ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE¶

class TLE(*args, **kwargs)¶

Bases: pybind11_object

A Two-Line Element set (TLE).

A TLE is a data format encoding a list of orbital elements of an Earth-orbiting object for a given point in time

Reference:: https://en.wikipedia.org/wiki/Two-line_element_set

Overloaded function.

__init__(self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE, first_line: ostk.core.type.String, second_line: ostk.core.type.String) -> None

Constructor.

Args:
first_line (str): The first line of the TLE. second_line (str): The second line of the TLE.
__init__(self: ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE, satellite_name: ostk.core.type.String, first_line: ostk.core.type.String, second_line: ostk.core.type.String) -> None

Constructor.

Args:
satellite_name (str): The name of the satellite. first_line (str): The first line of the TLE. second_line (str): The second line of the TLE.

Methods

`can_parse`	Check if a TLE can be parsed from two strings.
`construct`	Overloaded function.
`generate_checksum`	Generate the checksum of a string.
`get_aop`	Get the argument of perigee.
`get_b_star_drag_term`	Get the B* drag term.
`get_classification`	Get the classification.
`get_eccentricity`	Get the eccentricity.
`get_element_set_number`	Get the element set number.
`get_ephemeris_type`	Get the ephemeris type.
`get_epoch`	Get the epoch.
`get_first_line`	Get the first line of the TLE.
`get_first_line_checksum`	Get the checksum of the first line.
`get_inclination`	Get the inclination.
`get_international_designator`	Get the international designator.
`get_mean_anomaly`	Get the mean anomaly.
`get_mean_motion`	Get the mean motion.
`get_mean_motion_first_time_derivative_divided_by_two`	Get the mean motion first time derivative divided by two.
`get_mean_motion_second_time_derivative_divided_by_six`	Get the mean motion second time derivative divided by six.
`get_raan`	Get the right ascension of the ascending node.
`get_revolution_number_at_epoch`	Get the revolution number at epoch.
`get_satellite_name`	Get the name of the satellite.
`get_satellite_number`	Get the satellite number.
`get_second_line`	Get the second line of the TLE.
`get_second_line_checksum`	Get the checksum of the second line.
`is_defined`	Check if the TLE object is defined.
`load`	Load a TLE from a file.
`parse`	Parse a TLE from a string.
`set_epoch`	Set the epoch.
`set_revolution_number_at_epoch`	Set the revolution number at epoch.
`set_satellite_number`	Set the satellite number.
`undefined`	Create an undefined TLE object.

static can_parse( first_line: ostk.core.type.String, second_line: ostk.core.type.String, ) → bool¶

Check if a TLE can be parsed from two strings.

Parameters:

first_line (str) -- The first line of the TLE.
second_line (str) -- The second line of the TLE.

Returns:

True if the TLE can be parsed, False otherwise.

Return type:

bool

static construct(*args, **kwargs)¶

Overloaded function.

construct(satellite_name: ostk.core.type.String, satellite_number: ostk.core.type.Integer, classification: ostk.core.type.String, international_designator: ostk.core.type.String, epoch: ostk.physics.time.Instant, mean_motion_first_time_derivative_divided_by_two: ostk.core.type.Real, mean_motion_second_time_derivative_divided_by_six: ostk.core.type.Real, b_star_drag_term: ostk.core.type.Real, ephemeris_type: ostk.core.type.Integer, element_set_number: ostk.core.type.Integer, inclination: ostk.physics.unit.Angle, raan: ostk.physics.unit.Angle, eccentricity: ostk.core.type.Real, aop: ostk.physics.unit.Angle, mean_anomaly: ostk.physics.unit.Angle, mean_motion: ostk.physics.unit.Derived, revolution_number_at_epoch: ostk.core.type.Integer) -> ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

Construct a TLE.

Args:
satellite_name (str): The name of the satellite. satellite_number (int): The satellite number. classification (str): The classification. international_designator (str): The international designator. epoch (Instant): The epoch. mean_motion_first_time_derivative_divided_by_two (float): The mean motion first time derivative divided by two. mean_motion_second_time_derivative_divided_by_six (float): The mean motion second time derivative divided by six. b_star_drag_term (float): The B* drag term. ephemeris_type (int): The ephemeris type. element_set_number (int): The element set number. inclination (Angle): The inclination. raan (Angle): The right ascension of the ascending node. eccentricity (float): The eccentricity. aop (Angle): The argument of perigee. mean_anomaly (Angle): The mean anomaly. mean_motion (float): The mean motion. revolution_number_at_epoch (int): The revolution number at epoch.

Returns:
TLE: The constructed TLE.
construct(satellite_number: ostk.core.type.Integer, classification: ostk.core.type.String, international_designator: ostk.core.type.String, epoch: ostk.physics.time.Instant, mean_motion_first_time_derivative_divided_by_two: ostk.core.type.Real, mean_motion_second_time_derivative_divided_by_six: ostk.core.type.Real, b_star_drag_term: ostk.core.type.Real, ephemeris_type: ostk.core.type.Integer, element_set_number: ostk.core.type.Integer, inclination: ostk.physics.unit.Angle, raan: ostk.physics.unit.Angle, eccentricity: ostk.core.type.Real, aop: ostk.physics.unit.Angle, mean_anomaly: ostk.physics.unit.Angle, mean_motion: ostk.physics.unit.Derived, revolution_number_at_epoch: ostk.core.type.Integer) -> ostk.astrodynamics.trajectory.orbit.model.sgp4.TLE

Construct a TLE.

Args:
satellite_number (int): The satellite number. classification (str): The classification. international_designator (str): The international designator. epoch (Instant): The epoch. mean_motion_first_time_derivative_divided_by_two (float): The mean motion first time derivative divided by two. mean_motion_second_time_derivative_divided_by_six (float): The mean motion second time derivative divided by six. b_star_drag_term (float): The B* drag term. ephemeris_type (int): The ephemeris type. element_set_number (int): The element set number. inclination (Angle): The inclination. raan (Angle): The right ascension of the ascending node. eccentricity (float): The eccentricity. aop (Angle): The argument of perigee. mean_anomaly (Angle): The mean anomaly. mean_motion (float): The mean motion. revolution_number_at_epoch (int): The revolution number at epoch.

Returns:
TLE: The constructed TLE.