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SUPPORT SITE |
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Path: SC/BasicOrbit
% Converts eccentric anomaly to mean anomaly. -------------------------------------------------------------------------- Form: meanAnom = E2M( ecc, eccAnom ) -------------------------------------------------------------------------- ------ Inputs ------ ecc (1,:) Eccentricity eccAnom (1,:) Eccentric anomaly ------- Outputs ------- meanAnom (1,:) Mean anomaly -------------------------------------------------------------------------- References: Bate, R. R. Fundamentals of Astrodynamics. pp. 185-187. --------------------------------------------------------------------------
Common: Graphics/Plot2D Math: Linear/DupVect
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