Path: Orbit/OrbitMechanics
% Converts true anomaly to mean anomaly. -------------------------------------------------------------------------- Form: [meanAnom,eccAnom] = Nu2M( e, nu ) -------------------------------------------------------------------------- ------ Inputs ------ e (1,1) Eccentricity nu (1,:) True anomaly ------- Outputs ------- meanAnom (1,:) Mean anomaly eccAnom (1,:) Eccentric anomaly --------------------------------------------------------------------------
Orbit: OrbitMechanics/E2M Orbit: OrbitMechanics/Nu2E Common: Graphics/Plot2D
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