SGP4.propagate

SGP4.propagate

SGP4.propagate(t, state0, epoch=None, **kwargs)[source]

Propagate a state

#TODO: UPDATE THIS DOCSTRING

All state-vector are given in SI units.

Keyword arguments contain only information needed for ballistic coefficient B used by SGP4. Either B or C_D, A and m must be supplied. They also contain a option to give angles in radians or degrees. By default input is assumed to be degrees.

Frame:

The input frame is ECI (TEME) for orbital elements and Cartesian. The output frame is as standard ECEF (ITRF). But can be set to TEME.

Parameters

  • t (float/list/numpy.ndarray/astropy.time.TimeDelta) – Time to propagate relative the initial state epoch.

  • epoch (float/astropy.time.Time) – The epoch of the initial state.

  • state0 (numpy.ndarray) – 6-D Cartesian state vector in SI-units.

  • B (float) – Ballistic coefficient

  • C_D (float) – Drag coefficient

  • A (float) – Cross-sectional Area

  • m (float) – Mass

  • radians (bool) – If true, all angles are assumed to be in radians.

  • SGP4_mean_elements (bool) – If True, the input is not cartesian state but SGP4 mean elements.

Returns

6-D Cartesian state vectors in SI-units.