# Low_Earth_orbit

## Defining characteristics

A wide variety of sources[4][5][6] define LEO in terms of altitude. The altitude of an object in an elliptic orbit can vary significantly along the orbit. Even for circular orbits, the altitude above ground can vary by as much as 30 km (19 mi) (especially for polar orbits) due to the oblateness of Earth's spheroid figure and local topography. While definitions based on altitude are inherently ambiguous, most of them fall within the range specified by an orbit period of 128 minutes because, according to Kepler's third law, this corresponds to a semi-major axis of 8,413 km (5,228 mi). For circular orbits, this in turn corresponds to an altitude of 2,042 km (1,269 mi) above the mean radius of Earth, which is consistent with some of the upper altitude limits in some LEO definitions.

The LEO region is defined by some sources as a region in space that LEO orbits occupy.[3][7][8] Some highly elliptical orbits may pass through the LEO region near their lowest altitude (or perigee) but are not in a LEO orbit because their highest altitude (or apogee) exceeds 2,000 km (1,243 mi). Sub-orbital objects can also reach the LEO region but are not in a LEO orbit because they re-enter the atmosphere. The distinction between LEO orbits and the LEO region is especially important for analysis of possible collisions between objects which may not themselves be in LEO but could collide with satellites or debris in LEO orbits.

## Orbital characteristics

The mean orbital velocity needed to maintain a stable low Earth orbit is about 7.8 km/s (4.8 mi/s), which translates to 28,000 km/h (17,000 mph). However, this depends on the exact altitude of the orbit. Calculated for a circular orbit of 200 km (120 mi) the orbital velocity is 7.79 km/s (4.84 mi/s), but for a higher 1,500 km (930 mi) orbit the velocity is reduced to 7.12 km/s (4.42 mi/s).[9] The launch vehicle's delta-v needed to achieve low Earth orbit starts around 9.4 km/s (5.8 mi/s).

The pull of gravity in LEO is only slightly less than on the Earth's surface. This is because the distance to LEO from the Earth's surface is much less than the Earth's radius. However, an object in orbit is in a permanent free fall around Earth, because in orbit the gravitational force and the centrifugal force balance out each other.[lower-alpha 3] As a result, spacecraft in orbit continue to stay in orbit, and people inside or outside such craft continuously experience weightlessness.

Objects in LEO encounter atmospheric drag from gases in the thermosphere (approximately 80–600 km above the surface) or exosphere (approximately 600 km or 400 mi and higher), depending on orbit height. Orbits of satellites that reach altitudes below 300 km (190 mi) decay fast due to atmospheric drag. Objects in LEO orbit Earth between the denser part of the atmosphere and below the inner Van Allen radiation belt.

Equatorial low Earth orbits (ELEO) are a subset of LEO. These orbits, with low inclination to the Equator, allow rapid revisit times of low-latitude places on Earth and have the lowest delta-v requirement (i.e., fuel spent) of any orbit, provided they have the direct (not retrograde) orientation with respect to the Earth's rotation. Orbits with a very high inclination angle to the equator are usually called polar orbits or Sun-synchronous orbits.

Higher orbits include medium Earth orbit (MEO), sometimes called intermediate circular orbit (ICO), and further above, geostationary orbit (GEO). Orbits higher than low orbit can lead to early failure of electronic components due to intense radiation and charge accumulation.

In 2017, "very low Earth orbits" (VLEO) began to be seen in regulatory filings. These orbits, below about 450 km (280 mi), require the use of novel technologies for orbit raising because they operate in orbits that would ordinarily decay too soon to be economically useful.[10][11]

## Use

A low Earth orbit requires the lowest amount of energy for satellite placement. It provides high bandwidth and low communication latency. Satellites and space stations in LEO are more accessible for crew and servicing.

Since it requires less energy to place a satellite into a LEO, and a satellite there needs less powerful amplifiers for successful transmission, LEO is used for many communication applications, such as the Iridium phone system. Some communication satellites use much higher geostationary orbits and move at the same angular velocity as the Earth as to appear stationary above one location on the planet.

Unlike geosynchronous satellite, satellites in LEO have a small field of view and so can observe and communicate with only a fraction of the Earth at a time. This means that a network (or "constellation") of satellites is required to provide continuous coverage. Satellites in lower regions of LEO also suffer from fast orbital decay and require either periodic re-boosting to maintain a stable orbit or launching replacement satellites when old ones re-enter.

#### Examples

##### Former
• The Chinese Tiangong-1 station was in orbit at about 355 kilometres (221 mi),[14] until its de-orbiting in 2018.
• The Chinese Tiangong-2 station was in orbit at about 370 km (230 mi), until its de-orbiting in 2019.
• GOCE, another gravimetry mission, orbited at about 255 km (158 mi) to measure Earth's gravity field at highest sensitivity. The mission lifetime was limited because of atmospheric drag.

## Space debris

The LEO environment is becoming congested with space debris because of the frequency of object launches.[16] This has caused growing concern in recent years, since collisions at orbital velocities can be dangerous or deadly. Collisions can produce additional space debris, creating a domino effect known as Kessler syndrome. The Orbital Debris Program, part of NASA, tracks over 25,000 objects larger than 10 cm in LEO, the estimated number between 1 and 10 cm in diameter is 500,000. The amount of particles bigger than 1 mm exceeds 100 million.[17] The particles travel at speeds up to 7.8 km/s (28,000 km/h; 17,500 mph), so even a small particle impact can severely damage a spacecraft.[18]

## Notes

1. Orbital periods and speeds are calculated using the relations 4π2R3 = T2GM and V2R = GM, where R is the radius of orbit in metres; T is the orbital period in seconds; V is the orbital speed in m/s; G is the gravitational constant, approximately 6.673×10−11 Nm2/kg2; M is the mass of Earth, approximately 5.98×1024 kg (1.318×1025 lb).
2. Approximately 8.6 times (in radius and length) when the Moon is nearest (that is, 363,104 km/42,164 km), to 9.6 times when the Moon is farthest (that is, 405,696 km/42,164 km).
3. It is important to note here that “free fall” by definition requires that gravity is the only force acting on the object. That definition is still fulfilled when falling around Earth, as the other force, the centrifugal force is a fictitious force.

## References

1. "Current Catalog Files". Archived from the original on 26 June 2018. Retrieved 13 July 2018. LEO: Mean Motion > 11.25 & Eccentricity < 0.25
2. Sampaio, Jarbas; Wnuk, Edwin; Vilhena de Moraes, Rodolpho; Fernandes, Sandro (1 January 2014). "Resonant Orbital Dynamics in LEO Region: Space Debris in Focus". Mathematical Problems in Engineering. 2014: Figure 1: Histogram of the mean motion of the cataloged objects. doi:10.1155/2014/929810. Archived from the original on 1 October 2021. Retrieved 13 July 2018.
3. "IADC Space Debris Mitigation Guidelines" (PDF). INTER-AGENCY SPACE DEBRIS COORDINATION COMMITTEE: Issued by Steering Group and Working Group 4. September 2007. Archived (PDF) from the original on 17 July 2018. Retrieved 17 July 2018. Region A, Low Earth Orbit (or LEO) Region – spherical region that extends from the Earth's surface up to an altitude (Z) of 2,000 km
4. "Definition of LOW EARTH ORBIT". Merriam-Webster Dictionary. Archived from the original on 8 July 2018. Retrieved 8 July 2018.
5. "Frequently Asked Questions". FAA. Archived from the original on 2 June 2020. Retrieved 14 February 2020. LEO refers to orbits that are typically less than 2,400 km (1,491 mi) in altitude.
6. Campbell, Ashley (10 July 2015). "SCaN Glossary". NASA. Archived from the original on 3 August 2020. Retrieved 12 July 2018. Low Earth Orbit (LEO): A geocentric orbit with an altitude much less than the Earth's radius. Satellites in this orbit are between 80 and 2000 kilometers above the Earth's surface.
7. "What Is an Orbit?". NASA. David Hitt : NASA Educational Technology Services, Alice Wesson : JPL, J.D. Harrington : HQ;, Larry Cooper : HQ;, Flint Wild : MSFC;, Ann Marie Trotta : HQ;, Diedra Williams : MSFC. 1 June 2015. Archived from the original on 27 March 2018. Retrieved 8 July 2018. LEO is the first 100 to 200 miles (161 to 322 km) of space.{{cite news}}: CS1 maint: others (link)
8. Steele, Dylan (3 May 2016). "A Researcher's Guide to: Space Environmental Effects". NASA. p. 7. Archived from the original on 17 November 2016. Retrieved 12 July 2018. the low-Earth orbit (LEO) environment, defined as 200–1,000 km above Earth's surface
9. "LEO parameters". www.spaceacademy.net.au. Archived from the original on 11 February 2016. Retrieved 12 June 2015.
10. Crisp, N. H.; Roberts, P. C. E.; Livadiotti, S.; Oiko, V. T. A.; Edmondson, S.; Haigh, S. J.; Huyton, C.; Sinpetru, L.; Smith, K. L.; Worrall, S. D.; Becedas, J. (August 2020). "The Benefits of Very Low Earth Orbit for Earth Observation Missions". Progress in Aerospace Sciences. 117: 100619. arXiv:2007.07699. Bibcode:2020PrAeS.11700619C. doi:10.1016/j.paerosci.2020.100619. S2CID 220525689.
11. Messier, Doug (3 March 2017). "SpaceX Wants to Launch 12,000 Satellites". Parabolic Arc. Archived from the original on 22 January 2020. Retrieved 22 January 2018.
12. "Higher Altitude Improves Station's Fuel Economy". NASA. Archived from the original on 15 May 2015. Retrieved 12 February 2013.
13. Holli, Riebeek (4 September 2009). "NASA Earth Observatory". earthobservatory.nasa.gov. Archived from the original on 27 May 2018. Retrieved 28 November 2015.
14. ""天宫一号成功完成二次变轨"". Archived from the original on 13 November 2011. Retrieved 13 October 2020.
15. "Space station from 2001: A Space Odyssey".
16. United Nations Office for Outer Space Affairs (2010). "Space Debris Mitigation Guidelines of the Committee on the Peaceful Uses of Outer Space". Inter-Agency Space Debris Coordination Committee (IADC). Retrieved 19 October 2021.
17. "ARES | Orbital Debris Program Office | Frequently Asked Questions". NASA.gov. Archived from the original on 2 September 2022. Retrieved 2 September 2022.
18. Garcia, Mark (13 April 2015). "Space Debris and Human Spacecraft". NASA.gov. Archived from the original on 8 September 2022. Retrieved 2 September 2022.

This article incorporates public domain material from websites or documents of the National Aeronautics and Space Administration.