Path: Orbit/OrbitMechanics
% Computes the true anomaly from the mean anomaly without wrapping. Between -pi / pi -------------------------------------------------------------------------- Form: nu = M2NuAbs( e, M, tol, nMax ) -------------------------------------------------------------------------- ------ Inputs ------ e Eccentricity M Mean anomaly (rad) tol Tolerance (optional) nMax Maximum number of iterations (optional) ------- Outputs ------- nu True anomaly (rad) --------------------------------------------------------------------------
Orbit: OrbitMechanics/M2Nu
Back to the Orbit Module page