at 0.012W degrees per day. References: 2, 552, 554. Level: 1.

2002 July 14 - 01:34 GMT - Launch Site: Woomera. Launch Complex: LA1. Launch Pad: -. Launch Vehicle: S. Model: NAL-735. FAILURE: Failure.

National Experimental Supersonic Transport NEXST-1 test Agency: NAL. Apogee: 0 km ( mi). The intention was that an 11.5-m-long, one tenth scale model of the aircraft would be propelled by the NAL-735 solid rocket booster to Mach 2 at 18 km altitude. Instead the vehicle lost stability and crashed near the launch point. References: 2. Level: 1.

2002 August 3 - 14:24 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-31.

SEEK-2 Aeronomy mission Agency: ISAS. Apogee: 152 km (94 mi). References: 2. Level: 1.

2002 August 3 - 14:39 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-32.

SEEK-2 Aeronomy mission Agency: ISAS. Apogee: 117 km (72 mi). References: 2. Level: 1.

2002 September 10 - 08:20 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-3F.

USERS Mass: 1,726 kg (3,805 lb). Class: Materials. Spacecraft: USERS. Manufacturer: Mitsubishi Electric. Agency: NASDA (Japan). Perigee: 497 km (308 mi). Apogee: 508 km (315 mi). Inclination: 30.40 deg. Period: 94.70 min. COSPAR: 2002-042A. USAF Sat Cat: 27515. 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. References: 2, 552, 554. Level: 1.

DRTS Payload: Kodama (DRTS-W). Mass: 2,800 kg (6,100 lb). Class: Communications. Spacecraft: DRTS. Manufacturer: Mitsubishi Electric. Agency: NASDA (Japan). Perigee: 35,770 km (22,220 mi). Apogee: 35,804 km (22,247 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2002-042B. USAF Sat Cat: 27516. 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. References: 2, 552, 554. Level: 1.

2002 December 14 - 23:04 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 202. LV Configuration: H-IIA 202 H-IIA-4F.

Adeos 2 Payload: Midori 2. Mass: 3,730 kg (8,220 lb). Class: Earth. Type: Landsat. Spacecraft: Adeos. Manufacturer: Mitsubishi Electric. Agency: NASDA (Japan). Perigee: 804 km (499 mi). Apogee: 806 km (500 mi). Inclination: 98.70 deg. Period: 101.00 min. COSPAR: 2002-056A. USAF Sat Cat: 27597. Environment Monitoring, Aeronomy. References: 2, 552, 554. Level: 1.

Mu-Labsat Mass: 65 kg (143 lb). Class: Technology. Manufacturer: NASDA. Agency: NASDA. Perigee: 793 km (492 mi). Apogee: 806 km (500 mi). Inclination: 98.70 deg. Period: 100.90 min. COSPAR: 2002-056B. USAF Sat Cat: 27598. 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 References: 2, 552, 554. Level: 1.

WEOS Kanta-Kun Mass: 50 kg (110 lb). Class: Earth. Type: Landsat. Manufacturer: Chiba Institute of Technology (Japan). Agency: Chiba Institute of Technology (Japan). Perigee: 789 km (490 mi). Apogee: 804 km (499 mi). Inclination: 98.70 deg. Period: 100.80 min. COSPAR: 2002-056D. USAF Sat Cat: 27600. Ecology. References: 2, 552, 554. Level: 1.

2002 December 20 -

Nozomi, Earth Flyby Spacecraft: Nozomi. Level: 1.

2003 March 28 - 01:27 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-5F.

IGS-1a Mass: 850 kg (1,870 lb). Class: Surveillance. Type: Military. Spacecraft: IGS. Perigee: 483 km (300 mi). Apogee: 495 km (307 mi). Inclination: 97.30 deg. Period: 94.20 min. COSPAR: 2003-009A. USAF Sat Cat: 27698. 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. References: 2. Level: 1.

IGS-1b Mass: 1,200 kg (2,600 lb). Class: Surveillance. Type: Radarsat. Spacecraft: IGS. Perigee: 489 km (303 mi). Apogee: 500 km (310 mi). Inclination: 97.30 deg. Period: 94.20 min. COSPAR: 2003-009B. USAF Sat Cat: 27699. Radar satellite. References: 2. Level: 1.

2003 May 9 - Launch Site: Kagoshima. Launch Complex: M-V. Launch Pad: -. Launch Vehicle: M-V. Model: M-V. LV Configuration: M-V-1 M-V-5.

Hayabusa Payload: MUSES-C. Mass: 500 kg (1,100 lb). Class: Planetary. Type: Asteroid. Spacecraft: Hayabusa. Agency: ISAS. COSPAR: 2003-019A. USAF Sat Cat: 27809. Asteroid sample return probe launched toward asteroid 1998 SF36. Launch delayed from Nov. 24, 2002, then May 5, 2003. References: 2. Level: 1.

2003 June 11 - Launch Site: Kourou. Launch Complex: ELA3. Launch Pad: -. Launch Vehicle: Ariane 5. Model: Ariane 5G. LV Configuration: Ariane 5G V161.

BSAT-2c Program: BSAT. Payload: Star 1. Mass: 1,298 kg (2,861 lb). Class: Communications. Spacecraft: Star bus. Manufacturer: Orbital Sciences. Agency: Broadcasting Satellite System Corp. Perigee: 35,771 km (22,227 mi). Apogee: 35,802 km (22,246 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2003-028B. USAF Sat Cat: 27831. As of 2007 Mar 9 located at 155.98E drifting at 0.008W degrees per day. References: 2. Level: 1.

2003 June 19 -

Nozomi, Earth Flyby, Successful Spacecraft: Nozomi. Level: 1.

2003 June 30 - Launch Site: Plesetsk. Launch Complex: LC133/3. Launch Pad: -. Launch Vehicle: UR-100N. Model: Rokot. LV Configuration: Rokot / Briz-KM.

Cute-1 Mass: 1.00 kg (2.20 lb). Class: Technology. Spacecraft: Cubesat. Agency: Tokyo Institute of Technology. Perigee: 817 km (507 mi). Apogee: 833 km (517 mi). Inclination: 98.70 deg. Period: 101.40 min. COSPAR: 2003-031E. USAF Sat Cat: 27844. CUTE-I carried engineering test equipment and was built by the Tokyo Institute of Technology. References: 2. Level: 1.

CubeSat XI-IV Mass: 1.00 kg (2.20 lb). Class: Technology. Spacecraft: Cubesat. Agency: University of Tokyo. Perigee: 818 km (508 mi). Apogee: 833 km (517 mi). Inclination: 98.70 deg. Period: 101.40 min. COSPAR: 2003-031J. USAF Sat Cat: 27848. Cubesat XI carried technology tests for the University of Tokyo. References: 2. Level: 1.

2003 October 30 - 13:43 GMT - Launch Site: Plesetsk. Launch Complex: LC133/3. Launch Pad: -. Launch Vehicle: UR-100N. Model: Rokot. LV Configuration: Rokot 4921921121.

Servis-1 Mass: 840 kg (1,850 lb). Class: Technology. Spacecraft: SERVIS. Agency: USEF. Perigee: 984 km (611 mi). Apogee: 1,016 km (631 mi). Inclination: 99.50 deg. Period: 105.10 min. COSPAR: 2003-050A. USAF Sat Cat: 28060. The mission of the 'Space Environment Reliability Verification of Integrated System' was to flight test a range of commerical-grade spacecraft components including a computer, star tracker, battery, and laser gyro. The objective was to lower the cost of future satellites. References: 2. Level: 1.

2003 November 29 - 04:33 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: 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.

IGS-2a Mass: 850 kg (1,870 lb). Class: Surveillance. Type: Military. Spacecraft: IGS. COSPAR: F20031129A. 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. References: 2. Level: 1.

IGS-2b Mass: 1,200 kg (2,600 lb). Class: Surveillance. Type: Radarsat. Spacecraft: IGS. COSPAR: F20031129B. References: 2. Level: 1.

2003 December 14 -

Nozomi, Mars Flyby Spacecraft: Nozomi. The Japanese Mars probe, Nozomi, flew past the planet at a height of 1000 km. Attempts to operate the spacecraft's main propulsion system failed, and small thrusters were used to increase the flyby distance by about 100 km to ensure a clean miss. The mission was abandoned, and Nozomi entered a new orbit around the Sun. Level: 1.

2004 January 17 - 15:30 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-33.

WAVE2004 Aeronomy mission Agency: ISAS. Apogee: 141 km (87 mi). References: 2. Level: 1.

2004 March 13 - 05:40 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36B. Launch Pad: SLC36B. Launch Vehicle: Atlas V. Model: Atlas IIIA. LV Configuration: Atlas 3A AC-202.

MBSAT Mass: 4,143 kg (9,133 lb). Class: Communications. Spacecraft: FS-1300. Manufacturer: Space Systems/Loral. Agency: Mobile Broadcasting Corp. Perigee: 35,779 km (22,231 mi). Apogee: 35,795 km (22,241 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2004-007A. USAF Sat Cat: 28184. Mobile S-band digital broadcasting services for home and automobile users in Japan. As of 2007 Mar 9 located at 144.03E drifting at 0.009W degrees per day. References: 2, 552, 554. Level: 1.

2004 April 16 - 00:45 GMT - Launch Site: Cape Canaveral. Launch Complex: LC36A. Launch Pad: SLC36A. Launch Vehicle: Atlas. Model: Atlas IIAS. LV Configuration: Atlas IIAS AC-163.

Superbird 6 Class: Communications. Spacecraft: HS 601. Agency: Japanese Communications Corporation. Perigee: 35,775 km (22,229 mi). Apogee: 35,797 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2004-011A. USAF Sat Cat: 28218. The satellite was to provide Ka and Ku band communications for Japan's Space Communications Corporation. References: 2. Level: 1.

2004 May 19 -

Hayabusa (MUSES-C), Earth Gravity Assist, Successful Spacecraft: Hayabusa. Level: 1.

2004 August 9 - 08:15 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-34.

Solar Sails Technology mission Agency: ISAS. Apogee: 170 km (100 mi). References: 2. Level: 1.

2005 February 26 - 09:25 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 2022. LV Configuration: H-IIA 2022 H-IIA-7F.

Himawari 6 Payload: MT-Sat 1R. Mass: 3,300 kg (7,200 lb). Class: Meteorology. Spacecraft: FS-1300. Manufacturer: Space Systems/Loral. Agency: Ministry of Land, Infrastructure and Transport. Perigee: 35,778 km (22,231 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.00 deg. Period: 1,436.20 min. COSPAR: 2005-006A. USAF Sat Cat: 28622. 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. References: 2. Level: 1.

2005 July 10 - 03:30 GMT - Launch Site: Kagoshima. Launch Complex: M-V. Launch Pad: -. Launch Vehicle: M-V. Model: M-V. LV Configuration: M-V-1 M-V-6.

Suzaku Payload: Astro E2. Mass: 1,680 kg (3,700 lb). Class: Astronomy. Type: X-Ray. Spacecraft: ASTRO E. Manufacturer: NEC Toshiba. Agency: JAXA. Perigee: 562 km (349 mi). Apogee: 573 km (356 mi). Inclination: 31.40 deg. Period: 96.00 min. COSPAR: 2005-025A. USAF Sat Cat: 28773. Delayed from February, June 26, July 6 and 8, 2005. CUTE-1.7 nanosat mistakenly reported on this flight. Astro-E2 was renamed Suzaku (after a legendary red bird) after launch. It replaced the Astro-E, which never reached orbit due to an M-V-4 launch failure in 2000. The satellite had five 0.4-meter diameter X-ray telescopes, one with an XRS microcalorimeter and the other four with X-ray CCD cameras. However it was revealed that the XRS failed on 9 August due to leaking of helium coolant. References: 2. Level: 1.

2005 August 23 - 21:10 GMT - Launch Site: Baikonur. Launch Complex: LC109. Launch Pad: LC109/95. Launch Vehicle: R-36M. Model: Dnepr.

Kirari Mass: 570 kg (1,250 lb). Class: Technology. Spacecraft: Kirari. Manufacturer: NEC Toshiba. Agency: JAXA. Perigee: 596 km (370 mi). Apogee: 614 km (381 mi). Inclination: 97.80 deg. Period: 96.80 min. COSPAR: 2005-031A. USAF Sat Cat: 28809. Moved from J-1A . Delayed from August 15. Optical Inter-Orbit Communications Engineering Test Satellite. Its laser communications experiment was be used in with ESA's Artemis geostationary satellite. The satellite was renamed Kirari (twinkle) after launch. References: 2. Level: 1.

Reimei Payload: Index. Mass: 60 kg (132 lb). Class: Technology. Manufacturer: Mitsubishi Electric. Agency: JAXA. Perigee: 601 km (373 mi). Apogee: 650 km (400 mi). Inclination: 97.80 deg. Period: 97.20 min. COSPAR: 2005-031B. USAF Sat Cat: 28810. Plasma Science Technology. INDEX, renamed Reimei ("Dawn") after launch, was a test satellite with new lightweight satellite components, and a demonstration auroral imager payload. References: 2. Level: 1.

2005 September 12 -

Yohkoh Reenters Into Earth's Atmosphere Level: 1.

2005 September 12 -

Hayabusa (MUSES-C), Asteroid 25143 Itokawa Arrival, Successful Spacecraft: Hayabusa. Level: 1.

2005 October 27 - 06:52 GMT - Launch Site: Plesetsk. Launch Complex: LC132/1. Launch Pad: -. Launch Vehicle: Kosmos 3. Model: Kosmos 11K65M. LV Configuration: Kosmos 11K65M 104.

Cubesat XI-V Mass: 1.00 kg (2.20 lb). Class: Technology. Type: Civilian. Spacecraft: Cubesat. Agency: University of Tokyo. Perigee: 682 km (423 mi). Apogee: 708 km (439 mi). Inclination: 98.20 deg. Period: 98.70 min. COSPAR: 2005-043F. USAF Sat Cat: 28895. University of Tokyo cubesat. Released from SSETI Express. References: 2. Level: 1.

2005 November 9 -

Hayabusa releases target marker. Hayabusa released the first of three 10-cm target markers towards the surface of asteroid Itokawa. It missed the surface and floated off into deep space. Level: 1.

2005 November 12 -

Hayabusa, MINERVA Landing, Failed Spacecraft: Hayabusa. Level: 1.

2005 November 12 -

Hayabusa releases Minerva nano-lander. Hayabusa probe skimmed at an altitude of 55 m over asteroid Itokawa. The Minerva nano-lander was released, but missed the asteroid and floated out into deep space. Hayabusa was then moved to a safe position 5 km from the surface and the control team considered its next move. Level: 1.

2005 November 19 -

Hayabusa lands on Itokawa. Hayabusa released the second target marker at 20:30 GMT and this marker stayed on the surface, arriving at 20:36. Hayabusa then homed on the target and bounced off the surface at 21:10, followed by a firm landing at 21:30. It stayed on the surface until 21:58 - it was uncertain whether the planned surface sample had been obtained. A safe-mode command sent it Hayabusa to a distance of 100 km from the asteroid as the team considered their next move. Level: 1.

2005 November 20 -

Hayabusa (MUSES-C), first Asteroid 25143 Itokawa Sample Collection, Failed Spacecraft: Hayabusa. Level: 1.

2005 November 25 -

Hayabusa (MUSES-C), second Asteroid 25143 Itokawa Sample Collection Spacecraft: Hayabusa. Level: 1.

2005 November 27 -

Hayabusa returns to Itokawa. The spacecraft grazed the surface again at 22:07. However it was again uncertain if any surface material was obtained. Control of the spacecraft was lost again due to orientation jet failures which prevented the satellite from pointing its high gain antenna toward earth. Level: 1.

2005 December 1 -

Hayabusa (MUSES-C), Asteroid 25143 Itokawa Departure Spacecraft: Hayabusa. Level: 1.

2006 January 22 - 04:00 GMT - Launch Site: Kagoshima. Launch Complex: L. Launch Pad: K. Launch Vehicle: S. Model: S-310. LV Configuration: S-310-36.

Furoshiki Technology test Agency: JAXA. Apogee: 130 km (80 mi). References: 2. Level: 1.

2006 January 24 - 01:33 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 2022. LV Configuration: H-IIA 2022 H-IIA-8F.

Daichi Payload: ALOS-1. Mass: 3,850 kg (8,480 lb). Class: Surveillance. Spacecraft: Daichi. Manufacturer: NEC Toshiba. Agency: JAXA. Perigee: 693 km (430 mi). Apogee: 697 km (433 mi). Inclination: 98.20 deg. Period: 98.70 min. COSPAR: 2006-002A. USAF Sat Cat: 28931. 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. References: 2. Level: 1.

2006 February 18 - 06:27 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-9F.

MTSAT-2 Payload: MT-Sat 2. Mass: 3,000 kg (6,600 lb). Class: Meteorology. Spacecraft: DS2000. Manufacturer: Mitsubishi. Agency: Ministry of Land, Infrastructure and Transport. Perigee: 35,771 km (22,227 mi). Apogee: 35,803 km (22,246 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2006-004A. USAF Sat Cat: 28937. 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. References: 2. Level: 1.

2006 February 21 - 21:28 GMT - Launch Site: Kagoshima. Launch Complex: M-V. Launch Pad: -. Launch Vehicle: M-V. Model: M-V. LV Configuration: M-V-1 M-V-8.

Astro F (Akari) Mass: 960 kg (2,110 lb). Class: Astronomy. Type: Infrared. Spacecraft: Akari. Manufacturer: NEC Toshiba. Agency: JAXA. Perigee: 705 km (438 mi). Apogee: 719 km (446 mi). Inclination: 98.20 deg. Period: 99.00 min. COSPAR: 2006-005A. USAF Sat Cat: 28939. Carried a 0.67m-diameter liquid-helium-cooled infrared telescope with detectors ranging from the near infrared to 60 and 170 micron channels in the far IR. It was to carry out the first far infrared sky survey since IRAS in 1983. References: 2. Level: 1.

Cute 1.7 Mass: 3.00 kg (6.60 lb). Class: Technology. Manufacturer: Tokyo�Inst.�Tech. Agency: Tokyo�Inst.�Tech. Perigee: 297 km (184 mi). Apogee: 685 km (425 mi). Inclination: 98.20 deg. Period: 94.40 min. COSPAR: 2006-005C. USAF Sat Cat: 28941. Student subsatellite ejected from the M-V-8 third stage at 21:45 GMT. References: 2. Level: 1.

2006 April 12 - 23:30 GMT - Launch Site: Kiritimati. Launch Complex: -. Launch Pad: 0.0 N x 154.0 W. Launch Vehicle: Zenit. Model: Zenit-3SL. LV Configuration: Zenit-3SL 21.

JCSAT 9 Payload: A2100AX. Mass: 4,401 kg (9,702 lb). Class: Communications. Spacecraft: AS 2100. Manufacturer: Lockheed Martin, Sunnyvale. Agency: JSAT. Perigee: 35,785 km (22,235 mi). Apogee: 35,790 km (22,230 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2006-010A. USAF Sat Cat: 29045. As of 2007 Mar 8 located at 132.01E drifting at 0.014W degrees per day. References: 2. Level: 1.

2006 August 11 - 22:15 GMT - Launch Site: Kourou. Launch Complex: ELA3. Launch Pad: -. Launch Vehicle: Ariane 5. Model: Ariane 5ECA. LV Configuration: Ariane 5ECA V172 (531).

JCSAT 10 Payload: AS2100AX. Mass: 4,048 kg (8,924 lb). Class: Communications. Spacecraft: AS 2100. Manufacturer: Lockheed Martin, Sunnyvale. Agency: JSAT. Perigee: 35,781 km (22,233 mi). Apogee: 35,793 km (22,240 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2006-033A. USAF Sat Cat: 29272. Ku/C-band television broadcasting satellite for the Japanese market; mass 1858 kg dry. As of 2007 Mar 11 located at 128.01E drifting at 0.012W degrees per day. References: 2. Level: 1.

2006 September 11 - 04:35 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 202. LV Configuration: H-IIA 202 H-IIA-10.

IGS-3A Mass: 850 kg (1,870 lb). Class: Surveillance. Type: Military. Spacecraft: IGS. Manufacturer: Melco. Agency: JIDF. Perigee: 484 km (300 mi). Apogee: 491 km (305 mi). Inclination: 97.30 deg. COSPAR: 2006-037A. USAF Sat Cat: 29393. 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. References: 2. Level: 1.

2006 September 22 - 21:36 GMT - Launch Site: Kagoshima. Launch Complex: M-V. Launch Pad: -. Launch Vehicle: M-V. Model: M-V. LV Configuration: M-V-1 M-V-7.

Hinode (Solar B) Mass: 870 kg (1,910 lb). Class: Solar. Spacecraft: Hinode. Manufacturer: Melco. Agency: JAXA. Perigee: 674 km (418 mi). Apogee: 695 km (431 mi). Inclination: 98.10 deg. Period: 98.50 min. COSPAR: 2006-041A. USAF Sat Cat: 29479. Solar satellite with a large optical telescope and an X-ray telescope built by the Smithsonian Observatory. References: 2. Level: 1.

SSSat Mass: 1.00 kg (2.20 lb). Class: Technology. Agency: JAXA. Perigee: 279 km (173 mi). Apogee: 659 km (409 mi). Inclination: 98.30 deg. Period: 94.00 min. COSPAR: 2006-041D. USAF Sat Cat: 29484. Solar sail experiment. References: 2. Level: 1.

Hitsat Mass: 1.00 kg (2.20 lb). Class: Technology. Manufacturer: Hokkaido Space. Agency: Hokkaido Space. Perigee: 279 km (173 mi). Apogee: 659 km (409 mi). Inclination: 98.30 deg. Period: 94.00 min. COSPAR: 2006-041F. USAF Sat Cat: 29484. References: 2. Level: 1.

2006 October 13 - 20:56 GMT - Launch Site: Kourou. Launch Complex: ELA3. Launch Pad: -. Launch Vehicle: Ariane 5. Model: Ariane 5ECA. LV Configuration: Ariane 5ECA V173 (533).

LDREX 2 Class: Technology. Spacecraft: LDREX. Agency: JAXA. COSPAR: 2006-043C. USAF Sat Cat: 29496. LDREX-2 was attached to the upper stage. It deployed a 6.5-meter antenna design planned for the later ETS-8 satellite References: 2. Level: 1.

2006 December 16 - 06:32 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 204. LV Configuration: H-IIA 204 H-IIA-11.

Kiku 8 Payload: ETS-8. Mass: 5,817 kg (12,824 lb). Class: Technology. Spacecraft: ETS. Manufacturer: Melco. Agency: JAXA. Perigee: 35,775 km (22,229 mi). Apogee: 35,798 km (22,243 mi). Inclination: 0.0500 deg. Period: 1,436.11 min. COSPAR: 2006-059A. USAF Sat Cat: 29656. 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. References: 2. Level: 1.

2007 February 24 - 04:41 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 2024. LV Configuration: H-IIA 2024 H-IIA-12.

IGS-2 Payload: IGS 4A. Mass: 1,200 kg (2,600 lb). Class: Surveillance. Type: Radarsat. Spacecraft: IGS. Manufacturer: Melco. Agency: JAXA/CSICE. COSPAR: 2007-005A. USAF Sat Cat: 30586. Information Gathering Satellite Radar-2. Japanese military satellite using a synthetic aperture radar for all-weather, 24-hour, high-resolution surveillance of the earth. References: 2. Level: 1.

IGS-3V Payload: IGS 4B. Mass: 850 kg (1,870 lb). Class: Surveillance. Type: Military. Spacecraft: IGS. Manufacturer: Melco. Agency: JAXA/CSICE. COSPAR: 2007-005B. USAF Sat Cat: 30587. Optical-3 Verification Satellite, an experimental satellite on a six-month mission to test payloads planned for the Optical-3 second-generation Japanese military optical surveillance satellite. The production-type Optical-3 satellite was expected to launch in 2009. References: 2. Level: 1.

2007 August 14 - 23:44 GMT - Launch Site: Kourou. Launch Complex: ELA3. Launch Pad: -. Launch Vehicle: Ariane 5. Model: Ariane 5ECA. LV Configuration: Ariane 5ECA V177 (537).

BSAT-3A Payload: A2100A. Mass: 1,967 kg (4,336 lb). Class: Communications. Spacecraft: AS 2100. Manufacturer: Lockheed Martin, Sunnyvale. Agency: BSAT. Perigee: 35,746 km (22,211 mi). Apogee: 35,826 km (22,261 mi). Inclination: 0.10 deg. Period: 1,436.00 min. COSPAR: 2007-036B. USAF Sat Cat: 32019. Satllite launched for the Japan Broadcasting Satellite Systems Corp. (BSAT) with a Ku-band television payload. Mass 930 kg dry. References: 2. Level: 1.

2007 September 14 - 01:31 GMT - Launch Site: Tanegashima. Launch Complex: Y. Launch Pad: -. Launch Vehicle: H-2. Model: H-IIA 2022. LV Configuration: H-IIA 2022 H-IIA-13.

Kaguya Payload: Selene. Class: Planetary. Type: Lunar. Spacecraft: Kaguya. COSPAR: 2007-039A. USAF Sat Cat: 32054. 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. References: 2. Level: 1.

Okina Payload: Selene. Class: Planetary. Type: Lunar. Spacecraft: Kaguya. COSPAR: 2007-039B. USAF Sat Cat: 32055. 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. References: 2. Level: 1.

Ouna Payload: Selene. Class: Planetary. Type: Lunar. Spacecraft: Kaguya. COSPAR: 2007-039C. USAF Sat Cat: 32056. 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. References: 2. Level: 1.

2008 February 23 - 08:55 GMT - Launch Site: Tanegashima. Launch Vehicle: H-2. Model: H-IIA 2024.

Kizuna Mass: 2,700 kg (5,900 lb). Class: Communications. Spacecraft: Kizuna. Perigee: 35,775 km (22,229 mi). Apogee: 35,799 km (22,244 mi). Inclination: 0.00 deg. Period: 1,436.10 min. COSPAR: 2008-007A. USAF Sat Cat: 32500. WINDS, the Wide-band Internetworking Engineering Test and Demonstration Satellite, was designed to demonstrate delivery of high bandwidth Ka-band Internet service to remote areas of Japan and Southeast Asia from geostationary orbit at 143 deg E. Users with a small 45 cm in diameter antenna could receive data at up to 155 Mbps and transmit data at up to 6 Mbps. Level: 1.

2008 April 28 - 03:53 GMT - Launch Site: Sriharikota. Launch Vehicle: PSLV.

Cute-1.7-APD-II Mass: 4.00 kg (8.80 lb). Class: Technology. Perigee: 615 km (382 mi). Apogee: 635 km (394 mi). Inclination: 98.00 deg. Period: 97.20 min. COSPAR: 2008-021C. USAF Sat Cat: 32785. Tokyo Institute of Technology nanosat. Level: 1.

SEEDS 2 Class: Technology. Perigee: 614 km (381 mi). Apogee: 637 km (395 mi). Inclination: 98.00 deg. Period: 97.20 min. COSPAR: 2008-021J. USAF Sat Cat: 32791. Nihon University at Tokyo nanosat. Level: 1.

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