SGP4¶

SGP4/SDP4 orbit propagator implemented in JAX.

This module provides a JAX-native implementation of the SGP4 (Simplified General Perturbations 4) and SDP4 (Simplified Deep-space Perturbations 4) orbit propagators for propagating Two-Line Element (TLE) sets. The implementation supports JIT compilation and vmap over time arrays.

`WGS72 = EarthGravity(tumin=(1.0 / _xke_72), mu=_mu_72, radiusearthkm=_re_72, xke=_xke_72, j2=_j2_72, j3=_j3_72, j4=_j4_72, j3oj2=(_j3_72 / _j2_72))` `module-attribute` ¶

WGS 72 gravity model (standard for SGP4).

`WGS72OLD = EarthGravity(tumin=(1.0 / _xke_72old), mu=_mu_72old, radiusearthkm=_re_72old, xke=_xke_72old, j2=_j2_72old, j3=_j3_72old, j4=_j4_72old, j3oj2=(_j3_72old / _j2_72old))` `module-attribute` ¶

WGS 72 Old gravity model (legacy).

`WGS84 = EarthGravity(tumin=(1.0 / _xke_84), mu=_mu_84, radiusearthkm=_re_84, xke=_xke_84, j2=_j2_84, j3=_j3_84, j4=_j4_84, j3oj2=(_j3_84 / _j2_84))` `module-attribute` ¶

WGS 84 gravity model.

`EarthGravity` ¶

Bases: NamedTuple

Earth gravity model constants for SGP4 propagation.

Attributes:

Name	Type	Description
`tumin`	`float`	Time units per minute (1/xke).
`mu`	`float`	Gravitational parameter [km^3/s2].
`radiusearthkm`	`float`	Earth equatorial radius [km].
`xke`	`float`	Reciprocal of tumin (sqrt(GM) in SGP4 time units).
`j2`	`float`	Second zonal harmonic.
`j3`	`float`	Third zonal harmonic.
`j4`	`float`	Fourth zonal harmonic.
`j3oj2`	`float`	Ratio j3/j2.

`SGP4Elements` `dataclass` ¶

Parsed orbital elements from a TLE or OMM record.

This is a plain Python dataclass (not a JAX pytree) holding the parsed orbital elements, epoch information, and metadata extracted from a TLE or OMM record. All angular values are stored in their original units as parsed (degrees for user-facing, radians for SGP4-internal).

Attributes:

Name	Type	Description
`satnum_str`	`str`	Satellite catalog number as a string (e.g. `'25544'`).
`classification`	`str`	Classification character (`'U'`, `'C'`, or `'S'`).
`intldesg`	`str`	International designator (e.g. `'98067A'`).
`epochyr`	`int`	Two-digit epoch year (0-99).
`epochdays`	`float`	Day of year with fractional day.
`ndot`	`float`	First derivative of mean motion divided by 2 [rad/min^2].
`nddot`	`float`	Second derivative of mean motion divided by 6 [rad/min^3].
`bstar`	`float`	B* drag coefficient [1/earth_radii].
`ephtype`	`int`	Ephemeris type (typically 0).
`elnum`	`int`	Element set number.
`revnum`	`int`	Revolution number at epoch.
`inclo`	`float`	Inclination [rad].
`nodeo`	`float`	Right ascension of ascending node [rad].
`ecco`	`float`	Eccentricity [dimensionless].
`argpo`	`float`	Argument of perigee [rad].
`mo`	`float`	Mean anomaly [rad].
`no_kozai`	`float`	Mean motion (Kozai) [rad/min].
`jdsatepoch`	`float`	Julian date of epoch (whole days).
`jdsatepochF`	`float`	Julian date of epoch (fractional day).

`TLE` ¶

A parsed TLE with SGP4/SDP4 propagation and frame transforms.

Wraps TLE parsing, SGP4 initialization, and propagation into a single object. Provides orbital element properties in user-friendly units and state vector methods in various reference frames.

The propagate method returns raw SGP4 output in km/km/s (for comparison testing). The state_* methods return SI units (m, m/s).

Examples:

from astrojax.sgp4 import TLE

line1 = "1 25544U 98067A   08264.51782528 ..."
line2 = "2 25544  51.6416 247.4627 ..."
sat = TLE(line1, line2)

# Properties
sat.epoch       # Epoch object
sat.n           # mean motion [rev/day]
sat.e           # eccentricity
sat.i           # inclination [deg]

# Raw SGP4 output (km, km/s)
r_km, v_kms = sat.propagate(60.0)

# State in TEME (m, m/s) at epoch + 3600 seconds
x_teme = sat.state_teme(3600.0)

# State in GCRF at a specific Epoch
x_gcrf = sat.state_gcrf(some_epoch, eop=eop_data)

Parameters:

Name	Type	Description	Default
`line1`	`str`	First TLE line.	required
`line2`	`str`	Second TLE line.	required
`gravity`	`str \| EarthGravity`	Gravity model name or :class:`EarthGravity` instance.	`'wgs72'`

`M` `property` ¶

Mean anomaly [degrees].

`argp` `property` ¶

Argument of perigee [degrees].

`bstar` `property` ¶

B* drag coefficient [1/earth_radii].

`e` `property` ¶

Eccentricity [dimensionless].

`epoch` `property` ¶

TLE epoch as an :class:Epoch object.

`i` `property` ¶

Inclination [degrees].

`method` `property` ¶

Propagation method: 'n' (near-earth) or 'd' (deep-space).

`n` `property` ¶

Mean motion [rev/day].

`params` `property` ¶

Raw SGP4 parameter array (for advanced use).

`raan` `property` ¶

Right ascension of ascending node [degrees].

`satnum` `property` ¶

NORAD catalog number (string, e.g. '25544').

`from_elements(elements, gravity='wgs72')` `classmethod` ¶

Create a TLE from pre-parsed SGP4 orbital elements.

Parameters:

Name	Type	Description	Default
`elements`	`SGP4Elements`	Parsed orbital elements from `parse_tle` or `parse_omm`.	required
`gravity`	`str \| EarthGravity`	Gravity model name or :class:`EarthGravity` instance.	`'wgs72'`

Returns:

Type	Description
`TLE`	A new :class:`TLE` instance.

`from_gp_record(record, gravity='wgs72')` `classmethod` ¶

Create a TLE from a GPRecord.

Parameters:

Name	Type	Description	Default
`record`	`GPRecord`	A GP record from CelesTrak or SpaceTrack.	required
`gravity`	`str \| EarthGravity`	Gravity model name or :class:`EarthGravity` instance.	`'wgs72'`

Returns:

Type	Description
`TLE`	A new :class:`TLE` instance.

Raises:

Type	Description
`KeyError`	If the record is missing required fields.

`from_omm(fields, gravity='wgs72')` `classmethod` ¶

Create a TLE from OMM (Orbit Mean-Elements Message) fields.

Parameters:

Name	Type	Description	Default
`fields`	`dict[str, str]`	Dictionary mapping OMM field names to string values. See :func:`~astrojax.sgp4.parse_omm` for required keys.	required
`gravity`	`str \| EarthGravity`	Gravity model name or :class:`EarthGravity` instance.	`'wgs72'`

Returns:

Type	Description
`TLE`	A new :class:`TLE` instance.

Raises:

Type	Description
`KeyError`	If a required OMM field is missing.

`propagate(tsince_min)` ¶

Propagate using SGP4 and return raw output.

Parameters:

Name	Type	Description	Default
`tsince_min`	`float \| ArrayLike`	Time since TLE epoch in minutes.	required

Returns:

Type	Description
`Array`	Tuple `(r_km, v_kms)` — position [km] and velocity [km/s]
`Array`	in the TEME frame.

`state(t)` ¶

Compute state in the TEME frame (alias for :meth:state_teme).

Parameters:

Name	Type	Description	Default
`t`	`Epoch \| float \| ArrayLike`	:class:`Epoch` (absolute time) or seconds since TLE epoch.	required

Returns:

Type	Description
`Array`	6-element TEME state `[x, y, z, vx, vy, vz]` in m and m/s.

`state_gcrf(t, eop=None)` ¶

Compute state in the GCRF frame.

Parameters:

Name	Type	Description	Default
`t`	`Epoch \| float \| ArrayLike`	:class:`Epoch` (absolute time) or seconds since TLE epoch.	required
`eop`	`EOPData \| None`	EOP data. If `None`, uses zero EOP (no polar motion).	`None`

Returns:

Type	Description
`Array`	6-element GCRF state `[x, y, z, vx, vy, vz]` in m and m/s.

`state_itrf(t, eop=None)` ¶

Compute state in the ITRF frame.

Parameters:

Name	Type	Description	Default
`t`	`Epoch \| float \| ArrayLike`	:class:`Epoch` (absolute time) or seconds since TLE epoch.	required
`eop`	`EOPData \| None`	EOP data. If `None`, uses zero EOP (no polar motion).	`None`

Returns:

Type	Description
`Array`	6-element ITRF state `[x, y, z, vx, vy, vz]` in m and m/s.

`state_pef(t)` ¶

Compute state in the PEF frame.

Parameters:

Name	Type	Description	Default
`t`	`Epoch \| float \| ArrayLike`	:class:`Epoch` (absolute time) or seconds since TLE epoch.	required

Returns:

Type	Description
`Array`	6-element PEF state `[x, y, z, vx, vy, vz]` in m and m/s.

`state_teme(t)` ¶

Compute state in the TEME frame.

Parameters:

Name	Type	Description	Default
`t`	`Epoch \| float \| ArrayLike`	:class:`Epoch` (absolute time) or seconds since TLE epoch.	required

Returns:

Type	Description
`Array`	6-element TEME state `[x, y, z, vx, vy, vz]` in m and m/s.

`compute_checksum(line)` ¶

Compute the TLE checksum for a line.

The checksum is the sum of all digit characters plus 1 for each minus sign, modulo 10, computed over the first 68 characters.

Parameters:

Name	Type	Description	Default
`line`	`str`	A TLE line string (at least 68 characters).	required

Returns:

Type	Description
`int`	The checksum digit (0-9).

`create_sgp4_propagator(line1, line2, gravity='wgs72')` ¶

Create a JIT-compatible SGP4 propagator from TLE lines.

This is the functional API that returns a parameter array and a propagation closure suitable for jax.jit and jax.vmap.

Parameters:

Name	Type	Description	Default
`line1`	`str`	First TLE line.	required
`line2`	`str`	Second TLE line.	required
`gravity`	`str \| EarthGravity`	Gravity model name (`'wgs72'`, `'wgs84'`, `'wgs72old'`) or an `EarthGravity` instance.	`'wgs72'`

Returns:

Type	Description
`tuple[Array, Callable[[ArrayLike], tuple[Array, Array]]]`	Tuple of `(params, propagate_fn)` where: - `params` is a flat `jnp.array` of satellite parameters - `propagate_fn(tsince)` takes time since epoch in minutes and returns `(r_km, v_kms)` in the TEME frame

`create_sgp4_propagator_from_elements(elements, gravity='wgs72')` ¶

Create a JIT-compatible SGP4 propagator from pre-parsed elements.

Accepts an :class:SGP4Elements dataclass (e.g. from parse_tle or parse_omm) and returns a parameter array and propagation closure.

Parameters:

Name	Type	Description	Default
`elements`	`SGP4Elements`	Parsed orbital elements from `parse_tle` or `parse_omm`.	required
`gravity`	`str \| EarthGravity`	Gravity model name (`'wgs72'`, `'wgs84'`, `'wgs72old'`) or an `EarthGravity` instance.	`'wgs72'`

Returns:

Type	Description
`tuple[Array, Callable[[ArrayLike], tuple[Array, Array]]]`	Tuple of `(params, propagate_fn)` where: - `params` is a flat `jnp.array` of satellite parameters - `propagate_fn(tsince)` takes time since epoch in minutes and returns `(r_km, v_kms)` in the TEME frame

`create_sgp4_propagator_from_gp_record(record, gravity='wgs72')` ¶

Create a JIT-compatible SGP4 propagator from a GPRecord.

Accepts a :class:~astrojax.GPRecord (e.g. from CelesTrak or SpaceTrack) and returns a parameter array and propagation closure.

Parameters:

Name	Type	Description	Default
`record`	`GPRecord`	A GP record from CelesTrak or SpaceTrack.	required
`gravity`	`str \| EarthGravity`	Gravity model name (`'wgs72'`, `'wgs84'`, `'wgs72old'`) or an `EarthGravity` instance.	`'wgs72'`

Returns:

Type	Description
`tuple[Array, Callable[[ArrayLike], tuple[Array, Array]]]`	Tuple of `(params, propagate_fn)` where: - `params` is a flat `jnp.array` of satellite parameters - `propagate_fn(tsince)` takes time since epoch in minutes and returns `(r_km, v_kms)` in the TEME frame

Raises:

Type	Description
`KeyError`	If the record is missing required fields.

`create_sgp4_propagator_from_omm(fields, gravity='wgs72')` ¶

Create a JIT-compatible SGP4 propagator from OMM fields.

Accepts a dictionary of OMM (Orbit Mean-Elements Message) field names and string values, as would be parsed from a CSV or XML OMM record.

Parameters:

Name	Type	Description	Default
`fields`	`dict[str, str]`	Dictionary mapping OMM field names to string values. See :func:`~astrojax.sgp4.parse_omm` for required keys.	required
`gravity`	`str \| EarthGravity`	Gravity model name (`'wgs72'`, `'wgs84'`, `'wgs72old'`) or an `EarthGravity` instance.	`'wgs72'`

Returns:

Type	Description
`tuple[Array, Callable[[ArrayLike], tuple[Array, Array]]]`	Tuple of `(params, propagate_fn)` where: - `params` is a flat `jnp.array` of satellite parameters - `propagate_fn(tsince)` takes time since epoch in minutes and returns `(r_km, v_kms)` in the TEME frame

Raises:

Type	Description
`KeyError`	If a required OMM field is missing.

`elements_to_array(elements)` ¶

Convert SGP4Elements to a flat JAX array for use with sgp4_init_jax.

The returned array has shape (11,) with elements in the order: jdsatepoch, jdsatepochF, no_kozai, ecco, inclo, nodeo, argpo, mo, bstar, ndot, nddot.

Parameters:

Name	Type	Description	Default
`elements`	`SGP4Elements`	Parsed TLE elements from `parse_tle` or `parse_omm`.	required

Returns:

Type	Description
`Array`	Array of shape `(11,)` containing the numeric orbital elements.

`gp_record_to_array(record)` ¶

Convert a GPRecord to a flat JAX array for use with sgp4_init_jax.

This is a convenience wrapper that calls record.to_sgp4_elements() followed by elements_to_array.

Parameters:

Name	Type	Description	Default
`record`	`GPRecord`	A GP record from CelesTrak or SpaceTrack.	required

Returns:

Type	Description
`Array`	Array of shape `(11,)` containing the numeric orbital elements.

Raises:

Type	Description
`KeyError`	If the record is missing required fields.

`omm_to_array(fields)` ¶

Convert OMM fields dict to a flat JAX array for use with sgp4_init_jax.

This is a convenience wrapper that calls parse_omm followed by elements_to_array.

Parameters:

Name	Type	Description	Default
`fields`	`dict[str, str]`	Dictionary mapping OMM field names to string values. See :func:`~astrojax.sgp4.parse_omm` for required keys.	required

Returns:

Type	Description
`Array`	Array of shape `(11,)` containing the numeric orbital elements.

Raises:

Type	Description
`KeyError`	If a required OMM field is missing.

`parse_omm(fields)` ¶

Parse OMM (Orbit Mean-Elements Message) fields into SGP4 orbital elements.

Accepts a dictionary of OMM field names and string values, as would be parsed from a CSV or XML OMM record.

Parameters:

Name	Type	Description	Default
`fields`	`dict[str, str]`	Dictionary mapping OMM field names to string values. Required keys: `EPOCH`, `MEAN_MOTION`, `ECCENTRICITY`, `INCLINATION`, `RA_OF_ASC_NODE`, `ARG_OF_PERICENTER`, `MEAN_ANOMALY`, `NORAD_CAT_ID`, `BSTAR`. Optional keys: `CLASSIFICATION_TYPE`, `OBJECT_ID`, `EPHEMERIS_TYPE`, `ELEMENT_SET_NO`, `REV_AT_EPOCH`, `MEAN_MOTION_DOT`, `MEAN_MOTION_DDOT`.	required

Returns:

Type	Description
`SGP4Elements`	Parsed orbital elements ready for SGP4 initialization.

Raises:

Type	Description
`KeyError`	If a required field is missing.

`parse_tle(line1, line2)` ¶

Parse a Two-Line Element set into SGP4 orbital elements.

Follows the fixed-column TLE format specification. Angular values are converted to radians and mean motion to rad/min for SGP4 internal use.

Parameters:

Name	Type	Description	Default
`line1`	`str`	First TLE line (69 characters including checksum).	required
`line2`	`str`	Second TLE line (69 characters including checksum).	required

Returns:

Type	Description
`SGP4Elements`	Parsed orbital elements ready for SGP4 initialization.

Raises:

Type	Description
`ValueError`	If lines fail format validation, checksum check, or satellite numbers don't match.

`sgp4_init(elements, gravity=WGS72, opsmode='i')` ¶

Initialize SGP4 satellite parameters from parsed TLE elements.

This function runs at Python time (not under JIT). It computes all the intermediate parameters needed by the SGP4 propagator and packs them into a flat JAX array.

Parameters:

Name	Type	Description	Default
`elements`	`SGP4Elements`	Parsed TLE elements from `parse_tle` or `parse_omm`.	required
`gravity`	`EarthGravity`	Earth gravity model constants.	`WGS72`
`opsmode`	`str`	Operation mode ('i' for improved, 'a' for AFSPC).	`'i'`

Returns:

Type	Description
`Array`	Tuple of `(params, method)` where `params` is a flat
`str`	`jnp.array` of shape `(_NUM_PARAMS,)` and `method` is
`tuple[Array, str]`	`'n'` (near-Earth) or `'d'` (deep-space).

`sgp4_init_jax(elements, gravity=WGS72, opsmode='i')` ¶

Initialize SGP4 satellite parameters (JAX, JIT-compatible).

Unlike sgp4_init, this function is compatible with jax.jit, jax.vmap, and jax.grad. It accepts a flat array of numeric orbital elements and returns a flat parameter array with an embedded method flag (0.0 = near-earth, 1.0 = deep-space).

Use with jax.jit::

init_jit = jax.jit(sgp4_init_jax, static_argnames=('gravity', 'opsmode'))
params = init_jit(elements_arr)

Parameters:

Name	Type	Description	Default
`elements`	`Array`	Array of shape `(11,)` containing the numeric orbital elements. Use `elements_to_array` to convert from `SGP4Elements`. Order: jdsatepoch, jdsatepochF, no_kozai, ecco, inclo, nodeo, argpo, mo, bstar, ndot, nddot.	required
`gravity`	`EarthGravity`	Earth gravity model constants. Treated as a static argument under JIT (use `static_argnames`).	`WGS72`
`opsmode`	`str`	Operation mode ('i' for improved, 'a' for AFSPC). Treated as a static argument under JIT.	`'i'`

Returns:

Type	Description
`Array`	Flat `jnp.array` of shape `(_NUM_PARAMS,)` with all SGP4
`Array`	parameters, including a method flag at index `_IDX["method"]`.

`sgp4_propagate(params, tsince, method, max_dspace_iters=200)` ¶

Propagate a satellite using SGP4/SDP4.

This is the main propagation entry point. The method flag selects near-Earth ('n') or deep-space ('d') code path at Python trace time, making it compatible with jax.jit.

Parameters:

Name	Type	Description	Default
`params`	`Array`	Flat parameter array from `sgp4_init`.	required
`tsince`	`ArrayLike`	Time since epoch in minutes.	required
`method`	`str`	`'n'` for near-Earth SGP4, `'d'` for deep-space SDP4.	required
`max_dspace_iters`	`int`	Maximum number of deep-space resonance integration steps. Each step covers 720 minutes. Default 200 (≈100 days). Only used when `method='d'`.	`200`

Returns:

Type	Description
`Array`	Tuple of `(r, v)` where `r` is position [km] and `v` is
`Array`	velocity [km/s], both as 3-element arrays in the TEME frame.

`sgp4_propagate_unbounded(params, tsince, method)` ¶

Propagate a satellite using SGP4/SDP4 with unbounded deep-space integration.

This variant uses jax.lax.while_loop for deep-space resonance integration, imposing no upper bound on propagation time. It supports forward-mode AD (jax.jacfwd / jax.jvp) but not reverse-mode AD (jax.grad / jax.vjp).

For near-earth satellites (method='n'), the behavior is identical to :func:sgp4_propagate.

Parameters:

Name	Type	Description	Default
`params`	`Array`	Flat parameter array from `sgp4_init`.	required
`tsince`	`ArrayLike`	Time since epoch in minutes.	required
`method`	`str`	`'n'` for near-Earth SGP4, `'d'` for deep-space SDP4.	required

Returns:

Type	Description
`Array`	Tuple of `(r, v)` where `r` is position [km] and `v` is
`Array`	velocity [km/s], both as 3-element arrays in the TEME frame.

`sgp4_propagate_unified(params, tsince, max_dspace_iters=200)` ¶

Propagate a satellite using SGP4/SDP4 with auto-detection (JAX, JIT-compatible).

Unlike sgp4_propagate, this function does not require a separate method string. It reads the method flag from params (set by sgp4_init_jax or sgp4_init) and dispatches to the correct propagation branch using jax.lax.cond.

This enables vmap over satellites with mixed near-earth and deep-space orbits in a single batch.

Parameters:

Name	Type	Description	Default
`params`	`Array`	Flat parameter array from `sgp4_init` or `sgp4_init_jax`.	required
`tsince`	`ArrayLike`	Time since epoch in minutes.	required
`max_dspace_iters`	`int`	Maximum number of deep-space resonance integration steps. Each step covers 720 minutes. Default 200 (≈100 days).	`200`

Returns:

Type	Description
`Array`	Tuple of `(r, v)` where `r` is position [km] and `v` is
`Array`	velocity [km/s], both as 3-element arrays in the TEME frame.

`sgp4_propagate_unified_unbounded(params, tsince)` ¶

Propagate a satellite using SGP4/SDP4 with unbounded deep-space integration and auto-detection.

This variant uses jax.lax.while_loop for deep-space resonance integration, imposing no upper bound on propagation time. It supports forward-mode AD (jax.jacfwd / jax.jvp) but not reverse-mode AD (jax.grad / jax.vjp).

Unlike :func:sgp4_propagate_unbounded, this function does not require a separate method string. It reads the method flag from params and dispatches using jax.lax.cond.

Parameters:

Name	Type	Description	Default
`params`	`Array`	Flat parameter array from `sgp4_init` or `sgp4_init_jax`.	required
`tsince`	`ArrayLike`	Time since epoch in minutes.	required

Returns:

Type	Description
`Array`	Tuple of `(r, v)` where `r` is position [km] and `v` is
`Array`	velocity [km/s], both as 3-element arrays in the TEME frame.

`validate_tle_line(line, line_number)` ¶

Validate a TLE line's format and checksum.

Parameters:

Name	Type	Description	Default
`line`	`str`	A TLE line string.	required
`line_number`	`int`	Expected line number (1 or 2).	required

Raises:

Type	Description
`ValueError`	If the line fails format or checksum validation.

SGP4¶

WGS72 = EarthGravity(tumin=(1.0 / _xke_72), mu=_mu_72, radiusearthkm=_re_72, xke=_xke_72, j2=_j2_72, j3=_j3_72, j4=_j4_72, j3oj2=(_j3_72 / _j2_72)) module-attribute ¶

WGS72OLD = EarthGravity(tumin=(1.0 / _xke_72old), mu=_mu_72old, radiusearthkm=_re_72old, xke=_xke_72old, j2=_j2_72old, j3=_j3_72old, j4=_j4_72old, j3oj2=(_j3_72old / _j2_72old)) module-attribute ¶

WGS84 = EarthGravity(tumin=(1.0 / _xke_84), mu=_mu_84, radiusearthkm=_re_84, xke=_xke_84, j2=_j2_84, j3=_j3_84, j4=_j4_84, j3oj2=(_j3_84 / _j2_84)) module-attribute ¶

EarthGravity ¶

SGP4Elements dataclass ¶

TLE ¶

M property ¶

argp property ¶

bstar property ¶

e property ¶

epoch property ¶

i property ¶

method property ¶

n property ¶

params property ¶

raan property ¶

satnum property ¶

from_elements(elements, gravity='wgs72') classmethod ¶

from_gp_record(record, gravity='wgs72') classmethod ¶

from_omm(fields, gravity='wgs72') classmethod ¶

propagate(tsince_min) ¶

state(t) ¶

state_gcrf(t, eop=None) ¶

state_itrf(t, eop=None) ¶

state_pef(t) ¶

state_teme(t) ¶

compute_checksum(line) ¶

create_sgp4_propagator(line1, line2, gravity='wgs72') ¶

create_sgp4_propagator_from_elements(elements, gravity='wgs72') ¶

create_sgp4_propagator_from_gp_record(record, gravity='wgs72') ¶

create_sgp4_propagator_from_omm(fields, gravity='wgs72') ¶

elements_to_array(elements) ¶

gp_record_to_array(record) ¶

omm_to_array(fields) ¶

parse_omm(fields) ¶

parse_tle(line1, line2) ¶

sgp4_init(elements, gravity=WGS72, opsmode='i') ¶

sgp4_init_jax(elements, gravity=WGS72, opsmode='i') ¶

sgp4_propagate(params, tsince, method, max_dspace_iters=200) ¶

sgp4_propagate_unbounded(params, tsince, method) ¶

sgp4_propagate_unified(params, tsince, max_dspace_iters=200) ¶

sgp4_propagate_unified_unbounded(params, tsince) ¶

validate_tle_line(line, line_number) ¶

`WGS72 = EarthGravity(tumin=(1.0 / _xke_72), mu=_mu_72, radiusearthkm=_re_72, xke=_xke_72, j2=_j2_72, j3=_j3_72, j4=_j4_72, j3oj2=(_j3_72 / _j2_72))` `module-attribute` ¶

`WGS72OLD = EarthGravity(tumin=(1.0 / _xke_72old), mu=_mu_72old, radiusearthkm=_re_72old, xke=_xke_72old, j2=_j2_72old, j3=_j3_72old, j4=_j4_72old, j3oj2=(_j3_72old / _j2_72old))` `module-attribute` ¶

`WGS84 = EarthGravity(tumin=(1.0 / _xke_84), mu=_mu_84, radiusearthkm=_re_84, xke=_xke_84, j2=_j2_84, j3=_j3_84, j4=_j4_84, j3oj2=(_j3_84 / _j2_84))` `module-attribute` ¶

`EarthGravity` ¶

`SGP4Elements` `dataclass` ¶

`TLE` ¶

`M` `property` ¶

`argp` `property` ¶

`bstar` `property` ¶

`e` `property` ¶

`epoch` `property` ¶

`i` `property` ¶

`method` `property` ¶

`n` `property` ¶

`params` `property` ¶

`raan` `property` ¶

`satnum` `property` ¶

`from_elements(elements, gravity='wgs72')` `classmethod` ¶

`from_gp_record(record, gravity='wgs72')` `classmethod` ¶

`from_omm(fields, gravity='wgs72')` `classmethod` ¶

`propagate(tsince_min)` ¶

`state(t)` ¶

`state_gcrf(t, eop=None)` ¶

`state_itrf(t, eop=None)` ¶

`state_pef(t)` ¶

`state_teme(t)` ¶

`compute_checksum(line)` ¶

`create_sgp4_propagator(line1, line2, gravity='wgs72')` ¶

`create_sgp4_propagator_from_elements(elements, gravity='wgs72')` ¶

`create_sgp4_propagator_from_gp_record(record, gravity='wgs72')` ¶

`create_sgp4_propagator_from_omm(fields, gravity='wgs72')` ¶

`elements_to_array(elements)` ¶

`gp_record_to_array(record)` ¶

`omm_to_array(fields)` ¶

`parse_omm(fields)` ¶

`parse_tle(line1, line2)` ¶

`sgp4_init(elements, gravity=WGS72, opsmode='i')` ¶

`sgp4_init_jax(elements, gravity=WGS72, opsmode='i')` ¶

`sgp4_propagate(params, tsince, method, max_dspace_iters=200)` ¶

`sgp4_propagate_unbounded(params, tsince, method)` ¶

`sgp4_propagate_unified(params, tsince, max_dspace_iters=200)` ¶

`sgp4_propagate_unified_unbounded(params, tsince)` ¶

`validate_tle_line(line, line_number)` ¶