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Solve Kepler's Equation for E

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23 Oct 2006 (Updated )

Calculates Eccentric Anomaly given Mean Anomaly

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Description

Given mean anomaly and eccentricity of an orbit, eccentric anomaly can be calculated using Kepler's Equation. However, the equation is nonlinear, and an iterative technique must be used. This program uses a fixed-point iterative technique to output eccentric anomaly to a user defined tolerance, or to a default tolerance of 10^-9 radians.

Acknowledgements

Calc E.M inspired this file.

MATLAB release MATLAB 7.2 (R2006a)
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Comments and Ratings (5)
08 Nov 2012 Sherif

nice

18 Feb 2009 Rody Oldenhuis

fixed point iteration only works for small eccentricities (e< 0.4 or so), and hyperbolic equation is totally missing.

10 Oct 2007 Christian Panganiban  
29 Dec 2006 Jessica Grauss

Poor documentation and accuray is lower than most other programs

12 Dec 2006 Richard Rieber

CalcE.m is a more efficient method of solving Kepler's equation. (slightly more efficient)

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