This is an old revision of this page, as edited by Hadal (talk | contribs) at 04:32, 25 August 2004 (Reverted edits by 203.10.121.89 to last version by 24.130.180.236). The present address (URL) is a permanent link to this revision, which may differ significantly from the current revision.
Revision as of 04:32, 25 August 2004 by Hadal (talk | contribs) (Reverted edits by 203.10.121.89 to last version by 24.130.180.236)(diff) ← Previous revision | Latest revision (diff) | Newer revision → (diff)A geosynchronous orbit is an orbit that has the same orbital period as the rotational period of the body it orbits (usually the Earth, but geosynchronous orbits exist around all moons, planets and suns that have sufficient rotational speed for an orbit to be maintained above the surface).
If a geosynchronous orbit is circular and equatorial then it is also a geostationary orbit, and will maintain the same position relative to the body it rotates around. If one could see a satellite in geostationary orbit it would appear to hover in the same position.
A circular geosynchronous orbit in the plane of the Earth's equator has a radius of approximately 42,164 km (from the center of the Earth), approximately 35,790 km (22,240 statute miles) above mean sea level.
This can be demonstrated analytically by application of the Law of Gravity and the physics of centripetal acceleration. Drawing the free body diagram and using the analysis methods of engineering dynamics and Physics allows the determination of the distance from Earth's center of mass which will satisfy this specified operating condition.
Circular geosynchronous orbits
Circular geosynchronous orbits at the equator are known as geostationary orbits. A perfect stable geostationary orbit is an ideal that can only be approximated. In practice the satellite will drift out of this orbit (caused by forces such as the solar wind and the gravitational effect of the moon), and thrusters are used to maintain the orbit.
See Geostationary orbit.
Other geosynchronous orbits
Elliptical orbits can be and are designed for communications satellites that keep the satellite within view of its assigned ground stations or receivers. A satellite in an elliptical geosynchronous orbit will appear to oscillate in the sky from the viewpoint of a ground station, and satellites in highly elliptical orbits must be tracked by steerable ground stations.
Theoretically an active geosynchronous orbit can be maintained if forces other than gravity are also used to maintain the orbit, such as a solar sail. Such a statite can be geosynchronous in an orbit different (higher, lower, more or less elliptical, or some other path) from the conic section orbit formed by a gravitational body. Such devices are still theoretical.
A further form of geosynchronous orbit is obtained by the theoretical space elevator in which one end of the structure is tethered to the ground, maintaining a longer orbital period than by gravity alone.
History
Author Arthur C. Clarke is credited with popularizing the notion of using a geostationary orbit for communications satellites. The orbit is also known as the Clarke Orbit.
The first communications satellite placed in a geosynchronous orbit was Syncom 2, launched in 1963. Geosynchronous orbits have been in common use ever since including satellite television. Initially geostationary satellites also carried telephone calls but are no longer used for voice communication, partly due to the inherent disconcerting delay in getting information to the satellite and back (it takes light or radio about a quarter of a second to make the round trip.)