Editing Geostationary orbit (section)

==Implementation==

===Launch===
{{See also|Geostationary transfer orbit}}
{{multiple image|perrow = 1|total_width=
| image1 = Animation of EchoStar XVII trajectory.gif
| image2 = Animation of EchoStar XVII trajectory Equatorial view.gif
| footer = An example of a transition from temporary [[Geostationary transfer orbit|GTO]] to GSO.<br />{{legend2|magenta|[[EchoStar XVII]]}}{{·}}{{legend2|RoyalBlue|[[Earth]]}}.
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Geostationary satellites are launched to the east into a prograde orbit that matches the rotation rate of the equator. The smallest inclination that a satellite can be launched into is that of the launch site's latitude, so launching the satellite from close to the equator limits the amount of [[Orbital inclination change|inclination change]] needed later.<ref name="conf"/> Additionally, launching from close to the equator allows the speed of the Earth's rotation to give the satellite a boost. A launch site should have water or deserts to the east, so any failed rockets do not fall on a populated area.<ref>{{Cite web|url=https://www.eumetsat.int/website/home/Satellites/LaunchesandOrbits/LaunchingSatellites/index.html|title=Launching Satellites|website=Eumetsat|access-date=July 22, 2019|archive-date=December 21, 2019|archive-url=https://web.archive.org/web/20191221164243/https://www.eumetsat.int/website/home/Satellites/LaunchesandOrbits/LaunchingSatellites/index.html|url-status=dead}}</ref>

Most [[launch vehicle]]s place geostationary satellites directly into a [[geostationary transfer orbit]] (GTO), an elliptical orbit with an [[apsis|apogee]] at GEO height and a low [[apsis|perigee]]. On-board satellite propulsion is then used to raise the perigee, circularise and reach GEO.<ref name="conf">{{cite conference|url=https://www.researchgate.net/publication/282014319 |conference=20th International Symposium on Space Flight Dynamics|first1=Nicholas |last1=Farber |first2=Andrea |last2=Aresini |first3=Pascal |last3=Wauthier |first4=Philippe |last4=Francken|date=September 2007 |title=A general approach to the geostationary transfer orbit mission recovery |page=2}}</ref><ref>{{cite web|url=http://www.planetary.org/blogs/jason-davis/20140116-how-to-get-a-satellite-to-gto.html |title=How to get a satellite to geostationary orbit |author=Jason Davis|date=January 17, 2014|access-date=October 2, 2019 |publisher=The Planetary Society}}</ref>

=== Orbit allocation ===
{{see also|Bogota Declaration}}
Satellites in geostationary orbit must all occupy a single ring above the [[equator]]. The requirement to space these satellites apart, to avoid harmful radio-frequency interference during operations, means that there are a limited number of orbital slots available, and thus only a limited number of satellites can be operated in geostationary orbit. This has led to conflict between different countries wishing access to the same orbital slots (countries near the same [[longitude]] but differing [[latitudes]]) and [[radio frequencies]]. These disputes are addressed through the [[International Telecommunication Union]]'s allocation mechanism under the [[ITU Radio Regulations|Radio Regulations]].<ref>{{cite web|url=http://www.itu.int/ITU-R/conferences/seminars/mexico-2001/docs/06-procedure-mechanism.doc |archive-url=https://web.archive.org/web/20090327092830/http://www.itu.int/ITU-R/conferences/seminars/mexico-2001/docs/06-procedure-mechanism.doc|archive-date=March 27, 2009 |title=Orbit/Spectrum Allocation Procedures Registration Mechanism under the Radio Regulations |last=Henri |first=Yvon |publisher=Space Services Department}}</ref><ref>{{cite web|url=http://www.itu.int/ITU-R/go/space/en |access-date=July 26, 2019 |publisher=ITU |title=Space Services Division}}</ref> In the 1976 [[Bogota Declaration]], eight countries located on the Earth's equator claimed sovereignty over the geostationary orbits above their territory, but the claims gained no international recognition.<ref>{{cite journal|last=Oduntan|first= Gbenga|s2cid= 10047170| title = The Never Ending Dispute: Legal Theories on the Spatial Demarcation Boundary Plane between Airspace and Outer Space|journal= Hertfordshire Law Journal|volume=1|issue= 2|page=75}}</ref>

===Statite proposal===
A [[statite]] is a hypothetical satellite that uses [[Radiation pressure#Solar radiation pressure|radiation pressure]] from the sun against a [[solar sail]] to modify its orbit.

It would hold its location over the dark side of the Earth at a latitude of approximately 30 degrees. A statite is stationary relative to the Earth and Sun system rather than compared to surface of the Earth, and could ease congestion in the geostationary ring.<ref>{{cite patent |country = US |number = 5183225 |status = patent |title = STATITE: SPACECRAFT THAT UTILIZES SIGHT PRESSURE AND METHOD OF USE |pubdate = February 2, 1993 |pridate = 1989-01-09 |inventor-surname = Forward |inventor-given = Robert}}</ref><ref>{{cite magazine|magazine=New Scientist |date=March 9, 1991 |title=Science: Polar 'satellite' could revolutionise communications|issue=1759|url=https://www.newscientist.com/article/mg12917594-000-science-polar-satellite-could-revolutionisecommunications/ |access-date=October 2, 2019}}</ref>