orbitx.TLE

class orbitx.TLE(tle_xarray: Dataset)

Class to retrieve satellite TLEs. For more information on Two line elements, see the [Wikipedia page](https://en.wikipedia.org/wiki/Two-line_element_set)

__init__(tle_xarray: Dataset)

Methods

__init__(tle_xarray)
from_filepath(tle_filepath, ...[, ...])	Generates a TLE object from a TLE file.
from_sat_shortname(satellite_shortname, ...)	Generates a TLE object from the satellite shortname

Attributes

argument_perigee	The angle between the ascending node and the orbit's point of closest approach to the earth (perigee).
ballistic_coefficient	Also called the first derivative of mean motion, the ballistic coefficient is the daily rate of change in the number of revs the object completes each day, divided by 2.
classification	classified, S: secret)
creation_date	The date when this object was created
drag_term	Also called the radiation pressure coefficient (or BSTAR), the parameter is another drag term in the SGP4 predictor.
eccentricity	A constant defining the shape of the orbit (0=circular, Less than 1=elliptical).
element_set_number	The element set number is a running count of all 2 line element sets generated by USSPACECOM for this object (in this example, 529).
end_date	The end date for this object, used to filter the TLEs when is was created, represented in numpy datetime64[s]
end_date_seconds_since	The end date for this object, used to filter the TLEs when is was created, represented in seconds since the chosen reference date for this object.
inclination	The angle between the equator and the orbit plane.
launch_number	Number of this launch in the year (how many launches happened this year before this one, plus one)
launch_piece	Index of this object in the launch (in a launch that results in three objects orbiting, the second one is indexed B)
launch_year	Year in which the satellite was launched
mean_anomaly	The angle, measured from perigee, of the satellite location in the orbit referenced to a circular orbit with radius equal to the semi-major axis.
mean_motion	The value is the mean number of orbits per day the object completes.
reference_date	The reference date used to compute the 'seconds since' representation of the TLE dates, represented as a numpy datetime64
reference_date_seconds_since1970
revolution_number	The orbit number at Epoch Time.
right_ascension	The angle between vernal equinox and the point where the orbit crosses the equatorial plane (going north).
satellite_catalog_number	This is the catalog number USSPACECOM has designated for this object.
satellite_name	The name associated with the satellite (e.g., Cryosat-2).
satellite_shortname	The short name associated with the satellite (e.g., CS2).
second_derivative	The second derivative of mean motion is a second order drag term in the Simplified General Perturbations (SGP4) predictor used to model terminal orbit decay.
start_date	The end date for this object, used to filter the TLEs when is was created, represented in numpy datetime64[s]
start_date_seconds_since	The start date for this object, used to filter the TLEs when it was created, represented in seconds since the chosen reference date for this object.
tle_date	Date corresponding to this TLE
tle_date_seconds_since	The list of the dates corresponding to each TLE in this object, in seconds since the chosen reference date of this object.
tle_line_1	The list of all first TLE lines
tle_line_2	The list of all second TLE lines
tle_xarray	The xarray containing the information about all TLE's for this satellite
version	The orbitx version used to create this object