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ETS-2
ETS-2 -

Credit: NASDA. 9,475 bytes. 160 x 228 pixels.



Other Designations: Engineering Test Satellite. Class: Technology. Nation: Japan. Agency: Japan(ETS 1).

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.


Specification


ETS Chronology


09 September 1975 Kiku 1 Launch Site: Tanegashima . Launch Vehicle: N. Mass: 85 kg. Perigee: 975 km. Apogee: 1,103 km. Inclination: 47.0 deg.

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.


23 February 1977 Kiku 2 Launch Site: Tanegashima . Launch Vehicle: N. Mass: 130 kg. Perigee: 35,854 km. Apogee: 35,860 km. Inclination: 11.9 deg.

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.


11 February 1981 Kiku 3 Launch Site: Tanegashima . Launch Vehicle: N-2. Mass: 640 kg. Perigee: 240 km. Apogee: 20,680 km. Inclination: 28.2 deg.

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.


03 September 1982 Kiku 4 Launch Site: Tanegashima . Launch Vehicle: N. Mass: 385 kg. Perigee: 966 km. Apogee: 1,226 km. Inclination: 44.6 deg.


ETS-4ETS-4

Credit: NASDA. 9,504 bytes. 127 x 214 pixels.


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.
27 August 1987 Kiku 5 Launch Site: Tanegashima . Launch Vehicle: H-1. Mass: 550 kg. Perigee: 35,770 km. Apogee: 35,805 km. Inclination: 2.2 deg.

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.



ETS-6ETS-6

Credit: NASDA. 11,259 bytes. 227 x 220 pixels.


28 August 1994 Kiku 6 Launch Site: Tanegashima . Launch Vehicle: H-2. FAILURE: LAPS apogee kick motor failed to ignite. Partial Failure. Mass: 3,800 kg. Perigee: 8,565 km. Apogee: 38,677 km. Inclination: 13.2 deg.

Failed to reach geostationary orbit; Engineering Test Satellite; partial mission success. Also tested ion engines for NSSK.



Bibliography:



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Last update 12 March 2001.
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