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Kepler's equation


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An equation that relates the eccentric anomaly of a body in an elliptical orbit to its mean anomaly. The equation is

Ee 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.


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