boinor.twobody.thrust.change_ecc_inc
====================================

.. py:module:: boinor.twobody.thrust.change_ecc_inc


Functions
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.. autoapisummary::

   boinor.twobody.thrust.change_ecc_inc.change_ecc_inc


Module Contents
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.. py:function:: change_ecc_inc(orb_0, ecc_f, inc_f, f)

   Simultaneous eccentricity and inclination changes. Guidance law from the model. Thrust is aligned with an inertially fixed direction perpendicular to the semimajor axis of the orbit.

   :param orb_0: Initial orbit, containing all the information.
   :type orb_0: Orbit
   :param ecc_f: Final eccentricity.
   :type ecc_f: float
   :param inc_f: Final inclination.
   :type inc_f: ~astropy.units.quantity.Quantity
   :param f: Magnitude of constant acceleration.
   :type f: ~astropy.units.quantity.Quantity

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

   .. rubric:: References

   * Pollard, J. E. "Simplified Analysis of Low-Thrust Orbital Maneuvers", 2000.