astro.conversions

A set of conversions used to move between different methods of parameterizing and determining an orbit.

classical_2_state	Converts the classical orbital elements (where true anomaly is the fast parameter) into inertial position and velocity.
classical_2_state_p	Parabolic version of classical_2_state() which takes in the semi-latus rectum instead of the semi-major axis.
state_2_classical	Converts inertial position and velocity into the classical orbital elements (where true anomaly is the fast parameter).
state_2_classical_p	Parabolic version of state_2_classical() which takes in the semi-latus rectum instead of the semi-major axis.
equinoctial_2_state	Converts the modified equinoctial orbital elements (where true latitude is the fast parameter) into inertial position and velocity.
classical_2_equinoctial	Converts the classical orbital elements into the modified equinoctial orbital elements.
equinoctial_2_classical	Converts the modified equinoctial orbital elements to the classical orbital elements.