Hello community,
here is the log from the commit of package python-sgp4 for openSUSE:Factory
checked in at 2020-10-16 16:16:53
++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++
Comparing /work/SRC/openSUSE:Factory/python-sgp4 (Old)
and /work/SRC/openSUSE:Factory/.python-sgp4.new.3486 (New)
++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++
Package is "python-sgp4"
Fri Oct 16 16:16:53 2020 rev:2 rq:842091 version:2.13
Changes:
--------
--- /work/SRC/openSUSE:Factory/python-sgp4/python-sgp4.changes 2020-07-14
08:00:20.329993475 +0200
+++ /work/SRC/openSUSE:Factory/.python-sgp4.new.3486/python-sgp4.changes
2020-10-16 16:17:05.864742556 +0200
@@ -1,0 +2,7 @@
+Fri Oct 16 09:49:21 UTC 2020 - Benjamin Greiner <c...@bnavigator.de>
+
+- Update to version 2.13
+ * Enhanced sgp4init() with custom code that also sets the
+ epochdays and epochyr satellite attributes.
+
+-------------------------------------------------------------------
Old:
----
sgp4-2.12.tar.gz
New:
----
sgp4-2.13.tar.gz
++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++++
Other differences:
------------------
++++++ python-sgp4.spec ++++++
--- /var/tmp/diff_new_pack.epjOvh/_old 2020-10-16 16:17:08.852743473 +0200
+++ /var/tmp/diff_new_pack.epjOvh/_new 2020-10-16 16:17:08.856743474 +0200
@@ -19,7 +19,7 @@
%{?!python_module:%define python_module() python-%{**} python3-%{**}}
%define skip_python2 1
Name: python-sgp4
-Version: 2.12
+Version: 2.13
Release: 0
Summary: Track earth satellite TLE orbits using up-to-date 2010 version
of SGP4
License: MIT
@@ -52,8 +52,8 @@
%prep
%setup -q -n sgp4-%{version}
cp %{SOURCE99} .
-# ease precision tolerances for flaky platforms
-sed -i 's/GRAVITY_DIGITS = 12/GRAVITY_DIGITS = 10/' sgp4/tests.py
+# ease precision tolerances
https://github.com/brandon-rhodes/python-sgp4/issues/69
+sed -i 's/GRAVITY_DIGITS = (/GRAVITY_DIGITS = 10\nGRAVITY_DIGITS_UPSTREAM =(/'
sgp4/tests.py
sed -i 's/error = 2e-7/error = 2e-5/' sgp4/tests.py
%build
@@ -72,7 +72,6 @@
# Only the doctests acually import the compiled extension and fail if it is
not present
%pytest_arch --pyargs sgp4 --doctest-modules
-
%files %{python_files}
%license LICENSE
%{python_sitearch}/sgp4
++++++ sgp4-2.12.tar.gz -> sgp4-2.13.tar.gz ++++++
diff -urN '--exclude=CVS' '--exclude=.cvsignore' '--exclude=.svn'
'--exclude=.svnignore' old/sgp4-2.12/PKG-INFO new/sgp4-2.13/PKG-INFO
--- old/sgp4-2.12/PKG-INFO 2020-05-28 20:12:01.000000000 +0200
+++ new/sgp4-2.13/PKG-INFO 2020-10-15 01:51:09.000000000 +0200
@@ -1,6 +1,6 @@
Metadata-Version: 1.1
Name: sgp4
-Version: 2.12
+Version: 2.13
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
@@ -9,7 +9,7 @@
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
+ from a source like `Celestrak <https://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 0.1 mm** with the predictions of the standard distribution of
@@ -37,9 +37,9 @@
For conversions into other coordinate frames, look for a comprehensive
astronomy library that is built atop this one, like the `Skyfield
- <http://rhodesmill.org/skyfield/>`_ library:
+ <https://rhodesmill.org/skyfield/>`_ library:
- http://rhodesmill.org/skyfield/earth-satellites.html
+ https://rhodesmill.org/skyfield/earth-satellites.html
Usage
-----
@@ -59,9 +59,9 @@
>>> e, r, v = satellite.sgp4(jd, fr)
>>> e
0
- >>> print(r)
+ >>> print(r) # True Equator Mean Equinox position (km)
(-6102.44..., -986.33..., -2820.31...)
- >>> print(v)
+ >>> print(v) # True Equator Mean Equinox velocity (km/s)
(-1.45..., -5.52..., 5.10...)
As input, you can provide either:
@@ -234,6 +234,9 @@
[-3.85 6.28 -1.85]
[-3.91 6.25 -1.83]]]
+ Attributes
+ ----------
+
The attributes of a ``Satrec`` object carry the data loaded from the
TLE
entry.
Most of this class's hundred-plus attributes are intermediate values
@@ -331,6 +334,10 @@
To compute the “epoch” value, simply take a normal Julian date and
subtract ``2433281.5`` days.
+ In addition to setting the attributes natively set by the underlying
+ ``sgp4init()`` routine, this library also goes ahead and sets the date
+ fields ``epochyr``, ``epochdays``, ``jdsatepoch``, and ``jdsatepochF``.
+
The character provided as the second argument can be ``'a'`` to run the
computations so that they are compatible with the old Air Force Space
Command edition of the library, or ``'i'`` to run the new and improved
@@ -353,10 +360,10 @@
21–24.
If you would like to review the paper, it is `available online
- <http://www.celestrak.com/publications/AIAA/2006-6753/>`_. You can
+ <https://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>`_.
+
<https://www.celestrak.com/publications/AIAA/2006-6753/AIAA-2006-6753.zip>`_.
For developers
--------------
@@ -386,6 +393,7 @@
Changelog
---------
+ | 2020-10-14 — 2.13 — Enhanced ``sgp4init()`` with custom code that
also sets the ``epochdays`` and ``epochyr`` satellite attributes.
| 2020-05-28 — 2.12 — Moved the decision of whether to set the locale
during ``twoline2rv()`` from import time to runtime, for users who change
locales after their application is up and running.
| 2020-05-24 — 2.11 — Fixed a regression in how dates are split into
hours, minutes, and seconds that would sometimes produce a time whose
second=60, crashing the pure-Python version of the library.
| 2020-05-22 — 2.10 — Switch the locale temporarily to ``C`` during
the C++ accelerated ``twoline2rv()``, since it does not protect its
``sscanf()`` calls from locales that, like German, expect comma decimal points
instead of the period decimal points always used in a TLE.
diff -urN '--exclude=CVS' '--exclude=.cvsignore' '--exclude=.svn'
'--exclude=.svnignore' old/sgp4-2.12/extension/wrapper.cpp
new/sgp4-2.13/extension/wrapper.cpp
--- old/sgp4-2.12/extension/wrapper.cpp 2020-05-28 20:08:47.000000000 +0200
+++ new/sgp4-2.13/extension/wrapper.cpp 2020-10-15 01:36:35.000000000 +0200
@@ -179,7 +179,13 @@
bstar, ndot, nddot, ecco, argpo, inclo, mo, no_kozai,
nodeo, satrec);
- /* Populate jdsatepoch and jdsatepochF as SGP4Funcs::twoline2rv does */
+ /* Populate date fields that SGP4Funcs::twoline2rv would set. */
+ int y, m, d, H, M;
+ double S, jan0jd, jan0fr /* always comes out 0.0 */;
+ SGP4Funcs::invjday(2433281.5, epoch, y, m, d, H, M, S);
+ SGP4Funcs::jday(y, 1, 0, 0, 0, 0.0, jan0jd, jan0fr);
+ satrec.epochyr = y % 1000;
+ satrec.epochdays = 2433281.5 - jan0jd + epoch;
satrec.jdsatepochF = modf(epoch, &satrec.jdsatepoch);
satrec.jdsatepoch += 2433281.5;
diff -urN '--exclude=CVS' '--exclude=.cvsignore' '--exclude=.svn'
'--exclude=.svnignore' old/sgp4-2.12/setup.py new/sgp4-2.13/setup.py
--- old/sgp4-2.12/setup.py 2020-05-28 20:08:47.000000000 +0200
+++ new/sgp4-2.13/setup.py 2020-10-15 01:36:35.000000000 +0200
@@ -34,7 +34,7 @@
))
setup(name = 'sgp4',
- version = '2.12',
+ version = '2.13',
description = description,
long_description = long_description,
license = 'MIT',
diff -urN '--exclude=CVS' '--exclude=.cvsignore' '--exclude=.svn'
'--exclude=.svnignore' old/sgp4-2.12/sgp4/__init__.py
new/sgp4-2.13/sgp4/__init__.py
--- old/sgp4-2.12/sgp4/__init__.py 2020-05-28 20:08:47.000000000 +0200
+++ new/sgp4-2.13/sgp4/__init__.py 2020-10-15 01:36:35.000000000 +0200
@@ -3,7 +3,7 @@
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
+from a source like `Celestrak <https://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 0.1 mm** with the predictions of the standard distribution of
@@ -31,9 +31,9 @@
For conversions into other coordinate frames, look for a comprehensive
astronomy library that is built atop this one, like the `Skyfield
-<http://rhodesmill.org/skyfield/>`_ library:
+<https://rhodesmill.org/skyfield/>`_ library:
-http://rhodesmill.org/skyfield/earth-satellites.html
+https://rhodesmill.org/skyfield/earth-satellites.html
Usage
-----
@@ -53,9 +53,9 @@
>>> e, r, v = satellite.sgp4(jd, fr)
>>> e
0
->>> print(r)
+>>> print(r) # True Equator Mean Equinox position (km)
(-6102.44..., -986.33..., -2820.31...)
->>> print(v)
+>>> print(v) # True Equator Mean Equinox velocity (km/s)
(-1.45..., -5.52..., 5.10...)
As input, you can provide either:
@@ -228,6 +228,9 @@
[-3.85 6.28 -1.85]
[-3.91 6.25 -1.83]]]
+Attributes
+----------
+
The attributes of a ``Satrec`` object carry the data loaded from the TLE
entry. Look at the class's documentation for details.
@@ -292,6 +295,10 @@
To compute the “epoch” value, simply take a normal Julian date and
subtract ``2433281.5`` days.
+In addition to setting the attributes natively set by the underlying
+``sgp4init()`` routine, this library also goes ahead and sets the date
+fields ``epochyr``, ``epochdays``, ``jdsatepoch``, and ``jdsatepochF``.
+
The character provided as the second argument can be ``'a'`` to run the
computations so that they are compatible with the old Air Force Space
Command edition of the library, or ``'i'`` to run the new and improved
@@ -314,10 +321,10 @@
21–24.
If you would like to review the paper, it is `available online
-<http://www.celestrak.com/publications/AIAA/2006-6753/>`_. You can
+<https://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>`_.
+<https://www.celestrak.com/publications/AIAA/2006-6753/AIAA-2006-6753.zip>`_.
For developers
--------------
@@ -347,6 +354,7 @@
Changelog
---------
+| 2020-10-14 — 2.13 — Enhanced ``sgp4init()`` with custom code that also sets
the ``epochdays`` and ``epochyr`` satellite attributes.
| 2020-05-28 — 2.12 — Moved the decision of whether to set the locale during
``twoline2rv()`` from import time to runtime, for users who change locales
after their application is up and running.
| 2020-05-24 — 2.11 — Fixed a regression in how dates are split into hours,
minutes, and seconds that would sometimes produce a time whose second=60,
crashing the pure-Python version of the library.
| 2020-05-22 — 2.10 — Switch the locale temporarily to ``C`` during the C++
accelerated ``twoline2rv()``, since it does not protect its ``sscanf()`` calls
from locales that, like German, expect comma decimal points instead of the
period decimal points always used in a TLE.
diff -urN '--exclude=CVS' '--exclude=.cvsignore' '--exclude=.svn'
'--exclude=.svnignore' old/sgp4-2.12/sgp4/model.py new/sgp4-2.13/sgp4/model.py
--- old/sgp4-2.12/sgp4/model.py 2020-05-21 20:03:40.000000000 +0200
+++ new/sgp4-2.13/sgp4/model.py 2020-10-15 01:36:35.000000000 +0200
@@ -1,7 +1,7 @@
"""The Satellite class."""
from sgp4.earth_gravity import wgs72old, wgs72, wgs84
-from sgp4.ext import days2mdhms, jday
+from sgp4.ext import days2mdhms, invjday, jday
from sgp4.functions import jday as jday2
from sgp4.io import twoline2rv
from sgp4.propagation import sgp4, sgp4init
@@ -70,8 +70,15 @@
def sgp4init(self, whichconst, opsmode, satnum, epoch, bstar,
ndot, nddot, ecco, argpo, inclo, mo, no_kozai, nodeo):
whichconst = gravity_constants[whichconst]
+
+ y, m, d, H, M, S = invjday(epoch + 2433281.5)
+ jan0epoch = jday(y, 1, 0, 0, 0, 0.0) - 2433281.5
+
+ self.epochyr = y % 1000
+ self.epochdays = epoch - jan0epoch
self.jdsatepoch, self.jdsatepochF = divmod(epoch, 1.0)
self.jdsatepoch += 2433281.5
+
sgp4init(whichconst, opsmode, satnum, epoch, bstar, ndot, nddot,
ecco, argpo, inclo, mo, no_kozai, nodeo, self)
diff -urN '--exclude=CVS' '--exclude=.cvsignore' '--exclude=.svn'
'--exclude=.svnignore' old/sgp4-2.12/sgp4/omm.py new/sgp4-2.13/sgp4/omm.py
--- old/sgp4-2.12/sgp4/omm.py 1970-01-01 01:00:00.000000000 +0100
+++ new/sgp4-2.13/sgp4/omm.py 2020-10-15 01:36:35.000000000 +0200
@@ -0,0 +1,44 @@
+"""Support for the new Orbit Mean-Elements Message format for TLE data."""
+
+import csv
+import xml.etree.ElementTree as ET
+from datetime import datetime
+from math import pi
+from sgp4.api import WGS72
+
+def parse_csv(file):
+ return csv.DictReader(file)
+
+def parse_xml(file):
+ root = ET.parse(file).getroot()
+ for segment in root.findall('.//segment'):
+ metadata = segment.find('metadata')
+ data = segment.find('data')
+ meanElements = data.find('meanElements')
+ tleParameters = data.find('tleParameters')
+ fields = {}
+ for element in metadata, meanElements, tleParameters:
+ fields.update((field.tag, field.text) for field in element)
+ yield fields
+
+_epoch0 = datetime(1949, 12, 31)
+_to_radians = pi / 180.0
+_ndot_units = 1036800.0 / pi # See SGP4.cpp for details.
+
+def initialize(sat, fields):
+ epoch_datetime = datetime.strptime(fields['EPOCH'], '%Y-%m-%dT%H:%M:%S.%f')
+ epoch = (epoch_datetime - _epoch0).total_seconds() / 86400.0
+
+ argpo = float(fields['ARG_OF_PERICENTER']) * _to_radians
+ bstar = float(fields['BSTAR'])
+ ecco = float(fields['ECCENTRICITY'])
+ inclo = float(fields['INCLINATION']) * _to_radians
+ mo = float(fields['MEAN_ANOMALY']) * _to_radians
+ nddot = float(fields['MEAN_MOTION_DDOT'])
+ ndot = float(fields['MEAN_MOTION_DOT']) / _ndot_units
+ no_kozai = float(fields['MEAN_MOTION']) / 720.0 * pi
+ nodeo = float(fields['RA_OF_ASC_NODE']) * _to_radians
+ satnum = int(fields['NORAD_CAT_ID'])
+
+ sat.sgp4init(WGS72, 'i', satnum, epoch, bstar, ndot, nddot, ecco,
+ argpo, inclo, mo, no_kozai, nodeo)
diff -urN '--exclude=CVS' '--exclude=.cvsignore' '--exclude=.svn'
'--exclude=.svnignore' old/sgp4-2.12/sgp4/tests.py new/sgp4-2.13/sgp4/tests.py
--- old/sgp4-2.12/sgp4/tests.py 2020-05-25 03:00:56.000000000 +0200
+++ new/sgp4-2.13/sgp4/tests.py 2020-10-15 01:36:35.000000000 +0200
@@ -6,18 +6,24 @@
from unittest import TestCase, main
import datetime as dt
+import platform
import re
import sys
from doctest import DocTestSuite, ELLIPSIS
from math import pi, isnan
from pkgutil import get_data
+try:
+ from io import StringIO
+except ImportError:
+ from StringIO import StringIO
+
from sgp4.api import WGS72OLD, WGS72, WGS84, Satrec, jday, accelerated
from sgp4.earth_gravity import wgs72
from sgp4.ext import invjday, newtonnu, rv2coe
from sgp4.functions import days2mdhms, _day_of_year_to_month_day
from sgp4.propagation import sgp4, sgp4init
-from sgp4 import conveniences, io
+from sgp4 import conveniences, io, omm
from sgp4.exporter import export_tle
import sgp4.model as model
@@ -38,6 +44,7 @@
'satnum': 5,
'operationmode': 'i',
# Time
+ 'epochyr': 0,
'jdsatepoch': 2451722.5,
# Orbit
'bstar': 2.8098e-05,
@@ -51,7 +58,6 @@
'nodeo': 6.08638547138321,
}
VANGUARD_EPOCH = 18441.7849506199999894
-VANGUARD_EPOCHDAYS = 179.78495062
# Handle deprecated assertRaisesRegexp, but allow its use Python 2.6 and 2.7
if sys.version_info[:2] == (2, 7) or sys.version_info[:2] == (2, 6):
@@ -64,12 +70,10 @@
def test_satrec_built_with_twoline2rv():
sat = Satrec.twoline2rv(LINE1, LINE2)
verify_vanguard_1(sat)
- assertEqual(sat.epochdays, VANGUARD_EPOCHDAYS)
def test_legacy_built_with_twoline2rv():
sat = io.twoline2rv(LINE1, LINE2, wgs72)
verify_vanguard_1(sat, legacy=True)
- assertEqual(sat.epochdays, VANGUARD_EPOCHDAYS)
def test_satrec_initialized_with_sgp4init():
# epochyr and epochdays are not set by sgp4init
@@ -232,7 +236,14 @@
sat.sgp4init(WGS84, 'i', VANGUARD_ATTRS['satnum'], VANGUARD_EPOCH, *args)
assert_wgs84(sat)
-GRAVITY_DIGITS = 12 if accelerated else 4
+GRAVITY_DIGITS = (
+ # Why don't Python and C agree more closely?
+ 4 if not accelerated
+ # See https://github.com/conda-forge/sgp4-feedstock/pull/19 for details.
+ else 11 if platform.system() != 'Linux'
+ # Insist on very high precision on my Linux laptop.
+ else 12
+)
def assert_wgs72old(sat):
e, r, v = sat.sgp4_tsince(309.67110720001529)
@@ -377,6 +388,7 @@
if legacy:
attrs = attrs.copy()
+ del attrs['epochyr']
del attrs['jdsatepoch']
for name, value in attrs.items():
@@ -388,6 +400,7 @@
raise e
if not legacy:
+ assertAlmostEqual(sat.epochdays, 179.78495062, delta=3e-14)
assertAlmostEqual(sat.jdsatepochF, 0.78495062, delta=1e-13)
def sgp4init_args(d):
@@ -605,6 +618,73 @@
)
# ----------------------------------------------------------------------
+# NEW "OMM" FORMAT TESTS
+
+
+# https://celestrak.com/satcat/tle.php?CATNR=5
+VANGUARD_TLE = """\
+VANGUARD 1 \n\
+1 00005U 58002B 20287.20333880 -.00000016 00000-0 -22483-4 0 9998
+2 00005 34.2443 225.5254 1845686 162.2516 205.2356 10.84869164218149
+"""
+
+# https://celestrak.com/NORAD/elements/gp.php?CATNR=00005&FORMAT=XML
+VANGUARD_XML = """\
+<?xml version="1.0" encoding="UTF-8"?>
+<ndm xmlns:xsi="https://www.w3.org/2001/XMLSchema-instance";
xsi:noNamespaceSchemaLocation="https://sanaregistry.org/r/ndmxml/ndmxml-1.0-master.xsd";>
+<omm id="CCSDS_OMM_VERS" version="2.0">
+<header><CREATION_DATE/><ORIGINATOR/></header><body><segment><metadata><OBJECT_NAME>VANGUARD
1</OBJECT_NAME><OBJECT_ID>1958-002B</OBJECT_ID><CENTER_NAME>EARTH</CENTER_NAME><REF_FRAME>TEME</REF_FRAME><TIME_SYSTEM>UTC</TIME_SYSTEM><MEAN_ELEMENT_THEORY>SGP4</MEAN_ELEMENT_THEORY></metadata><data><meanElements><EPOCH>2020-10-13T04:52:48.472320</EPOCH><MEAN_MOTION>10.84869164</MEAN_MOTION><ECCENTRICITY>.1845686</ECCENTRICITY><INCLINATION>34.2443</INCLINATION><RA_OF_ASC_NODE>225.5254</RA_OF_ASC_NODE><ARG_OF_PERICENTER>162.2516</ARG_OF_PERICENTER><MEAN_ANOMALY>205.2356</MEAN_ANOMALY></meanElements><tleParameters><EPHEMERIS_TYPE>0</EPHEMERIS_TYPE><CLASSIFICATION_TYPE>U</CLASSIFICATION_TYPE><NORAD_CAT_ID>5</NORAD_CAT_ID><ELEMENT_SET_NO>999</ELEMENT_SET_NO><REV_AT_EPOCH>21814</REV_AT_EPOCH><BSTAR>-.22483E-4</BSTAR><MEAN_MOTION_DOT>-1.6E-7</MEAN_MOTION_DOT><MEAN_MOTION_DDOT>0</MEAN_MOTION_DDOT></tleParameters></data></segment></body></omm>
+</ndm>
+"""
+
+# https://celestrak.com/NORAD/elements/gp.php?CATNR=00005&FORMAT=CSV
+VANGUARD_CSV = """\
+OBJECT_NAME,OBJECT_ID,EPOCH,MEAN_MOTION,ECCENTRICITY,INCLINATION,RA_OF_ASC_NODE,ARG_OF_PERICENTER,MEAN_ANOMALY,EPHEMERIS_TYPE,CLASSIFICATION_TYPE,NORAD_CAT_ID,ELEMENT_SET_NO,REV_AT_EPOCH,BSTAR,MEAN_MOTION_DOT,MEAN_MOTION_DDOT
+VANGUARD
1,1958-002B,2020-10-13T04:52:48.472320,10.84869164,.1845686,34.2443,225.5254,162.2516,205.2356,0,U,5,999,21814,-.22483E-4,-1.6E-7,0
+"""
+
+def test_omm_xml_matches_old_tle():
+ line0, line1, line2 = VANGUARD_TLE.splitlines()
+ sat1 = Satrec.twoline2rv(line1, line2)
+
+ fields = next(omm.parse_xml(StringIO(VANGUARD_XML)))
+ sat2 = Satrec()
+ omm.initialize(sat2, fields)
+
+ assert_satellites_match(sat1, sat2)
+
+def test_omm_csv_matches_old_tle():
+ line0, line1, line2 = VANGUARD_TLE.splitlines()
+ sat1 = Satrec.twoline2rv(line1, line2)
+
+ fields = next(omm.parse_csv(StringIO(VANGUARD_CSV)))
+ sat2 = Satrec()
+ omm.initialize(sat2, fields)
+
+ assert_satellites_match(sat1, sat2)
+
+def assert_satellites_match(sat1, sat2):
+ julian_fractions = {'epochdays', 'jdsatepochF'}
+ todo = {'classification', 'elnum', 'ephtype', 'intldesg', 'revnum',
+ 'whichconst'}
+
+ for attr in dir(sat1):
+ if attr.startswith('_'):
+ continue
+ if attr in todo:
+ continue
+ value1 = getattr(sat1, attr, None)
+ if value1 is None:
+ continue
+ if callable(value1):
+ continue
+ value2 = getattr(sat2, attr)
+ if attr in julian_fractions:
+ value1 = round(value1, 10)
+ value2 = round(value2, 10)
+ assertEqual(value1, value2)
+
+# ----------------------------------------------------------------------
def load_tests(loader, tests, ignore):
"""Run our main documentation as a test, plus all test functions."""
