def test_eci_aer(useastropy):
t = '2013-01-15T12:00:05'
aer1 = pm.eci2aer(*eci0, 42, -100, 0, t, useastropy=useastropy)
assert aer1 == approx([83.73050, -6.614478, 1.473510e6], rel=0.001)
assert pm.aer2eci(*aer1, 42, -100, 0, t, useastropy=useastropy) == approx(eci0, rel=0.001)
with pytest.raises(ValueError):
pm.aer2eci(aer1[0], aer1[1], -1, 42, -100, 0, t, useastropy=useastropy)
def test_eci_aer(useastropy):
pytest.importorskip("numpy")
t = "2013-01-15T12:00:05"
aer1 = pm.eci2aer(*eci0, 42, -100, 0, t, useastropy=useastropy)
assert aer1 == approx([83.73050, -6.614478, 1.473510e6], rel=0.001)
assert pm.aer2eci(*aer1, 42, -100, 0, t, useastropy=useastropy) == approx(eci0, rel=0.001)
with pytest.raises(ValueError):
pm.aer2eci(aer1[0], aer1[1], -1, 42, -100, 0, t, useastropy=useastropy)
def test_eci2aer(use_astropy):
# test coords from Matlab eci2aer
pytest.importorskip("numpy")
if use_astropy:
pytest.importorskip("astropy")
t = datetime(1969, 7, 20, 21, 17, 40)
eci = [-3.8454e8, -0.5099e8, -0.3255e8]
lla = [28.4, -80.5, 2.7]
aer = pm.eci2aer(*eci, *lla, t, use_astropy=use_astropy)
rel = 0.0001 if use_astropy else 0.01
assert aer == approx([162.55, 55.12, 384013940.9], rel=rel)
def get_observer_azimuth_elevation(self, observer_latitude,
observer_longitude, observer_altitude, date,
north_offset=0.0):
'''Returns the satellite directions (azimuth, elevation) for the given
observer's positions'''
assert(date.tzinfo == timezone.utc)
eci_position = self.propagate(date)[0]
aer_position = pm.eci2aer(eci_position, observer_latitude,
observer_longitude, observer_altitude, date)
az = (aer_position[0][0] - north_offset) % 360.0
el = aer_position[1][0]
return az, el
def _is_satellite_in_frame(self, ra, dec, loc, fov, sat_pass, ts):
ra_rng = (ra - fov, ra + fov)
dec_rng = (dec - fov, dec + fov)
lat, lon, alt = loc
for i, t in enumerate(ts):
dt = datetime.fromtimestamp(int(t.value))
x, y, z = sat_pass[i]
az, el, rng = pm.eci2aer(sat_pass[i], lat, lon, alt, dt)
ra_sat, dec_sat = pm.azel2radec(az, el, lat, lon, dt)
if ra_rng[0] <= ra_sat <= ra_rng[1]:
if dec_rng[0] <= dec_sat <= dec_rng[1]:
return True
return False
def test_eci():
tlla = (42, -82, 200)
teci = (-3.977913815668146e6, -2.582332196263046e6, 4.250818828152067e6)
t = datetime(2013, 1, 15, 12, 0, 5, tzinfo=UTC)
lla = asarray(pm.eci2geodetic(teci, t)).squeeze()
assert_allclose(lla, tlla, rtol=0.2)
assert_allclose(
pm.eci2ecef(teci, t).squeeze(),
[649012.04640917, -4697980.55129606, 4250818.82815207])
assert_allclose(
pm.ecef2eci([649012.04640917, -4697980.55129606, 4250818.82815207],
t).squeeze(), teci)
assert_allclose(
asarray(pm.eci2aer(teci, 42, -100, 0, t)).squeeze(),
[83.73050, -6.614478, 1.473510e6])
def get_observer_azimuth_elevation(self,
observer_latitude,
observer_longitude,
observer_altitude,
date=None):
'''Returns the satellite directions (azimuth, elevation) for the given
observer's positions'''
if date is None:
date = datetime.now(timezone.utc)
eci_position = self.propagate(date)[0]
aer_position = pm.eci2aer(eci_position, observer_latitude,
observer_longitude, observer_altitude, date)
az = aer_position[0][0]
el = aer_position[1][0]
return az, el
def test_eci_vallado():
t = '2013-01-15T12:00:05'
lla = pm.eci2geodetic(eci0, t, useastropy=False)
assert lla == approx(lla0, rel=0.2)
eci1 = pm.eci2ecef(eci0, t, useastropy=False)
assert eci1 == approx(
[649012.04640917, -4697980.55129606, 4250818.82815207], rel=0.001)
assert pm.ecef2eci(eci1, t, useastropy=False) == approx(eci0, rel=0.001)
aer1 = pm.eci2aer(eci0, 42, -100, 0, t, useastropy=False)
assert aer1 == approx([83.73050, -6.614478, 1.473510e6], rel=0.001)
assert pm.aer2eci(*aer1, 42, -100, 0, t,
useastropy=False) == approx(eci0, rel=0.001)
with pytest.raises(ValueError):
pm.aer2eci(aer1[0], aer1[1], -1, 42, -100, 0, t, useastropy=False)
def test_eci_astropy():
pytest.importorskip('astropy')
t = '2013-01-15T12:00:05'
lla = pm.eci2geodetic(eci0, t)
assert lla == approx(lla0, rel=0.2)
eci1 = pm.eci2ecef(eci0, t)
assert eci1 == approx(
[649012.04640917, -4697980.55129606, 4250818.82815207])
assert pm.ecef2eci(eci1, t) == approx(eci0)
aer1 = pm.eci2aer(eci0, 42, -100, 0, t)
assert aer1 == approx([83.73050, -6.614478, 1.473510e6])
assert pm.aer2eci(*aer1, 42, -100, 0, t) == approx(eci0)
with pytest.raises(ValueError):
pm.aer2eci(aer1[0], aer1[1], -1, 42, -100, 0, t)
def iridium_ncdf(fn,day,tlim,ellim, camlla):
assert len(ellim) == 2,'must specify elevation limits'
fn = Path(fn).expanduser()
day = forceutc(day)
#%% get all sats psuedo SV number
with Dataset(str(fn),'r') as f:
#psv_border = nonzero(diff(f['pseudo_sv_num'])!=0)[0] #didn't work because of consequtively reused psv #unique doesn't work because psv's can be recycled
psv_border = (diff(f['time'])<0).nonzero()[0] + 1 #note unequal number of samples per satellite, +1 for how diff() is defined
#%% iterate over psv, but remember different number of time samples for each sv.
# since we are only interested in one satellite at a time, why not just iterate one by one, throwing away uninteresting results
# qualified by crossing of FOV.
#%% consider only satellites above az,el limits for this location
#TODO assumes only one satellite meets elevation and time criteria
lind = [0,0] #init
for i in psv_border:
lind = [lind[1],i]
cind = arange(lind[0],lind[1]-1,dtype=int) # all times for this SV
#now handle times for this SV
t = array([day + timedelta(hours=h) for h in f['time'][cind].astype(float)])
if tlim:
mask = (tlim[0] <= t) & (t <= tlim[1])
t = t[mask]
cind = cind[mask]
#now filter by az,el criteria
az,el,r = eci2aer(f['pos_eci'][cind,:], camlla[0], camlla[1], camlla[2],t)
if ellim and ((ellim[0] <= el) & (el <= ellim[1])).any():
# print(t)
#print('sat psv {}'.format(f['pseudo_sv_num'][i]))
eci = f['pos_eci'][cind,:]
lat,lon,alt = eci2geodetic(eci,t)
x,y,z = eci2ecef(eci,t)
#print('ecef {} {} {}'.format(x,y,z))
ecef = DataFrame(index=t, columns=['x','y','z'], data=column_stack((x,y,z)))
lla = DataFrame(index=t, columns=['lat','lon','alt'], data=column_stack((lat,lon,alt)))
aer = DataFrame(index=t, columns=['az','el','srng'], data=column_stack((az,el,r)))
return ecef,lla,aer,eci
print('no FOV crossings for your time span were found.')
return (None,None)
def see_satellite(satellite,
obs_lat,
obs_lon,
obs_alt,
start,
end,
count=None,
annotate=True,
title=''):
positions_at = satellite.propagate_positions(start, end, count=count)
azimuth = []
elevation = []
dates = []
for position_at in positions_at:
eci, date = position_at
aer = pm.eci2aer(eci, obs_lat, obs_lon, obs_alt, date)
az = aer[0][0]
el = aer[1][0]
azimuth.append(az)
elevation.append(el)
dates.append(date)
print('plotted points between [{}] and [{}].'.format(dates[0], dates[-1]))
plot_az_el(azimuth, elevation)
dates = [x[1] for x in positions_at]
ax = plt.gca()
plt.suptitle(title, size=20)
df = pd.DataFrame({
'Azimuth': azimuth,
'Elevation': elevation,
'Date': dates
})
return df
def test_eci(self):
if numpy is None or astropy is None:
logging.warning('ECI not tested')
return
teci = (-3.977913815668146e6, -2.582332196263046e6,
4.250818828152067e6)
t = datetime(2013, 1, 15, 12, 0, 5, tzinfo=UTC)
lla = numpy.asarray(pm.eci2geodetic(teci, t)).squeeze()
assert_allclose(lla, lla0, rtol=0.2)
assert_allclose(
pm.eci2ecef(teci, t).squeeze(),
[649012.04640917, -4697980.55129606, 4250818.82815207])
assert_allclose(
pm.ecef2eci([649012.04640917, -4697980.55129606, 4250818.82815207],
t).squeeze(), teci)
assert_allclose(
numpy.asarray(pm.eci2aer(teci, 42, -100, 0, t)).squeeze(),
[83.73050, -6.614478, 1.473510e6])
