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In astrodynamics, the ** vis-viva equation**, also referred to as

*Vis viva* (Latin for "living force") is a term from the history of mechanics, and it survives in this sole context. It represents the principle that the difference between the total work of the accelerating forces of a system and that of the retarding forces is equal to one half the *vis viva* accumulated or lost in the system while the work is being done.

For any Keplerian orbit (elliptic, parabolic, hyperbolic, or radial), the *vis-viva* equation^{[1]} is as follows:^{[2]}

where:

*v*is the relative speed of the two bodies*r*is the distance between the two bodies centers of mass*a*is the length of the semi-major axis (*a*> 0 for ellipses,*a*= ∞ or 1/*a*= 0 for parabolas, and*a*< 0 for hyperbolas)*G*is the gravitational constant*M*is the mass of the central body

The product of GM can also be expressed as the standard gravitational parameter using the Greek letter μ.

In the vis-viva equation the mass *m* of the orbiting body (e.g., a spacecraft) is taken to be negligible in comparison to the mass *M* of the central body (e.g., the Earth). The central body and orbiting body are also often referred to as the primary and a particle respectively. In the specific cases of an elliptical or circular orbit, the vis-viva equation may be readily derived from conservation of energy and momentum.

Specific total energy is constant throughout the orbit. Thus, using the subscripts *a* and *p* to denote apoapsis (apogee) and periapsis (perigee), respectively,

Rearranging,

Recalling that for an elliptical orbit (and hence also a circular orbit) the velocity and radius vectors are perpendicular at apoapsis and periapsis, conservation of angular momentum requires specific angular momentum , thus :

Isolating the kinetic energy at apoapsis and simplifying,

From the geometry of an ellipse, where *a* is the length of the semimajor axis. Thus,

Substituting this into our original expression for specific orbital energy,

Thus, and the vis-viva equation may be written

or

Therefore, the conserved **angular momentum** L = mh can be derived using and ,

where a is **semi-major axis** and b is **semi-minor axis** of the elliptical orbit, as follows -

and alternately,

Therefore, specific angular momentum , and

Total angular momentum

Given the total mass and the scalars *r* and *v* at a single point of the orbit, one can compute *r* and *v* at any other point in the orbit.^{[notes 1]}

Given the total mass and the scalars *r* and *v* at a single point of the orbit, one can compute the specific orbital energy , allowing an object orbiting a larger object to be classified as having not enough energy to remain in orbit, hence being "suborbital" (a ballistic missile, for example), having enough energy to be "orbital", but without the possibility to complete a full orbit anyway because it eventually collides with the other body, or having enough energy to come from and/or go to infinity (as a meteor, for example).

The formula for escape velocity can be obtained from the Vis-viva equation by taking the limit as approaches :

**^**For the three-body problem there is hardly a comparable vis-viva equation: conservation of energy reduces the larger number of degrees of freedom by only one.

**^**Tom Logsdon (1998).*Orbital Mechanics: Theory and Applications*. John Wiley & Sons. ISBN 978-0-471-14636-0.**^**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.