astro.classical_2_state#

hohmannpy.astro.classical_2_state(sm_axis, eccentricity, raan, argp, inclination, true_anomaly, grav_param=398600441800000.0)#

Converts the classical orbital elements (where true anomaly is the fast parameter) into inertial position and velocity.

Parameters:

sm_axis (float) – Semi-major axis.
eccentricity (float) – Eccentricity.
raan (float) – Right ascension (longitude) of the ascending node.
argp (float) – Argument of periapsis.
inclination (float) – Inclination.
true_anomaly (float) – True anomaly.
grav_param (float) – Gravitational parameter of the central body (defaults to that of the Earth in \(\text{m}^3/\text{s}^2\)).

Returns:

position (np.ndarray) – Position of the satellite in planet-centered inertial coordinates.
velocity (np.ndarray) – Velocity of the satellite in planet-centered inertial coordinates.