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ETS
ETS-2
ETS-2
Credit: NASDA
Japanese technology satellite. Technology satellite operated by NASDA, Japan. Launched 1975.

AKA: Engineering Test Satellite;Kiku. Status: Operational 1975. First Launch: 1975-09-09. Last Launch: 1994-08-28. Number: 6 . Gross mass: 85 kg (187 lb).

Japanese Engineering Test Satellite are intended for preliminary experiments for confirmation of the launching technologies, acquiring the satellite tracking and control technologies, and for extension tests of the extendable antennas, measurement of satellite environment, measurement of satellite attitudes, etc.


More at: ETS.

Subtopics

ETS 2 (Kiku 2) Technology satellite built by Mitsubishi Electric (MELCO) for NASDA, Japan. Launched 1977.

ETS 4 (Kiku 3) Technology satellite built by Mitsubishi Electric (MELCO) for NASDA, Japan. Launched 1981.

ETS 3 (Kiku 4) Technology satellite operated by NASDA, Japan. Launched 1982.

ETS 5 (Kiku 5) Communication Technology satellite built by Mitsubishi Electric (MELCO) for NASDA, Japan. Launched 1987.

ETS 6 (Kiku 6) Communication Technology satellite operated by NASDA, Japan. Launched 1994.

ETS-7 Japanese rendezvous technology satellite. Hikoboshi. Technology satellite, to accomplish remote automatic rendezvous and docking. Technology satellite operated by NASDA, Japan. Launched 1997.

ETS-7 Target Japanese rendezvous technology satellite. Orihime. Attached to Hikoboshi. Docking target for ETS-7.

ETS 8 (Kiku 8) Communication Technology satellite built by Mitsubishi Electric (MELCO) for NASDA, Japan. Launched 2006. Used the ETS-8 bus bus.

ETS 9 (Kiku 9) Communication Technology satellite built by Mitsubishi Electric (MELCO) for JAXA, Japan.

Family: Medium earth orbit, Technology, Technology satellite. Country: Japan. Launch Vehicles: Thor, Delta, N-1, N-2, H-1, H-II, H-IIA 204. Launch Sites: Tanegashima, Tanegashima N, Tanegashima Y. Bibliography: 2, 279, 6, 11036, 12327, 12328, 12329, 12330, 12331, 12332.
Photo Gallery

ETS-4ETS-4
Credit: NASDA


ETS-6ETS-6
Credit: NASDA


Kiku 1Kiku 1
Credit: Manufacturer Image


Kiku 2Kiku 2
Credit: Manufacturer Image


Kiku 4Kiku 4
Credit: Manufacturer Image


Kiku 3Kiku 3
Credit: Manufacturer Image


Kiku 5Kiku 5
Credit: Manufacturer Image


Kiku 6Kiku 6
Credit: Manufacturer Image


Kiku 8Kiku 8
Credit: Manufacturer Image



1975 September 9 - . 05:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.
  • Kiku 1 - . Payload: ETS 1 (JETS). Mass: 85 kg (187 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 8197 . COSPAR: 1975-082A. Apogee: 1,103 km (685 mi). Perigee: 975 km (605 mi). Inclination: 47.0000 deg. Period: 106.00 min.

    JETS-1 (Japanese Engineering Test Satellite -1, national name 'Kiku') is intended for preliminary experiments for confirmation of the launching technologies, acquiring the satellite tracking and control technologies, and for extension tests of the extenda ble antennas, measurement of satellite environment, measurement of satellite attitudes, etc. Launch time 0530 GMT.


1977 February 23 - . 08:50 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.
  • Kiku 2 - . Payload: ETS 2. Mass: 130 kg (280 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. Completed Operations Date: 1990-12-01 . USAF Sat Cat: 9852 . COSPAR: 1977-014A. Apogee: 35,860 km (22,280 mi). Perigee: 35,854 km (22,278 mi). Inclination: 11.9000 deg. Period: 1,439.70 min.

    Engineering test satellite. Engineering Test Satellite Type II (ETS II), Kiku 2. Launch by N launch vehicle no 3. Geographical longitude of the geostationary orbit: 130 deg E. Preliminary experiments to acquire technologies to launch,track, and control geostationary satellites. P ropagation experiment of millimetre and quasi-millimetre waves. Characteristics: Weight at launch 245 kg. Configuration: cylindrical. Height 191 cm including antenna. Diameter 141 cm. Attitude control: spin stabilization. Expected life at least 6 months. Positioned in geosynchronous orbit over the Pacific Ocean at 130 deg E in 1977-1990 As of 5 September 2001 located at 16.93 deg E drifting at 0.930 deg W per day. As of 2007 Mar 9 located at 85.65W drifting at 0.986W degrees per day.


1981 February 11 - . 08:30 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-2.
  • Kiku 3 - . Payload: ETS 4. Mass: 640 kg (1,410 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 12295 . COSPAR: 1981-012A. Apogee: 16,237 km (10,089 mi). Perigee: 305 km (189 mi). Inclination: 28.5000 deg. Period: 294.10 min.

    Kiku 3 (ETS-IV). Launching organization NASDA. Acquisition of the technology to handle a large-scale heavy satellite and test of the functions of on-board equipment and devices, as well as confirmation of the launching capacity of the N-II launch vehicle. Also tested ion thruster.


1982 September 3 - . 05:00 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: N-1.
  • Kiku 4 - . Payload: ETS 3. Mass: 385 kg (848 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. USAF Sat Cat: 13492 . COSPAR: 1982-087A. Apogee: 1,006 km (625 mi). Perigee: 988 km (613 mi). Inclination: 44.6000 deg. Period: 105.10 min.

    Engineering test satellite. Engineering Test Satellite III (ETS-III) launched 0500 GMT 3 Sep 1982 from Osaki launch site, Tanegashima. Launching organization: National Space Development Agency of Japan (NASDA). Verification of three axis attitude control function; verification of so lar array paddle deployment function; verification of active thermal control function; functional test of mission equipment in the space. N launch vehicle flight no 9.


1987 August 27 - . 09:20 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima N. LV Family: Thor. Launch Vehicle: H-1.
  • Kiku 5 - . Payload: ETS 5. Mass: 550 kg (1,210 lb). Nation: Japan. Agency: NASDA. Class: Technology. Type: Navigation technology satellite. Spacecraft: ETS. Completed Operations Date: 1997-09-10 . USAF Sat Cat: 18316 . COSPAR: 1987-070A. Apogee: 36,072 km (22,414 mi). Perigee: 36,029 km (22,387 mi). Inclination: 7.9000 deg. Period: 1,449.60 min.

    Stationed at 150 deg E. ETS-V (Kiku-5). Establishment of basic technology for bus systems needed for 3-axis stabilized geostationary satellites. Accumulation of key technologies required for high performance in the next generation of applications satellites; Experiment of mobile satellite communications for the control of aircrafts over the Pacific Ocean, and for the communication, navigational aid, search and rescue of ships. H-I (3-stage) launch vehicle. Launching organization NASDA. Launch time 0920 GMT. Positioned in geosynchronous orbit at 150 deg E in 1987-1997 As of 5 September 2001 located at 92.55 deg W drifting at 3.394 deg W per day. As of 2007 Mar 10 located at 49.74W drifting at 3.380W degrees per day.


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: 13.2300 deg. Period: 861.84 min. Failed to reach geostationary orbit; Engineering Test Satellite; partial mission success. Also tested ion engines for NSSK..

1997 November 27 - . 21:27 GMT - . Launch Site: Tanegashima. Launch Complex: Tanegashima Y. LV Family: H-2. Launch Vehicle: H-II.
  • 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: 35.0000 deg. Period: 95.50 min.

    The Orihime and Hikoboshi satellites undocked and redocked on July 7 1998 in the FP-1 test of automated docking systems. Despite claims of the NASDA space agency that this is a first, automated Russian craft have docked on many occasions since the Kosmos-186/188 docking in 1968.

  • Orihime - . Payload: ETS-7 Target. Nation: Japan. Agency: NASDA. Manufacturer: Toshiba. Class: Technology. Type: Navigation technology satellite. Spacecraft 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: 34.5000 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..


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