boinor.core.propagation.markley
===============================

.. py:module:: boinor.core.propagation.markley

.. autoapi-nested-parse::

   module related to propagation of an orbit using Markley's method in the core sub-package



Functions
---------

.. autoapisummary::

   boinor.core.propagation.markley.markley_coe
   boinor.core.propagation.markley.markley


Module Contents
---------------

.. py:function:: markley_coe(k, p, ecc, inc, raan, argp, nu, tof)

   actual calculation of propagation of an orbit using Markley's method


.. py:function:: markley(k, r0, v0, tof)

   Solves the kepler problem by a non-iterative method. Relative error is
   around 1e-18, only limited by machine double-precision errors.

   :param k: Standar Gravitational parameter.
   :type k: float
   :param r0: Initial position vector wrt attractor center.
   :type r0: numpy.ndarray
   :param v0: Initial velocity vector.
   :type v0: numpy.ndarray
   :param tof: Time of flight.
   :type tof: float

   :returns: * **rr** (*numpy.ndarray*) -- Final position vector.
             * **vv** (*numpy.ndarray*) -- Final velocity vector.

   .. rubric:: Notes

   The following algorithm was taken from http://dx.doi.org/10.1007/BF00691917.