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 the object is much less massive than the largest body in the system, its speed relative to that largest body. The speed in this latter case may be relative to the surface of the larger body or relative to its center of mass.
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, perhelion, etc.), while minimum speed for objects in closed orbits occurs at apoapsis (aphelion, apogee, etc.). In ideal twobody systems, objects in open orbits continue to slow down forever as their distance to the barycenter increases.
When a system approximates a twobody 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. (Specific orbital energy is constant and independent of position.)
In the following, it is assumed that the system is a twobody system and the orbiting object has a negligible mass compared to the larger (central) object. In realworld orbital mechanics, it is the system's barycenter, not the larger object, which is at the focus.
Specific orbital energy = K.E. + P.E. (kinetic energy + potential energy). Since kinetic energy is always nonnegative (greater than or equal to zero, >=0) and potential energy is always nonpositive (less than or equal to zero,
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.^{[1]}
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.
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.^{[2]}
where v is the orbital velocity, a is the length of the semimajor axis, T is the orbital period, and ?=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 twobody 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 as:
or assuming r equal to the body's radius
Where M is the (greater) mass around which this negligible mass or body is orbiting, and v_{e} 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:
The mean orbital speed decreases with eccentricity.
For the precise orbital speed of a body at any given point in its trajectory, both the mean distance and the precise distance are taken into account:
where ? is the standard gravitational parameter, r is the distance at which the speed is to be calculated, and a is the length of the semimajor axis of the elliptical orbit. This expression is called the visviva equation. For the Earth at perihelion,
which is slightly faster than Earth's average orbital speed of 29,800 m/s, as expected from Kepler's 2nd Law.
Orbit  Centertocenter distance 
Altitude above the Earth's surface 
Speed  Orbital period  Specific orbital energy 

Earth's own rotation at surface (for comparison  not an orbit)  6,378km  0km  465.1m/s (1,674km/h or 1,040mph)  23h 56min  62.6MJ/kg 
Orbiting at Earth's surface (equator)  6,378km  0km  7.9km/s (28,440km/h or 17,672mph)  1h 24min 18sec  31.2MJ/kg 
Low Earth orbit  6,6008,400km  2002,000km 

1h 29min  2h 8min  29.8MJ/kg 
Molniya orbit  6,90046,300km  50039,900km  1.510.0km/s (5,40036,000km/h or 3,33522,370mph) respectively  11h 58min  4.7MJ/kg 
Geostationary  42,000km  35,786km  3.1km/s (11,600km/h or 6,935mph)  23h 56min  4.6MJ/kg 
Orbit of the Moon  363,000406,000km  357,000399,000km  0.971.08km/s (3,4923,888km/h or 2,1702,416mph) respectively  27.3days  0.5MJ/kg 
...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.