In the study of orbital dynamics the mean anomaly is a measure of time, specific to the orbiting body p, which is a multiple of 2π radians at and only at periapsis. It is the fraction of the orbital period that has elapsed since the last passage at periapsis z, expressed as an angle. In the diagram below, it is M (the angle z-c-y).

The point y is defined such that the circular sector area z-c-y is equal to the elliptic sector area z-s-p, scaled up by the ratio of the major to minor axes of the ellipse.

Calculation

In astrodynamics mean anomaly <math>M\,\!<math> can be calculated as follows:

<math>M=E - e \cdot \sin E\,\!<math>

where:

• <math>E\,\!<math> is orbit's eccentric anomaly,
• <math>e\,\!<math> is orbit's eccentricity.

See also

• Kepler's laws of planetary motion
• Eccentric anomaly
• True anomaly

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