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4.0 | 1 rating Rate this file 11 Downloads (last 30 days) File Size: 1.4 KB File ID: #6779

CalcE.m

24 Jan 2005 (Updated 26 Jan 2005)

Calculates eccentric anomaly given mean anomaly and eccentricity of an elliptical orbit.

File Information
Description	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).
Acknowledgements	This submission has inspired the following: Solve Kepler's Equation for E
MATLAB release	MATLAB 6.5 (R13)

Tags for This File
Everyone's Tags	aerodef, aeronautics, aerospace, anomaly, eccentric, eccentricity, ellipse, elliptical, orbit
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Comments and Ratings (3)
23 Mar 2005	ion seteanu	excellent product useful for engineering work
16 Dec 2005	Ben Asbury	I was using the fzero function to solve Keplar's Equation and noticed lots of error. So I tried this and it resulted in a more accurate solution
23 Mar 2010	Toto	Very good work

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Updates
26 Jan 2005	Didn't notice that MatLab already had a function entitled calce.m, so the file has been renamed to CalcEA.m.