Path: Orbit/OrbitMechanics
% Eccentric anomaly for a hyperbola. Computed from the mean anomaly and the eccentricity. This uses Kepler's method to iterate on the solution For a demo plot use M2EHy( e ). -------------------------------------------------------------------------- Form: eccAnom = M2EHy( e, meanAnom, tol, nMax ) -------------------------------------------------------------------------- ------ Inputs ------ e (1,:) Eccentricity meanAnom (1,:) Mean anomaly tol (1,1) Tolerance nMax (1,1) Maximum number of iterations ------- Outputs ------- eccAnom (1,:) Eccentric anomaly --------------------------------------------------------------------------
Common: Graphics/Plot2D
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