boinor.twobody.thrust.change_argp
=================================

.. py:module:: boinor.twobody.thrust.change_argp

.. autoapi-nested-parse::

   Argument of perigee change, with formulas developed by Pollard.

   .. rubric:: References

   * Pollard, J. E. "Simplified Approach for Assessment of Low-Thrust
     Elliptical Orbit Transfers", 1997.
   * Pollard, J. E. "Evaluation of Low-Thrust Orbital Maneuvers", 1998.



Functions
---------

.. autoapisummary::

   boinor.twobody.thrust.change_argp.change_argp


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

.. py:function:: change_argp(k, a, ecc, argp_0, argp_f, f)

   Change argument of perigee, with formulas developed by Pollard.
   Guidance law from the model.
   Thrust is aligned with an inertially fixed direction perpendicular to the
   semimajor axis of the orbit.

   :param k: Gravitational parameter (km**3 / s**2)
   :type k: ~astropy.units.quantity.Quantity
   :param a: Semi-major axis (km)
   :type a: ~astropy.units.quantity.Quantity
   :param ecc: Eccentricity
   :type ecc: float
   :param argp_0: Initial argument of periapsis (rad)
   :type argp_0: ~astropy.units.quantity.Quantity
   :param argp_f: Final argument of periapsis (rad)
   :type argp_f: ~astropy.units.quantity.Quantity
   :param f: Magnitude of constant acceleration (km / s**2)
   :type f: ~astropy.units.quantity.Quantity

   :returns: **a_d, delta_V, t_f**
   :rtype: tuple (function, ~astropy.units.quantity.Quantity, ~astropy.time.Time)