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 --------------------------------------------------------------------------