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# Orbital Eccentricity - gravitational force

## Description

The orbital eccentricity of an astronomical object is a parameter that determines the amount by which its orbit around another body deviates from a perfect circle. A value of 0 is a circular orbit, values between 0 and 1 form an elliptical orbit, 1 is a parabolic escape orbit, and greater than 1 is a hyperbola. The term derives its name from the parameters of conic sections, as every Kepler orbit is a conic section. It is normally used for the isolated two-body problem, but extensions exist for objects following a rosette orbit through the galaxy.
In a two-body problem with inverse-square-law force, every orbit is a Kepler orbit. The eccentricity of this Kepler orbit is a non-negative number that defines its shape.

The eccentricity may take the following values:
-circular orbit: e=0
-elliptic orbit: 0<e<1 (see Ellipse)
-parabolic trajectory: e=1 (see Parabola)
-hyperbolic trajectory: e>1 (see Hyperbola)

In the case of a gravitational force, the formula is as shown here.

Related formulas

## Variables

 e orbital eccentricity (dimensionless) ϵ specific orbital energy (J/kg) h specific relative angular momentum (angular momentum divided by the reduced mass) (m2/s) μ standard gravitational parameter (m3*s-2)