Publisher review:CalcE.m calculates eccentric anomaly given mean anomaly and eccentricity of an elliptical orbit. Since the eccentric anomaly cannot be directly calculated from certain given values, this function performs a simple Newton-Raphson iteration to solve for the eccentric anomaly within a given tolerance (default 10^-8 radians). Requirements: ยท MATLAB Release: R13
CalcE.m is a Matlab script for Astronomy/Aerospace scripts design by Richard Rieber.
It runs on following operating system: Windows / Linux / BSD / Solaris.
CalcE.m calculates eccentric anomaly given mean anomaly and eccentricity of an elliptical orbit.
Operating system:Windows / Linux / BSD / Solaris