KEPLER'S EQUATION



 

Kepler's Equation is a deceptively simple equation that relates an orbit's Mean Anomaly (M) with its Eccentric Anomaly (E):

M(t) = E(t) - esinE(t)

where: M(t) = The Mean Anomaly at time t;
            E(t) = The
Eccentric Anomaly (E) at time t; and
                e = The
satellite orbit's Eccentricity.

 

Kepler's Equation is transcendental and therefore cannot be analytically solved for E(t). Instead, computers can be used to find the best value of E(t) that satisfies the equation for the known values of M(t) and e.

Once E(t) is determined, the True Anomaly, n(t), can be determined.




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Kepler's Equation Was Last Modified On May 23, 2010