This article needs additional citations for verification .(December 2015) |

A **geocentric orbit** or **Earth orbit** involves any object orbiting Earth, such as the Moon or artificial satellites. In 1997, NASA estimated there were approximately 2,465 artificial satellite payloads orbiting Earth and 6,216 pieces of space debris as tracked by the Goddard Space Flight Center.^{ [1] } More than 16,291 objects previously launched have undergone orbital decay and entered Earth's atmosphere.^{ [1] }

- List of terms and concepts
- Types
- Altitude classifications
- Inclination classifications
- Eccentricity classifications
- Directional classifications
- Geosynchronous classifications
- Special classifications
- Non-geocentric classifications
- Tangential velocities at altitude
- See also
- References
- External links

A spacecraft enters orbit when its centripetal acceleration due to gravity is less than or equal to the centrifugal acceleration due to the horizontal component of its velocity. For a low Earth orbit, this velocity is about 7,800 m/s (28,100 km/h; 17,400 mph);^{ [2] } by contrast, the fastest manned airplane speed ever achieved (excluding speeds achieved by deorbiting spacecraft) was 2,200 m/s (7,900 km/h; 4,900 mph) in 1967 by the North American X-15.^{ [3] } The energy required to reach Earth orbital velocity at an altitude of 600 km (370 mi) is about 36 MJ/kg, which is six times the energy needed merely to climb to the corresponding altitude.^{ [4] }

Spacecraft with a perigee below about 2,000 km (1,200 mi) are subject to drag from the Earth's atmosphere,^{ [5] } which decreases the orbital altitude. The rate of orbital decay depends on the satellite's cross-sectional area and mass, as well as variations in the air density of the upper atmosphere. Below about 300 km (190 mi), decay becomes more rapid with lifetimes measured in days. Once a satellite descends to 180 km (110 mi), it has only hours before it vaporizes in the atmosphere.^{ [6] } The escape velocity required to pull free of Earth's gravitational field altogether and move into interplanetary space is about 11,200 m/s (40,300 km/h; 25,100 mph).^{ [7] }

- Altitude
- as used here, the height of an object above the average surface of the Earth's oceans.
- Analemma
- a term in astronomy used to describe the plot of the positions of the Sun on the celestial sphere throughout one year. Closely resembles a figure-eight.
- Apogee
- is the farthest point that a satellite or celestial body can go from Earth, at which the orbital velocity will be at its minimum.
- Eccentricity
- a measure of how much an orbit deviates from a perfect circle. Eccentricity is strictly defined for all circular and elliptical orbits, and parabolic and hyperbolic trajectories.
- Equatorial plane
- as used here, an imaginary plane extending from the equator on the Earth to the celestial sphere.
- Escape velocity
- as used here, the minimum velocity an object without propulsion needs to have to move away indefinitely from the Earth. An object at this velocity will enter a parabolic trajectory; above this velocity it will enter a hyperbolic trajectory.
- Impulse
- the integral of a force over the time during which it acts. Measured in (N·sec or lb * sec).
- Inclination
- the angle between a reference plane and another plane or axis. In the sense discussed here the reference plane is the Earth's equatorial plane.
- Orbital characteristics
- the six parameters of the Keplerian elements needed to specify that orbit uniquely.
- Orbital period
- as defined here, time it takes a satellite to make one full orbit around the Earth.
- Perigee
- is the nearest approach point of a satellite or celestial body from Earth, at which the orbital velocity will be at its maximum.
- Sidereal day
- the time it takes for a celestial object to rotate 360°. For the Earth this is: 23 hours, 56 minutes, 4.091 seconds.
- Solar time
- as used here, the local time as measured by a sundial.
- Velocity
- an object's speed in a particular direction. Since velocity is defined as a vector, both speed and direction are required to define it.

The following is a list of different geocentric orbit classifications.

- Low Earth orbit (LEO)
- Geocentric orbits ranging in altitude from 160 kilometers (100 statute miles) to 2,000 kilometres (1,200 mi) above mean sea level. At 160 km, one revolution takes approximately 90 minutes, and the circular orbital speed is 8,000 metres per second (26,000 ft/s).
- Medium Earth orbit (MEO)
- Geocentric orbits with altitudes at apogee ranging between 2,000 kilometres (1,200 mi) and that of the geosynchronous orbit at 35,786 kilometres (22,236 mi).
- Geosynchronous orbit (GEO)
- Geocentric circular orbit with an altitude of 35,786 kilometres (22,236 mi). The period of the orbit equals one sidereal day, coinciding with the rotation period of the Earth. The speed is approximately 3,000 metres per second (9,800 ft/s).
- High Earth orbit (HEO)
- Geocentric orbits with altitudes at apogee higher than that of the geosynchronous orbit. A special case of high Earth orbit is the highly elliptical orbit, where altitude at perigee is less than 2,000 kilometres (1,200 mi).
^{ [8] }

- Inclined orbit
- An orbit whose inclination in reference to the equatorial plane is not 0.
- Polar orbit
- A satellite that passes above or nearly above both poles of the planet on each revolution. Therefore it has an inclination of (or very close to) 90 degrees.
- Polar sun synchronous orbit
- A nearly polar orbit that passes the equator at the same local time on every pass. Useful for image-taking satellites because shadows will be the same on every pass.

- Circular orbit
- An orbit that has an eccentricity of 0 and whose path traces a circle.
- Elliptic orbit
- An orbit with an eccentricity greater than 0 and less than 1 whose orbit traces the path of an ellipse.
- Hohmann transfer orbit
- An orbital maneuver that moves a spacecraft from one circular orbit to another using two engine impulses. This maneuver was named after Walter Hohmann.
- Geosynchronous transfer orbit (GTO)
- A geocentric-elliptic orbit where the perigee is at the altitude of a Low Earth Orbit (LEO) and the apogee at the altitude of a geosynchronous orbit.
- Highly elliptical orbit (HEO)
- Geocentric orbit with apogee above 35,786 km and low perigee (about 1,000 km) that result in long dwell times near apogee.
- Molniya orbit
- A highly elliptical orbit with inclination of 63.4° and orbital period of ½ of a sidereal day (roughly 12 hours). Such a satellite spends most of its time over a designated area of the Earth.
- Tundra orbit
- A highly elliptical orbit with inclination of 63.4° and orbital period of one sidereal day (roughly 24 hours). Such a satellite spends most of its time over a designated area of the Earth.

- Hyperbolic trajectory
- An "orbit" with eccentricity greater than 1. The object's velocity reaches some value in excess of the escape velocity, therefore it will escape the gravitational pull of the Earth and continue to travel infinitely with a velocity (relative to Earth) decelerating to some finite value, known as the hyperbolic excess velocity.
- Escape Trajectory
- This trajectory must be used to launch an interplanetary probe away from Earth, because the excess over escape velocity is what changes its heliocentric orbit from that of Earth.
- Capture Trajectory
- This is the mirror image of the escape trajectory; an object traveling with sufficient speed, not aimed directly at Earth, will move toward it and accelerate. In the absence of a decelerating engine impulse to put it into orbit, it will follow the escape trajectory after periapsis.

- Parabolic trajectory
- An "orbit" with eccentricity exactly equal to 1. The object's velocity equals the escape velocity, therefore it will escape the gravitational pull of the Earth and continue to travel with a velocity (relative to Earth) decelerating to 0. A spacecraft launched from Earth with this velocity would travel some distance away from it, but follow it around the Sun in the same heliocentric orbit. It is possible, but not likely that an object approaching Earth could follow a parabolic capture trajectory, but speed and direction would have to be precise.

- Prograde orbit
- an orbit in which the projection of the object onto the equatorial plane revolves about the Earth in the same direction as the rotation of the Earth.
- Retrograde orbit
- an orbit in which the projection of the object onto the equatorial plane revolves about the Earth in the direction opposite that of the rotation of the Earth.

- Semi-synchronous orbit (SSO)
- An orbit with an altitude of approximately 20,200 km (12,600 mi) and an orbital period of approximately 12 hours
- Geosynchronous orbit (GEO)
- Orbits with an altitude of approximately 35,786 km (22,236 mi). Such a satellite would trace an analemma (figure 8) in the sky.
- Geostationary orbit (GSO)
- A geosynchronous orbit with an inclination of zero. To an observer on the ground this satellite would appear as a fixed point in the sky.
- Clarke orbit
- Another name for a geostationary orbit. Named after the writer Arthur C. Clarke.
- Earth orbital libration points
- The libration points for objects orbiting Earth are at 105 degrees west and 75 degrees east. More than 160 satellites are gathered at these two points.
^{ [9] }

- Supersynchronous orbit
- A disposal / storage orbit above GSO/GEO. Satellites will drift west.
- Subsynchronous orbit
- A drift orbit close to but below GSO/GEO. Satellites will drift east.
- Graveyard orbit, disposal orbit, junk orbit
- An orbit a few hundred kilometers above geosynchronous that satellites are moved into at the end of their operation.

- Sun-synchronous orbit
- An orbit which combines altitude and inclination in such a way that the satellite passes over any given point of the planet's surface at the same local solar time. Such an orbit can place a satellite in constant sunlight and is useful for imaging, spy, and weather satellites.
- Moon orbit
- The orbital characteristics of Earth's Moon. Average altitude of 384,403 kilometres (238,857 mi), elliptical – inclined orbit.

- Horseshoe orbit
- An orbit that appears to a ground observer to be orbiting a planet but is actually in co-orbit with it. See asteroids 3753 (Cruithne) and 2002 AA
_{29}. - Sub-orbital flight
- A launch where a spacecraft approaches the height of orbit but lacks the velocity to sustain it.

Orbit | Center-to-center distance | Altitude above the Earth's surface | Speed | Orbital period | Specific orbital energy |
---|---|---|---|---|---|

Earth's own rotation at surface (for comparison— not an orbit) | 6,378 km | 0 km | 465.1 m/s (1,674 km/h or 1,040 mph) | 23 h 56 min 4.09 sec | −62.6 MJ/kg |

Orbiting at Earth's surface (equator) theoretical | 6,378 km | 0 km | 7.9 km/s (28,440 km/h or 17,672 mph) | 1 h 24 min 18 sec | −31.2 MJ/kg |

Low Earth orbit | 6,600–8,400 km | 200–2,000 km | - Circular orbit: 6.9–7.8 km/s (24,840–28,080 km/h or 14,430–17,450 mph) respectively
- Elliptic orbit: 6.5–8.2 km/s respectively
| 1 h 29 min – 2 h 8 min | −29.8 MJ/kg |

Molniya orbit | 6,900–46,300 km | 500–39,900 km | 1.5–10.0 km/s (5,400–36,000 km/h or 3,335–22,370 mph) respectively | 11 h 58 min | −4.7 MJ/kg |

Geostationary | 42,000 km | 35,786 km | 3.1 km/s (11,600 km/h or 6,935 mph) | 23 h 56 min 4.09 sec | −4.6 MJ/kg |

Orbit of the Moon | 363,000–406,000 km | 357,000–399,000 km | 0.97–1.08 km/s (3,492–3,888 km/h or 2,170–2,416 mph) respectively | 27.27 days | −0.5 MJ/kg |

In celestial mechanics, an **orbit** is the curved trajectory of an object such as the trajectory of a planet around a star, or of a natural satellite around a planet, or of an artificial satellite around an object or position in space such as a planet, moon, asteroid, or Lagrange point. Normally, orbit refers to a regularly repeating trajectory, although it may also refer to a non-repeating trajectory. To a close approximation, planets and satellites follow elliptic orbits, with the center of mass being orbited at a focal point of the ellipse, as described by Kepler's laws of planetary motion.

In the context of spaceflight, a **satellite** is an object that has been intentionally placed into orbit. These objects are called **artificial satellites** to distinguish them from natural satellites such as Earth's Moon.

A **geosynchronous orbit** is an Earth-centered orbit with an orbital period that matches Earth's rotation on its axis, 23 hours, 56 minutes, and 4 seconds. The synchronization of rotation and orbital period means that, for an observer on Earth's surface, an object in geosynchronous orbit returns to exactly the same position in the sky after a period of one sidereal day. Over the course of a day, the object's position in the sky may remain still or trace out a path, typically in a figure-8 form, whose precise characteristics depend on the orbit's inclination and eccentricity. A circular geosynchronous orbit has a constant altitude of 35,786 km (22,236 mi).

A **geostationary orbit**, also referred to as a **geosynchronous equatorial orbit** (**GEO**), is a circular geosynchronous orbit 35,786 km (22,236 mi) in altitude above Earth's Equator and following the direction of Earth's rotation.

A **low Earth orbit** (**LEO**) is an Earth-centered orbit near the planet, often specified as having an orbital period of 128 minutes or less and an eccentricity less than 0.25. Most of the artificial objects in outer space are in LEO, with an altitude never more than about one-third of the radius of Earth.

In orbital mechanics, the **Hohmann transfer orbit** is an elliptical orbit used to transfer between two circular orbits of different radii around a central body in the same plane that is sometimes tangential to both. The Hohmann transfer often uses the lowest possible amount of propellant in traveling between these orbits, but bi-elliptic transfers can use less in some cases.

A **geosynchronous transfer orbit** or **geostationary transfer orbit** (**GTO**) is a type of geocentric orbit. Satellites that are destined for geosynchronous (GSO) or geostationary orbit (GEO) are (almost) always put into a GTO as an intermediate step for reaching their final orbit.

**Orbital mechanics** or **astrodynamics** is the application of ballistics and celestial mechanics to the practical problems concerning the motion of rockets and other spacecraft. The motion of these objects is usually calculated from Newton's laws of motion and law of universal gravitation. Orbital mechanics is a core discipline within space-mission design and control.

In gravitationally bound systems, the **orbital speed** of an astronomical body or object is the speed at which it orbits around either the barycenter or, if one object is much more massive than the other bodies in the system, its speed relative to the center of mass of the most massive body.

The **Molniya** series satellites are military and communications satellites launched by the Soviet Union from 1965 to 2004. These satellites use highly eccentric elliptical orbits known as Molniya orbits, which have a long dwell time over high latitudes. They are suited for communications purposes in polar regions, in the same way that geostationary satellites are used for equatorial regions.

A **Molniya orbit** is a type of satellite orbit designed to provide communications and remote sensing coverage over high latitudes. It is a highly elliptical orbit with an inclination of 63.4 degrees, an argument of perigee of 270 degrees, and an orbital period of approximately half a sidereal day. The name comes from the *Molniya* satellites, a series of Soviet/Russian civilian and military communications satellites which have used this type of orbit since the mid-1960s.

An **orbital spaceflight** is a spaceflight in which a spacecraft is placed on a trajectory where it could remain in space for at least one orbit. To do this around the Earth, it must be on a free trajectory which has an altitude at perigee around 80 kilometers (50 mi); this is the boundary of space as defined by NASA, the US Air Force and the FAA. To remain in orbit at this altitude requires an orbital speed of ~7.8 km/s. Orbital speed is slower for higher orbits, but attaining them requires greater delta-v. The Fédération Aéronautique Internationale has established the Kármán line at an altitude of 100 km (62 mi) as a working definition for the boundary between aeronautics and astronautics. This is used because at an altitude of about 100 km (62 mi), as Theodore von Kármán calculated, a vehicle would have to travel faster than orbital velocity to derive sufficient aerodynamic lift from the atmosphere to support itself.

A **Sun-synchronous orbit** (**SSO**), also called a **heliosynchronous orbit**, is a nearly polar orbit around a planet, in which the satellite passes over any given point of the planet's surface at the same local mean solar time. More technically, it is an orbit arranged so that it precesses through one complete revolution each year, so it always maintains the same relationship with the Sun.

A **supersynchronous orbit** is either an orbit with a period greater than that of a synchronous orbit, or just an orbit whose apoapsis is higher than that of a synchronous orbit. A synchronous orbit has a period equal to the rotational period of the body which contains the barycenter of the orbit.

A **Tundra orbit** is a highly elliptical geosynchronous orbit with a high inclination, an orbital period of one sidereal day, and a typical eccentricity between 0.2 and 0.3. A satellite placed in this orbit spends most of its time over a chosen area of the Earth, a phenomenon known as apogee dwell, which makes them particularly well suited for communications satellites serving high-latitude regions. The ground track of a satellite in a Tundra orbit is a closed figure 8 with a smaller loop over either the northern or southern hemisphere. This differentiates them from Molniya orbits designed to service high-latitude regions, which have the same inclination but half the period and do not loiter over a single region.

The Moon orbits Earth in the prograde direction and completes one revolution relative to the Vernal Equinox and the stars in about 27.32 days and one revolution relative to the Sun in about 29.53 days. Earth and the Moon orbit about their barycentre, which lies about 4,670 km (2,900 mi) from Earth's centre, forming a satellite system called the **Earth–Moon system**. On average, the distance to the Moon is about 385,000 km (239,000 mi) from Earth's centre, which corresponds to about 60 Earth radii or 1.282 light-seconds.

A **near-equatorial orbit** is an orbit that lies close to the equatorial plane of the object orbited. Such an orbit has an inclination near 0°. On Earth, such orbits lie on the celestial equator, the great circle of the imaginary celestial sphere on the same plane as the equator of Earth. A geostationary orbit is a particular type of equatorial orbit, one which is geosynchronous. A satellite in a geostationary orbit appears stationary, always at the same point in the sky, to observers on the surface.

A **ground track** or **ground trace** is the path on the surface of a planet directly below an aircraft's or satellite's trajectory. In the case of satellites, it is also known as a **suborbital track**, and is the vertical projection of the satellite's orbit onto the surface of the Earth.

This **glossary of astronomy** is a list of definitions of terms and concepts relevant to astronomy and cosmology, their sub-disciplines, and related fields. Astronomy is concerned with the study of celestial objects and phenomena that originate outside the atmosphere of Earth. The field of astronomy features an extensive vocabulary and a significant amount of jargon.

- 1 2 "Satellite Situation Report, 1997". NASA Goddard Space Flight Center. 2000-02-01. Archived from the original on 2006-08-23. Retrieved 2006-09-10.
- ↑ Hill, James V. H. (April 1999), "Getting to Low Earth Orbit",
*Space Future*, archived from the original on 2012-03-19, retrieved 2012-03-18. - ↑ Shiner, Linda (November 1, 2007),
*X-15 Walkaround*, Air & Space Magazine, retrieved 2009-06-19. - ↑ Dimotakis, P.; et al. (October 1999),
*100 lbs to Low Earth Orbit (LEO): Small-Payload Launch Options*, The Mitre Corporation, pp. 1–39, archived from the original on 2017-08-29, retrieved 2012-01-21. - ↑ Ghosh, S. N. (2000),
*Atmospheric Science and Environment*, Allied Publishers, pp. 47–48, ISBN 978-8177640434 - ↑ Kennewell, John; McDonald, Andrew (2011),
*Satellite Lifetimes and Solar Activity*, Commonwealth of Australia Bureau of Weather, Space Weather Branch, archived from the original on 2011-12-28, retrieved 2011-12-31. - ↑ Williams, David R. (November 17, 2010), "Earth Fact Sheet",
*Lunar & Planetary Science*, NASA, archived from the original on October 30, 2010, retrieved 2012-05-10. - ↑ Definitions of geocentric orbits from the Goddard Space Flight Center Archived May 27, 2010, at the Wayback Machine
- ↑ Out-of-Control Satellite Threatens Other Nearby Spacecraft, by Peter B. de Selding, SPACE.com, 5/3/10. Archived May 5, 2010, at the Wayback Machine

- http://www.freemars.org/jeff/speed/index.htm
- http://www.tech-faq.com/medium-earth-orbit.shtml
- NASA.gov
- https://web.archive.org/web/20100221072300/http://www.space.com/scienceastronomy/solarsystem/second_moon_991029.html
- http://www.astro.uwo.ca/~wiegert/3753/3753.html
- http://www.astro.uwo.ca/~wiegert/AA29/AA29.html

This page is based on this Wikipedia article

Text is available under the CC BY-SA 4.0 license; additional terms may apply.

Images, videos and audio are available under their respective licenses.

Text is available under the CC BY-SA 4.0 license; additional terms may apply.

Images, videos and audio are available under their respective licenses.