Path: Orbit/OrbitMechanics
% Computes the eccentric anomaly from the mean anomaly and the eccentricity. -------------------------------------------------------------------------- Form: eccAnom = M2E( e, meanAnom, tol, nMax ) -------------------------------------------------------------------------- ------ Inputs ------ e (1,:) Eccentricity meanAnom (1,:) Mean anomaly (rad) tol (1,1) Tolerance nMax (1,1) Maximum number of iterations ------- Outputs ------- eccAnom (1,:) Eccentric anomaly (rad) --------------------------------------------------------------------------