astro.state_2_classical

hohmannpy.astro.state_2_classical(position, velocity, grav_param=398600441800000.0)

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

Parameters:

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

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

• grav_param (float) – Gravitational parameter of the central body (defaults to that of the Earth in \(\text{m}^3/\text{s}^2\)).

Returns:

• 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 \(\text{m}^3/\text{s}^2\)).

See also

state_2_classical_p()

Alternate version of this function which returns the semi-latus rectum instead of the semi-major axis. Useful for parabolic orbits where the semi-major axis is infinite.