Tanegashima Y (original) (raw)

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z

Tanegashima Y

Part of Tanegashima

H-2 launch complex. Yoshinobu Launch Complex, Osaki Site.

AKA: Yoshinobu Launch Complex LP1. First Launch: 1994-02-03. Last Launch: 2014-05-24. Number: 31 . Longitude: 130.98 deg. Latitude: 30.40 deg.

Country: Japan. Spacecraft: Daichi-2, DCAM, DESPATCH, Ginrei, GPM, Horyu, MASCOT, Minerva II, Raijin, Shin'en, Shizuku, SOCRATES, SPROUT, STARS-2, Target Marker, Teikyosat, UNIFORM, ETS, Himawari, FS-1300, OREX, VEP, SFU, ADEOS, Fuji, ETS-7, ETS-7 Target, TRMM, Kakehashi, KOMPSAT, LRE, DASH 2002, MDS, DRTS, USERS, FedSat, Mu-Labsat, WEOS Kanta-Kun, IGS, Hayabusa, Cubesat, Daichi, DS2000, Kaguya, JAXA SDS. Launch Vehicles: H-II, H-IIA 202, H-IIA 2024, H-IIA 2022, H-IIA 204. Launch Sites: Tanegashima. Agency: GMS.

1994 February 3 - . 22:20 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II.

OREX - . Payload: Ryusei. Mass: 865 kg (1,906 lb). Nation: Japan. Class: Technology. Type: Re-entry test vehicle. Spacecraft: OREX. Decay Date: 1994-02-03 . USAF Sat Cat: 22978 . COSPAR: 1994-007A. Apogee: 451 km (280 mi). Perigee: 450 km (270 mi). Inclination: 30.50 deg. Period: 93.50 min. Orbital Reentry Experiment. Orbital Re-entry Experiment Vehicle (OREX) Ryusei. Acquisition of data related to atmospheric reentry. Launch vehicle H-II rocket test flight H-II 1F. Launching organization NASDA. Launch time 2220:00 UT. .
VEP - . Payload: Myojo / LAPS. Mass: 2,391 kg (5,271 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: VEP. USAF Sat Cat: 22979 . COSPAR: 1994-007B. Apogee: 36,261 km (22,531 mi). Perigee: 449 km (278 mi). Inclination: 28.60 deg. Period: 645.00 min.
Vehicle Evaluation Payload; monitored H-2 performance. Vehicle Evaluation Payload (VEP) MYOJO. Provides a ranging function as well as functions to measure the acceleration and deformation, in order to confirm the accuracy of the H-II rocket orbit injection and understand the environment of the payload equipme nt. Launch vehicle H-II rocket test flight H-II 1F. Launching organization NASDA. Launch time 2220:00 UT.

1994 August 28 - . 07:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. FAILURE: LAPS apogee kick motor failed to ignite. Partial Failure.. Failed Stage: 3.

Kiku 6 - . Payload: ETS 6. Mass: 3,800 kg (8,300 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 23230 . COSPAR: 1994-056A. Apogee: 38,677 km (24,032 mi). Perigee: 8,565 km (5,322 mi). Inclination: 13.23 deg. Period: 861.84 min. Failed to reach geostationary orbit; Engineering Test Satellite; partial mission success. Also tested ion engines for NSSK..

1995 March 18 - . 08:01 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II.

SFU - . Mass: 4,000 kg (8,800 lb). Nation: Japan. Agency: NASDA. Class: Materials. Type: Materials science satellite. Spacecraft: SFU. Decay Date: 1996-01-20 . USAF Sat Cat: 23521 . COSPAR: 1995-011A. Apogee: 483 km (300 mi). Perigee: 471 km (292 mi). Inclination: 28.50 deg. Period: 94.10 min. Space Flyer Unit; carried materials, astronomy, biological experiments; retrieved by STS-72 1/20/96..
Himawari 5 - . Payload: GMS 5. Mass: 746 kg (1,644 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Weather satellite. Spacecraft: Himawari. USAF Sat Cat: 23522 . COSPAR: 1995-011B. Apogee: 35,791 km (22,239 mi). Perigee: 35,784 km (22,235 mi). Inclination: 0.60 deg. Period: 1,436.00 min.
Geostationary Meteorological Satellite; carried search and rescue package. Stationed at 140.2 deg E. Positioned in geosynchronous orbit at 160 deg E in 1995; 140 deg E in 1995-1999 As of 5 September 2001 located at 139.99 deg E drifting at 0.028 deg W per day. As of 2007 Mar 10 located at 45.88E drifting at 3.134W degrees per day.

1996 August 17 - . 01:53 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II.

ADEOS - . Mass: 135 kg (297 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Atmosphere satellite. Spacecraft: ADEOS. USAF Sat Cat: 24277 . COSPAR: 1996-046A. Apogee: 800 km (490 mi). Perigee: 799 km (496 mi). Inclination: 98.60 deg. Period: 100.90 min.
JAS-2 - . Nation: Japan. Agency: JARL. Class: Communications. Type: Civilian communications satellite. Spacecraft: Fuji. USAF Sat Cat: 24278 . COSPAR: 1996-046B. Apogee: 1,323 km (822 mi). Perigee: 801 km (497 mi). Inclination: 98.60 deg. Period: 106.50 min. Japanese amateur radio satellite..

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

TRMM - . Nation: USA. Agency: NASA Greenbelt. Class: Earth. Type: Atmosphere satellite. Spacecraft: TRMM. Decay Date: 2015-06-16 . USAF Sat Cat: 25063 . COSPAR: 1997-074A. Apogee: 403 km (250 mi). Perigee: 395 km (245 mi). Inclination: 35.00 deg. Period: 92.50 min. TRMM was an international mission dedicated to measuring tropical and subtropical rainfall. The spacecraft and four instruments were provided by the USA, while Japan provided one instrument and launch services..
Hikoboshi - . Payload: ETS-7. Nation: Japan. Agency: NASDA. Manufacturer: Toshiba. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ETS. Spacecraft: ETS-7. Decay Date: 2015-11-13 . USAF Sat Cat: 25064 . COSPAR: 1997-074B. Apogee: 548 km (340 mi). Perigee: 545 km (338 mi). Inclination: 35.00 deg. Period: 95.50 min.
The Orihime and Hikoboshi satellites undocked and redocked on July 7 1998 in the FP-1 test of automated docking systems. Despite claims of the NASDA space agency that this is a first, automated Russian craft have docked on many occasions since the Kosmos-186/188 docking in 1968.
Orihime - . Payload: ETS-7 Target. Nation: Japan. Agency: NASDA. Manufacturer: Toshiba. Class: Technology. Type: Navigation technology satellite. Spacecraft Bus: ETS. Spacecraft: ETS-7 Target. Decay Date: 1999-01-27 . USAF Sat Cat: 25424 . COSPAR: 1997-074E. Apogee: 458 km (284 mi). Perigee: 346 km (214 mi). Inclination: 34.50 deg. Period: 92.60 min. Attached to Hikoboshi. It would later separate and serve as a passive docking target for the Hikobishi active automatic docking technology spacecraft..

1998 February 21 - . 07:55 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II.

Kakehashi - . Payload: COMETS. Nation: Japan. Agency: NASDA. Manufacturer: NEC, Toshiba. Class: Communications. Type: Civilian communications satellite. Spacecraft: Kakehashi. USAF Sat Cat: 25175 . COSPAR: 1998-011A. Apogee: 17,727 km (11,015 mi). Perigee: 1,033 km (641 mi). Inclination: 30.10 deg. Period: 328.10 min.
Kakehashi, meaning 'Bridge', was called Communuications and Broadcasting Experimental Test Satellite (COMETS) before launch. It contained Ka-band communications and inter-satellite data relay payloads. Premature shutdown 44 seconds into the H-II second stage second burn put the satellite into a much lower than planned orbit. The on-board Unified Propulsion System was used to raise it to a more useful orbit.

1999 November 15 - . 07:29 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II. FAILURE: Failure during first stage burn.. Failed Stage: 1.

MTSAT - . Mass: 2,900 kg (6,300 lb). Nation: Japan. Agency: NASDA. Manufacturer: Palo Alto. Class: Communications. Type: Civilian communications satellite. Spacecraft: FS-1300.
Multi-functional Transportation Satellite intended to provide communications and air traffic control for the Japanese transportation ministry and a meteorological data for the Japanese Meteorological Agency. The spacecraft had a mass of 1223 kg dry and was a follow-on to the GMS (Himawari) weather satellite series.

2001 August 29 - . 07:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

LRE - . Mass: 3,500 kg (7,700 lb). Nation: Japan. Agency: NASDA. Class: Earth. Type: Geodetic satellite. Spacecraft: LRE. USAF Sat Cat: 26898 . COSPAR: 2001-038A. Apogee: 33,306 km (20,695 mi). Perigee: 241 km (149 mi). Inclination: 28.59 deg. Period: 584.29 min.
Launch postponed from february, July 22 and August 25. First launch of the H-2A launch vehicle. A failure after all of the problems with the earlier H-2 version would probably have resulted in cancellation of the program. The Laser Ranging Experiment satellite carried 126 laser retro reflectors and separated from the second stage at 0739 GMT into its operational 'Molniya' type orbit. The eventual goal of H-2A was to launch geosynchronous spacecraft at costs comparable to those of other countries. The LRE remained in a simulated geosynchronous transfer orbit; laser reflections from it would be used to precisely ascertain the orbital injection accuracy of the H-2A.
VEP-2 - . Mass: 3,500 kg (7,700 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: VEP. USAF Sat Cat: 26899 . COSPAR: 2001-038B. Apogee: 35,979 km (22,356 mi). Perigee: 291 km (180 mi). Inclination: 28.60 deg. Period: 636.60 min. Vehicle Evaluation Payload-2 consisted of ballast and monitoring instrumentation that remained attached to the launch vehicle's second stage. It included a Doppler ranging experiment for orbit determination..

2002 February 4 - . 02:45 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024.

MDS-1 - . Mass: 304 kg (670 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: MDS. USAF Sat Cat: 27367 . COSPAR: 2002-003A. Apogee: 35,753 km (22,215 mi). Perigee: 373 km (231 mi). Inclination: 28.30 deg. Period: 633.80 min.
Technology qualification flight - maiden flight of H-2A booster. Launch delayed from January 31 and February 3. The second stage began its first burn at 0251 UTC and at 0257 UTC entered a 500 km circular parking orbit. After a 12 minute coast the second burn put stage 2 in geostationary transfer orbit. At 0315 UTC the small DASH vehicle was meant to separate from the upper adapter, but this apparently did not occur. At 0325 UTC VEP-3/upper adapter/DASH combination separated from the second stage, followed by two semi-cylindrical side panels, revealing the previously enclosed MDS-1 technology satellite which was ejected at 0331 UTC. At 0425 UTC the second stage was scheduled to make a third burn to test engine restart, completing the H-2A-2F mission.
DASH - . Mass: 70 kg (154 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: DASH 2002. USAF Sat Cat: 27368 . COSPAR: 2002-003B. Apogee: 35,778 km (22,231 mi). Perigee: 357 km (221 mi). Inclination: 28.30 deg. Period: 634.00 min.
The VEP-3 launch instrumentation package mounted on top of the DASH had a mass of 33 kg. The side adapter panels were halves of a 4.1m long 4.0m diameter cylinder. DASH (Demonstrator of Atmospheric Reentry System and Hypervelocity) was to test the reentry system for the MUSES-C asteroid probe. The plan was to fire the deorbit motor three days after launch, then separate the reentry capsule which would enter the Earth's atmosphere at 10 km/s and land in the Hodh el Gharbi region of Mauritania at about 8.5W 17.2N. Typical satellite reentries are at only 7.5 km/s, while hyperbolic (escape) velocity at the top of the atmosphere is over 11 km/s, so DASH would have been travelling much faster than typical reentry vehicles, but not quite at escape velocity.

2002 September 10 - . 08:20 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024.

USERS - . Mass: 1,726 kg (3,805 lb). Nation: Japan. Agency: NASDA. Manufacturer: Mitsubishi. Class: Materials. Type: Materials science satellite. Spacecraft: USERS. Decay Date: 2007-06-15 . USAF Sat Cat: 27515 . COSPAR: 2002-042A. Apogee: 508 km (315 mi). Perigee: 497 km (308 mi). Inclination: 30.40 deg. Period: 94.70 min.
Launch delayed from August 2002. First operational flight of H-2A booster. USERS (Unmanned Space Experiment Recovery System) was a Japanese microgravity experimental satellite. After 8.5 months in orbit, a reentry vehicle was to be returned to earth with the materials manufacturered in space.
Kodama - . Payload: DRTS-W. Mass: 2,800 kg (6,100 lb). Nation: Japan. Agency: NASDA. Manufacturer: Mitsubishi. Class: Communications. Type: Civilian communications satellite. Spacecraft: DS2000. USAF Sat Cat: 27516 . COSPAR: 2002-042B. Apogee: 35,804 km (22,247 mi). Perigee: 35,770 km (22,220 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
Launch delayed from August 2002. First operational flight of H-2A booster. DRTS (Data Relay Transponder Satellite) was a Japanese geostationary communications spacecraft which was to relay images and data procured by the to-be-launched ADEOS 2 and ALOS satellites, and the KIBO module on ISS, after being parked over 90� E. However the engine failed after a couple of burns. As of 2007 Mar 11 located at 90.76E drifting at 0.005W degrees per day.

2002 December 14 - . 23:04 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

Adeos 2 - . Payload: Midori 2. Mass: 3,730 kg (8,220 lb). Nation: Japan. Agency: NASDA. Manufacturer: Mitsubishi. Class: Earth. Type: Earth resources satellite. Spacecraft: Adeos. USAF Sat Cat: 27597 . COSPAR: 2002-056A. Apogee: 806 km (500 mi). Perigee: 804 km (499 mi). Inclination: 98.70 deg. Period: 101.00 min. Environment Monitoring, Aeronomy..
WEOS (Kanta Kun) - . Mass: 50 kg (110 lb). Nation: Japan. Agency: NASDA. Manufacturer: Chiba. Class: Earth. Type: Earth resources satellite. Spacecraft Bus: WEOS. Spacecraft: WEOS. USAF Sat Cat: 27600 . COSPAR: 2002-056D. Apogee: 804 km (499 mi). Perigee: 789 km (490 mi). Inclination: 98.70 deg. Period: 100.80 min. Ecology, Whale Monitoring satellite for Chiba Institute of Technology, Japan..
Mu-Labsat - . Mass: 65 kg (143 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: Mu-Labsat. USAF Sat Cat: 27598 . COSPAR: 2002-056B. Apogee: 806 km (500 mi). Perigee: 793 km (492 mi). Inclination: 98.70 deg. Period: 100.90 min.
Technology. In 2003 the satellite released two tiny subsatellites in an experiment to test an onboard tracking imager for inspector satellites. The RITE (Remote Inspection Technology Experiment) targets are disks about 0.1m in diameter. They were released from Micro-LabSat on 2003 Mar 14 at 0140 UTC and 2003 May 14 at 0150 UTC
FedSat - . Mass: 58 kg (127 lb). Nation: Australia. Agency: CSS. Manufacturer: CRCSS. Class: Communications. Type: Civilian communications satellite. Spacecraft: FedSat. USAF Sat Cat: 27599 . COSPAR: 2002-056C. Apogee: 805 km (500 mi). Perigee: 791 km (491 mi). Inclination: 98.70 deg. Period: 100.80 min.
FedSat contained high-tech communication, space science, navigation and computing equipment and was intended to help bring broadband Internet services to remote parts of Australia. Data from its three-year mission was to be shared between Japan and Australia.

2003 March 28 - . 01:27 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024.

IGS-1a - . Mass: 850 kg (1,870 lb). Nation: Japan. Agency: NASDA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: IGS. Decay Date: 2014-07-18 . USAF Sat Cat: 27698 . COSPAR: 2003-009A. Apogee: 495 km (307 mi). Perigee: 483 km (300 mi). Inclination: 97.30 deg. Period: 94.20 min.
Optical reconnaisance satellite. First Japanese military space mission. Dual payload. Delayed from February 2003. The Tanegashima facility was under strict security, guarded by 400 police officers wearing bullet-proof vests. Waters near the pad were patrolled by the coast guard.
IGS-1b - . Mass: 1,200 kg (2,600 lb). Nation: Japan. Agency: NASDA. Class: Surveillance. Type: Civilian Radarsat. Spacecraft: IGS. Decay Date: 2012-07-26 . USAF Sat Cat: 27699 . COSPAR: 2003-009B. Apogee: 500 km (310 mi). Perigee: 489 km (303 mi). Inclination: 97.30 deg. Period: 94.20 min. Radar satellite..

2003 November 29 - . 04:33 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024. FAILURE: Destroyed by range safety after solid booster nozzle burn-through resulted in motor not separating from core.. Failed Stage: 0.

IGS-2a - . Mass: 850 kg (1,870 lb). Nation: Japan. Agency: NASDA. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: IGS. The launch failure meant that Japan's planned intelligence satellite constellation was crippled. The system was already in trouble due to the reported poor performance of the first two elements launched..
IGS-2b - . Mass: 1,200 kg (2,600 lb). Nation: Japan. Agency: NASDA. Class: Surveillance. Type: Civilian Radarsat. Spacecraft: IGS.

2005 February 26 - . 09:25 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2022.

Himawari 6 - . Payload: MT-Sat 1R. Mass: 3,300 kg (7,200 lb). Nation: Japan. Agency: MLIT. Manufacturer: Palo Alto. Class: Earth. Type: Weather satellite. Spacecraft: FS-1300. USAF Sat Cat: 28622 . COSPAR: 2005-006A. Apogee: 35,798 km (22,243 mi). Perigee: 35,778 km (22,231 mi). Inclination: 0.00 deg. Period: 1,436.20 min.
Return to flight after earlier failure; first commercial mission for H-2A. Delayed from August 2003, January 2004, and February 24, 2005. The dual-purpose satellite was to provide weather data for the Japanese Meteorological Agency (as with others in the Himawari-GMS series), and air traffic control support (airplane-ATC voice/data links, GPS augmentation and airplane position tracking) for the Japanese Civil Aviation Bureau. As of 2007 Mar 11 located at 140.26E drifting at 0.000E degrees per day.

2006 January 24 - . 01:33 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2022.

Daichi - . Payload: ALOS-1. Mass: 3,850 kg (8,480 lb). Nation: Japan. Agency: JAXA. Manufacturer: Toshiba. Class: Surveillance. Type: Military Radarsat. Spacecraft: Daichi. USAF Sat Cat: 28931 . COSPAR: 2006-002A. Apogee: 697 km (433 mi). Perigee: 693 km (430 mi). Inclination: 98.20 deg. Period: 98.70 min. Advanced Land Observing Satellite, which carried an L-band synthetic aperture radar, an optical 2.5-meter resolution mapping camera, and a 10-meter resolution visible/near-infrared radiometer..

2006 February 18 - . 06:27 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024.

MTSAT-2 - . Payload: MT-Sat 2. Mass: 3,000 kg (6,600 lb). Nation: Japan. Agency: MLIT. Manufacturer: Mitsubishi. Class: Earth. Type: Weather satellite. Spacecraft: DS2000. USAF Sat Cat: 28937 . COSPAR: 2006-004A. Apogee: 35,803 km (22,246 mi). Perigee: 35,771 km (22,227 mi). Inclination: 0.00 deg. Period: 1,436.10 min.
Multifunctional Transport Satellite. An aeronautical payload provided communications relay between aircraft and air traffic control; GPS augmentation navigation for aircraft; and transmitted the location of aircraft to air traffic control. A Japan Advanced Meteorological Imager weather camera had one visible and four infrared channels. MTSAT-2 was built by Mitsubishi using the new DS2000 bus. As of 2007 Mar 8 located at 144.93E drifting at 0.016W degrees per day.

2006 September 11 - . 04:35 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

IGS-3A - . Mass: 850 kg (1,870 lb). Nation: Japan. Agency: JIDF. Manufacturer: Melco. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: IGS. Decay Date: 2016-10-29 . USAF Sat Cat: 29393 . COSPAR: 2006-037A. Apogee: 491 km (305 mi). Perigee: 484 km (300 mi). Inclination: 97.30 deg. Information Gathering Satellite / Optical-2 military surveillance satellite, launched to replace IGS O-1 launched in 2003, which demonstrated technical problems. The first replacement, IGS-O-2, was lost in a launch failure in 2003..

2006 December 16 - . 06:32 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 204.

Kiku 8 - . Payload: ETS-8. Mass: 5,817 kg (12,824 lb). Nation: Japan. Agency: JAXA. Manufacturer: Melco. Class: Technology. Type: Navigation technology satellite. Spacecraft: DS2000. USAF Sat Cat: 29656 . COSPAR: 2006-059A. Apogee: 35,798 km (22,243 mi). Perigee: 35,775 km (22,229 mi). Inclination: 0.0500 deg. Period: 1,436.11 min.
Engineering Test Satellite-8 was a Japanese prototype/operational demonstration for a number of new technologies: a large satellite bus, large-scale deployable 40-m-span antennae, mobile satellite communications system, mobile satellite digital multimedia broadcasting, and basic positioning using high-accuracy time standard devices. It will be positioned in geosynchronous orbit at 146 degrees East. JAXA developed two portable terrestrial systems to communicate directly with the satellite - a tiny telephone and a portable laptop computer. The satellite was to have a lifetime of ten years. As of 2007 Mar 11 located at 145.97E drifting at 0.010W degrees per day.

2007 February 24 - . 04:41 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2024.

IGS 2 - . Payload: IGS 4A. Mass: 1,200 kg (2,600 lb). Nation: Japan. Agency: CSICE, JAXA. Manufacturer: Melco. Class: Surveillance. Type: Civilian Radarsat. Spacecraft: IGS. Decay Date: 2014-04-13 . USAF Sat Cat: 30586 . COSPAR: 2007-005A. Information Gathering Satellite Radar-2. Japanese military satellite using a synthetic aperture radar for all-weather, 24-hour, high-resolution surveillance of the earth..
IGS 3V - . Payload: IGS 4B. Mass: 850 kg (1,870 lb). Nation: Japan. Agency: CSICE, JAXA. Manufacturer: Melco. Class: Surveillance. Type: Military surveillance satellite. Spacecraft: IGS. Decay Date: 2013-11-12 . USAF Sat Cat: 30587 . COSPAR: 2007-005B.
Optical-3 Verification Satellite, an experimental satellite on a six-month mission to test payloads planned for the Optical-3 second-generation Japanese military optical surveillance satellite. The production-type Optical-3 satellite was expected to launch in 2009.

2007 September 14 - . 01:31 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 2022.

Kaguya - . Payload: Selene. Mass: 3,000 kg (6,600 lb). Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. Decay Date: 2009-06-10 . USAF Sat Cat: 32054 . COSPAR: 2007-039A.
Another of a series of new lunar probes to be launched in the next few years by China, India, Japan, USA, and Europe. Selene was dubbed Kaguya, a Japanese moon goddess, after launch. It included an HDTV camera. In lunar orbit two subsatellites would be released to provide continuous communications as well as better characterize the moon's gravity field. By 30 September Kaguya was in a 2243 km x 378,132 km lunar transfer orbit. On 3 October at 21:00 GMT it entered its initial 101 km x 11741 km x 95 deg lunar orbit. It then began maneuvers to enter its operational 100 km circular orbit, releasing the subsatellites on 9 and 12 October.
Okina - . Payload: Selene. Mass: 45 kg (99 lb). Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. Decay Date: 2009-02-12 . USAF Sat Cat: 32055 . COSPAR: 2007-039B. The Okina relay satellite was released from Kaguya into a 115 km x 2,399 km lunar orbit at 00:36 GMT on 9 October 2007..
Ouna - . Payload: Selene. Mass: 45 kg (99 lb). Nation: Japan. Agency: Mitsubishi. Class: Moon. Type: Lunar probe. Spacecraft: Kaguya. USAF Sat Cat: 32056 . COSPAR: 2007-039C. 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..

2012 May 17 - . 16:39 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

Shizuku - . Mass: 1,991 kg (4,389 lb). Nation: Japan. Class: Earth. Type: Climate satellite. Spacecraft: Shizuku. USAF Sat Cat: 38337 . COSPAR: 2012-025A. Apogee: 694 km (431 mi). Perigee: 692 km (429 mi). Inclination: 98.20 deg. Period: 98.60 min. Global Change Observation Mission. Primary instrument was the AMS-4 microwave scanning radiometer..
Arirang-3 - . Payload: Kompsat-3. Mass: 800 kg (1,760 lb). Nation: Korea South. Class: Surveillance. Type: Military surveillance satellite. Spacecraft Bus: T200. Spacecraft: Kompsat. USAF Sat Cat: 38338 . COSPAR: 2012-025B. Apogee: 677 km (420 mi). Perigee: 665 km (413 mi). Inclination: 98.10 deg. Period: 98.20 min. South Korean imaging satellite..
SDS-4 - . Mass: 50 kg (110 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft: JAXA SDS. USAF Sat Cat: 38339 . COSPAR: 2012-025C. Apogee: 673 km (418 mi). Perigee: 662 km (411 mi). Inclination: 98.20 deg. Period: 98.10 min. Small Demonstration Satellite; carried four technology experiments including a space-based AIS (ship tracking) payload..
Horyu-2 - . Mass: 7.00 kg (15.40 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft: Horyu. USAF Sat Cat: 38340 . COSPAR: 2012-025D. Apogee: 671 km (416 mi). Perigee: 652 km (405 mi). Inclination: 98.20 deg. Period: 98.00 min. Kyushu Institute of Technology satellite to study spacecraft charging effects and test a camera payload for Surrey Satellite (which observed the second stage after payload deployment to support development of improved propellant insulation)..

2014 February 27 - . 18:37 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

Ginrei - . Payload: SHINDAISAT. Mass: 33 kg (72 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft: Ginrei. Decay Date: 2014-11-24 . USAF Sat Cat: 39572 . COSPAR: 2014-009A. Apogee: 371 km (230 mi). Perigee: 348 km (216 mi). Inclination: 65.01 deg. Period: 91.73 min. Microsatellite from Shinshu University to study use of LED's for long-distance communication..
Hayato-2 - . Payload: ITF 1. Mass: 1.00 kg (2.20 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2014-06-29 . USAF Sat Cat: 39573 . COSPAR: 2014-009B. Apogee: 256 km (159 mi). Perigee: 233 km (144 mi). Inclination: 65.00 deg. Period: 89.40 min. Cubesat from Tsukuba University..
GPM-C - . Mass: 3,850 kg (8,480 lb). Nation: Japan. Class: Earth. Type: Climate Satellite. Spacecraft: GPM. USAF Sat Cat: 39574 . COSPAR: 2014-009C. Apogee: 405 km (251 mi). Perigee: 392 km (243 mi). Inclination: 65.02 deg. Period: 92.53 min.
Joint US-Japanese Global Precipitation Measurement satellite; carried the JAXA/NICT/NEC Toshiba Dual-frequency Precipitation Radar and the GSFC/Ball GPM Microwave Imager. The satellite was built by NASA's Goddard Space Flight Center and registered as a US satellite.
OPUSat - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2014-07-24 . USAF Sat Cat: 39575 . COSPAR: 2014-009D. Apogee: 310 km (190 mi). Perigee: 288 km (178 mi). Inclination: 65.00 deg. Period: 90.50 min. 1U cubesat from Osaka Prefectural University. Technology mission..
Teikyosat-3 - . Mass: 22 kg (48 lb). Nation: Japan. Class: Biology. Type: Biology satellite. Spacecraft: Teikyosat. Decay Date: 2014-10-25 . USAF Sat Cat: 39576 . COSPAR: 2014-009E. Apogee: 359 km (223 mi). Perigee: 338 km (210 mi). Inclination: 65.01 deg. Period: 91.51 min. Microsatellite from Teikyo University..
Invader - . Mass: 1.00 kg (2.20 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft: Cubesat. Decay Date: 2014-09-02 . USAF Sat Cat: 39577 . COSPAR: 2014-009F. Apogee: 336 km (208 mi). Perigee: 315 km (195 mi). Inclination: 65.01 deg. Period: 91.04 min. Cubesat from Tama Art University..
STARS-2 - . Mass: 22 kg (48 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft: STARS-2. Decay Date: 2014-05-18 . USAF Sat Cat: 39578 . COSPAR: 2014-009G. Apogee: 178 km (110 mi). Perigee: 164 km (101 mi). Inclination: 64.97 deg. Period: 87.91 min. Microsatellite from Kagawa University. Composed of two sections and a tether, deployed length 300 metres. Believed to have succeeded based on later orbital decay rate..
Yui - . Payload: K-SAT2. Mass: 1.00 kg (2.20 lb). Nation: Japan. Class: Technology. Type: Education satellite. Spacecraft: Cubesat. Decay Date: 2014-04-26 . USAF Sat Cat: 39579 . COSPAR: 2014-009H. Apogee: 162 km (100 mi). Perigee: 145 km (90 mi). Inclination: 64.99 deg. Period: 87.56 min. Cubesat from Kagoshima University..

2014 May 24 - . 03:05 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

Daichi-2 - . Payload: ALOS 2. Mass: 2,120 kg (4,670 lb). Nation: Japan. Class: Surveillance. Type: Military Radarsat. Spacecraft Bus: Daichi. Spacecraft: Daichi-2. USAF Sat Cat: 39766 . COSPAR: 2014-029A. Apogee: 632 km (392 mi). Perigee: 630 km (390 mi). Inclination: 97.92 deg. Period: 97.33 min. Advanced Land Observing Satellite 2, placed in a noon/midnight sun-synchronous orbit. Carried the PALSAR-2 radar imager with 1 to 3 meter resolution in spotlight mode and 3 to 10 m in high resolution mode..
UNIFORM-1 - . Mass: 50 kg (110 lb). Nation: Japan. Class: Earth. Type: Disaster monitoring satellite. Spacecraft: UNIFORM. USAF Sat Cat: 39767 . COSPAR: 2014-029B. Apogee: 629 km (390 mi). Perigee: 622 km (386 mi). Inclination: 97.87 deg. Period: 97.22 min. Microsatellite for Wakayama University, carrying a 10-12 micron IR microbolometer array for wildfire monitoring..
SOCRATES - . Mass: 50 kg (110 lb). Nation: Japan. Class: Communications. Type: Laser communications satellite. Spacecraft: SOCRATES. USAF Sat Cat: 39768 . COSPAR: 2014-029C. Apogee: 627 km (389 mi). Perigee: 619 km (384 mi). Inclination: 97.87 deg. Period: 97.17 min. Microsatellite for the Japanese communications research lab NICT, with a laser communications experiment..
Raijin-2 - . Payload: RISING 2. Mass: 50 kg (110 lb). Nation: Japan. Class: Science. Type: Science satellite. Spacecraft: Raijin. USAF Sat Cat: 39769 . COSPAR: 2014-029D. Apogee: 630 km (390 mi). Perigee: 626 km (388 mi). Inclination: 97.88 deg. Period: 97.26 min. Microsatellite for Tohoku University mission for studies of lightning with visible and mid-IR imagers and a VLF receiver..
SPROUT - . Mass: 7.00 kg (15.40 lb). Nation: Japan. Class: Technology. Type: Technology satellite. Spacecraft: SPROUT. USAF Sat Cat: 39770 . COSPAR: 2014-029E. Apogee: 627 km (389 mi). Perigee: 615 km (382 mi). Inclination: 97.87 deg. Period: 97.13 min. Microsatellite with a Nihon University experiment to deploy a 1.5m inflatable triangular membrane..

2014 December 3 - . 04:22 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. Launch Pad: Tanegashima Y1. LV Family: H-2. Launch Vehicle: H-IIA 202.

Hayabusa-2 - . Mass: 590 kg (1,300 lb). Nation: Japan. Class: Astronomy. Type: Space probe. Spacecraft: Hayabusa. USAF Sat Cat: 40319 . COSPAR: 2014-076A. Apogee: -50,912 km (-50,912 mi). Perigee: 245 km (152 mi). Inclination: 29.90 deg.
The spacecraft was intended to rendezvous with asteroid 1999 JU3, survey it from orbit, touch down briefly to sample the surface, and return samples to Earth. Launched into a 0.915 AU x 1.089 AU x 6.8 deg solar orbit. Five small, beanbag-like 'target markers' could be ejected onto the surface in advance to help guide the vehicle. Hayabusa-2 also carried three 1 kg class lander/hopper devices, Minerva II-1a, II-1b and II-2, which were to be ejected onto the surface, together with a 10 kg German-built lander called MASCOT. Hayabusa-2 was also to eject a 'Self-Contained Impactor' (SCI) device onto the surface. As the parent spacecraft moved off to the side it would further eject the DCAM-3 camera subsatellite, which would monitor detonation of SCI's high explosive, intended to ram the SCI's body into the asteroid and generate an artificial crater.
Shin'en-2 - . Mass: 15 kg (33 lb). Nation: Japan. Class: Technology. Type: Communications technology satellite. Spacecraft: Shin'en. USAF Sat Cat: 40320 . COSPAR: 2014-076B. Apogee: -50,912 km (-50,912 mi). Perigee: 245 km (152 mi). Inclination: 29.90 deg. Communications payload designed to demonstrate deep space communications with a small spacecraft from a 0.915 AU x 1.089 AU x 6.8 deg solar orbit..
DESPATCH - . Mass: 32 kg (70 lb). Nation: Japan. Class: Technology. Type: Art satellite. Spacecraft: DESPATCH. USAF Sat Cat: 40321 . COSPAR: 2014-076C. Apogee: -50,912 km (-50,912 mi). Perigee: 245 km (152 mi). Inclination: 29.90 deg.
Also known as ArtSat-2; from Tama Art University. The yellowish, tapered-helix assembly was intended mainly as a work of art although it also carries an amateur radio communications payload with a limited range. In a 0.915 AU x 1.089 AU x 6.8 deg solar orbit.
PROCYON - . Mass: 59 kg (130 lb). Nation: Japan. Class: Astronomy. Type: Space probe. USAF Sat Cat: 40322 . COSPAR: 2014-076D. Apogee: -50,912 km (-50,912 mi). Perigee: 245 km (152 mi). Inclination: 29.90 deg.
Small spacecraft experiment to test interplanetary navigation with an ion engine. As of May 2015 the mission plan to perform an Earth swingby followed by flyby of asteroid 2000 DP107 had been abandoned following malfunction of its ion engine. The probe, in solar orbit, continued to make scientific measurements with its ultraviolet camera. Procyon was originally in a 0.9 x 1.1 AU x 6.8 deg solar orbit.
MASCOT - . Nation: Japan. Spacecraft: MASCOT. COSPAR: 2014-076. Attached to Hayabusa-2.
Minerva II-1a - . Nation: Japan. Spacecraft: Minerva II. COSPAR: 2014-076. Attached to Hayabusa-2.
Minerva II-1b - . Nation: Japan. Spacecraft: Minerva II. COSPAR: 2014-076. Attached to Hayabusa-2.
Minerva II-2 - . Nation: Japan. Spacecraft: Minerva II. COSPAR: 2014-076. Attached to Hayabusa-2.
SCI - . Nation: Japan. Spacecraft: Hayabusa. COSPAR: 2014-076. Attached to Hayabusa-2.
DCAM-3 - . Nation: Japan. Spacecraft: DCAM. COSPAR: 2014-076. Attached to Hayabusa-2.
Target Marker 1 - . Nation: Japan. Spacecraft: Target Marker. COSPAR: 2014-076. Attached to Hayabusa-2.
Target Marker 2 - . Nation: Japan. Spacecraft: Target Marker. COSPAR: 2014-076. Attached to Hayabusa-2.
Target Marker 3 - . Nation: Japan. Spacecraft: Target Marker. COSPAR: 2014-076. Attached to Hayabusa-2.
Target Marker 4 - . Nation: Japan. Spacecraft: Target Marker. COSPAR: 2014-076. Attached to Hayabusa-2.
Target Marker 5 - . Nation: Japan. Spacecraft: Target Marker. COSPAR: 2014-076. Attached to Hayabusa-2.

2016 November 2 - . 06:20 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

Himawari 9 - . Nation: Japan. Class: Earth. Type: Weather satellite. Spacecraft: DS2000. USAF Sat Cat: 41836 . COSPAR: 2016-064A. Apogee: 35,857 km (22,280 mi). Perigee: 243 km (150 mi). Inclination: 22.40 deg. Himawari 9 weather satellite was launched to geotransfer orbit by H-IIA-31. By Nov 8 the satellite was on station in GEO at 140.8E..

2017 June 1 - . 00:16 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

Michibiki-2 - . Payload: QZSS 2; QZS-2. Nation: Japan. USAF Sat Cat: 42738 . COSPAR: 2017-028A. Apogee: 38,937 km (24,194 mi). Perigee: 32,634 km (20,277 mi). Inclination: 43.82 deg. Period: 1,436.06 min. See QZS 2 (Michibiki 2). ..

2017 August 19 - . 05:28 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 204.

Michibiki-3 - . Payload: QZSS 3; QZS-3. Nation: Japan. USAF Sat Cat: 42917 . COSPAR: 2017-048A. Apogee: 35,793 km (22,240 mi). Perigee: 35,781 km (22,233 mi). Inclination: 0.0600 deg. Period: 1,436.13 min. See QZS 3 (Michibiki 3). ..

2017 October 9 - . 22:01 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

Michibiki-4 - . Payload: QZSS 4; QZS-4. Nation: Japan. USAF Sat Cat: 42965 . COSPAR: 2017-062A. Apogee: 38,943 km (24,198 mi). Perigee: 32,614 km (20,265 mi). Inclination: 40.71 deg. Period: 1,435.68 min. See QZS 4 (Michibiki 4). ..

2017 December 23 - . 01:25 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

Shikisai - . Payload: GCOM-C. Nation: Japan. USAF Sat Cat: 43065 . COSPAR: 2017-082A. Apogee: 801 km (497 mi). Perigee: 800 km (490 mi). Inclination: 98.64 deg. Period: 100.89 min. See GCOM-C (Shikisai). ..
Tsubame - . Payload: SLATS. Nation: Japan. USAF Sat Cat: 43066 . COSPAR: 2017-082B. Apogee: 295 km (183 mi). Perigee: 294 km (182 mi). Inclination: 98.31 deg. Period: 90.41 min. See SLATS (Tsubame). ..

2018 February 27 - . 04:33 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

JSE kougaku 6 gouki - . Payload: IGS Optical-6; IGS O-6. Nation: Japan. USAF Sat Cat: 43223 . COSPAR: 2018-021A. See IGS-Optical 6. ..

2018 June 12 - . 04:19 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

JSE reda-6 gouki - . Payload: IGS Radar-6; IGS R-6. Nation: Japan. USAF Sat Cat: 43495 . COSPAR: 2018-052A. See IGS-Radar 6. ..

2018 October 29 - . 04:07 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-IIA 202.

Ten-Koh - . Payload: LEO Environments Obs Sat; TENKOU. Nation: Japan. USAF Sat Cat: 43671 . COSPAR: 2018-084A. Apogee: 577 km (358 mi). Perigee: 540 km (330 mi). Inclination: 97.82 deg. Period: 95.83 min. See Ten-Koh. ..
Ibuki 2 - . Payload: GOSAT 2. Nation: Japan. USAF Sat Cat: 43672 . COSPAR: 2018-084B. Apogee: 617 km (383 mi). Perigee: 615 km (382 mi). Inclination: 97.83 deg. Period: 97.02 min. See GOSAT 2 (Ibuki 2). ..
KhalifaSat - . Nation: UAE. USAF Sat Cat: 43676 . COSPAR: 2018-084F. Apogee: 613 km (380 mi). Perigee: 591 km (367 mi). Inclination: 97.83 deg. Period: 96.73 min. See KhalifaSat. ..
Diwata-2B - . Nation: Philippines. USAF Sat Cat: 43678 . COSPAR: 2018-084H. Apogee: 601 km (373 mi). Perigee: 586 km (364 mi). Inclination: 97.84 deg. Period: 96.55 min. See Diwata 2B. ..
AUTCube-2 - . Nation: Japan. USAF Sat Cat: 43679 . COSPAR: 2018-084J. Apogee: 599 km (372 mi). Perigee: 585 km (363 mi). Inclination: 97.84 deg. Period: 96.52 min. See AUTcube 2 (Gamacube). ..
Aoi - . Payload: STARS-AO. Nation: TBD. USAF Sat Cat: 43681 . COSPAR: 2018-084K. Apogee: 600 km (370 mi). Perigee: 586 km (364 mi). Inclination: 97.84 deg. Period: 96.54 min. See STARS-AO (Aoi). ..

Home - Search - Browse - Alphabetic Index: 0- 1- 2- 3- 4- 5- 6- 7- 8- 9
A- B- C- D- E- F- G- H- I- J- K- L- M- N- O- P- Q- R- S- T- U- V- W- X- Y- Z