pymgp.satorb.keplerm#

pymgp.satorb.keplerm(M, ecc, TOL=1e-10)[source]#

Compute eccentric and true anomaly from mean anomaly solving Kepler’s eqn.

Parameters:

Marray_like: Mean anomaly (radians)
eccarray_like: Eccentricity (unity)
tolfloat, default 1e-10: Stop criterion for iterations

Returns:

Earray_like: Eccentric anomaly (radians)
nuarray_like: True anomaly (radians)

See also

kepler, keplernu

Notes

Kepler’s equation M=E-ecc*sin(E) is solved iteratively using Newton’s method.

This routine should only be used for elliptical orbits. Parabolic and hyperbolic orbits are not supported and give false results (this is nowhere checked for).