Path: Orbit/OrbitMechanics
% Approximate root to Kepler's Equation for elliptical and hyperbolic orbits.
Since version 1.
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Form:
eccAnom = M2EApp( e, meanAnom )
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Inputs
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e (: or 1) Eccentricity
meanAnom (:) Mean anomaly
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Outputs
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eccAnom (:) Eccentric anomaly
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References: Battin, R.H. (1987). An Introduction to the
Mathematics and Methods of Astrodynamics, AIAA Press, p. 194.
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Common: Graphics/Plot2D Math: Linear/DupVect
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