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ATS-6
ATS-6 (Applications Technology Satellite-6) 〔ATS-6 Significance, R.B. Marsten IEEE transactions on Aerospace & Electronic Systems vol.AES-11 N°6〕 was a NASA experimental satellite, built by Fairchild Space and Electronics Division〔(【引用サイトリンク】title=table4.156 )〕 It has been called the world's first educational satellite as well as world's first experimental Direct Broadcast Satellite as part of the Satellite Instructional Television Experiment between NASA and ISRO. It was launched May 30, 1974, and decommissioned July 1979. At the time of launch, it was the most powerful telecommunication satellite in orbit.〔http://hdl.handle.net/2060/19820008279 ATS-6 engineering performance report. Volume 6: Scientific experiments〕 ATS-6 carried no fewer than 23 different experiments, and introduced several breakthroughs. It was the first 3-axis stabilized spacecraft in geostationary orbit. It was also the first to use experimentally with some success electric propulsion in geostationary orbit. It also carried several particle physics experiments, including the first heavy ion detection in geostationary orbit.
During its five-year life, ATS-6 transmitted educational programming to various countries, including India, the United States and other regions. The vehicle also conducted air traffic control tests, was used to practice satellite-assisted search and rescue techniques, carried an experimental radiometer subsequently carried as a standard instrument aboard weather satellites, and pioneered direct broadcast TV.
ATS-6 was a precursor to many technologies still in use today on geostationary spacecraft: large deployable antenna, 3-axis attitude control with slewing capabilities, antenna pointing through RF sensing, electric propulsion, meteorological radiometer in geostationary orbit, and direct to home broadcasting. It is also possible that ATS-6 was a forerunner of the large ELINT satellites such as Mentor.
== Launch ==
ATS-6 was launched on May 30, 1974, by a Titan III-C launch vehicle. The spacecraft was inserted directly in the geosynchronous orbit. This reduced the on-board fuel requirements to less than 40 kg (for a total mass at launch of nearly 1400 kg). The highly accurate orbit insertion further lowered the amount of fuel required for final positioning to 9 kg. This enabled a life extension from the original 2 year to 5 years, even accounting for the premature failure of the electric propulsion subsystem (the station-keeping fuel requirement being around 1.6 kg/year).
抄文引用元・出典: フリー百科事典『 ウィキペディア（Wikipedia）』
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