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. EitherB
orC_D
,A
andm
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.