An equation that relates the eccentric anomaly of a body in an elliptical orbit to its mean anomaly. The equation is
E − e sinE = M,
where E is the eccentric anomaly, M the mean anomaly, and e the eccentricity of the orbit. It is important as one of the mathematical relations enabling the position of a planet about the Sun, or a satellite about its planet, to be calculated from the orbital elements for any time.
Subjects: Astronomy and Astrophysics.