orbitx.utils._orbit.propagate_orbit.propagate_orbit

orbitx.utils._orbit.propagate_orbit.propagate_orbit(tle_line1: str, tle_line2: str, start_date: datetime64, end_date: datetime64, propagation_sampling_interval: timedelta64, reference_date: datetime64 = np.datetime64('1970-01-01T00:00:00')) → Tuple[ndarray[tuple[Any, ...], dtype[float64]], ndarray[tuple[Any, ...], dtype[datetime64]], ndarray[tuple[Any, ...], dtype[float64]], ndarray[tuple[Any, ...], dtype[float64]], ndarray[tuple[Any, ...], dtype[float64]], ndarray[tuple[Any, ...], dtype[float64]], ndarray[tuple[Any, ...], dtype[float64]]]

Propagate satellite orbit for given two-line-elements and associated time

Parameters:

• tle_line1 (str) – first line of the reference two-line-element

• tle_line2 (str) – second line of the reference two-line-element

• start_date (np.datetime64) – start time of orbit propagation

• end_date (np.datetime64) – end time of orbit propagation

• propagation_sampling_interval (np.timedelta64) – sampling interval in seconds

• reference_date (np.datetime64, optional) – The reference date used to represent time in seconds since. Defaults to np.datetime64(“1970-01-01T00:00:00”).

Returns:

Tuple containing the date in seconds from 1970, the date in datetime, orbit latitude, longitude, altitude, elevation angle, and azimuth angle

Return type:

Tuple[ npt.NDArray[np.float64], npt.NDArray[np.datetime64], npt.NDArray[np.float64], npt.NDArray[np.float64], npt.NDArray[np.float64], npt.NDArray[np.float64], npt.NDArray[np.float64], ]