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Kepler's Equation

version 1.0.0.0 (291 KB) by David Eagle
A suite of MATLAB functions for solving Kepler's equation.

6 Downloads

Updated 12 Nov 2012

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Four MATLAB functions for solving Kepler's equation using Danby's method, Danby's method with Mikkola's initial guess, Stumpff functions, Gooding's two iteration method, and heliocentric parabolic and near-parabolic orbitsusing a modified Barker algorithm.

Comments and Ratings (3)

BlueEyes

Test of kepler3 related to an highly extremized orbit (eccentricity close to unit, namely 0.9999)
----------
>> format long g
>> [eanom] = kepler3 (6.28, 0.9999)
eanom = 6.01624579599393
>>
----------
Confirmation comes from here: http://astrodinamica.altervista.org/abstract/duncan.htm
where the 20-digit precision of a program written in Bash (bc library) is used.
----- kepelliptic.sh ----------
Enter Orbit Eccentricity e [interval 0,1; input 0.9999]: 0.9999
Enter Mean Anomaly M [ >0, in radians, input 6.28]: 6.28
-24.03222116834530089817
33.02180806953306726007
8.15159496160507614216
7.44354946962703746597
7.03310249968481243444
6.76629275343311319883
6.57590219830378155372
6.40287748113928231867
5.92274143819527543051
5.99428747155899498330
6.01463320196906619567
6.01623621653209031046
6.01624579565316377384
6.01624579599391258536
6.01624579599391258592
Computed Eccentric Anomaly E= 6.01624579599391258592 rad

Good!

HENRY XSCC

sun Chong

MATLAB Release Compatibility
Created with R2011a
Compatible with any release
Platform Compatibility
Windows macOS Linux

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