This article needs additional citations for verification. (September 2007) (Learn how and when to remove this template message) 
Part of a series on 
Astrodynamics 

Orbital parameters 
Gravitational influences 
Preflight engineering 
Efficiency measures 
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.
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 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, sometimes called "total energy". Specific orbital energy is constant and independent of position.^{[1]}
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, or total energy, is equal to K.E. − P.E. (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]}
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]}
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]}
where v is the orbital velocity, a is the length of the semimajor axis in meters, 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 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:^{[1]}
or assuming r equal to the body's radius^{[citation needed]}
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 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:
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 semimajor axis of the elliptical orbit. This expression is called the visviva equation.^{[1]}
For the Earth at perihelion, the value is:
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)  6,378 km  0 km  465.1 m/s (1,674 km/h or 1,040 mph)  23 h 56 min  −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 

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  −4.6 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  27.3 days  −0.5 MJ/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.