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Full Version: solving Kepler's equation using Danby's method
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This HP Prime program demonstrates how to solve Kepler's equation for elliptical and hyperbolic orbits using Professor Danby's numerical method.

Here is the output from this program.


mean anomaly = 79.4849999996 degrees

eccentricity = 1.735

true anomaly = 91.4538050798 degrees

The attached zip file also includes a PDF document which provides additional information about the implementation.
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