Orbital eccentricity

From Wikipedia, the free encyclopedia
Jump to: navigation, search
Examples of four orbital trajectories with different eccentricities

In astrodynamics, orbital eccentricity shows how much the shape of an object's orbit is different from a circle.

Eccentricity (e\,\!) is defined for all circular, elliptic, parabolic and hyperbolic orbits. It can take the following values:

Finding eccentricity[change | edit source]

Use this formula:

e_{obj}=\frac {r_a-r_p} {r_a+r_p}, where eobj is the eccentricity, ra is the apoapsis (far point) of the object's orbit, and rp is the periapsis (near point) of the object's orbit. The near and far points are the apsides.