Geostationary orbit - wikipedia Geostationary orbit Two geostationary satellites in same orbit A 5 × 6 degree view of a part of the geostationary belt, showing several geostationary satellites. Those with inclination 0 ° form a diagonal belt across the image ; a few objects with small inclinations to the equator are visible above this line. The satellites are pinpoint, while stars have created small trails due to the Earth 's rotation. For orbits that have a period of one day, see geosynchronous orbit. A geostationary orbit, geostationary Earth orbit ( often loosely referred to as geosynchronous equatorial orbit ) ( GEO ) is a circular geosynchronous orbit 35,786 kilometres ( 22,236 mi ) above the Earth 's equator and following the direction of the Earth 's rotation. An object in such an orbit appears motionless, at a fixed position in the sky, to ground observers. Communications satellites and weather satellites are often placed in geostationary orbits, so that the satellite antennas ( located on Earth ) that communicate with them do not have to rotate to track them, but can be pointed permanently at the position in the sky where the satellites are located. Using this characteristic, ocean color satellites with visible and near - infrared light sensors ( e.g. the Geostationary Ocean Color Imager ( GOCI ) ) can also be operated in geostationary orbit in order to monitor sensitive changes of ocean environments. A geostationary orbit is a particular type of geosynchronous orbit, which is an orbit which has an orbital period equal to the Earth 's rotational period ( one sidereal day ) and thus the distinction being that while an object in geosynchronous orbit returns to the same point in the sky at the same time each day, an object in geostationary orbit never leaves that position. Geosynchronous orbits move around relative to a point on the earth 's surface, because while geostationary orbits have an inclination of 0 degrees relative to the equator, geosynchronous orbits have varying inclinations and eccentricities. Contents 1 History 2 Practical uses 2.1 Communications 2.2 Orbit allocation 3 Orbital stability 3.1 Limitations to usable life of geostationary satellites 4 Derivation of geostationary altitude 5 See also 6 Notes 7 References 8 External links History The first appearance of a geostationary orbit in popular literature was in the first Venus Equilateral story by George O. Smith, but Smith did not go into details. British science fiction author Arthur C. Clarke disseminated the idea widely, with more details on how it would work, in a 1945 paper entitled `` Extra-Terrestrial Relays -- Can Rocket Stations Give Worldwide Radio Coverage ? '', published in Wireless World magazine. Clarke acknowledged the connection in his introduction to The Complete Venus Equilateral. The orbit, which Clarke first described as useful for broadcast and relay communications satellites, is sometimes called the Clarke Orbit. Similarly, the Clarke Belt is the part of space about 35,786 km ( 22,236 mi ) above sea level, in the plane of the equator, where near - geostationary orbits may be implemented. The Clarke Orbit is about 265,000 km ( 165,000 mi ) in circumference. Practical uses See also : Geosynchronous satellite Most commercial communications satellites, broadcast satellites and SBAS satellites operate in geostationary orbits. A geostationary transfer orbit is used to move a satellite from low Earth orbit ( LEO ) into a geostationary orbit. The first satellite placed into a geostationary orbit was the Syncom - 3, launched by a Delta D rocket in 1964. A worldwide network of operational geostationary meteorological satellites is used to provide visible and infrared images of Earth 's surface and atmosphere. These satellite systems include : the United States GOES Meteosat, launched by the European Space Agency and operated by the European Weather Satellite Organization, EUMETSAT the Japanese Himawari Chinese Fengyun India 's INSAT series A statite, a hypothetical satellite that uses a solar sail to modify its orbit, could theoretically hold itself in a geostationary `` orbit '' with different altitude and / or inclination from the `` traditional '' equatorial geostationary orbit. Communications Satellites in geostationary orbits are far enough away from Earth that communication latency becomes significant -- about a quarter of a second for a trip from one ground - based transmitter to the satellite and back to another ground - based transmitter ; close to half a second for a round - trip communication from one Earth station to another and then back to the first. For example, for ground stations at latitudes of φ = ± 45 ° on the same meridian as the satellite, the time taken for a signal to pass from Earth to the satellite and back again can be computed using the cosine rule, given the geostationary orbital radius r ( derived below ), the Earth 's radius R and the speed of light c, as Δ t = 2 c R 2 + r 2 − 2 R r cos ⁡ φ ≈ 253 ms. ( displaystyle Delta t = ( \frac ( 2 ) ( c ) ) ( sqrt ( R ^ ( 2 ) + r ^ ( 2 ) - 2Rr cos \varphi ) ) approx 253 ~ ( \text ( ms ) ). ) ( Note that r is the orbital radius, the distance from the centre of the Earth, not the height above the equator. ) This delay presents problems for latency - sensitive applications such as voice communication. Geostationary satellites are directly overhead at the equator and appear lower in the sky to an observer nearer the poles. As the observer 's latitude increases, communication becomes more difficult due to factors such as atmospheric refraction, Earth 's thermal emission, line - of - sight obstructions, and signal reflections from the ground or nearby structures. At latitudes above about 81 °, geostationary satellites are below the horizon and can not be seen at all. Because of this, some Russian communication satellites have used elliptical Molniya and Tundra orbits, which have excellent visibility at high latitudes. Orbit allocation 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. In the 1976 Bogotá 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. Orbital stability A geostationary orbit can be achieved only at an altitude very close to 35,786 km ( 22,236 mi ) and directly above the equator. This equates to an orbital velocity of 3.07 km / s ( 1.91 mi / s ) and an orbital period of 1,436 minutes, which equates to almost exactly one sidereal day ( 23.934461223 hours ). This ensures that the satellite will match the Earth 's rotational period and has a stationary footprint on the ground. All geostationary satellites have to be located on this ring. A combination of lunar gravity, solar gravity, and the flattening of the Earth at its poles causes a precession motion of the orbital plane of any geostationary object, with an orbital period of about 53 years and an initial inclination gradient of about 0.85 ° per year, achieving a maximal inclination of 15 ° after 26.5 years. To correct for this orbital perturbation, regular orbital stationkeeping manoeuvres are necessary, amounting to a delta - v of approximately 50 m / s per year. A second effect to be taken into account is the longitudinal drift, caused by the asymmetry of the Earth -- the equator is slightly elliptical. There are two stable ( at 75.3 ° E and 252 ° E ) and two unstable ( at 165.3 ° E and 14.7 ° W ) equilibrium points. Any geostationary object placed between the equilibrium points would ( without any action ) be slowly accelerated towards the stable equilibrium position, causing a periodic longitude variation. The correction of this effect requires station - keeping maneuvers with a maximal delta - v of about 2 m / s per year, depending on the desired longitude. Solar wind and radiation pressure also exert small forces on satellites ; over time, these cause them to slowly drift away from their prescribed orbits. In the absence of servicing missions from the Earth or a renewable propulsion method, the consumption of thruster propellant for station keeping places a limitation on the lifetime of the satellite. Hall - effect thrusters, which are currently in use, have the potential to prolong the service life of a satellite by providing high - efficiency electric propulsion. Limitations to usable Life of geostationary satellites When they run out of thruster fuel, the satellites are at the end of their service life, as they are no longer able to stay in their allocated orbital position. The transponders and other onboard systems generally outlive the thruster fuel and, by stopping N -- S station keeping, some satellites can continue to be used in inclined orbits ( where the orbital track appears to follow a figure - eight loop centred on the equator ), or else be elevated to a `` graveyard '' disposal orbit. Derivation of geostationary altitude Comparison of geostationary Earth orbit with GPS, GLONASS, Galileo and Compass ( medium Earth orbit ) satellite navigation system orbits with the International Space Station, Hubble Space Telescope and Iridium constellation orbits, and the nominal size of the Earth. The Moon 's orbit is around 9 times larger ( in radius and length ) than geostationary orbit. In any circular orbit, the centripetal force required to maintain the orbit ( F ) is provided by the gravitational force on the satellite ( F ). To calculate the geostationary orbit altitude, one begins with this equivalence : F c = F g. ( displaystyle mathbf ( F ) _ ( \text ( c ) ) = mathbf ( F ) _ ( \text ( g ) ). ) By Newton 's second law of motion, we can replace the forces F with the mass m of the object multiplied by the acceleration felt by the object due to that force : m a c = m g. ( displaystyle m mathbf ( a ) _ ( \text ( c ) ) = m mathbf ( g ). ) We note that the mass of the satellite m appears on both sides -- geostationary orbit is independent of the mass of the satellite. Calculating the geostationary altitude, therefore, simplifies down to calculating the altitude where the magnitudes of the centripetal acceleration required for orbital motion and the gravitational acceleration provided by Earth 's gravity are equal. The centripetal acceleration 's magnitude is : a c = ω 2 r, ( displaystyle mathbf ( a ) _ ( \text ( c ) ) = omega ^ ( 2 ) r, ) where ω is the angular speed, and r is the orbital radius as measured from the Earth 's center of mass. The magnitude of the gravitational acceleration is : g = G M r 2, ( displaystyle mathbf ( g ) = ( \frac ( GM ) ( r ^ ( 2 ) ) ), ) where M is the mass of Earth, 5.9736 × 10 kg, and G is the gravitational constant, ( 6.67428 ± 0.00067 ) × 10 m kg s. Equating the two accelerations gives : r 3 = G M ω 2 → r = G M ω 2 3. ( displaystyle r ^ ( 3 ) = ( \frac ( GM ) ( omega ^ ( 2 ) ) ) \to r = ( sqrt ( ( 3 ) ) ( \frac ( GM ) ( omega ^ ( 2 ) ) ) ). ) The product GM is known with much greater precision than either factor alone ; it is known as the geocentric gravitational constant μ = 398,600.4418 ± 0.0008 km s. Hence r = μ ω 2 3 ( displaystyle r = ( sqrt ( ( 3 ) ) ( \frac ( mu ) ( omega ^ ( 2 ) ) ) ) ) The angular speed ω is found by dividing the angle travelled in one revolution ( 360 ° = 2π rad ) by the orbital period ( the time it takes to make one full revolution ). In the case of a geostationary orbit, the orbital period is one sidereal day, or 7004861640905400000 ♠ 86 164. 090 54 s ). This gives ω ≈ 2 π rad 86 164 s ≈ 7.2921 × 10 − 5 rad / s. ( displaystyle omega approx ( \frac ( 2 pi ~ ( \text ( rad ) ) ) ( 86 , 164 ~ ( \text ( s ) ) ) ) approx 7.2921 \times 10 ^ ( - 5 ) ~ ( \text ( rad / s ) ). ) The resulting orbital radius is 42,164 kilometres ( 26,199 mi ). Subtracting the Earth 's equatorial radius, 6,378 kilometres ( 3,963 mi ), gives the altitude of 35,786 kilometres ( 22,236 mi ). Orbital speed is calculated by multiplying the angular speed by the orbital radius : v = ω r ≈ 3.0746 km / s ≈ 11 068 km / h ≈ 6877.8 mph. ( displaystyle v = omega r approx 3.0746 ~ ( \text ( km / s ) ) approx 11 , 068 ~ ( \text ( km / h ) ) approx 6877.8 ~ ( \text ( mph ) ). ) By the same formula, we can find the geostationary - type orbit of an object in relation to Mars ( this type of orbit above is referred to as an areostationary orbit if it is above Mars ). The geocentric gravitational constant GM ( which is μ ) for Mars has the value of 42,828 km s, and the known rotational period ( T ) of Mars is 88,642.66 seconds. Since ω = 2π / T, using the formula above, the value of ω is found to be approx 7.088218 × 10 s. Thus r = 8.5243 × 10 km, whose cube root is 20,427 km ( the orbital radius ) ; subtracting the equatorial radius of Mars ( 3396.2 km ) gives the orbital altitude of 17,031 km. Orbital speed of a Mars geostationary orbit can be calculated as for Earth above : v = ω r ≈ 1.4479 km / s ≈ 5 212 km / h. ( displaystyle v = omega r approx 1.4479 ~ ( \text ( km / s ) ) approx 5 , 212 ~ ( \text ( km / h ) ). ) See also Spaceflight portal Graveyard orbit List of orbits List of satellites in geosynchronous orbit Orbital stationkeeping Space elevator Notes Jump up ^ Orbital periods and speeds are calculated using the relations 4π2R3 = T2GM and V2R = GM, where R = radius of orbit in metres, T = orbital period in seconds, V = orbital speed in m / s, G = gravitational constant ≈ 6.673 × 10 Nm2 / kg2, M = mass of Earth ≈ 5.98 × 10 kg. Jump up ^ Approximately 8.6 times when the moon is nearest ( 363 104 km ÷ 42 164 km ) to 9.6 times when the moon is farthest ( 405 696 km ÷ 42 164 km ). Jump up ^ In the small - body approximation, the geostationary orbit is independent of the satellite 's mass. For satellites having a mass less than M μ / μ ≈ 10 kg, that is, over a billion times that of the ISS, the error due to the approximation is smaller than the error on the universal geocentric gravitational constant ( and thus negligible ). References Jump up ^ `` Ariane 5 User 's Manual Issue 5 Revision 1 '' ( PDF ). arianespace. July 2011. Archived from the original ( PDF ) on 4 October 2013. Retrieved 28 July 2013. Jump up ^ `` ( Korvus 's message is sent ) to a small, squat building at the outskirts of Northern Landing. It was hurled at the sky.... It... arrived at the relay station tired and worn,... when it reached a space station only five hundred miles above the city of North Landing. '' Smith, George O. ( 1976 ). The Complete Venus Equilateral. New York : Ballantine Books. pp. 3 -- 4. ISBN 978 - 0 - 345 - 28953 - 7. Jump up ^ `` It is therefore quite possible that these stories influenced me subconsciously when... I worked out the principles of synchronous communications satellistes... '', op. cit, p. x Jump up ^ `` Extra-Terrestrial Relays -- Can Rocket Stations Give Worldwide Radio Coverage ? '' ( PDF ). Arthur C. Clarke. October 1945. Archived from the original ( PDF ) on 18 March 2009. Retrieved 4 March 2009. Jump up ^ `` Basics of Space Flight Section 1 Part 5, Geostationary Orbits ''. NASA. Retrieved 21 June 2009. Jump up ^ US patent 5183225, Forward, Robert, `` STATITE : SPACECRAFT THAT UTILIZES SIGHT PRESSURE AND METHOD OF USE '', published 1993 - 02 - 02 Jump up ^ The Teledesic Network : Using Low - Earth - Orbit Satellites to Provide Broadband, Wireless, Real - Time Internet Access Worldwide. Jump up ^ p. 123. Jump up ^ ( 1 ) Archived March 27, 2009, at the Wayback Machine. Jump up ^ ITU Space Services Division. Jump up ^ Oduntan, Gbenga. `` The Never Ending Dispute : Legal Theories on the Spatial Demarcation Boundary Plane between Airspace and Outer Space '' ( PDF ). Hertfordshire Law Journal, 1 ( 2 ), p. 75. ^ Jump up to : OPERATIONAL CONSIDERATIONS OF GEO DEBRIS SYNCHRONIZATION DYNAMICS. Anderson Jump up ^ Shi Hu - Li, Han Yan - Ben, Ma Li - Hua, Pei Jun, Yin Zhi - Qiang and Ji Hai - Fu ( 2010 ). Beyond Life - Cycle Utilization of Geostationary Communication Satellites in End - of - Life, Satellite Communications, Nazzareno Diodato ( Ed. ), ISBN 978 - 953 - 307 - 135 - 0, InTech, `` Beyond Life - Cycle Utilization of Geostationary Communication Satellites in End - of - Life ''. Jump up ^ `` Inclined orbit operation ''. Jump up ^ `` Newton 's Second Law ''. The Physics Classroom. Jump up ^ Edited by P. Kenneth Seidelmann, `` Explanatory Supplement to the Astronomical Almanac '', University Science Books, 1992, p. 700. This article incorporates public domain material from the General Services Administration document `` Federal Standard 1037C '' ( in support of MIL - STD - 188 ). External links Orbital Mechanics ( Rocket and Space Technology ) List of satellites in geostationary orbit Clarke Belt Snapshot Calculator 3D Real Time Satellite Tracking Geostationary satellite orbit overview Daily animation of the Earth, made by geostationary satellite ' Electro L ' photos Satellite shoots 48 images of the planet every day. Gravitational orbits Types General Box Capture Circular Elliptical / Highly elliptical Escape Graveyard Horseshoe Hyperbolic trajectory Inclined / Non-inclined Osculating Parabolic trajectory Parking Synchronous semi sub Transfer orbit Geocentric Geosynchronous Geostationary Sun - synchronous Low Earth Medium Earth High Earth Molniya Near - equatorial Orbit of the Moon Polar Tundra About other points Areosynchronous Areostationary Halo Lissajous Lunar Heliocentric Heliosynchronous Parameters Shape Size e Eccentricity a Semi-major axis b Semi-minor axis Q, q Apsides Orientation i Inclination Ω Longitude of the ascending node ω Argument of periapsis π Longitude of the periapsis Position M Mean anomaly ν, θ, f True anomaly E Eccentric anomaly L Mean longitude l True longitude Variation T Orbital period n Mean motion v Orbital speed t Epoch Maneuvers Collision avoidance ( spacecraft ) Delta - v Delta - v budget Bi-elliptic transfer Geostationary transfer Gravity assist Gravity turn Hohmann transfer Low energy transfer Oberth effect Inclination change Phasing Rocket equation Rendezvous Transposition, docking, and extraction Orbital mechanics Celestial coordinate system Characteristic energy Escape velocity Ephemeris Equatorial coordinate system Ground track Hill sphere Interplanetary Transport Network Kepler 's laws of planetary motion Lagrangian point n - body problem Orbit equation Orbital state vectors Perturbation Retrograde motion Specific orbital energy Specific relative angular momentum Two - line elements List of orbits Arthur C. Clarke Bibliography Novels Prelude to Space The Sands of Mars Islands in the Sky Against the Fall of Night Childhood 's End Earthlight The City and the Stars The Deep Range A Fall of Moondust Dolphin Island Glide Path Imperial Earth The Fountains of Paradise The Songs of Distant Earth Cradle ( with Gentry Lee ) The Ghost from the Grand Banks The Hammer of God Richter 10 ( with Mike McQuay ) The Trigger ( with Michael Kube - McDowell ) The Light of Other Days ( with Stephen Baxter ) The Last Theorem ( with Frederik Pohl ) Novel series Space Odyssey 2001 : A Space Odyssey 2010 : Odyssey Two 2061 : Odyssey Three 3001 : The Final Odyssey Rama series Rendezvous with Rama Rama II ( with Gentry Lee ) The Garden of Rama ( with Gentry Lee ) Rama Revealed ( with Gentry Lee ) A Time Odyssey Time 's Eye ( with Stephen Baxter ) Sunstorm ( with Stephen Baxter ) Firstborn ( with Stephen Baxter ) Short story collections Expedition to Earth Reach for Tomorrow Tales from the White Hart The Other Side of the Sky Tales of Ten Worlds The Nine Billion Names of God Of Time and Stars The Wind from the Sun The Best of Arthur C. Clarke The Sentinel Tales from Planet Earth More Than One Universe The Collected Stories of Arthur C. Clarke Non-fiction Interplanetary Flight : An Introduction to Astronautics The Lost Worlds of 2001 The View from Serendip The Odyssey File : The Making of 2010 How the World Was One : Beyond the Global Village An Encyclopedia of Claims, Frauds, and Hoaxes of the Occult and Supernatural Adaptations 2001 : A Space Odyssey ( film ) 2001 : A Space Odyssey ( comics ) 2010 ( film ) `` The Star '' ( TV episode ) Rendezvous with Rama ( video game ) The Songs of Distant Earth ( album ) Rama ( video game ) Childhood 's End ( TV miniseries ) Related Arthur C. Clarke in media Sir Arthur Clarke Award Arthur C. Clarke Award Geostationary orbit Clarke 's three laws Arthur C. Clarke 's Mysterious World Arthur C. Clarke 's World of Strange Powers Arthur C. Clarke 's Mysterious Universe Arthur C. Clarke Institute for Modern Technologies Great Basses wreck 4923 Clarke Serendipaceratops GRB 080319B Retrieved from `` https://en.wikipedia.org/w/index.php?title=Geostationary_orbit&oldid=828254559 '' Categories : Astrodynamics Earth orbits Artificial satellites in geosynchronous orbit Hidden categories : Webarchive template wayback links Wikipedia articles incorporating text from the Federal Standard 1037C Wikipedia articles incorporating text from MIL - STD - 188 Talk Contents About Wikipedia Azərbaycanca বাংলা Беларуская Беларуская ( тарашкевіца ) ‎ Български Bosanski Brezhoneg Català Čeština Dansk Deutsch Eesti Ελληνικά Español فارسی Français Galego 한국어 हिन्दी Bahasa Indonesia Italiano עברית ქართული Қазақша Latviešu Magyar Nederlands 日本 語 Norsk Norsk nynorsk Polski Português Русский Simple English Slovenčina Slovenščina Српски / srpski Srpskohrvatski / српскохрватски Basa Sunda Suomi Svenska தமிழ் తెలుగు ไทย Türkçe Українська Tiếng Việt 中文 40 more Edit links This page was last edited on 1 March 2018, at 13 : 40. 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Question: the orbital speed of geo stationary satellite is
Answer: 3.07 km/s (1.91 mi/s)