High Earth orbit

This article is about a type of geocentric orbit defined by altitude. For a more common disambiguation of HEO, see Highly elliptical orbit.

Geocentric orbit with an altitude entirely above that of a geosynchronous orbit

Space of high Earth orbits (HEO), between medium Earth orbits (MEO) and the orbit of the Moon.

A high Earth orbit is a geocentric orbit with an apogee farther than that of the geosynchronous orbit, which is 35,786 km (22,236 mi) away from Earth.[1] In this article, the non-standard abbreviation of HEO is used for high Earth orbit.[2]

The development of HEO technology has had a significant impact on space exploration and has paved the way for future missions to deep space. The ability to place satellites in HEO has allowed scientists to make groundbreaking discoveries in astronomy and Earth science, while also enabling global communication and navigation systems.[3]

## Common types of high Earth orbits

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A view of a crescent Earth taken from inside Apollo 13’s Lunar Module on 17 April 1970. Credit: NASA / restored by Toby Ord Orbit | Name

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GEO | Geostationary orbit
GSO | Geosynchronous orbit
GTO | Geostationary transfer orbit
HEO | Highly elliptical orbit
NRHO | Near-rectilinear halo orbit

Satellites in High Earth orbits are primarily used for communication, navigation, scientific research, and military applications.[4] One of the main benefits of HEO is that it provides a nearly unobstructed view of the Earth and deep space. This makes it an ideal location for astronomical observations and Earth monitoring. In addition, satellites in HEO can provide a continuous coverage of the Earth's surface, making it very useful for communication and navigation purposes.[5] A variety of satellites, such as TESS,[6] have been placed in HEO.

There are four main reasons that most satellite are placed in lower orbits. First, a HEO can take a month or more per orbit. This is because HEOs are very large orbits and move at only 7000 mph. Meanwhile, a LEO (low Earth orbit) can take less than 90 minutes.[7] So, for satellites that need to orbit quickly, HEO is not a good fit. Second, HEOs take far more energy to place a satellite into than LEOs. To place a satellite into HEO takes nearly as much energy as to place it into a heliocentric orbit. For example, an expended Falcon 9 can carry 50,000 pounds to LEO. However, it can only carry around 10,000 pounds to HEO. [8] This means that it costs 5 times more to place a payload in HEO versus placing it in LEO. Third, HEOs are extremely far from Earth. This means that there is a constant communication delay when sending signals to and from the satellite. This is actually because the signals can only travel at the speed of light. This means that it can take around 0.1 to 4.5 seconds in delay time each way. This makes it useless for internet, and hard to use for other things as well. The fourth reason is radiation. HEO is outside of the magnetic field of Earth. This means that there is far more radiation in HEO. As a result, spacecraft in HEO require specialized equipment and shielding to protect them from radiation. As a result, only satellites that require the unique characteristics of HEO use this orbit.

A special case of a high Earth orbit is the highly elliptical orbit where altitude at perigee may reach as low as 2,000 km (1,200 mi).

## Examples of satellites in high Earth orbit

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Name  | NSSDC id.  | Launch date  | Perigee  | Apogee  | Period  | Inclination

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Vela 1A[9][10] | 1963-039A  | 1963-10-17  | 101,925 km  | 116,528 km  | 108 hr 39 min  | 37.8°
IBEX | 2008-051A  | 2008-10-19  | 61,941 km  | 290,906 km  | 216 hr 3 min  | 16.9°
TESS[6][11] | 2018-038A  | 2018-04-18  | 108,000 km  | 375,000 km  | 328 hr 48 min  | 37.00°
Chdryn.-3 prop. module | 2023-098B  | 2023-07-14  | 115,000 km  | 154,000 km  | ~312 hr  | 27°

## See also

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* List of orbits

## References

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1. ^ "Catalog of Earth Satellite Orbits". earthobservatory.nasa.gov. NASA Earth Observatory. 2009-09-04. p. 1. Retrieved 2023-04-05.
2. ^ "Types of Orbits". spacefoundation.org. Space Foundation. Retrieved 2023-04-22.
3. ^ "Catalog of Earth Satellite Orbits: Three Classes of Orbit". earthobservatory.nasa.gov. NASA Earth Observatory. 2009-09-04. p. 2. Retrieved 2023-04-05.
4. ^ "Types of Orbits". spacefoundation.org. Retrieved April 22, 2023.
5. ^ "Advantages of HEO Highly Elliptical Orbit | Disadvantages of HEO orbit".
6. ^ a b "MIT TESS mission". Retrieved November 12, 2022.
7. ^ "Popular Orbits 101". Aerospace Security. 30 November 2017. Retrieved 2023-04-05.
8. ^ "Capabilities & Services" (PDF). spacex.com. Retrieved April 22, 2023.
9. ^ "Vela". Astronautix.com. Retrieved November 12, 2022.
10. ^ "Trajectory Details for Vela 1A from the National Space Science Data Center". Retrieved November 12, 2022.
11. ^ "NASA - TESS Science Support Center". 25 July 2023.

* v
* t
* e

Gravitational orbits

Types|

| General|

* Box
* Capture
* Circular
* Elliptical / Highly elliptical
* Escape
* Horseshoe
* Hyperbolic trajectory
* Inclined / Non-inclined
* Kepler
* Lagrange point
* Osculating
* Parabolic trajectory
* Parking
* Prograde / Retrograde
* Synchronous
* semi
* sub
* Transfer orbit

|

Geocentric|

* Geosynchronous
* Geostationary
* Geostationary transfer
* Graveyard
* High Earth
* Low Earth
* Medium Earth
* Molniya
* Near-equatorial
* Orbit of the Moon
* Polar
* Sun-synchronous
* Transatmospheric
* Tundra
* Very low Earth

About
other points|

* Mars
* Areocentric
* Areosynchronous
* Areostationary
* Lagrange points
* Distant retrograde
* Halo
* Lissajous
* Libration
* Lunar
* Sun
* Heliocentric
* Earth's orbit
* Mars cycler
* Heliosynchronous
* Other
* Lunar cycler

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
* t0 Epoch

Maneuvers|

* Bi-elliptic transfer
* Collision avoidance (spacecraft)
* Delta-v
* Delta-v budget
* Gravity assist
* Gravity turn
* Hohmann transfer
* Inclination change
* Low-energy transfer
* Oberth effect
* Phasing
* Rocket equation
* Rendezvous
* Trans-lunar injection
* Transposition, docking, and extraction

Orbital
mechanics|

* Astronomical coordinate systems
* Characteristic energy
* Escape velocity
* Ephemeris
* Equatorial coordinate system
* Ground track
* Hill sphere
* Interplanetary Transport Network
* Kepler's laws of planetary motion
* Kozai mechanism
* Lagrangian point
* n-body problem
* Orbit equation
* Orbital state vectors
* Perturbation
* Retrograde and prograde motion
* Specific orbital energy
* Specific angular momentum
* Two-line elements

* List of orbits

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*[e]: Edit this template