Library API

This section provides detailed information about all the classes, functions, and modules available in the ASTRA-RL toolbox. Each entry includes a description of its purpose, parameters, and usage examples.

This documentation is generated automatically from the codebase using docstrings and comments, ensuring that it stays up-to-date with the latest changes.

brahe

Brahe - Satellite Dynamics and Astrodynamics Library

A high-performance library for orbital mechanics, time systems, coordinate transformations, and attitude representations. Brahe provides both Rust and Python interfaces for satellite dynamics computations.

The library is organized into submodules that mirror the Rust core structure: - time: Time systems, epochs, and conversions - orbits: Orbital mechanics, propagators, and TLE handling - coordinates: Coordinate system transformations - frames: Reference frame transformations (ECI/ECEF) - eop: Earth Orientation Parameters - attitude: Attitude representations (quaternions, Euler angles, etc.) - trajectories: Trajectory containers and interpolation

All functionality is re-exported at the top level for convenience, so you can use either: from brahe import Epoch from brahe.time import Epoch

AS2RAD module-attribute

AS2RAD = 4.84813681109536e-06

Convert a string or number to a floating-point number, if possible.

AU module-attribute

AU = 149597870700.0

Convert a string or number to a floating-point number, if possible.

C_LIGHT module-attribute

C_LIGHT = 299792458.0

Convert a string or number to a floating-point number, if possible.

DEG2RAD module-attribute

DEG2RAD = 0.017453292519943295

Convert a string or number to a floating-point number, if possible.

ECC_EARTH module-attribute

ECC_EARTH = 0.081819190842622

Convert a string or number to a floating-point number, if possible.

GM_EARTH module-attribute

GM_EARTH = 398600441500000.0

Convert a string or number to a floating-point number, if possible.

GM_JUPITER module-attribute

GM_JUPITER = 1.267127648e+17

Convert a string or number to a floating-point number, if possible.

GM_MARS module-attribute

GM_MARS = 42828375210000.0

Convert a string or number to a floating-point number, if possible.

GM_MERCURY module-attribute

GM_MERCURY = 22031780000000.0

Convert a string or number to a floating-point number, if possible.

GM_MOON module-attribute

GM_MOON = 4902800066000.0

Convert a string or number to a floating-point number, if possible.

GM_NEPTUNE module-attribute

GM_NEPTUNE = 6836527100580000.0

Convert a string or number to a floating-point number, if possible.

GM_PLUTO module-attribute

GM_PLUTO = 977000000000.0

Convert a string or number to a floating-point number, if possible.

GM_SATURN module-attribute

GM_SATURN = 3.79405852e+16

Convert a string or number to a floating-point number, if possible.

GM_SUN module-attribute

GM_SUN = 1.327124400419394e+20

Convert a string or number to a floating-point number, if possible.

GM_URANUS module-attribute

GM_URANUS = 5794548600000000.0

Convert a string or number to a floating-point number, if possible.

GM_VENUS module-attribute

GM_VENUS = 324858592000000.0

Convert a string or number to a floating-point number, if possible.

GPS module-attribute

GPS = TimeSystem.GPS

Enumeration of supported time systems.

Time systems define different conventions for measuring and representing time. Each system has specific uses in astrodynamics and timekeeping applications.

GPS_TAI module-attribute

GPS_TAI = -19.0

Convert a string or number to a floating-point number, if possible.

GPS_TT module-attribute

GPS_TT = -51.184

Convert a string or number to a floating-point number, if possible.

GPS_ZERO module-attribute

GPS_ZERO = 44244.0

Convert a string or number to a floating-point number, if possible.

J2_EARTH module-attribute

J2_EARTH = 0.0010826358191967

Convert a string or number to a floating-point number, if possible.

MJD2000 module-attribute

MJD2000 = 51544.5

Convert a string or number to a floating-point number, if possible.

MJD_ZERO module-attribute

MJD_ZERO = 2400000.5

Convert a string or number to a floating-point number, if possible.

OMEGA_EARTH module-attribute

OMEGA_EARTH = 7.292115146706979e-05

Convert a string or number to a floating-point number, if possible.

P_SUN module-attribute

P_SUN = 4.56e-06

Convert a string or number to a floating-point number, if possible.

RAD2AS module-attribute

RAD2AS = 206264.80624709636

Convert a string or number to a floating-point number, if possible.

RAD2DEG module-attribute

RAD2DEG = 57.29577951308232

Convert a string or number to a floating-point number, if possible.

R_EARTH module-attribute

R_EARTH = 6378136.3

Convert a string or number to a floating-point number, if possible.

R_MOON module-attribute

R_MOON = 1738000.0

Convert a string or number to a floating-point number, if possible.

R_SUN module-attribute

R_SUN = 695700000.0

Convert a string or number to a floating-point number, if possible.

TAI module-attribute

TAI = TimeSystem.TAI

Enumeration of supported time systems.

Time systems define different conventions for measuring and representing time. Each system has specific uses in astrodynamics and timekeeping applications.

TAI_GPS module-attribute

TAI_GPS = 19.0

Convert a string or number to a floating-point number, if possible.

TAI_TT module-attribute

TAI_TT = -32.184

Convert a string or number to a floating-point number, if possible.

TT module-attribute

TT = TimeSystem.TT

Enumeration of supported time systems.

Time systems define different conventions for measuring and representing time. Each system has specific uses in astrodynamics and timekeeping applications.

TT_GPS module-attribute

TT_GPS = 51.184

Convert a string or number to a floating-point number, if possible.

TT_TAI module-attribute

TT_TAI = 32.184

Convert a string or number to a floating-point number, if possible.

UT1 module-attribute

UT1 = TimeSystem.UT1

Enumeration of supported time systems.

Time systems define different conventions for measuring and representing time. Each system has specific uses in astrodynamics and timekeeping applications.

UTC module-attribute

UTC = TimeSystem.UTC

Enumeration of supported time systems.

Time systems define different conventions for measuring and representing time. Each system has specific uses in astrodynamics and timekeeping applications.

WGS84_A module-attribute

WGS84_A = 6378137.0

Convert a string or number to a floating-point number, if possible.

WGS84_F module-attribute

WGS84_F = 0.0033528106647474805

Convert a string or number to a floating-point number, if possible.

anomaly_eccentric_to_mean builtin

anomaly_eccentric_to_mean(anm_ecc: float, e: float, angle_format: AngleFormat) -> float

Converts eccentric anomaly into mean anomaly.

Parameters:

Name	Type	Description	Default
anm_ecc	float	Eccentric anomaly in radians or degrees.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required
angle_format	AngleFormat	Interprets input and returns output in AngleFormat.DEGREES or AngleFormat.RADIANS.	required

Returns:

Name	Type	Description
float	float	Mean anomaly in radians or degrees.

anomaly_eccentric_to_true builtin

anomaly_eccentric_to_true(anm_ecc: float, e: float, angle_format: AngleFormat) -> float

Converts eccentric anomaly into true anomaly.

Parameters:

Name	Type	Description	Default
anm_ecc	float	Eccentric anomaly in radians or degrees.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required
angle_format	AngleFormat	Interprets input and returns output in AngleFormat.DEGREES or AngleFormat.RADIANS.	required

Returns:

Name	Type	Description
float	float	True anomaly in radians or degrees.

anomaly_mean_to_eccentric builtin

anomaly_mean_to_eccentric(anm_mean: float, e: float, angle_format: AngleFormat) -> float

Converts mean anomaly into eccentric anomaly.

Parameters:

Name	Type	Description	Default
anm_mean	float	Mean anomaly in radians or degrees.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required
angle_format	AngleFormat	Interprets input and returns output in AngleFormat.DEGREES or AngleFormat.RADIANS.	required

Returns:

Name	Type	Description
float	float	Eccentric anomaly in radians or degrees.

anomaly_mean_to_true builtin

anomaly_mean_to_true(anm_mean: float, e: float, angle_format: AngleFormat) -> float

Converts mean anomaly into true anomaly.

Parameters:

Name	Type	Description	Default
anm_mean	float	Mean anomaly in radians or degrees.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required
angle_format	AngleFormat	Interprets input and returns output in AngleFormat.DEGREES or AngleFormat.RADIANS.	required

Returns:

Name	Type	Description
float	float	True anomaly in radians or degrees.

anomaly_true_to_eccentric builtin

anomaly_true_to_eccentric(anm_true: float, e: float, angle_format: AngleFormat) -> float

Converts true anomaly into eccentric anomaly.

Parameters:

Name	Type	Description	Default
anm_true	float	True anomaly in radians or degrees.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required
angle_format	AngleFormat	Interprets input and returns output in AngleFormat.DEGREES or AngleFormat.RADIANS.	required

Returns:

Name	Type	Description
float	float	Eccentric anomaly in radians or degrees.

anomaly_true_to_mean builtin

anomaly_true_to_mean(anm_true: float, e: float, angle_format: AngleFormat) -> float

Converts true anomaly into mean anomaly.

Parameters:

Name	Type	Description	Default
anm_true	float	True anomaly in radians or degrees.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required
angle_format	AngleFormat	Interprets input and returns output in AngleFormat.DEGREES or AngleFormat.RADIANS.	required

Returns:

Name	Type	Description
float	float	Mean anomaly in radians or degrees.

apoapsis_distance builtin

apoapsis_distance(a: float, e: float) -> float

Calculate the distance of an object at its apoapsis.

Parameters:

Name	Type	Description	Default
a	float	The semi-major axis of the astronomical object in meters.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required

Returns:

Name	Type	Description
float	float	The distance of the object at apoapsis in meters.

apoapsis_velocity builtin

apoapsis_velocity(a: float, e: float, gm: float) -> float

Computes the apoapsis velocity of an astronomical object around a general body.

Parameters:

Name	Type	Description	Default
a	float	The semi-major axis of the astronomical object in meters.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required
gm	float	The standard gravitational parameter of primary body in m³/s².	required

Returns:

Name	Type	Description
float	float	The magnitude of velocity of the object at apoapsis in m/s.

apogee_velocity builtin

apogee_velocity(a: float, e: float) -> float

Computes the apogee velocity of an astronomical object around Earth.

Parameters:

Name	Type	Description	Default
a	float	The semi-major axis of the astronomical object in meters.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required

Returns:

Name	Type	Description
float	float	The magnitude of velocity of the object at apogee in m/s.

bias_precession_nutation builtin

bias_precession_nutation(epc: Epoch) -> np.ndarray

Computes the Bias-Precession-Nutation matrix transforming the GCRS to the CIRS intermediate reference frame. This transformation corrects for the bias, precession, and nutation of Celestial Intermediate Origin (CIO) with respect to inertial space.

This formulation computes the Bias-Precession-Nutation correction matrix according using a CIO based model using using the IAU 2006 precession and IAU 2000A nutation models.

The function will utilize the global Earth orientation and loaded data to apply corrections to the Celestial Intermediate Pole (CIP) derived from empirical observations.

Parameters:

Name	Type	Description	Default
epc	Epoch	Epoch instant for computation of transformation matrix	required

Returns:

Type	Description
ndarray	3x3 rotation matrix transforming GCRS -> CIRS

References

IAU SOFA Tools For Earth Attitude, Example 5.5 http://www.iausofa.org/2021_0512_C/sofa/sofa_pn_c.pdf Software Version 18, 2021-04-18

calculate_tle_line_checksum builtin

calculate_tle_line_checksum(line: str) -> int

Calculate TLE line checksum.

Parameters:

Name	Type	Description	Default
line	str	TLE line.	required

Returns:

Name	Type	Description
int	int	Checksum value.

create_tle_lines builtin

create_tle_lines(epoch: Epoch, inclination: float, raan: float, eccentricity: float, arg_perigee: float, mean_anomaly: float, mean_motion: float, norad_id: str, ephemeris_type: int, element_set_number: int, revolution_number: int, classification=None, intl_designator=None, first_derivative=None, second_derivative=None, bstar=None) -> tuple

Create complete TLE lines from all parameters.

Creates Two-Line Element (TLE) lines from complete set of orbital and administrative parameters. Provides full control over all TLE fields including derivatives and drag terms.

Parameters:

Name	Type	Description	Default
epoch	Epoch	Epoch of the elements.	required
inclination	float	Inclination in degrees.	required
raan	float	Right ascension of ascending node in degrees.	required
eccentricity	float	Eccentricity (dimensionless).	required
arg_perigee	float	Argument of periapsis in degrees.	required
mean_anomaly	float	Mean anomaly in degrees.	required
mean_motion	float	Mean motion in revolutions per day.	required
norad_id	str	NORAD catalog number (supports numeric and Alpha-5 format).	required
ephemeris_type	int	Ephemeris type (0-9).	required
element_set_number	int	Element set number.	required
revolution_number	int	Revolution number at epoch.	required
classification	str	Security classification. Defaults to ' '.	None
intl_designator	str	International designator. Defaults to ''.	None
first_derivative	float	First derivative of mean motion. Defaults to 0.0.	None
second_derivative	float	Second derivative of mean motion. Defaults to 0.0.	None
bstar	float	BSTAR drag term. Defaults to 0.0.	None

Returns:

Name	Type	Description
tuple	tuple	A tuple containing (line1, line2) - the two TLE lines as strings.

datetime_to_jd builtin

datetime_to_jd(year: int, month: int, day: int, hour: int, minute: int, second: float, nanosecond: float) -> float

Convert a Gregorian calendar date to the equivalent Julian Date.

Note: Due to the ambiguity of the nature of leap second insertion, this method should not be used if a specific behavior for leap second insertion is expected. This method treats leap seconds as if they don't exist.

Parameters:

Name	Type	Description	Default
year	int	Year	required
month	int	Month (1-12)	required
day	int	Day of month (1-31)	required
hour	int	Hour (0-23)	required
minute	int	Minute (0-59)	required
second	float	Second with fractional part	required
nanosecond	float	Nanosecond component	required

Returns:

Type	Description
float	Julian date of epoch

datetime_to_mjd builtin

datetime_to_mjd(year: int, month: int, day: int, hour: int, minute: int, second: float, nanosecond: float) -> float

Convert a Gregorian calendar date to the equivalent Modified Julian Date.

Note: Due to the ambiguity of the nature of leap second insertion, this method should not be used if a specific behavior for leap second insertion is expected. This method treats leap seconds as if they don't exist.

Parameters:

Name	Type	Description	Default
year	int	Year	required
month	int	Month (1-12)	required
day	int	Day of month (1-31)	required
hour	int	Hour (0-23)	required
minute	int	Minute (0-59)	required
second	float	Second with fractional part	required
nanosecond	float	Nanosecond component	required

Returns:

Type	Description
float	Modified Julian date of epoch

download_c04_eop_file builtin

download_c04_eop_file(filepath: str) -> None

Download latest C04 Earth orientation parameter file. Will attempt to download the latest parameter file to the specified location. Creating any missing directories as required.

The download source is the IERS Earth Orientation Data Products

Parameters:

Name	Type	Description	Default
filepath	str	Path of desired output file	required

download_standard_eop_file builtin

download_standard_eop_file(filepath: str) -> None

Download latest standard Earth orientation parameter file. Will attempt to download the latest parameter file to the specified location. Creating any missing directories as required.

The download source is the IERS Earth Orientation Data Products

Parameters:

Name	Type	Description	Default
filepath	str	Path of desired output file	required

earth_rotation builtin

earth_rotation(epc: Epoch) -> np.ndarray

Computes the Earth rotation matrix transforming the CIRS to the TIRS intermediate reference frame. This transformation corrects for the Earth rotation.

Parameters:

Name	Type	Description	Default
epc	Epoch	Epoch instant for computation of transformation matrix	required

Returns:

Type	Description
ndarray	3x3 rotation matrix transforming CIRS -> TIRS

epoch_from_tle builtin

epoch_from_tle(line1: str) -> Epoch

Extract Epoch from TLE line 1

Extracts and parses the epoch timestamp from the first line of TLE data. The epoch is returned in UTC time system.

Parameters:

Name	Type	Description	Default
line1	str	First line of TLE data	required

Returns:

Name	Type	Description
Epoch	Epoch	Extracted epoch in UTC time system

Examples:

>>> line1 = "1 25544U 98067A   21001.50000000  .00001764  00000-0  40967-4 0  9997"
>>> epoch = epoch_from_tle(line1)
>>> epoch.year()
2021

get_global_dxdy builtin

get_global_dxdy(mjd: float) -> tuple[float, float]

Get celestial pole offsets from the global EOP provider.

Parameters:

Name	Type	Description	Default
mjd	float	Modified Julian Date	required

Returns:

Type	Description
tuple[float, float]	tuple[float, float]: Celestial pole offsets dx and dy in radians

get_global_eop builtin

get_global_eop(mjd: float) -> tuple[float, float, float, float, float, float]

Get all EOP parameters from the global EOP provider.

Parameters:

Name	Type	Description	Default
mjd	float	Modified Julian Date	required

Returns:

Type	Description
tuple[float, float, float, float, float, float]	tuple[float, float, float, float, float, float]: UT1-UTC, pm_x, pm_y, dx, dy, lod

get_global_eop_extrapolation builtin

get_global_eop_extrapolation() -> str

Get the extrapolation method of the global EOP provider.

Returns:

Name	Type	Description
str	str	Extrapolation method string

get_global_eop_initialization builtin

get_global_eop_initialization() -> bool

Check if the global EOP provider is initialized.

Returns:

Name	Type	Description
bool	bool	True if global EOP provider is initialized

get_global_eop_interpolation builtin

get_global_eop_interpolation() -> bool

Check if interpolation is enabled in the global EOP provider.

Returns:

Name	Type	Description
bool	bool	True if interpolation is enabled

get_global_eop_len builtin

get_global_eop_len() -> int

Get the number of EOP data points in the global provider.

Returns:

Name	Type	Description
int	int	Number of EOP data points

get_global_eop_mjd_last_dxdy builtin

get_global_eop_mjd_last_dxdy() -> float

Get the last Modified Julian Date with dx/dy data in the global provider.

Returns:

Name	Type	Description
float	float	Last MJD with dx/dy data

get_global_eop_mjd_last_lod builtin

get_global_eop_mjd_last_lod() -> float

Get the last Modified Julian Date with LOD data in the global provider.

Returns:

Name	Type	Description
float	float	Last MJD with LOD data

get_global_eop_mjd_max builtin

get_global_eop_mjd_max() -> float

Get the maximum Modified Julian Date in the global EOP dataset.

Returns:

Name	Type	Description
float	float	Maximum MJD

get_global_eop_mjd_min builtin

get_global_eop_mjd_min() -> float

Get the minimum Modified Julian Date in the global EOP dataset.

Returns:

Name	Type	Description
float	float	Minimum MJD

get_global_eop_type builtin

get_global_eop_type() -> str

Get the EOP data type of the global provider.

Returns:

Name	Type	Description
str	str	EOP type string

get_global_lod builtin

get_global_lod(mjd: float) -> float

Get length of day offset from the global EOP provider.

Parameters:

Name	Type	Description	Default
mjd	float	Modified Julian Date	required

Returns:

Name	Type	Description
float	float	Length of day offset in seconds

get_global_pm builtin

get_global_pm(mjd: float) -> tuple[float, float]

Get polar motion components from the global EOP provider.

Parameters:

Name	Type	Description	Default
mjd	float	Modified Julian Date	required

Returns:

Type	Description
tuple[float, float]	tuple[float, float]: Polar motion x and y components in radians

get_global_ut1_utc builtin

get_global_ut1_utc(mjd: float) -> float

Get UT1-UTC time difference from the global EOP provider.

Parameters:

Name	Type	Description	Default
mjd	float	Modified Julian Date	required

Returns:

Name	Type	Description
float	float	UT1-UTC time difference in seconds

jd_to_datetime builtin

jd_to_datetime(jd: float) -> tuple

Convert a Julian Date to the equivalent Gregorian calendar date.

Note: Due to the ambiguity of the nature of leap second insertion, this method should not be used if a specific behavior for leap second insertion is expected. This method treats leap seconds as if they don't exist.

Parameters:

Name	Type	Description	Default
jd	float	Julian date	required

Returns:

Name	Type	Description
tuple	tuple	A tuple containing (year, month, day, hour, minute, second, nanosecond)

keplerian_elements_from_tle builtin

keplerian_elements_from_tle(line1: str, line2: str) -> None

Extract Keplerian orbital elements from TLE lines.

Extracts the standard six Keplerian orbital elements from Two-Line Element (TLE) data. Returns elements in standard order: [a, e, i, raan, argp, M] where angles are in radians.

Parameters:

Name	Type	Description	Default
line1	str	First line of TLE data.	required
line2	str	Second line of TLE data.	required

Returns:

Name	Type	Description
tuple	None	A tuple containing: - epoch (Epoch): Epoch of the TLE data. - elements (numpy.ndarray): Six Keplerian elements [a, e, i, raan, argp, M] where a is semi-major axis in meters, e is eccentricity (dimensionless), and i, raan, argp, M are in radians.

keplerian_elements_to_tle builtin

keplerian_elements_to_tle(epoch: Epoch, elements: ndarray, norad_id: str) -> tuple

Convert Keplerian elements to TLE lines.

Converts standard Keplerian orbital elements to Two-Line Element (TLE) format. Input angles should be in degrees for compatibility with TLE format.

Parameters:

Name	Type	Description	Default
epoch	Epoch	Epoch of the elements.	required
elements	ndarray	Keplerian elements [a (m), e, i (deg), raan (deg), argp (deg), M (deg)].	required
norad_id	str	NORAD catalog number (supports numeric and Alpha-5 format).	required

Returns:

Name	Type	Description
tuple	tuple	A tuple containing (line1, line2) - the two TLE lines as strings.

mean_motion builtin

mean_motion(a: float, angle_format: AngleFormat) -> float

Computes the mean motion of an astronomical object around Earth.

Parameters:

Name	Type	Description	Default
a	float	The semi-major axis of the astronomical object in meters.	required
angle_format	AngleFormat	Return output in AngleFormat.DEGREES or AngleFormat.RADIANS.	required

Returns:

Name	Type	Description
float	float	The mean motion of the astronomical object in radians or degrees.

mean_motion_general builtin

mean_motion_general(a: float, gm: float, angle_format: AngleFormat) -> float

Computes the mean motion of an astronomical object around a general body given a semi-major axis.

Parameters:

Name	Type	Description	Default
a	float	The semi-major axis of the astronomical object in meters.	required
gm	float	The standard gravitational parameter of primary body in m³/s².	required
angle_format	AngleFormat	Return output in AngleFormat.DEGREES or AngleFormat.RADIANS.	required

Returns:

Name	Type	Description
float	float	The mean motion of the astronomical object in radians or degrees.

mjd_to_datetime builtin

mjd_to_datetime(mjd: float) -> tuple

Convert a Modified Julian Date to the equivalent Gregorian calendar date.

Note: Due to the ambiguity of the nature of leap second insertion, this method should not be used if a specific behavior for leap second insertion is expected. This method treats leap seconds as if they don't exist.

Parameters:

Name	Type	Description	Default
mjd	float	Modified Julian date	required

Returns:

Name	Type	Description
tuple	tuple	A tuple containing (year, month, day, hour, minute, second, nanosecond)

norad_id_alpha5_to_numeric builtin

norad_id_alpha5_to_numeric(alpha5_id: str) -> int

Convert Alpha-5 NORAD ID to numeric format.

Parameters:

Name	Type	Description	Default
alpha5_id	str	Alpha-5 format ID (e.g., "A0001").	required

Returns:

Name	Type	Description
int	int	Numeric NORAD ID.

norad_id_numeric_to_alpha5 builtin

norad_id_numeric_to_alpha5(norad_id: int) -> str

Convert numeric NORAD ID to Alpha-5 format.

Parameters:

Name	Type	Description	Default
norad_id	int	Numeric NORAD ID (100000-339999).	required

Returns:

Name	Type	Description
str	str	Alpha-5 format ID (e.g., "A0001").

orbital_period builtin

orbital_period(a: float) -> float

Computes the orbital period of an object around Earth.

Uses rastro.constants.GM_EARTH as the standard gravitational parameter for the calculation.

Parameters:

Name	Type	Description	Default
a	float	The semi-major axis of the astronomical object in meters.	required

Returns:

Type	Description
float	The orbital period of the astronomical object in seconds.

orbital_period_general builtin

orbital_period_general(a: float, gm: float) -> float

Computes the orbital period of an astronomical object around a general body.

Parameters:

Name	Type	Description	Default
a	float	The semi-major axis of the astronomical object in meters.	required
gm	float	The standard gravitational parameter of primary body in m³/s².	required

Returns:

Name	Type	Description
float	float	The orbital period of the astronomical object in seconds.

parse_norad_id builtin

parse_norad_id(norad_str: str) -> int

Parse NORAD ID from string, handling both classic and Alpha-5 formats.

Parameters:

Name	Type	Description	Default
norad_str	str	NORAD ID string from TLE.	required

Returns:

Name	Type	Description
int	int	Parsed numeric NORAD ID.

periapsis_distance builtin

periapsis_distance(a: float, e: float) -> float

Calculate the distance of an object at its periapsis.

Parameters:

Name	Type	Description	Default
a	float	The semi-major axis of the astronomical object in meters.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required

Returns:

Name	Type	Description
float	float	The distance of the object at periapsis in meters.

periapsis_velocity builtin

periapsis_velocity(a: float, e: float, gm: float) -> float

Computes the periapsis velocity of an astronomical object around a general body.

Parameters:

Name	Type	Description	Default
a	float	The semi-major axis of the astronomical object in meters.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required
gm	float	The standard gravitational parameter of primary body in m³/s².	required

Returns:

Name	Type	Description
float	float	The magnitude of velocity of the object at periapsis in m/s.

perigee_velocity builtin

perigee_velocity(a: float, e: float) -> float

Computes the perigee velocity of an astronomical object around Earth.

Parameters:

Name	Type	Description	Default
a	float	The semi-major axis of the astronomical object in meters.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required

Returns:

Name	Type	Description
float	float	The magnitude of velocity of the object at perigee in m/s.

polar_motion builtin

polar_motion(epc: Epoch) -> np.ndarray

Computes the Earth rotation matrix transforming the TIRS to the ITRF reference frame.

The function will utilize the global Earth orientation and loaded data to apply corrections to compute the polar motion correction based on empirical observations of polar motion drift.

Parameters:

Name	Type	Description	Default
epc	Epoch	Epoch instant for computation of transformation matrix	required

Returns:

Type	Description
ndarray	3x3 rotation matrix transforming TIRS -> ITRF

position_ecef_to_eci builtin

position_ecef_to_eci(epc: Epoch, x: ndarray) -> np.ndarray

Transforms a position vector from the Earth Centered Earth Fixed (ECEF/ITRF) frame to the Earth Centered Inertial (ECI/GCRF) frame.

Applies the full IAU 2006/2000A transformation including bias, precession, nutation, Earth rotation, and polar motion corrections using global Earth orientation parameters.

Parameters:

Name	Type	Description	Default
epc	Epoch	Epoch instant for the transformation	required
x	ndarray	Position vector in ECEF frame (m), shape (3,)	required

Returns:

Type	Description
ndarray	Position vector in ECI frame (m), shape (3,)

position_ecef_to_geocentric builtin

position_ecef_to_geocentric(x_ecef: ndarray, angle_format: AngleFormat) -> np.ndarray

Convert ECEF Cartesian position to geocentric coordinates.

Transforms a position from Earth-Centered Earth-Fixed (ECEF) Cartesian coordinates to geocentric spherical coordinates (latitude, longitude, radius).

Parameters:

Name	Type	Description	Default
x_ecef	ndarray	ECEF Cartesian position [x, y, z] in meters.	required
angle_format	AngleFormat	Angle format for output angular coordinates (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	Geocentric position [latitude, longitude, radius] where latitude is in radians or degrees, longitude is in radians or degrees, and radius is in meters.

position_ecef_to_geodetic builtin

position_ecef_to_geodetic(x_ecef: ndarray, angle_format: AngleFormat) -> np.ndarray

Convert ECEF Cartesian position to geodetic coordinates.

Transforms a position from Earth-Centered Earth-Fixed (ECEF) Cartesian coordinates to geodetic coordinates (latitude, longitude, altitude) using the WGS84 ellipsoid model.

Parameters:

Name	Type	Description	Default
x_ecef	ndarray	ECEF Cartesian position [x, y, z] in meters.	required
angle_format	AngleFormat	Angle format for output angular coordinates (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	Geodetic position [latitude, longitude, altitude] where latitude is in radians or degrees, longitude is in radians or degrees, and altitude is in meters above the WGS84 ellipsoid.

position_eci_to_ecef builtin

position_eci_to_ecef(epc: Epoch, x: ndarray) -> np.ndarray

Transforms a position vector from the Earth Centered Inertial (ECI/GCRF) frame to the Earth Centered Earth Fixed (ECEF/ITRF) frame.

Applies the full IAU 2006/2000A transformation including bias, precession, nutation, Earth rotation, and polar motion corrections using global Earth orientation parameters.

Parameters:

Name	Type	Description	Default
epc	Epoch	Epoch instant for the transformation	required
x	ndarray	Position vector in ECI frame (m), shape (3,)	required

Returns:

Type	Description
ndarray	Position vector in ECEF frame (m), shape (3,)

position_enz_to_azel builtin

position_enz_to_azel(x_enz: ndarray, angle_format: AngleFormat) -> np.ndarray

Convert position from East-North-Up (ENZ) frame to azimuth-elevation-range.

Transforms a position from the local East-North-Up (ENZ) topocentric frame to azimuth-elevation-range spherical coordinates.

Parameters:

Name	Type	Description	Default
x_enz	ndarray	Position in ENZ frame [east, north, up] in meters.	required
angle_format	AngleFormat	Angle format for output angular coordinates (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	Azimuth-elevation-range [azimuth, elevation, range] where azimuth and elevation are in radians or degrees, and range is in meters.

position_geocentric_to_ecef builtin

position_geocentric_to_ecef(x_geoc: ndarray, angle_format: AngleFormat) -> np.ndarray

Convert geocentric position to ECEF Cartesian coordinates.

Transforms a position from geocentric spherical coordinates (latitude, longitude, radius) to Earth-Centered Earth-Fixed (ECEF) Cartesian coordinates.

Parameters:

Name	Type	Description	Default
x_geoc	ndarray	Geocentric position [latitude, longitude, radius] where latitude is in radians or degrees, longitude is in radians or degrees, and radius is in meters.	required
angle_format	AngleFormat	Angle format for input angular coordinates (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	ECEF Cartesian position [x, y, z] in meters.

position_geodetic_to_ecef builtin

position_geodetic_to_ecef(x_geod: ndarray, angle_format: AngleFormat) -> np.ndarray

Convert geodetic position to ECEF Cartesian coordinates.

Transforms a position from geodetic coordinates (latitude, longitude, altitude) using the WGS84 ellipsoid model to Earth-Centered Earth-Fixed (ECEF) Cartesian coordinates.

Parameters:

Name	Type	Description	Default
x_geod	ndarray	Geodetic position [latitude, longitude, altitude] where latitude is in radians or degrees, longitude is in radians or degrees, and altitude is in meters above the WGS84 ellipsoid.	required
angle_format	AngleFormat	Angle format for input angular coordinates (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	ECEF Cartesian position [x, y, z] in meters.

position_sez_to_azel builtin

position_sez_to_azel(x_sez: ndarray, angle_format: AngleFormat) -> np.ndarray

Convert position from South-East-Zenith (SEZ) frame to azimuth-elevation-range.

Transforms a position from the local South-East-Zenith (SEZ) topocentric frame to azimuth-elevation-range spherical coordinates.

Parameters:

Name	Type	Description	Default
x_sez	ndarray	Position in SEZ frame [south, east, zenith] in meters.	required
angle_format	AngleFormat	Angle format for output angular coordinates (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	Azimuth-elevation-range [azimuth, elevation, range] where azimuth and elevation are in radians or degrees, and range is in meters.

relative_position_ecef_to_enz builtin

relative_position_ecef_to_enz(location_ecef: ndarray, r_ecef: ndarray, conversion_type: str) -> np.ndarray

Convert relative position from ECEF to East-North-Up (ENZ) frame.

Transforms a relative position vector from Earth-Centered Earth-Fixed (ECEF) coordinates to the local East-North-Up (ENZ) topocentric frame at the specified location.

Parameters:

Name	Type	Description	Default
location_ecef	ndarray	Reference location in ECEF coordinates [x, y, z] in meters.	required
r_ecef	ndarray	Position vector in ECEF coordinates [x, y, z] in meters.	required
conversion_type	str	Type of ellipsoidal conversion, either "Geocentric" or "Geodetic".	required

Returns:

Type	Description
ndarray	Relative position in ENZ frame [east, north, up] in meters.

relative_position_ecef_to_sez builtin

relative_position_ecef_to_sez(location_ecef: ndarray, r_ecef: ndarray, conversion_type: str) -> np.ndarray

Convert relative position from ECEF to South-East-Zenith (SEZ) frame.

Transforms a relative position vector from Earth-Centered Earth-Fixed (ECEF) coordinates to the local South-East-Zenith (SEZ) topocentric frame at the specified location.

Parameters:

Name	Type	Description	Default
location_ecef	ndarray	Reference location in ECEF coordinates [x, y, z] in meters.	required
r_ecef	ndarray	Position vector in ECEF coordinates [x, y, z] in meters.	required
conversion_type	str	Type of ellipsoidal conversion, either "Geocentric" or "Geodetic".	required

Returns:

Type	Description
ndarray	Relative position in SEZ frame [south, east, zenith] in meters.

relative_position_enz_to_ecef builtin

relative_position_enz_to_ecef(location_ecef: ndarray, r_enz: ndarray, conversion_type: str) -> np.ndarray

Convert relative position from East-North-Up (ENZ) frame to ECEF.

Transforms a relative position vector from the local East-North-Up (ENZ) topocentric frame to Earth-Centered Earth-Fixed (ECEF) coordinates at the specified location.

Parameters:

Name	Type	Description	Default
location_ecef	ndarray	Reference location in ECEF coordinates [x, y, z] in meters.	required
r_enz	ndarray	Relative position in ENZ frame [east, north, up] in meters.	required
conversion_type	str	Type of ellipsoidal conversion, either "Geocentric" or "Geodetic".	required

Returns:

Type	Description
ndarray	Position vector in ECEF coordinates [x, y, z] in meters.

relative_position_sez_to_ecef builtin

relative_position_sez_to_ecef(location_ecef: ndarray, x_sez: ndarray, conversion_type: str) -> np.ndarray

Convert relative position from South-East-Zenith (SEZ) frame to ECEF.

Transforms a relative position vector from the local South-East-Zenith (SEZ) topocentric frame to Earth-Centered Earth-Fixed (ECEF) coordinates at the specified location.

Parameters:

Name	Type	Description	Default
location_ecef	ndarray	Reference location in ECEF coordinates [x, y, z] in meters.	required
x_sez	ndarray	Relative position in SEZ frame [south, east, zenith] in meters.	required
conversion_type	str	Type of ellipsoidal conversion, either "Geocentric" or "Geodetic".	required

Returns:

Type	Description
ndarray	Position vector in ECEF coordinates [x, y, z] in meters.

rotation_ecef_to_eci builtin

rotation_ecef_to_eci(epc: Epoch) -> np.ndarray

Computes the combined rotation matrix from the Earth-fixed to the inertial reference frame. Applies corrections for bias, precession, nutation, Earth-rotation, and polar motion.

The transformation is accomplished using the IAU 2006/2000A, CIO-based theory using classical angles. The method as described in section 5.5 of the SOFA C transformation cookbook.

The function will utilize the global Earth orientation and loaded data to apply corrections for Celestial Intermidate Pole (CIP) and polar motion drift derived from empirical observations.

Parameters:

Name	Type	Description	Default
epc	Epoch	Epoch instant for computation of transformation matrix	required

Returns:

Type	Description
ndarray	3x3 rotation matrix transforming ITRF -> GCRF

rotation_eci_to_ecef builtin

rotation_eci_to_ecef(epc: Epoch) -> np.ndarray

Computes the combined rotation matrix from the inertial to the Earth-fixed reference frame. Applies corrections for bias, precession, nutation, Earth-rotation, and polar motion.

The transformation is accomplished using the IAU 2006/2000A, CIO-based theory using classical angles. The method as described in section 5.5 of the SOFA C transformation cookbook.

The function will utilize the global Earth orientation and loaded data to apply corrections for Celestial Intermidate Pole (CIP) and polar motion drift derived from empirical observations.

Parameters:

Name	Type	Description	Default
epc	Epoch	Epoch instant for computation of transformation matrix	required

Returns:

Type	Description
ndarray	3x3 rotation matrix transforming GCRF -> ITRF

rotation_ellipsoid_to_enz builtin

rotation_ellipsoid_to_enz(x_ellipsoid: ndarray, angle_format: AngleFormat) -> np.ndarray

Compute rotation matrix from ellipsoidal coordinates to East-North-Up (ENZ) frame.

Calculates the rotation matrix that transforms vectors from an ellipsoidal coordinate frame (geocentric or geodetic) to the local East-North-Up (ENZ) topocentric frame at the specified location.

Parameters:

Name	Type	Description	Default
x_ellipsoid	ndarray	Ellipsoidal position [latitude, longitude, altitude/radius] where latitude is in radians or degrees, longitude is in radians or degrees.	required
angle_format	AngleFormat	Angle format for input angular coordinates (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	3x3 rotation matrix from ellipsoidal frame to ENZ frame.

rotation_ellipsoid_to_sez builtin

rotation_ellipsoid_to_sez(x_ellipsoid: ndarray, angle_format: AngleFormat) -> np.ndarray

Compute rotation matrix from ellipsoidal coordinates to South-East-Zenith (SEZ) frame.

Calculates the rotation matrix that transforms vectors from an ellipsoidal coordinate frame (geocentric or geodetic) to the local South-East-Zenith (SEZ) topocentric frame at the specified location.

Parameters:

Name	Type	Description	Default
x_ellipsoid	ndarray	Ellipsoidal position [latitude, longitude, altitude/radius] where latitude is in radians or degrees, longitude is in radians or degrees.	required
angle_format	AngleFormat	Angle format for input angular coordinates (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	3x3 rotation matrix from ellipsoidal frame to SEZ frame.

rotation_enz_to_ellipsoid builtin

rotation_enz_to_ellipsoid(x_ellipsoid: ndarray, angle_format: AngleFormat) -> np.ndarray

Compute rotation matrix from East-North-Up (ENZ) frame to ellipsoidal coordinates.

Calculates the rotation matrix that transforms vectors from the local East-North-Up (ENZ) topocentric frame to an ellipsoidal coordinate frame (geocentric or geodetic) at the specified location.

Parameters:

Name	Type	Description	Default
x_ellipsoid	ndarray	Ellipsoidal position [latitude, longitude, altitude/radius] where latitude is in radians or degrees, longitude is in radians or degrees.	required
angle_format	AngleFormat	Angle format for input angular coordinates (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	3x3 rotation matrix from ENZ frame to ellipsoidal frame.

rotation_sez_to_ellipsoid builtin

rotation_sez_to_ellipsoid(x_ellipsoid: ndarray, angle_format: AngleFormat) -> np.ndarray

Compute rotation matrix from South-East-Zenith (SEZ) frame to ellipsoidal coordinates.

Calculates the rotation matrix that transforms vectors from the local South-East-Zenith (SEZ) topocentric frame to an ellipsoidal coordinate frame (geocentric or geodetic) at the specified location.

Parameters:

Name	Type	Description	Default
x_ellipsoid	ndarray	Ellipsoidal position [latitude, longitude, altitude/radius] where latitude is in radians or degrees, longitude is in radians or degrees.	required
angle_format	AngleFormat	Angle format for input angular coordinates (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	3x3 rotation matrix from SEZ frame to ellipsoidal frame.

semimajor_axis builtin

semimajor_axis(n: float, angle_format: AngleFormat) -> float

Computes the semi-major axis of an astronomical object from Earth given the object's mean motion.

Parameters:

Name	Type	Description	Default
n	float	The mean motion of the astronomical object in radians or degrees.	required
angle_format	AngleFormat	Interpret mean motion as AngleFormat.DEGREES or AngleFormat.RADIANS.	required

Returns:

Name	Type	Description
float	float	The semi-major axis of the astronomical object in meters.

semimajor_axis_from_orbital_period builtin

semimajor_axis_from_orbital_period(period: float) -> float

Computes the semi-major axis from orbital period around Earth.

Parameters:

Name	Type	Description	Default
period	float	The orbital period in seconds.	required

Returns:

Name	Type	Description
float	float	The semi-major axis in meters.

semimajor_axis_from_orbital_period_general builtin

semimajor_axis_from_orbital_period_general(period: float, gm: float) -> float

Computes the semi-major axis from orbital period for a general body.

Parameters:

Name	Type	Description	Default
period	float	The orbital period in seconds.	required
gm	float	The standard gravitational parameter of primary body in m³/s².	required

Returns:

Name	Type	Description
float	float	The semi-major axis in meters.

semimajor_axis_general builtin

semimajor_axis_general(n: float, gm: float, angle_format: AngleFormat) -> float

Computes the semi-major axis of an astronomical object from a general body given the object's mean motion.

Parameters:

Name	Type	Description	Default
n	float	The mean motion of the astronomical object in radians or degrees.	required
gm	float	The standard gravitational parameter of primary body in m³/s².	required
angle_format	AngleFormat	Interpret mean motion as AngleFormat.DEGREES or AngleFormat.RADIANS.	required

Returns:

Name	Type	Description
float	float	The semi-major axis of the astronomical object in meters.

set_global_eop_provider_from_file_provider builtin

set_global_eop_provider_from_file_provider(provider: FileEOPProvider) -> None

Set the global EOP provider using a file-based provider.

Parameters:

Name	Type	Description	Default
provider	FileEOPProvider	File-based EOP provider to set globally	required

set_global_eop_provider_from_static_provider builtin

set_global_eop_provider_from_static_provider(provider: StaticEOPProvider) -> None

Set the global EOP provider using a static provider.

Parameters:

Name	Type	Description	Default
provider	StaticEOPProvider	Static EOP provider to set globally	required

state_cartesian_to_osculating builtin

state_cartesian_to_osculating(x_cart: ndarray, angle_format: AngleFormat) -> np.ndarray

Convert Cartesian state to osculating orbital elements.

Transforms a state vector from Cartesian position and velocity coordinates to osculating Keplerian orbital elements.

Parameters:

Name	Type	Description	Default
x_cart	ndarray	Cartesian state [x, y, z, vx, vy, vz] where position is in meters and velocity is in meters per second.	required
angle_format	AngleFormat	Angle format for output angular elements (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	Osculating orbital elements [a, e, i, RAAN, omega, M] where a is semi-major axis (meters), e is eccentricity (dimensionless), i is inclination (radians or degrees), RAAN is right ascension of ascending node (radians or degrees), omega is argument of periapsis (radians or degrees), and M is mean anomaly (radians or degrees).

state_ecef_to_eci builtin

state_ecef_to_eci(epc: Epoch, x_ecef: ndarray) -> np.ndarray

Transforms a state vector (position and velocity) from the Earth Centered Earth Fixed (ECEF/ITRF) frame to the Earth Centered Inertial (ECI/GCRF) frame.

Applies the full IAU 2006/2000A transformation including bias, precession, nutation, Earth rotation, and polar motion corrections using global Earth orientation parameters. The velocity transformation accounts for the Earth's rotation rate.

Parameters:

Name	Type	Description	Default
epc	Epoch	Epoch instant for the transformation	required
x_ecef	ndarray	State vector in ECEF frame [position (m), velocity (m/s)], shape (6,)	required

Returns:

Type	Description
ndarray	State vector in ECI frame [position (m), velocity (m/s)], shape (6,)

state_eci_to_ecef builtin

state_eci_to_ecef(epc: Epoch, x_eci: ndarray) -> np.ndarray

Transforms a state vector (position and velocity) from the Earth Centered Inertial (ECI/GCRF) frame to the Earth Centered Earth Fixed (ECEF/ITRF) frame.

Applies the full IAU 2006/2000A transformation including bias, precession, nutation, Earth rotation, and polar motion corrections using global Earth orientation parameters. The velocity transformation accounts for the Earth's rotation rate.

Parameters:

Name	Type	Description	Default
epc	Epoch	Epoch instant for the transformation	required
x_eci	ndarray	State vector in ECI frame [position (m), velocity (m/s)], shape (6,)	required

Returns:

Type	Description
ndarray	State vector in ECEF frame [position (m), velocity (m/s)], shape (6,)

state_osculating_to_cartesian builtin

state_osculating_to_cartesian(x_oe: ndarray, angle_format: AngleFormat) -> np.ndarray

Convert osculating orbital elements to Cartesian state.

Transforms a state vector from osculating Keplerian orbital elements to Cartesian position and velocity coordinates.

Parameters:

Name	Type	Description	Default
x_oe	ndarray	Osculating orbital elements [a, e, i, RAAN, omega, M] where a is semi-major axis (meters), e is eccentricity (dimensionless), i is inclination (radians or degrees), RAAN is right ascension of ascending node (radians or degrees), omega is argument of periapsis (radians or degrees), and M is mean anomaly (radians or degrees).	required
angle_format	AngleFormat	Angle format for angular elements (RADIANS or DEGREES).	required

Returns:

Type	Description
ndarray	Cartesian state [x, y, z, vx, vy, vz] where position is in meters and velocity is in meters per second.

sun_synchronous_inclination builtin

sun_synchronous_inclination(a: float, e: float, angle_format: AngleFormat) -> float

Computes the inclination for a Sun-synchronous orbit around Earth based on the J2 gravitational perturbation.

Parameters:

Name	Type	Description	Default
a	float	The semi-major axis of the astronomical object in meters.	required
e	float	The eccentricity of the astronomical object's orbit (dimensionless).	required
angle_format	AngleFormat	Return output in AngleFormat.DEGREES or AngleFormat.RADIANS.	required

Returns:

Name	Type	Description
float	float	Inclination for a Sun synchronous orbit in degrees or radians.

time_system_offset_for_datetime builtin

time_system_offset_for_datetime(year: int, month: int, day: int, hour: int, minute: int, second: float, nanosecond: float, time_system_src: TimeSystem, time_system_dst: TimeSystem) -> float

Calculate the offset between two time systems for a given Gregorian calendar date.

Parameters:

Name	Type	Description	Default
year	int	Year	required
month	int	Month (1-12)	required
day	int	Day of month (1-31)	required
hour	int	Hour (0-23)	required
minute	int	Minute (0-59)	required
second	float	Second with fractional part	required
nanosecond	float	Nanosecond component	required
time_system_src	TimeSystem	Source time system	required
time_system_dst	TimeSystem	Destination time system	required

Returns:

Name	Type	Description
float	float	Offset between time systems in seconds

time_system_offset_for_jd builtin

time_system_offset_for_jd(jd: float, time_system_src: TimeSystem, time_system_dst: TimeSystem) -> float

Calculate the offset between two time systems for a given Julian Date.

Parameters:

Name	Type	Description	Default
jd	float	Julian date	required
time_system_src	TimeSystem	Source time system	required
time_system_dst	TimeSystem	Destination time system	required

Returns:

Name	Type	Description
float	float	Offset between time systems in seconds

time_system_offset_for_mjd builtin

time_system_offset_for_mjd(mjd: float, time_system_src: TimeSystem, time_system_dst: TimeSystem) -> float

Calculate the offset between two time systems for a given Modified Julian Date.

Parameters:

Name	Type	Description	Default
mjd	float	Modified Julian date	required
time_system_src	TimeSystem	Source time system	required
time_system_dst	TimeSystem	Destination time system	required

Returns:

Name	Type	Description
float	float	Offset between time systems in seconds

validate_tle_line builtin

validate_tle_line(line: str) -> bool

Validate single TLE line.

Parameters:

Name	Type	Description	Default
line	str	TLE line to validate.	required

Returns:

Name	Type	Description
bool	bool	True if the line is valid.

validate_tle_lines builtin

validate_tle_lines(line1: str, line2: str) -> bool

Validate TLE lines.

Parameters:

Name	Type	Description	Default
line1	str	First line of TLE data.	required
line2	str	Second line of TLE data.	required

Returns:

Name	Type	Description
bool	bool	True if both lines are valid.