# Orbital speed

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In gravitationally bound systems, the orbital speed of an astronomical body or object (e.g. planet, moon, artificial satellite, spacecraft, or star) 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.

## Contents

The term can be used to refer to either the mean orbital speed, i.e. the average speed over an entire orbit, or its instantaneous speed at a particular point in its orbit. Maximum (instantaneous) orbital speed occurs at periapsis (perigee, perihelion, etc.), while minimum speed for objects in closed orbits occurs at apoapsis (apogee, aphelion, etc.). In ideal two-body systems, objects in open orbits continue to slow down forever as their distance to the barycenter increases.

When a system approximates a two-body system, instantaneous orbital speed at a given point of the orbit can be computed from its distance to the central body and the object's specific orbital energy, sometimes called "total energy". Specific orbital energy is constant and independent of position. [1]

In the following, it is thought that the system is a two-body system and the orbiting object has a negligible mass compared to the larger (central) object. In real-world orbital mechanics, it is the system's barycenter, not the larger object, which is at the focus.

Specific orbital energy, or total energy, is equal to Ek  Ep. (kinetic energy  potential energy). The sign of the result may be positive, zero, or negative and the sign tells us something about the type of orbit: [1]

## Transverse orbital speed

The transverse orbital speed is inversely proportional to the distance to the central body because of the law of conservation of angular momentum, or equivalently, Kepler's second law. This states that as a body moves around its orbit during a fixed amount of time, the line from the barycenter to the body sweeps a constant area of the orbital plane, regardless of which part of its orbit the body traces during that period of time. [2]

This law implies that the body moves slower near its apoapsis than near its periapsis, because at the smaller distance along the arc it needs to move faster to cover the same area. [1]

## Mean orbital speed

For orbits with small eccentricity , the length of the orbit is close to that of a circular one, and the mean orbital speed can be approximated either from observations of the orbital period and the semimajor axis of its orbit, or from knowledge of the masses of the two bodies and the semimajor axis. [3]

${\displaystyle v\approx {2\pi a \over T}\approx {\sqrt {\mu \over a}}}$

where v is the orbital velocity, a is the length of the semimajor axis, T is the orbital period, and μ = GM is the standard gravitational parameter. This is an approximation that only holds true when the orbiting body is of considerably lesser mass than the central one, and eccentricity is close to zero.

When one of the bodies is not of considerably lesser mass see: Gravitational two-body problem

So, when one of the masses is almost negligible compared to the other mass, as the case for Earth and Sun, one can approximate the orbit velocity ${\displaystyle v_{o}}$ as: [1]

${\displaystyle v_{o}\approx {\sqrt {\frac {GM}{r}}}}$

or assuming r equal to the radius of the orbit[ citation needed ]

${\displaystyle v_{o}\approx {\frac {v_{e}}{\sqrt {2}}}}$

Where M is the (greater) mass around which this negligible mass or body is orbiting, and ve is the escape velocity.

For an object in an eccentric orbit orbiting a much larger body, the length of the orbit decreases with orbital eccentricity e, and is an ellipse. This can be used to obtain a more accurate estimate of the average orbital speed: [4]

${\displaystyle v_{o}={\frac {2\pi a}{T}}\left[1-{\frac {1}{4}}e^{2}-{\frac {3}{64}}e^{4}-{\frac {5}{256}}e^{6}-{\frac {175}{16384}}e^{8}-\cdots \right]}$

The mean orbital speed decreases with eccentricity.

## Instantaneous orbital speed

For the instantaneous orbital speed of a body at any given point in its trajectory, both the mean distance and the instantaneous distance are taken into account:

${\displaystyle v={\sqrt {\mu \left({2 \over r}-{1 \over a}\right)}}}$

where μ is the standard gravitational parameter of the orbited body, r is the distance at which the speed is to be calculated, and a is the length of the semi-major axis of the elliptical orbit. This expression is called the vis-viva equation. [1]

For the Earth at perihelion, the value is:

${\displaystyle {\sqrt {1.327\times 10^{20}~{\text{m}}^{3}{\text{s}}^{-2}\cdot \left({2 \over 1.471\times 10^{11}~{\text{m}}}-{1 \over 1.496\times 10^{11}~{\text{m}}}\right)}}\approx 30,300~{\text{m}}/{\text{s}}}$

which is slightly faster than Earth's average orbital speed of 29,800 m/s (67,000 mph), as expected from Kepler's 2nd Law.

## Tangential velocities at altitude

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 km0 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) theoretical6,378 km0 km7.9 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 km200–2,000 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 km500–39,900 km1.5–10.0 km/s (5,400–36,000 km/h or 3,335–22,370 mph) respectively11 h 58 min−4.7 MJ/kg
Geostationary 42,000 km35,786 km3.1 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 km357,000–399,000 km0.97–1.08 km/s (3,492–3,888 km/h or 2,170–2,416 mph) respectively27.27 days−0.5 MJ/kg

## Planets

The closer an object is to the Sun the faster it needs to move to maintain the orbit. Objects move fastest at perihelion (closest approach to the Sun) and slowest at aphelion (furthest distance from the Sun). Since planets in the Solar System are in nearly circular orbits their individual orbital velocities do not vary much. Being closest to the Sun and having the most eccentric orbit, Mercury's orbital speed varies from about 59 km/s at perihelion to 39 km/s at aphelion. [5]

Orbital velocities of the Planets [6]
PlanetOrbital
velocity
Mercury 47.9 km/s
Venus 35.0 km/s
Earth 29.8 km/s
Mars 24.1 km/s
Jupiter 13.1 km/s
Saturn 9.7 km/s
Uranus 6.8 km/s
Neptune 5.4 km/s

Halley's Comet on an eccentric orbit that reaches beyond Neptune will be moving 54.6 km/s when 0.586  AU (87,700 thousand  km ) from the Sun, 41.5 km/s when 1 AU from the Sun (passing Earth's orbit), and roughly 1 km/s at aphelion 35 AU (5.2 billion km) from the Sun. [7] Objects passing Earth's orbit going faster than 42.1 km/s have achieved escape velocity and will be ejected from the Solar System if not slowed down by a gravitational interaction with a planet.

Velocities of better-known numbered objects that have perihelion close to the Sun
ObjectVelocity at perihelionVelocity at 1 AU
(passing Earth's orbit)
322P/SOHO 181 km/s @ 0.0537 AU37.7 km/s
96P/Machholz 118 km/s @ 0.124 AU38.5 km/s
3200 Phaethon 109 km/s @ 0.140 AU32.7 km/s
1566 Icarus 93.1 km/s @ 0.187 AU30.9 km/s
66391 Moshup 86.5 km/s @ 0.200 AU19.8 km/s
1P/Halley 54.6 km/s @ 0.586 AU41.5 km/s

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## References

1. Lissauer, Jack J.; de Pater, Imke (2019). Fundamental Planetary Sciences: physics, chemistry, and habitability. New York, NY, USA: Cambridge University Press. pp. 29–31. ISBN   9781108411981.
2. Gamow, George (1962). . New York, NY, USA: Anchor Books, Doubleday & Co. pp.  66. ISBN   0-486-42563-0. ...the motion of planets along their elliptical orbits proceeds in such a way that an imaginary line connecting the Sun with the planet sweeps over equal areas of the planetary orbit in equal intervals of time.
3. Wertz, James R.; Larson, Wiley J., eds. (2010). Space mission analysis and design (3rd ed.). Hawthorne, CA, USA: Microcosm. p. 135. ISBN   978-1881883-10-4.
4. Stöcker, Horst; Harris, John W. (1998). . Springer. pp.  386. ISBN   0-387-94746-9.
5. "Horizons Batch for Mercury aphelion (2021-Jun-10) to perihelion (2021-Jul-24)". JPL Horizons (VmagSn is velocity with respect to Sun.). Jet Propulsion Laboratory. Retrieved 26 August 2021.
6. v = 42.1219 1/r − 0.5/a, where r is the distance from the Sun, and a is the major semi-axis.