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.
--------------------------------------------------------------------------
Form:
eccLong = ML2K( P1, P2, meanLong, tol, nmax )
--------------------------------------------------------------------------
------
Inputs
------
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)
-------
Outputs
-------
eccLong Eccentric longitude (K)
--------------------------------------------------------------------------
References: Battin, R.H., An Introduction to the Methods and Mathematics
of Astrodynamics, AIAA, New York, 1987, p. 493.
--------------------------------------------------------------------------
Orbit: OrbitCoord/ML2KApp Common: Graphics/Plot2D
Back to the Orbit Module page