def from_tle(cls, sate_id, source, date=None):
"""Returns approximate keplerian elements from TLE.
The conversion between mean elements in the TEME reference
frame to osculating elements in any standard reference frame
is not well defined in literature (see Vallado 3rd edition, pp 236 to 240)
"""
# Get latest TLE, or the one corresponding to a specified date
if date is None:
date = datetime.datetime.utcnow()
tle = source.get_tle(sate_id, date)
# Retrieve TLE epoch and corresponding position
epoch = twoline2rv(tle.lines[0], tle.lines[1], wgs84).epoch
pos = TLEPredictor(sate_id, source).get_position(epoch)
# Convert position from ECEF to ECI
gmst = gstime_from_datetime(epoch)
position_eci = coordinate_systems.ecef_to_eci(pos.position_ecef, gmst)
velocity_eci = coordinate_systems.ecef_to_eci(pos.velocity_ecef, gmst)
# Convert position to Keplerian osculating elements
p, ecc, inc, raan, argp, ta = rv2coe(wgs84.mu, np.array(position_eci),
np.array(velocity_eci))
sma = p / (1 - ecc**2)
return cls(sma, ecc, degrees(inc), degrees(raan), degrees(argp),
degrees(ta), epoch)
def setUp(self):
# Source
self.db = MemoryTLESource()
self.db.add_tle(BUGSAT_SATE_ID, BUGSAT1_TLE_LINES,
dt.datetime.utcnow())
# Predictor
self.predictor = TLEPredictor(BUGSAT_SATE_ID, self.db)
def setUp(self):
# Source
self.db = MemoryTLESource()
self.db.add_tle(SATE_ID, BUGSAT1_TLE_LINES, datetime.datetime.now())
# Predictor
self.predictor = TLEPredictor(SATE_ID, self.db)
date = datetime.datetime.strptime("2014-10-22 20:18:11.921921", '%Y-%m-%d %H:%M:%S.%f')
self.next_pass = self.predictor.get_next_pass(tortu1, when_utc=date)
def setUp(self):
# Source
self.db = MemoryTLESource()
self.start = dt.datetime(2017, 3, 6, 7, 51)
self.db.add_tle(SATE_ID, LINES, self.start)
# Predictor
self.predictor = TLEPredictor(SATE_ID, self.db)
self.end = self.start + dt.timedelta(days=5)
def setUp(self):
tle_lines = (
"1 42760U 17034C 19070.46618549 .00000282 00000-0 30543-4 0 9995",
"2 42760 43.0166 56.1509 0009676 356.3576 146.0151 15.09909885 95848",
)
self.db = MemoryTLESource()
self.db.add_tle("42760U", tle_lines, dt.datetime.now())
self.predictor = TLEPredictor("42760U", self.db)
def get_predictor_from_tle_lines(tle_lines):
db = MemoryTLESource()
sgp4_sat = Satrec.twoline2rv(tle_lines[0], tle_lines[1])
db.add_tle(
sgp4_sat.satnum,
tuple(tle_lines),
datetime_from_jday(sgp4_sat.jdsatepoch, sgp4_sat.jdsatepochF),
)
predictor = TLEPredictor(sgp4_sat.satnum, db)
return predictor
def setUp(self):
# Source
self.db = MemoryTLESource()
self.db.add_tle(BUGSAT_SATE_ID, BUGSAT1_TLE_LINES,
dt.datetime.utcnow())
# Predictor
self.predictor = TLEPredictor(BUGSAT_SATE_ID, self.db)
self.is_ascending_mock = self._patch(
'orbit_predictor.predictors.base.LocationPredictor._is_ascending')
self.start = dt.datetime(2017, 3, 6, 7, 51)
logassert.setup(self, 'orbit_predictor.predictors.pass_iterators')
def test_from_tle_returns_same_initial_conditions_on_epoch(self):
start = datetime(2017, 3, 6, 7, 51)
db = MemoryTLESource()
db.add_tle(self.SATE_ID, self.LINES, start)
keplerian_predictor = KeplerianPredictor.from_tle(self.SATE_ID, db, start)
tle_predictor = TLEPredictor(self.SATE_ID, db)
epoch = keplerian_predictor._epoch
pos_keplerian = keplerian_predictor.get_position(epoch)
pos_tle = tle_predictor.get_position(epoch)
assert_allclose(pos_keplerian.position_ecef, pos_tle.position_ecef, rtol=1e-11)
assert_allclose(pos_keplerian.velocity_ecef, pos_tle.velocity_ecef, rtol=1e-13)
def from_tle(cls, sate_id, source, date=None):
"""Returns approximate keplerian elements from TLE.
The conversion between mean elements in the TEME reference
frame to osculating elements in any standard reference frame
is not well defined in literature (see Vallado 3rd edition, pp 236 to 240)
"""
# Get latest TLE, or the one corresponding to a specified date
if date is None:
date = dt.datetime.utcnow()
# Retrieve TLE position at given date as starting point
pos = TLEPredictor(sate_id, source).get_position(date)
return cls(*pos.osculating_elements, epoch=date)
def get_predictor(self, sate_id):
"""Return a Predictor instance using the current storage."""
return TLEPredictor(sate_id, self)
def get_predictor_from_tle_lines(tle_lines):
db = MemoryTLESource()
sgp4_sat = twoline2rv(tle_lines[0], tle_lines[1], wgs84)
db.add_tle(sgp4_sat.satnum, tuple(tle_lines), sgp4_sat.epoch)
predictor = TLEPredictor(sgp4_sat.satnum, db)
return predictor
def get_predictor(self, sate_id, precise=False):
"""Return a Predictor instance using the current storage."""
if precise:
return HighAccuracyTLEPredictor(sate_id, self)
return TLEPredictor(sate_id, self)
def setUpClass(cls):
# Source
cls.db = MemoryTLESource()
cls.db.add_tle(SATE_ID, BUGSAT1_TLE_LINES, datetime.datetime.now())
# Predictor
cls.predictor = TLEPredictor(SATE_ID, cls.db)
def setUp(self):
self.db = MemoryTLESource()
self.db.add_tle(TRICKY_SAT_ID, TRICKY_SAT_TLE_LINES, dt.datetime.now())
self.predictor = TLEPredictor(TRICKY_SAT_ID, self.db)
import matplotlib.pyplot as plt
import cartopy.crs as ccrs
import pandas as pd
from orbit_predictor.sources import EtcTLESource
from orbit_predictor.predictors import TLEPredictor
source = EtcTLESource(filename=r'e:/resource.txt')
#source = EtcTLESource(filename=r'd:/visual.txt')
predictor = TLEPredictor("WORLDVIEW-2 (WV-2) ", source)
#predictor = TLEPredictor('ATLAS CENTAUR 2 ', source)
dates = pd.date_range(start="2018-04-01 00:00", periods=1000, freq="30S")
latlon = pd.DataFrame(index=dates, columns=["lat", "lon"])
for date in dates:
lat, lon, _ = predictor.get_position(date).position_llh
latlon.loc[date] = (lat, lon)
latlon.plot()
plt.figure(figsize=(15, 25))
ax = plt.axes(projection=ccrs.PlateCarree())
ax.stock_img()
plt.plot(
latlon["lon"],
latlon["lat"],