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24 Jan 2005 (Updated )

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

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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).


This file inspired Solve Kepler's Equation For E.

MATLAB release MATLAB 6.5 (R13)
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Comments and Ratings (3)
23 Mar 2010 Toto

Toto (view profile)

Very good work

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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 2005 ion seteanu

excellent product useful for engineering work

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