astro.classical_2_equinoctial#

hohmannpy.astro.classical_2_equinoctial(sm_axis, eccentricity, raan, argp, inclination, true_anomaly)#

Converts the classical orbital elements into the modified equinoctial orbital elements.

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.

Returns:

  • 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.

Notes

For a parabolic orbit this function will still run if an infinite semi-major axis is passed in. The resultant semi-latus rectum will be NAN but all other parameters will be correct.

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