SpaceObject.get_state

SpaceObject.get_state

SpaceObject.get_state(t)

Gets ECEF state at specified times using propagator instance.

Parameters

t (int/float/list/numpy.ndarray/astropy.time.Time/astropy.time.TimeDelta) – Time relative epoch in seconds.

Returns

Array of state (position and velocity) as a function of time.

Return type

numpy.ndarray of size (6,len(t))