boinor.core.propagation.recseries
=================================

.. py:module:: boinor.core.propagation.recseries

.. autoapi-nested-parse::

   module related to propagation of an orbit using the recursive series approximation method in the sub sub-package



Functions
---------

.. autoapisummary::

   boinor.core.propagation.recseries.recseries_coe
   boinor.core.propagation.recseries.recseries


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

.. py:function:: recseries_coe(k, p, ecc, inc, raan, argp, nu, tof, method='rtol', order=8, numiter=100, rtol=1e-08)

   using the recursive series approximation method to propagate an orbit using classical orbital elements


.. py:function:: recseries(k, r0, v0, tof, method='rtol', order=8, numiter=100, rtol=1e-08)

   Kepler solver for elliptical orbits with recursive series approximation
   method. The order of the series is a user defined parameter.

   :param k: Standard gravitational parameter of the attractor.
   :type k: float
   :param r0: Position vector.
   :type r0: numpy.ndarray
   :param v0: Velocity vector.
   :type v0: numpy.ndarray
   :param tof: Time of flight.
   :type tof: float
   :param method: Type of termination method ('rtol','order')
   :type method: str
   :param order: Order of recursion, defaults to 8.
   :type order: int, optional
   :param numiter: Number of iterations, defaults to 100.
   :type numiter: int, optional
   :param rtol: Relative error for accuracy of the method, defaults to 1e-8.
   :type rtol: float, optional

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

   .. rubric:: Notes

   This algorithm uses series discussed in the paper *Recursive solution to
   Kepler’s problem for elliptical orbits - application in robust
   Newton-Raphson and co-planar closest approach estimation*
   with DOI: http://dx.doi.org/10.13140/RG.2.2.18578.58563/1