Part of a series on
Astrodynamics
Orbital mechanics
Orbital elements Apsis Argument of periapsis Eccentricity Inclination Mean anomaly Orbital nodes Semi-major axis True anomaly
Types of two-body orbits by eccentricity Circular orbit Elliptic orbit Transfer orbit (Hohmann transfer orbit Bi-elliptic transfer orbit) Parabolic orbit Hyperbolic orbit Radial orbit Decaying orbit
Equations Dynamical friction Escape velocity Kepler's equation Kepler's laws of planetary motion Orbital period Orbital velocity Surface gravity Specific orbital energy Vis-viva equation
Celestial mechanics
Gravitational influences Barycenter Hill sphere Perturbations Sphere of influence
N-body orbits Lagrangian points (Halo orbits) Lissajous orbits Lyapunov orbits
Engineering and efficiency
Preflight engineering Mass ratio Payload fraction Propellant mass fraction Tsiolkovsky rocket equation
Efficiency measures Gravity assist Oberth effect

In astrodynamics, the vis-viva equation, also referred to as orbital-energy-invariance law or Burgas formula, is one of the equations that model the motion of orbiting bodies. It is the direct result of the principle of conservation of mechanical energy which applies when the only force acting on an object is its own weight which is the gravitational force determined by the product of the mass of the object and the strength of the surrounding gravitational field.

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.

Equation

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

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

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 G·M can also be expressed as the standard gravitational parameter using the Greek letter μ.

Derivation for elliptic orbits (0 ≤ eccentricity < 1)

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,

${\displaystyle \varepsilon ={\frac {v_{a}^{2}}{2}}-{\frac {GM}{r_{a}}}={\frac {v_{p}^{2}}{2}}-{\frac {GM}{r_{p}}}}$

Rearranging,

${\displaystyle {\frac {v_{a}^{2}}{2}}-{\frac {v_{p}^{2}}{2}}={\frac {GM}{r_{a}}}-{\frac {GM}{r_{p}}}}$

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 ${\displaystyle h=r_{p}v_{p}=r_{a}v_{a}={\text{constant}}}$, thus ${\displaystyle v_{p}={\frac {r_{a}}{r_{p}}}v_{a}}$:

${\displaystyle {\frac {1}{2}}\left(1-{\frac {r_{a}^{2}}{r_{p}^{2}}}\right)v_{a}^{2}={\frac {GM}{r_{a}}}-{\frac {GM}{r_{p}}}}$

${\displaystyle {\frac {1}{2}}\left({\frac {r_{p}^{2}-r_{a}^{2}}{r_{p}^{2}}}\right)v_{a}^{2}={\frac {GM}{r_{a}}}-{\frac {GM}{r_{p}}}}$

Isolating the kinetic energy at apoapsis and simplifying,

${\displaystyle {\frac {1}{2}}v_{a}^{2}=\left({\frac {GM}{r_{a}}}-{\frac {GM}{r_{p}}}\right)\cdot {\frac {r_{p}^{2}}{r_{p}^{2}-r_{a}^{2}}}}$

${\displaystyle {\frac {1}{2}}v_{a}^{2}=GM\left({\frac {r_{p}-r_{a}}{r_{a}r_{p}}}\right){\frac {r_{p}^{2}}{r_{p}^{2}-r_{a}^{2}}}}$

${\displaystyle {\frac {1}{2}}v_{a}^{2}=GM{\frac {r_{p}}{r_{a}(r_{p}+r_{a})}}}$

From the geometry of an ellipse, ${\displaystyle 2a=r_{p}+r_{a}}$ where a is the length of the semimajor axis. Thus,

${\displaystyle {\frac {1}{2}}v_{a}^{2}=GM{\frac {2a-r_{a}}{r_{a}(2a)}}=GM\left({\frac {1}{r_{a}}}-{\frac {1}{2a}}\right)={\frac {GM}{r_{a}}}-{\frac {GM}{2a}}}$

Substituting this into our original expression for specific orbital energy,

${\displaystyle \varepsilon ={\frac {v^{2}}{2}}-{\frac {GM}{r}}={\frac {v_{p}^{2}}{2}}-{\frac {GM}{r_{p}}}={\frac {v_{a}^{2}}{2}}-{\frac {GM}{r_{a}}}=-{\frac {GM}{2a}}}$

Thus, ${\displaystyle \varepsilon =-{\frac {GM}{2a}}}$ and the vis-viva equation may be written

${\displaystyle {\frac {v^{2}}{2}}-{\frac {GM}{r}}=-{\frac {GM}{2a}}}$

or

${\displaystyle v^{2}=GM\left({\frac {2}{r}}-{\frac {1}{a}}\right)}$

Therefore, the conserved angular momentum L = mh can be derived using ${\displaystyle r_{a}+r_{p}=2a}$ and ${\displaystyle r_{a}r_{p}=b^{2}}$,

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

${\displaystyle v_{a}^{2}=GM\left({\frac {2}{r_{a}}}-{\frac {1}{a}}\right)={\frac {GM}{a}}\left({\frac {2a-r_{a}}{r_{a}}}\right)={\frac {GM}{a}}\left({\frac {r_{p}}{r_{a}}}\right)={\frac {GM}{a}}\left({\frac {b}{r_{a}}}\right)^{2}}$

and alternately,

${\displaystyle v_{p}^{2}=GM\left({\frac {2}{r_{p}}}-{\frac {1}{a}}\right)={\frac {GM}{a}}\left({\frac {2a-r_{p}}{r_{p}}}\right)={\frac {GM}{a}}\left({\frac {r_{a}}{r_{p}}}\right)={\frac {GM}{a}}\left({\frac {b}{r_{p}}}\right)^{2}}$

Therefore, specific angular momentum ${\displaystyle h=r_{p}v_{p}=r_{a}v_{a}=b{\sqrt {\frac {GM}{a}}}}$, and

Total angular momentum ${\displaystyle L=mh=mb{\sqrt {\frac {GM}{a}}}}$

Practical applications

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]} and

• the specific orbital energy ${\displaystyle \varepsilon \,\!}$, 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 ${\displaystyle a}$ approaches ${\displaystyle \infty }$:

${\displaystyle v_{e}^{2}=GM\left({\frac {2}{r}}-0\right)\rightarrow v_{e}={\sqrt {\frac {2GM}{r}}}}$

Notes

References