Path: Orbit/OrbitCoord
% Eccentric longitude from the mean longitude by solving Kepler's equation.
If meanLong is not entered a vector from 0 to 2*pi is used.
Since version 1.
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Form:
eccLong = ML2K( P1, P2, meanLong, tol, nmax )
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Inputs
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P1 e sin(longitude of pericenter)
P2 e cos(longitude of pericenter)
meanLong Mean longitude
tol Tolerance for Newton-Raphson (default 1e-8)
nMax Max number of iterations (default is inf)
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Outputs
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eccLong Eccentric longitude (K)
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References: Battin, R.H., An Introduction to the Methods and Mathematics
of Astrodynamics, AIAA, New York, 1987, p. 493.
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Orbit: OrbitCoord/ML2KApp Common: CommonData/SwooshWatermark Common: General/CellToMat Common: General/MatToCell Common: General/Watermark Common: Graphics/NewFig Common: Graphics/Plot2D Common: Graphics/PltStyle
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