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- update to 2.23:
  * Tweaked tests to resolve breakage introduced by Python 3.12.
    writing code that will break when the C++ extension is available.
     epochdays and epochyr satellite attributes.
- yank Python 2 package
- initial package with version 2.12

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- update to 2.22:
  * Added a ``satnum_str`` attribute, exposing the fact that the C++ now
    stores the satellite number as a string; and check that ``satnum`` is
    never greater than 339999.
  * Fixed the units of the ``nddot`` attribute when the value is loaded
    from an OMM record.  (Since the TLE computation itself ignores this
    attribute, this did not affect any satellite positions.)
  * Enhanced the fallback Python version of ``twoline2rv()`` to verify
    that TLE lines are ASCII, and added documentation using it to
    double-check TLEs that might suffer from non-ASCII characters.
  * If the user doesn’t set a satellite’s ``classification``, it now
    defaults to ``'U'`` for ‘unclassified’.
  * Added ``dump_satrec()`` to the ``sgp4.conveniences`` module.
  * Fixed the ``Satrec`` attribute ``.error``, which was previously
    building a nonsense integer from the wrong data in memory.
  * Removed ``.whichconst`` from Python ``Satrec``, to help users avoid
    writing code that will break when the C++ extension is available.

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- Update to version 2.20
  * Taught sgp4init() to round both epochdays and jdsatepochF to
    the same 8 decimal places used for the date fraction in a TLE,
    if the user-supplied epoch itself has 8 or fewer digits behind
    the decimal point. This should make it easier to build
    satellites that round-trip to TLE format with perfect accuracy.
  * Fixed how export_tle() formats the BSTAR field when its value,
    if written in scientific notation, has a positive exponent.
  * Fixed the epochyr assigned by sgp4init() so years before 2000
    have two digits instead of three (for example, so that 1980
    produces an epochyr of 80 instead of 980).
- Release 2.19
  * Extended the documentation on the Python Package Index and in
    the module docstring so it lists every Satrec attribute that
    this library exposes; even the more obscure ones might be
    useful to folks working to analyze satellite orbits.
- Release 2.18
  * If a TLE satellite number lacks the required 5 digits,
    twoline2rv() now gives the underlying C++ library a little
    help so it can still parse the classification and
    international designator correctly.
  * The Satrec attributes jdsatepoch, jdsatepochF, epochyr, and
    epochdays are now writeable, so users can adjust their values
    manually — which should make up for the fact that the sgp4init
    () method can’t set them with full floating point precision.
- Release 2.17
  * Fixed where in the output array the sgp4_array() method writes
    NaN values when an SGP4 propagation fails.

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- Update to Version 2.16
  * Fixed ``days2mdhms()`` rounding to always match TLE epoch.
- Changes in Version 2.15
  * Fixed parsing of the ``satnum`` TLE field in the Python
    fallback code, when the field has a leading space
  * added OMM export routine.
- skip python36 (NEP 29, NumPy 1.20)

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- Update to Version 2.16
  * Fixed ``days2mdhms()`` rounding to always match TLE epoch.
- Changes in Version 2.15
  * Fixed parsing of the ``satnum`` TLE field in the Python
    fallback code, when the field has a leading space
  * added OMM export routine.
- skip python36 (NEP 29, NumPy 1.20)

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- Update to Version 2.14
  * New data formats: added OMM message support for both XML and
    CSV, and added support for the new Alpha-5 extension to TLE
    files.
- Drop sgp4-fix69-precision.patch merged upstream

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- Update to version 2.13
  *  Enhanced sgp4init() with custom code that also sets the
     epochdays and epochyr satellite attributes.

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initialized devel package after accepting 820694

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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. 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 0.1 mm with the predictions of the standard distribution 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.

If your platform supports it, this package compiles the verbatim source code
from the official C++ version of SGP4. You can call the routine directly, or
through an array API that loops over arrays of satellites and arrays of times
with machine code instead of Python. Otherwise, a slower but reliable Python
implementation of SGP4 is used instead.

Submitting because it is an optional package for python-astropy

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