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{
"type": "package",
"path": "./tudat-multidoc/docstrings",
"file": "__package__.yaml",
"_implicit_name": "docstrings",
"config": {
"name": "tudatpy",
"version": null
},
"summary": "TU Delft Astrodynamics Toolbox in Python, or tudatpy, is a library that\nprimarily exposes the powerful set of C++ libraries, Tudat. TudatPy\naims at accelerating the implementation of Tudat simulations, providing\nan interface between Tudat and popular machine learning frameworks and\nestablishing a platform to provide quality education in the field of\nastrodynamics.\n",
"extended_summary": null,
"routine_listings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null,
"enums": null,
"classes": null,
"functions": null,
"constants": null,
"modules": [
"astro",
"interface",
"numerical_simulation",
"plotting",
"util"
],
"name": "tudatpy",
"version": null,
"astro": {
"type": "package",
"path": "./tudat-multidoc/docstrings/astro",
"file": "__package__.yaml",
"_implicit_name": "astro",
"config": null,
"summary": "Fundamental astrodynamics calculations.",
"extended_summary": "Provides diverse low-level to support astrodynamics calculations.\nThis module can be used as standalone together with the math module.\nThe other modules make extensive use of the functionality exposed here.\n",
"routine_listings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null,
"enums": null,
"classes": null,
"functions": null,
"constants": null,
"modules": [
"frame_conversion",
"element_conversion"
],
"name": "astro",
"version": null,
"frame_conversion": {
"type": "module",
"path": "./tudat-multidoc/docstrings/astro",
"file": "frame_conversion.yaml",
"_implicit_name": "frame_conversion",
"config": null,
"summary": "Conversions between different reference frames.\n",
"extended_summary": "This module provide a variety of functions and classes to convert\nbetween different reference frames. Functionality to convert between\ndifferent state representations is provided in the\n:ref:`\\`\\`element_conversion\\`\\`` module.\n",
"routine_listings": null,
"see_also": null,
"notes": "- All reference frames used should be assumed as right handed:\n :math:`\\mathbf{X}\\times\\mathbf{Y}=\\mathbf{Z}`.\n\n- We distinguish between two different uses of the term 'inertial:\n\n * An *inertial origin*: the frame has a non-accelerating origin. On solar\n system scales, the solar system barycenter (SSB) is considered to be \n the only inertial origin.\n * An *inertial orientation*: the unit axes of the frame are non-rotating\n with respect to the celestial background. This module is concerned \n primarily with conversions between different orientations.\n\n- Examples of and inertial origin include J2000 (a.k.a EME2000), as\n well as the SPICE-defined ECLIPJ2000 frame (see `this description <https://tudat-space.readthedocs.io/en/latest/_src_user_guide/environment_setup/use_of_reference_frames.html#predefined-orientations>`_\n on our user guide). The use of the ICRF frame (difference from J2000\n is <0.1 arcseconds) in Tudat is presently limited to the\n :ref:`\\`\\`numerical_simulation\\`\\`` model, see\n :func:`~tudatpy.numerical_simulation.environment_setup.rotation_model.gcrs_to_itrs`.\n\n.. raw:: html\n\n <object\n data=\"_static/J2000_.svg\"\n type=\"image/svg+xml\"\n class=\"center invertible\">\n </object>\n",
"references": ".. [1] Archinal, B.A., Acton, C.H., A\u2019Hearn, M.F. et al. Report of\n the IAU Working Group on Cartographic Coordinates and\n Rotational Elements: 2015. Celest Mech Dyn Astr 130, 22\n (2018). https://doi.org/10.1007/s10569-017-9805-5\n",
"examples": null,
"enums": null,
"classes": null,
"functions": [
{
"name": "inertial_to_rsw_rotation_matrix",
"short_summary": "Computes the rotation matrix from inertial to RSW frame.\n",
"deprecation_warning": null,
"extended_summary": "Function to compute the rotation matrix from inertial to RSW frame.\nThe RSW frame is defined by the state of a body w.r.t. to some\ncentral body. The x-axis of the RSW frame points away from the\norigin, and the y-axis lies in the orbital plane, and is positive\nfor in the direction of the velocity vector (but is not colinear\nwith the velocity vector, except for circular orbits). The z-axis\nis perpendicular to the orbital plane, and completes the\nright-handed coordinate system.\n",
"parameters": [
{
"name": "inertial_cartesian_state",
"type": "numpy.ndarray",
"description": "Cartesian state, in an inertial frame, for which the rotation\nmatrix is to be calculated. Note that the RSW frame is defined\nw.r.t. some central body, and this Cartesian state must be\ndefined w.r.t. that central body (e.g. central body at the\norigin).\n"
}
],
"returns": {
"name": null,
"type": "numpy.ndarray",
"description": "Rotation matrix from inertial to RSW frame."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "rsw_to_inertial_rotation_matrix",
"short_summary": "Computes the rotation matrix from RSW to inertial frame.\n",
"deprecation_warning": null,
"extended_summary": "Function to compute the rotation matrix from RSW to inertial. The\nRSW frame is defined by the state of a body w.r.t. to some central\nbody. The x-axis of the RSW frame points away from the origin, and\nthe y-axis lies in the orbital plane, and is positive for in the\ndirection of the velocity vector (but is not colinear with the\nvelocity vector, except for circular orbits). The z-axis is\nperpendicular to the orbital plane, and completes the right-handed\ncoordinate system.\n",
"parameters": [
{
"name": "inertial_cartesian_state",
"type": "numpy.ndarray",
"description": "Cartesian state, in an inertial frame, for which the rotation\nmatrix is to be calculated. Note that the RSW frame is defined\nw.r.t. some central body, and this Cartesian state must be\ndefined w.r.t. that central body (e.g. central body at the\norigin).\n"
}
],
"returns": {
"name": null,
"type": "numpy.ndarray",
"description": "Rotation matrix from RSW to inertial frame."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "inertial_to_tnw_rotation_matrix",
"short_summary": "Computes the rotation matrix from inertial to TNW frame.\n",
"deprecation_warning": null,
"extended_summary": "Function to compute the rotation matrix from inertial to TNW frame.\nThe TNW frame is defined by the state of a body w.r.t. to some\ncentral body. The x-axis of the TNW frame points along the velocity\nvector, and the y-axis lies in the orbital plane, and is positive\nin the direction away from the central body (or positive **towards**\nthe central body if the ``n_axis_points_away_from_central_body``\nvariable is set to false, see below). The z-axis is perpendicular\nto the orbital plane, and completes the right-handed coordinate\nsystem.\n",
"parameters": [
{
"name": "inertial_cartesian_state",
"type": "numpy.ndarray",
"description": "Cartesian state, in an inertial frame, for which the rotation\nmatrix is to be calculated. Note that the RSW frame is defined\nw.r.t. some central body, and this Cartesian state must be\ndefined w.r.t. that central body (e.g. central body at the\norigin).\n"
},
{
"name": "n_axis_points_away_from_central_body",
"type": "Boolean",
"description": "Boolean (default is ``True``) defining whether the N axis of the\nTNW frame points away from the central body (if ``True``) or\ntowards the central body (if ``False``).\n"
}
],
"returns": {
"name": null,
"type": "numpy.ndarray",
"description": "Rotation matrix from inertial to TNW frame."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "tnw_to_inertial_rotation_matrix",
"short_summary": "Computes the rotation matrix from TNW to inertial frame.\n",
"deprecation_warning": null,
"extended_summary": "Function to compute the rotation matrix from TNW to inertial frame.\nThe TNW frame is defined by the state of a body w.r.t. to some\ncentral body. The x-axis of the TNW frame points along the velocity\nvector, and the y-axis lies in the orbital plane, and is positive\nin the direction away from the central body (or positive **towards**\nthe central body if the ``n_axis_points_away_from_central_body``\nvariable is set to false, see below). The z-axis is perpendicular\nto the orbital plane, and completes the right-handed coordinate\nsystem.\n",
"parameters": [
{
"name": "inertial_cartesian_state",
"type": "numpy.ndarray",
"description": "Cartesian state, in an inertial frame, for which the rotation\nmatrix is to be calculated. Note that the TNW frame is defined\nw.r.t. some central body, and this Cartesian state must be\ndefined w.r.t. that central body (e.g. central body at the\norigin).\n"
},
{
"name": "n_axis_points_away_from_central_body",
"type": "bool",
"description": "Boolean (default=``True``) defining whether the N axis of the\nTNW frame points away from the central body (if ``True``) or\ntowards the central body (if ``False``).\n"
}
],
"returns": {
"name": null,
"type": "numpy.ndarray",
"description": "Rotation matrix from TNW to inertial frame"
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "inertial_to_body_fixed_rotation_matrix",
"short_summary": "Computes the rotation matrix from inertial to body-fixed frame.\n",
"deprecation_warning": null,
"extended_summary": "Function to compute the rotation matrix from inertial to body-fixed\nframe, using typical pole right ascension (:math:`\\alpha`), pole\ndeclination (:math:`\\delta`), and prime meridian longitude\n(:math:`W`) angles.\n",
"parameters": [
{
"name": "pole_declination",
"type": "float",
"description": "Declination of body pole in inertial frame (:math:`\\delta`).\n"
},
{
"name": "pole_right_ascension",
"type": "float",
"description": "Right ascension of body pole in inertial frame (:math:`\\alpha`).\n"
},
{
"name": "prime_meridian_longitude",
"type": "float",
"description": "Longitude of prime meridian w.r.t. intermediate frame\n(:math:`W`).\n"
}
],
"returns": {
"name": null,
"type": "numpy.ndarray",
"description": "Rotation matrix from inertial to body-fixed frame"
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": "This definition of a body-fixed orientation is used by, for\ninstance, the IAU Working Group on Cartographic Coordinates and\nRotational Elements. Rotation is performed by a succesive z-x-z\nEuler angle rotation (see Archinal et al. [1]_).\n",
"references": null,
"examples": null
},
{
"name": "body_fixed_to_inertial_rotation_matrix",
"short_summary": "Computes the rotation matrix from body-fixed to inertial frame.\n",
"deprecation_warning": null,
"extended_summary": "Function to compute the rotation matrix from body-fixed to inertial\nframe, using typical pole right ascension (:math:`\\alpha`), pole\ndeclination (:math:`\\delta`), and prime meridian longitude\n(:math:`W`) angles.\n",
"parameters": [
{
"name": "pole_declination",
"type": "float",
"description": "Declination of body pole in inertial frame (:math:`\\delta`).\n"
},
{
"name": "pole_right_ascension",
"type": "float",
"description": "Right ascension of body pole in inertial frame (:math:`\\alpha`).\n"
},
{
"name": "prime_meridian_longitude",
"type": "float",
"description": "Longitude of prime meridian w.r.t. intermediate frame\n(:math:`W`).\n"
}
],
"returns": {
"name": null,
"type": "numpy.ndarray",
"description": "Rotation matrix from body-fixed to inertial frame.\n"
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": "This definition of a body-fixed orientation is used by,\nfor instance, the IAU Working Group on Cartographic Coordinates\nand Rotational Elements. Rotation is performed by a succesive z-x-z\nEuler angle rotation (see Archinal et al. [1]_).\n",
"references": null,
"examples": null
}
],
"constants": null,
"name": "frame_conversion",
"version": null,
"inertial_to_rsw_rotation_matrix": "\nComputes the rotation matrix from inertial to RSW frame.\n\n\nFunction to compute the rotation matrix from inertial to RSW frame.\nThe RSW frame is defined by the state of a body w.r.t. to some\ncentral body. The x-axis of the RSW frame points away from the\norigin, and the y-axis lies in the orbital plane, and is positive\nfor in the direction of the velocity vector (but is not colinear\nwith the velocity vector, except for circular orbits). The z-axis\nis perpendicular to the orbital plane, and completes the\nright-handed coordinate system.\n\n\nParameters\n----------\ninertial_cartesian_state : numpy.ndarray\n Cartesian state, in an inertial frame, for which the rotation\n matrix is to be calculated. Note that the RSW frame is defined\n w.r.t. some central body, and this Cartesian state must be\n defined w.r.t. that central body (e.g. central body at the\n origin).\n\nReturns\n-------\nnumpy.ndarray\n Rotation matrix from inertial to RSW frame.\n\n\n\n\n\n",
"rsw_to_inertial_rotation_matrix": "\nComputes the rotation matrix from RSW to inertial frame.\n\n\nFunction to compute the rotation matrix from RSW to inertial. The\nRSW frame is defined by the state of a body w.r.t. to some central\nbody. The x-axis of the RSW frame points away from the origin, and\nthe y-axis lies in the orbital plane, and is positive for in the\ndirection of the velocity vector (but is not colinear with the\nvelocity vector, except for circular orbits). The z-axis is\nperpendicular to the orbital plane, and completes the right-handed\ncoordinate system.\n\n\nParameters\n----------\ninertial_cartesian_state : numpy.ndarray\n Cartesian state, in an inertial frame, for which the rotation\n matrix is to be calculated. Note that the RSW frame is defined\n w.r.t. some central body, and this Cartesian state must be\n defined w.r.t. that central body (e.g. central body at the\n origin).\n\nReturns\n-------\nnumpy.ndarray\n Rotation matrix from RSW to inertial frame.\n\n\n\n\n\n",
"inertial_to_tnw_rotation_matrix": "\nComputes the rotation matrix from inertial to TNW frame.\n\n\nFunction to compute the rotation matrix from inertial to TNW frame.\nThe TNW frame is defined by the state of a body w.r.t. to some\ncentral body. The x-axis of the TNW frame points along the velocity\nvector, and the y-axis lies in the orbital plane, and is positive\nin the direction away from the central body (or positive **towards**\nthe central body if the ``n_axis_points_away_from_central_body``\nvariable is set to false, see below). The z-axis is perpendicular\nto the orbital plane, and completes the right-handed coordinate\nsystem.\n\n\nParameters\n----------\ninertial_cartesian_state : numpy.ndarray\n Cartesian state, in an inertial frame, for which the rotation\n matrix is to be calculated. Note that the RSW frame is defined\n w.r.t. some central body, and this Cartesian state must be\n defined w.r.t. that central body (e.g. central body at the\n origin).\n\nn_axis_points_away_from_central_body : Boolean\n Boolean (default is ``True``) defining whether the N axis of the\n TNW frame points away from the central body (if ``True``) or\n towards the central body (if ``False``).\n\nReturns\n-------\nnumpy.ndarray\n Rotation matrix from inertial to TNW frame.\n\n\n\n\n\n",
"tnw_to_inertial_rotation_matrix": "\nComputes the rotation matrix from TNW to inertial frame.\n\n\nFunction to compute the rotation matrix from TNW to inertial frame.\nThe TNW frame is defined by the state of a body w.r.t. to some\ncentral body. The x-axis of the TNW frame points along the velocity\nvector, and the y-axis lies in the orbital plane, and is positive\nin the direction away from the central body (or positive **towards**\nthe central body if the ``n_axis_points_away_from_central_body``\nvariable is set to false, see below). The z-axis is perpendicular\nto the orbital plane, and completes the right-handed coordinate\nsystem.\n\n\nParameters\n----------\ninertial_cartesian_state : numpy.ndarray\n Cartesian state, in an inertial frame, for which the rotation\n matrix is to be calculated. Note that the TNW frame is defined\n w.r.t. some central body, and this Cartesian state must be\n defined w.r.t. that central body (e.g. central body at the\n origin).\n\nn_axis_points_away_from_central_body : bool\n Boolean (default=``True``) defining whether the N axis of the\n TNW frame points away from the central body (if ``True``) or\n towards the central body (if ``False``).\n\nReturns\n-------\nnumpy.ndarray\n Rotation matrix from TNW to inertial frame\n\n\n\n\n\n",
"inertial_to_body_fixed_rotation_matrix": "\nComputes the rotation matrix from inertial to body-fixed frame.\n\n\nFunction to compute the rotation matrix from inertial to body-fixed\nframe, using typical pole right ascension (:math:`\\alpha`), pole\ndeclination (:math:`\\delta`), and prime meridian longitude\n(:math:`W`) angles.\n\n\nParameters\n----------\npole_declination : float\n Declination of body pole in inertial frame (:math:`\\delta`).\n\npole_right_ascension : float\n Right ascension of body pole in inertial frame (:math:`\\alpha`).\n\nprime_meridian_longitude : float\n Longitude of prime meridian w.r.t. intermediate frame\n (:math:`W`).\n\nReturns\n-------\nnumpy.ndarray\n Rotation matrix from inertial to body-fixed frame\n\n\n\nNotes\n-----\nThis definition of a body-fixed orientation is used by, for\ninstance, the IAU Working Group on Cartographic Coordinates and\nRotational Elements. Rotation is performed by a succesive z-x-z\nEuler angle rotation (see Archinal et al. [1]_).\n\n\n\n",
"body_fixed_to_inertial_rotation_matrix": "\nComputes the rotation matrix from body-fixed to inertial frame.\n\n\nFunction to compute the rotation matrix from body-fixed to inertial\nframe, using typical pole right ascension (:math:`\\alpha`), pole\ndeclination (:math:`\\delta`), and prime meridian longitude\n(:math:`W`) angles.\n\n\nParameters\n----------\npole_declination : float\n Declination of body pole in inertial frame (:math:`\\delta`).\n\npole_right_ascension : float\n Right ascension of body pole in inertial frame (:math:`\\alpha`).\n\nprime_meridian_longitude : float\n Longitude of prime meridian w.r.t. intermediate frame\n (:math:`W`).\n\nReturns\n-------\nnumpy.ndarray\n Rotation matrix from body-fixed to inertial frame.\n\n\n\n\nNotes\n-----\nThis definition of a body-fixed orientation is used by,\nfor instance, the IAU Working Group on Cartographic Coordinates\nand Rotational Elements. Rotation is performed by a succesive z-x-z\nEuler angle rotation (see Archinal et al. [1]_).\n\n\n\n"
},
"element_conversion": {
"type": "module",
"path": "./tudat-multidoc/docstrings/astro",
"file": "element_conversion.yaml",
"_implicit_name": "element_conversion",
"config": null,
"summary": "Functions for converting between sets of orbital elements.",
"extended_summary": "This module provide a variety of functions and classes to\nconvert between different representations of translational and\nrotational states (e.g. Cartesian \u2194 Keplerian).\n\n.. note:: Rotations between different reference frames are provided in\n the :ref:`\\`\\`frame_conversion\\`\\`` module.\n",
"routine_listings": null,
"see_also": null,
"notes": "\nIn general, unless specified otherwise, the Keplerian elements are\nordered as:\n\n+-------+--------------------------------------------------------------------------------------+\n| Index | Keplerian Element |\n+-------+--------------------------------------------------------------------------------------+\n| ``0`` | Semi-major axis (except if eccentricity = ``1.0``, then represents semi-latus rectum |\n+-------+--------------------------------------------------------------------------------------+\n| ``1`` | Eccentricity |\n+-------+--------------------------------------------------------------------------------------+\n| ``2`` | Inclination |\n+-------+--------------------------------------------------------------------------------------+\n| ``3`` | Argument of periapsis |\n+-------+--------------------------------------------------------------------------------------+\n| ``4`` | Longitude of ascending node |\n+-------+--------------------------------------------------------------------------------------+\n| ``5`` | True anomaly |\n+-------+--------------------------------------------------------------------------------------+\n",
"references": null,
"examples": null,
"enums": null,
"classes": null,
"functions": [
{
"name": "cartesian_to_keplerian",
"short_summary": "Convert Cartesian to Keplerian elements.",
"deprecation_warning": null,
"extended_summary": "Function to convert from Cartesian elements to standard Keplerian\nelements.\n\n.. note:: See module level documentation for the standard ordering\n convention of Keplerian elements used.\n",
"parameters": [
{
"name": "cartesian_elements",
"type": "numpy.ndarray",
"description": "Cartesian state that is to be converted to Keplerian elements"
},
{
"name": "gravitational_parameter",
"type": "float",
"description": "Gravitational parameter of central body used for conversion"
}
],
"returns": {
"name": null,
"type": "numpy.ndarray",
"description": "Keplerian elements, as computed from Cartesian element input."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "keplerian_to_cartesian",
"short_summary": "Convert Keplerian elements to Cartesian.",
"deprecation_warning": null,
"extended_summary": "Function to convert from standard Keplerian elements to Cartesian\nelements.\n\n.. note:: See module level documentation for the standard ordering\n convention of Keplerian elements used.\n",
"parameters": [
{
"name": "keplerian_elements",
"type": "numpy.ndarray",
"description": "Keplerian state that is to be converted to Cartesian elements"
},
{
"name": "gravitational_parameter",
"type": "float",
"description": "Gravitational parameter of central body used for conversion"
}
],
"returns": {
"name": null,
"type": "numpy.ndarray",
"description": "Keplerian elements, as computed from Cartesian element input."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "keplerian_to_cartesian_elementwise",
"short_summary": "Convert Keplerian elements to Cartesian, with elementwise input.",
"deprecation_warning": null,
"extended_summary": "Function to convert from standard Keplerian elements to Cartesian\nelements, with elementwise input.\n\n.. note:: The final Keplerian element is always the true anomaly.\n",
"parameters": [
{
"name": "semi_major_axis",
"type": "float",
"description": "Semi-major axis (except if eccentricity = 1.0, then represents semi-latus rectum)"
},
{
"name": "eccentricity",
"type": "float",
"description": "Eccentricity"
},
{
"name": "inclination",
"type": "float",
"description": "Inclination"
},
{
"name": "argument_of_periapsis",
"type": "float",
"description": "Argument of periapsis"
},
{
"name": "longitude_of_ascending_node",
"type": "float",
"description": "Longitude of ascending node"
},
{
"name": "true_anomaly",
"type": "float",
"description": "True anomaly"
},
{
"name": "gravitational_parameter",
"type": "float",
"description": "Gravitational parameter of central body used for conversion"
}
],
"returns": {
"name": null,
"type": "numpy.ndarray",
"description": "Keplerian elements, as computed from Cartesian element input."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
}
],
"constants": null,
"name": "element_conversion",
"version": null,
"cartesian_to_keplerian": "\nConvert Cartesian to Keplerian elements.\n\nFunction to convert from Cartesian elements to standard Keplerian\nelements.\n\n.. note:: See module level documentation for the standard ordering\n convention of Keplerian elements used.\n\n\nParameters\n----------\ncartesian_elements : numpy.ndarray\n Cartesian state that is to be converted to Keplerian elements\ngravitational_parameter : float\n Gravitational parameter of central body used for conversion\nReturns\n-------\nnumpy.ndarray\n Keplerian elements, as computed from Cartesian element input.\n\n\n\n\n\n",
"keplerian_to_cartesian": "\nConvert Keplerian elements to Cartesian.\n\nFunction to convert from standard Keplerian elements to Cartesian\nelements.\n\n.. note:: See module level documentation for the standard ordering\n convention of Keplerian elements used.\n\n\nParameters\n----------\nkeplerian_elements : numpy.ndarray\n Keplerian state that is to be converted to Cartesian elements\ngravitational_parameter : float\n Gravitational parameter of central body used for conversion\nReturns\n-------\nnumpy.ndarray\n Keplerian elements, as computed from Cartesian element input.\n\n\n\n\n\n",
"keplerian_to_cartesian_elementwise": "\nConvert Keplerian elements to Cartesian, with elementwise input.\n\nFunction to convert from standard Keplerian elements to Cartesian\nelements, with elementwise input.\n\n.. note:: The final Keplerian element is always the true anomaly.\n\n\nParameters\n----------\nsemi_major_axis : float\n Semi-major axis (except if eccentricity = 1.0, then represents semi-latus rectum)\neccentricity : float\n Eccentricity\ninclination : float\n Inclination\nargument_of_periapsis : float\n Argument of periapsis\nlongitude_of_ascending_node : float\n Longitude of ascending node\ntrue_anomaly : float\n True anomaly\ngravitational_parameter : float\n Gravitational parameter of central body used for conversion\nReturns\n-------\nnumpy.ndarray\n Keplerian elements, as computed from Cartesian element input.\n\n\n\n\n\n"
}
},
"interface": {
"type": "package",
"path": "./tudat-multidoc/docstrings/interface",
"file": "__package__.yaml",
"_implicit_name": "interface",
"config": null,
"summary": null,
"extended_summary": null,
"routine_listings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null,
"enums": null,
"classes": null,
"functions": null,
"constants": null,
"modules": [
"spice"
],
"name": "interface",
"version": null,
"spice": {
"type": "module",
"path": "./tudat-multidoc/docstrings/interface",
"file": "spice.yaml",
"_implicit_name": "spice",
"config": null,
"summary": null,
"extended_summary": "This module provides an interface to NAIF's ``SPICE`` package.\n",
"routine_listings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null,
"enums": null,
"classes": [
{
"name": "SpiceEphemeris",
"short_summary": "Ephemeris derived class which retrieves the state of a body directly from the SPICE library.",
"deprecation_warning": null,
"extended_summary": "Ephemeris derived class which retrieves the state of a body directly from the SPICE library.\nThe body of which the ephemeris is to be retrieved, as well as the origin and orientation\nof the reference frame in which the states are returned, and any corrections that are\napplied, are defined once during object construction.\n",
"parameters": null,
"attributes": null,
"properties": null,
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null,
"methods": [
{
"name": "__init__",
"short_summary": "Constructor.",
"deprecation_warning": null,
"extended_summary": "Constructor, sets the input variables for the calls to the spice function to retrieve state.",
"parameters": [
{
"name": "target_body_name",
"type": null,
"description": "Name of body of which the ephemeris is to be calculated."
},
{
"name": "observer_body_name",
"type": null,
"description": "Name of body relative to which the ephemeris is to be calculated."
},
{
"name": "correct_for_stellar_aberration",
"type": null,
"description": "Boolean whether to correct for stellar Aberration in retrieved values of (observed state).\n"
},
{
"name": "correct_for_light_time_aberration",
"type": null,
"description": "Boolean whether to correct for light time in retrieved values of (observed state).\n"
},
{
"name": "converge_ligh_time_aberration",
"type": null,
"description": "Boolean whether to use single iteration or max. 3 iterations for calculating light time.\n"
},
{
"name": "reference_frame_name",
"type": null,
"description": "Name of the reference frame in which the ephemeris is to be calculated.\n"
},
{
"name": "reference_julian_day",
"type": null,
"description": "Reference julian day w.r.t. which ephemeris is evaluated.\n"
}
],
"returns": null,
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "get_cartesian_state",
"short_summary": "Get Cartesian state from ephemeris.",
"deprecation_warning": null,
"extended_summary": " Returns Cartesian state from ephemeris at given Julian day.",
"parameters": [
{
"name": "seconds_since_epoch",
"type": "float",
"description": "Seconds since epoch at which ephemeris is to be evaluated."
}
],
"returns": null,
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
}
],
"autoclass": null
}
],
"functions": [
{
"name": "convert_julian_date_to_ephemeris_time",
"short_summary": "Convert a Julian date to ephemeris time (equivalent to TDB in Spice).",
"deprecation_warning": null,
"extended_summary": "Function to convert a Julian date to ephemeris time, which is\nequivalent to barycentric dynamical time. A leap second kernel\nmust have been loaded to use this function.\n",
"parameters": [
{
"name": "julian_date",
"type": "int",
"description": "Julian date that is to be converted to ephemeris time."
}
],
"returns": {
"name": "ephemeris_time",
"type": "float",
"description": "Julian date calculated from ephemeris time."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "convert_ephemeris_time_to_julian_date",
"short_summary": "Convert ephemeris time (equivalent to TDB) to a Julian date.",
"deprecation_warning": null,
"extended_summary": "Function to convert ephemeris time, which is nearly equal to\nbarycentric dynamical time, to the Julian date. A leap second\nkernel must have been loaded to use this function.\n",
"parameters": [
{
"name": "ephemeris_time",
"type": "float",
"description": "Ephemeris time that is to be converted to Julian date."
}
],
"returns": {
"name": "julian_date",
"type": "float",
"description": "Julian date calculated from ephemeris time."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "convert_date_string_to_ephemeris_time",
"short_summary": "Converts a date string to ephemeris time.",
"deprecation_warning": null,
"extended_summary": "Function to convert a date string, for instance\n1988 June 13, 3:29:48 to ephemeris time, wrapper for `str2et_c`\nspice function.\n",
"parameters": [
{
"name": "date_string",
"type": "str",
"description": "String representing the date. See documentation of spice\nfunction `str2et_c` for details on supported formats.\n"
}
],
"returns": {
"name": "ephemeris_time",
"type": "str",
"description": "Ephemeris time corresponding to given date_string."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "get_body_cartesian_state_at_epoch",
"short_summary": "Get Cartesian state of a body, as observed from another body.",
"deprecation_warning": null,
"extended_summary": "This function returns the state of a body, relative to another\nbody, in a frame specified by the user. Corrections for light-time\ncorrection and stellar aberration can be applied to obtain the\nstate of one of the bodies, as observed from the other. Wrapper\nfor `spkezr_c` spice function.\n",
"parameters": [
{
"name": "target_body_name",
"type": "str",
"description": "Name of the body of which the state is to be obtained. A kernel\nwith the ephemeris of this body must have been loaded. The\nstring must be a spice-recognized name or ID.\n"
},
{
"name": "observer_body_name",
"type": "str",
"description": "Name of the body relative to which the state is to be obtained.\nA kernel with the ephemeris of this body must have been loaded.\nThe string must be a spice-recognized name or ID.\n"
},
{
"name": "reference_frame_name",
"type": "str",
"description": "The spice-recognized name of the reference frame in which the\nstate is to be returned. Spice kernel(s) required to perform\nthe necessary conversion from the states of the target and\nobserver bodies to this frame need to have been loaded.\n"
},
{
"name": "aberration_corrections",
"type": "str",
"description": "Setting for correction for setting corrections. See Spice\ndocumentation for extended discussion.\nShort summary:\n\n- NONE: none\n- LT: light time corrected (one iteration for calculation)\n- CN: light time corrected (multiple iterations, max 3) for calculation\n- S: Stellar aberration corrected.\n- XLT and XCN: can be provided to make the ephemeris time input argument the transmission time, instead of reception time. Arguments can be combined (i.e.\"LT+S\" or \"XCN+S\").\n"
},
{
"name": "ephemeris_time",
"type": "float",
"description": "Observation time (or transmission time of observed light, see description\nof aberrationCorrections).\n"
}
],
"returns": {
"name": "cartesian_state_vector",
"type": "np.ndarray[6,]",
"description": "Cartesian state vector (x,y,z, position+velocity)."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "get_body_cartesian_position_at_epoch",
"short_summary": "Get Cartesian position of a body, as observed from another body.",
"deprecation_warning": null,
"extended_summary": "This function returns the position of a body, relative to another\nbody, in a frame specified by the user. Corrections for light-time\ncorrection and stellar aberration can be applied to obtain the\nstate of one of the bodies, as observed from the other. Wrapper\nfor `spkpos_c` spice function.\n",
"parameters": [
{
"name": "target_body_name",
"type": "str",
"description": "Name of the body of which the state is to be obtained. A kernel\nwith the ephemeris of this body must have been loaded. The\nstring must be a spice-recognized name or ID.\n"
},
{
"name": "observer_body_name",
"type": "str",
"description": "Name of the body relative to which the state is to be obtained.\nA kernel with the ephemeris of this body must have been loaded.\nThe string must be a spice-recognized name or ID.\n"
},
{
"name": "reference_frame_name",
"type": "str",
"description": "The spice-recognized name of the reference frame in which the\nstate is to be returned. Spice kernel(s) required to perform\nthe necessary conversion from the states of the target and\nobserver bodies to this frame need to have been loaded.\n"
},
{
"name": "aberration_corrections",
"type": "str",
"description": "Setting for correction for setting corrections. See Spice\ndocumentation for extended discussion.\nShort summary:\n\n- NONE: none\n- LT: light time corrected (one iteration for calculation)\n- CN: light time corrected (multiple iterations, max 3) for calculation,\n- S: Stellar aberration corrected.\n- XLT and XCN: can be provided to make the ephemeris time input argument the transmission time, instead of reception time. Arguments can be combined (i.e.\"LT+S\" or \"XCN+S\").\n"
},
{
"name": "ephemeris_time",
"type": "float",
"description": "Observation time (or transmission time of observed light, see description\nof aberrationCorrections).\n"
}
],
"returns": null,
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "get_cartesian_state_from_tle_at_epoch",
"short_summary": "Get Cartesian state of a satellite from its two-line element set at a specified epoch.",
"deprecation_warning": null,
"extended_summary": "This function retrieves the state of a satellite at a certain epoch\nby propagating the SGP or SDP models (near-Earth resp. deep space)\nwith the given two-line elements (TLE). This function serves as a\nwrapper for the `ev2lin_` function in CSpice.\n",
"parameters": [
{
"name": "epoch",
"type": "float",
"description": "Time in seconds since J2000 at which the state is to be retrieved."
},
{
"name": "tle",
"type": ":class:`~tudatpy.kernel.astro.ephemerides.Tle`",
"description": "Shared pointer to a Tle object containing the SGP/SDP model parameters as derived from the element set."
}
],
"returns": {
"name": "cartesian_state_vector",
"type": "np.ndarray[6,]",
"description": "Cartesian state vector (x,y,z, position+velocity)."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "compute_rotation_quaternion_between_frames",
"short_summary": "Compute quaternion of rotation between two frames.",
"deprecation_warning": null,
"extended_summary": "This function computes the quaternion of rotation between two\nframes at a given time instant. kernels defining the two frames,\nas well as any required intermediate frames, at the requested\ntime must have been loaded. Wrapper for `pxform_c` spice function.\n",
"parameters": [
{
"name": "original_frame",
"type": null,
"description": "Reference frame from which the rotation is made."
},
{
"name": "new_frame",
"type": null,
"description": "Reference frame to which the rotation is made."
},
{
"name": "ephemeris_time",
"type": null,
"description": "Value of ephemeris time at which rotation is to be determined."
}
],
"returns": {
"name": null,
"type": null,
"description": "Rotation quaternion from original to new frame at given time."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "compute_rotation_matrix_derivative_between_frames",
"short_summary": "Computes time derivative of rotation matrix between two frames.",
"deprecation_warning": null,
"extended_summary": "This function computes the derivative of the rotation matrix\nbetween two frames at a given time instant. kernels defining the\ntwo frames, as well as any required intermediate frames, at the\nrequested time must have been loaded. Wrapper for (part of) `sxform_c` spice function.\n",
"parameters": [
{
"name": "original_frame",
"type": null,
"description": "Reference frame from which the rotation is made."
},
{
"name": "new_frame",
"type": null,
"description": "Reference frame to which the rotation is made."
},
{
"name": "ephemeris_time",
"type": null,
"description": "Value of ephemeris time at which rotation is to be determined."
}
],
"returns": {
"name": null,
"type": null,
"description": "Time derivative of rotation matrix from original to new frame at given time."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "get_angular_velocity_vector_of_frame_in_original_frame",
"short_summary": "Computes the angular velocity of one frame w.r.t. to another frame.",
"deprecation_warning": null,
"extended_summary": "Computes the angular velocity of one frame w.r.t. to another frame.\nat a given time instant. kernels defining the two frames, as well\nas any required intermediate frames, at the requested time must\nhave been loaded. Wrapper for `xf2rav_c`_ spice function (utilizing `sxform_c`_).\n\n.. _`xf2rav_c`: https://naif.jpl.nasa.gov/pub/naif/toolkit_docs/C/cspice/xf2rav_c.html\n.. _`sxform_c`: https://naif.jpl.nasa.gov/pub/naif/toolkit_docs/C/cspice/sxform_c.html\n",
"parameters": [
{
"name": "original_frame",
"type": null,
"description": "Reference frame from which the rotation is made."
},
{
"name": "new_frame",
"type": null,
"description": "Reference frame to which the rotation is made."
},
{
"name": "ephemeris_time",
"type": null,
"description": "Value of ephemeris time at which rotation is to be determined."
}
],
"returns": {
"name": null,
"type": null,
"description": "Angular velocity of newFrame w.r.t. originalFrame, expressed in originalFrame."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "get_body_properties",
"short_summary": "Get property of a body from Spice.",
"deprecation_warning": null,
"extended_summary": "Function to retrieve a property of a body from Spice, wraps the bodvrd_c Spice function.\n",
"parameters": [
{
"name": "body_name",
"type": null,
"description": "Name of the body of which the property is to be retrieved."
},
{
"name": "property",
"type": null,
"description": "Name of the property that is to be retrieved. Naming conventions can be found\nin the `bodvrd_c`_ function documentation.\n\n.. _`bodvrd_c`: https://naif.jpl.nasa.gov/pub/naif/toolkit_docs/C/cspice/bodvrd_c.html\n"
},
{
"name": "maximum_number_of_values",
"type": "int",
"description": "Number of values by which the property is expressed (i.e. 1 for\ngravitational parameter, 3 for tri-axial ellipsoid principal axes).\n"
}
],
"returns": {
"name": null,
"type": null,
"description": "Property value(s) expressed in an STL vector of doubles."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": "Function returns values with distance unit km, not m!\n",
"references": null,
"examples": null
},
{
"name": "get_body_gravitational_parameter",
"short_summary": "Get gravitational parameter of a body.",
"deprecation_warning": null,
"extended_summary": "This function retrieves the gravitational parameter of a body.\nWraps the `bodvrd_c`_ spice function with \"GM\" as property type.\n\n.. _`bodvrd_c`: https://naif.jpl.nasa.gov/pub/naif/toolkit_docs/C/cspice/bodvrd_c.html\n",
"parameters": [
{
"name": "body",
"type": null,
"description": "Name of the body of which the parameter is to be retrieved."
}
],
"returns": {
"name": null,
"type": null,
"description": "Gravitational parameter of requested body."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "get_average_radius",
"short_summary": "Get the (arithmetic) mean of the three principal axes of the tri-axial ellipsoid shape.",
"deprecation_warning": null,
"extended_summary": "Returns the (arithmetic) mean of the three principal axes of the\ntri-axial ellipsoid shape of the requested body. Uses the `bodvrd_c` spice function with \"RADII\" as property type.\n\n.. _`bodvrd_c`: https://naif.jpl.nasa.gov/pub/naif/toolkit_docs/C/cspice/bodvrd_c.html\n",
"parameters": [
{
"name": "body",
"type": null,
"description": "Name of the body of which the average radius is to be retrieved."
}
],
"returns": {
"name": null,
"type": null,
"description": "Arithmetic mean of principal axes of tri-axial ellipsoid shape model of body."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "convert_body_name_to_naif_id",
"short_summary": "Convert a body name to its NAIF identification number.",
"deprecation_warning": null,
"extended_summary": "This function converts a body name to its NAIF identification\nnumber. The NAIF id number is required for a number of spice\nfunctions, whereas the name is easily interpretable by the user.\nWrapper for the ``bods2c_c`` function.\n",
"parameters": [
{
"name": "body_name",
"type": null,
"description": "Name of the body for which NAIF id is to be retrieved."
}
],
"returns": {
"name": null,
"type": null,
"description": "NAIF id number for the body with bodyName."
},
"yields": null,
"other_parameters": null,
"raises": null,
"warns": null,
"warnings": null,
"see_also": null,
"notes": null,
"references": null,
"examples": null
},
{
"name": "check_body_property_in_kernel_pool",
"short_summary": "Check if a certain property of a body is in the kernel pool.",
"deprecation_warning": null,
"extended_summary": "This function checks if a certain property of a body is in the\nkernel pool. These properties are defined in PCK kernels. Their\nnames are given in the kernel file, typical names can be found in\nthe Spice documentation. Wrapper for the `bodfnd_c`_ function.\n\n.. _`bodfnd_c`: https://naif.jpl.nasa.gov/pub/naif/toolkit_docs/C/cspice/bodfnd_c.html\n",
"parameters": [
{
"name": "body_name",
"type": null,
"description": "Name of the body of which the property is to be checked."
},
{
"name": "body_property",
"type": null,
"description": "Name of the property of which the presence is to be checked, not case-sensitive."