Metadata-Version: 1.0
Name: sgp4
Version: 1.1
Summary: Track earth satellite TLE orbits using up-to-date 2010 version of SGP4
Home-page: https://github.com/brandon-rhodes/python-sgp4
Author: Brandon Rhodes
Author-email: brandon@rhodesmill.org
License: MIT
Description:
        This Python package computes the position and velocity of an
        earth-orbiting satellite, given the satellite's TLE orbital elements
        from a source like `Celestrak <http://celestrak.com/>`_.  It implements
        the most recent version of SGP4, and is regularly run against the SGP4
        test suite to make sure that its satellite position predictions **agree
        to within 1 µm** of the predictions of the standard C++ implementation
        of the algorithm.  This error is far less than the 1–3 km/day by which
        satellites themselves deviate from the ideal orbits described in TLE
        files.

        The C++ function names have been retained, since users may already be
        familiar with this library in other languages.  Here is how to compute
        the x,y,z position and velocity for Vanguard 1 at 12:50:19 on 29
        June 2000:

        >>> from sgp4.earth_gravity import wgs72
        >>> from sgp4.io import twoline2rv
        >>> line1 = ('1 00005U 58002B   00179.78495062  '
        ...          '.00000023  00000-0  28098-4 0  4753')
        >>> line2 = ('2 00005  34.2682 348.7242 1859667 '
        ...          '331.7664  19.3264 10.82419157413667')
        >>>
        >>> satellite = twoline2rv(line1, line2, wgs72)
        >>> position, velocity = satellite.propagate(
        ...     2000, 6, 29, 12, 50, 19)
        >>>
        >>> position
        [5576.056952400586, -3999.371134576452, -1521.9571594376037]
        >>> velocity
        [4.772627303379319, 5.119817120959591, 4.275553909172126]

        The position vector measures the satellite position in **meters** from
        the center of the earth.  The velocity is the rate at which those same
        three parameters are changing, expressed in **meters per second**.

        There are three gravity models available that you can import from the
        ``earth_gravity`` module:

        * ``wgs72``
        * ``wgs72old``
        * ``wgs84``

        The ``wgs72`` model seems to be the most commonly used in the satellite
        tracking community, and is probably the model behind most TLE elements
        that are available for download.

        The ``twoline2rv()`` function returns a ``Satellite`` object whose
        attributes carry the data loaded from the TLE entry.
        Most of this class's hundred-plus attributes are intermediate values
        of interest only to the propagation algorithm itself.  Here are the
        attributes set by ``sgp4.io.twoline2rv()`` in which users are likely
        to be interested:

        ``satnum``
            Unique satellite number given in the TLE file.
        ``epochyr``
            Full four-digit year of this element set's epoch moment.
        ``epochdays``
            Fractional days into the year of the epoch moment.
        ``jdsatepoch``
            Julian date of the epoch (computed from ``epochyr`` and ``epochdays``).
        ``ndot``
            First time derivative of the mean motion (ignored by SGP4).
        ``nddot``
            Second time derivative of the mean motion (ignored by SGP4).
        ``bstar``
            Ballistic drag coefficient B* in inverse earth radii.
        ``inclo``
            Inclination in radians.
        ``nodeo``
            Right ascension of ascending node in radians.
        ``ecco``
            Eccentricity.
        ``argpo``
            Argument of perigee in radians.
        ``mo``
            Mean anomaly in radians.
        ``no``
            Mean motion in radians per minute.



        This implementation passes all of the automated tests in the August 2010
        release of the reference implementation of SGP4 by Vallado et al., who
        originally published their revision of SGP4 in 2006:

            Vallado, David A., Paul Crawford, Richard Hujsak, and T.S. Kelso, “Revisiting Spacetrack Report #3,” presented at the AIAA/AAS Astrodynamics Specialist Conference, Keystone, CO, 2006 August 21–24.

        If you would like to review the paper, it is `available online
        <http://www.celestrak.com/publications/AIAA/2006-6753/>`_.  You can
        always download the latest version of their code for comparison against
        this Python module (or other implementations) at `AIAA-2006-6753.zip
        <http://www.celestrak.com/publications/AIAA/2006-6753/AIAA-2006-6753.zip>`_.

        This module was adapted from Vallado's C++ code since its revision date
        was the most recently updated SGP4 implementation in their zip file:

        * C++, August 2010
        * Fortran, August 2008
        * Pascal, August 2008
        * Matlab, May 2008
        * Java, July 2005

        Changelog
        ---------

        | 2012-11-22 — 1.1 — Python 3 compatibility; more documentation
        | 2012-08-27 — 1.0 — Initial release


Platform: UNKNOWN
Classifier: Development Status :: 5 - Production/Stable
Classifier: Intended Audience :: Science/Research
Classifier: License :: OSI Approved :: MIT License
Classifier: Programming Language :: Python :: 2
Classifier: Programming Language :: Python :: 2.6
Classifier: Programming Language :: Python :: 2.7
Classifier: Programming Language :: Python :: 3
Classifier: Programming Language :: Python :: 3.1
Classifier: Programming Language :: Python :: 3.2
Classifier: Topic :: Scientific/Engineering :: Astronomy