astro.equinoctial_2_state

hohmannpy.astro.equinoctial_2_state(sl_rectum, e_component1, e_component2, n_component1, n_component2, true_latitude, grav_param=398600441800000.0)

Converts the modified equinoctial orbital elements (where true latitude is the fast parameter) into inertial position and velocity.

Parameters:

• sl_rectum (float) – Semi-latus rectum.

• e_component1 (float) – x-component of the eccentricity vector in the planet-centered inertial basis.

• e_component2 (float) – y-component of the eccentricity vector in the planet-centered inertial basis.

• n_component1 (float) – x-component of the nodal vector in the planet-centered inertial basis.

• n_component2 (float) – y-component of the nodal vector in the planet-centered inertial basis.

• true_latitude (float) – True latitude.

• 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.