def test_plot_trajectory_without_attractor_raises_error():
frame = OrbitPlotter2D()
with pytest.raises(ValueError) as excinfo:
frame.plot_trajectory({})
assert ("An attractor must be set up first, please use "
"set_attractor(Major_Body)." in excinfo.exconly())
def test_plot_sets_attractor():
frame = OrbitPlotter2D()
assert frame._attractor is None
assert frame._attractor_data == {}
frame.plot(iss)
assert frame._attractor == iss.attractor
assert frame._attractor_data["name"] == iss.attractor.name
def test_get_figure_has_expected_properties():
frame = OrbitPlotter2D()
figure = frame.figure
assert figure["data"] == [{}]
assert figure["layout"]["autosize"] is True
assert "xaxis" in figure["layout"]
assert "yaxis" in figure["layout"]
def test_plot_2d_trajectory_without_frame_raises_error():
frame = OrbitPlotter2D()
with pytest.raises(ValueError) as excinfo:
frame.set_attractor(Sun)
frame.plot_trajectory({})
assert ("A frame must be set up first, please use "
"set_orbit_frame(orbit) or plot(orbit)" in excinfo.exconly())
def test_show_calls_prepare_plot(mock_prepare_plot, mock_iplot):
m = OrbitPlotter2D()
earth = Orbit.from_body_ephem(Earth)
m.plot(orbit=earth, label="Obj")
m.show()
assert mock_iplot.call_count == 1
mock_prepare_plot.assert_called_once_with()
def test_savefig_calls_prepare_plot(mock_prepare_plot, mock_export):
m = OrbitPlotter2D()
earth = Orbit.from_body_ephem(Earth)
m.plot(orbit=earth, label="Obj")
with tempfile.NamedTemporaryFile() as fp:
m.savefig(filename=fp.name + ".jpeg")
assert mock_export.call_count == 1
mock_prepare_plot.assert_called_once_with()
def test_plot_trajectory_plots_a_trajectory():
frame = OrbitPlotter2D()
assert len(frame._data) == 0
earth = Orbit.from_body_ephem(Earth)
_, trajectory = earth.sample()
frame.set_attractor(Sun)
frame.plot_trajectory(trajectory)
assert len(frame._data) == 1
assert frame._attractor == Sun
def test_ephem_without_frame_raises_error():
epochs = time.Time("2020-04-29 10:43", scale="tdb")
earth = Ephem.from_body(Earth, epochs)
plotter = OrbitPlotter2D()
with pytest.raises(ValueError) as excinfo:
plotter.set_attractor(Sun)
plotter.plot_ephem(earth)
assert ("A frame must be set up first, please use "
"set_orbit_frame(orbit) or plot(orbit)" in excinfo.exconly())
def test_savefig_calls_prepare_plot():
patcher = mock.patch.object(OrbitPlotter2D, '_prepare_plot')
patched = patcher.start()
m = OrbitPlotter2D()
earth = Orbit.from_body_ephem(Earth)
m.plot(orbit=earth, label="Obj")
m.savefig(filename="a.jpeg")
assert patched.call_count == 1
patched.assert_called_with()
def test_set_different_attractor_raises_error():
body1 = Earth
body2 = Mars
frame = OrbitPlotter2D()
frame.set_attractor(body1)
with pytest.raises(NotImplementedError) as excinfo:
frame.set_attractor(body2)
assert "Attractor has already been set to Earth." in excinfo.exconly()
def test_plot_2d_trajectory_plots_a_trajectory():
frame = OrbitPlotter2D()
assert len(frame.trajectories) == 0
trajectory = churi.sample()
frame.set_attractor(Sun)
frame.set_orbit_frame(churi)
frame.plot_trajectory(trajectory)
assert len(frame.trajectories) == 1
assert frame._attractor == Sun
def test_plot_2d_trajectory_plots_a_trajectory():
frame = OrbitPlotter2D()
assert len(frame.trajectories) == 0
earth = Orbit.from_body_ephem(Earth)
trajectory = earth.sample()
frame.set_attractor(Sun)
frame.set_frame(*earth.pqw())
frame.plot_trajectory(trajectory)
assert len(frame.trajectories) == 1
assert frame._attractor == Sun
def on_button_clicked():
#Two body calculation
aPoli = apogee.value() * u.km
eccPoli = ecc.value() * u.one
incPoli = inc.value() * u.deg
raanPoli = raan.value() * u.deg
aopPoli = aop.value() * u.deg
nuPoli = nu.value() * u.deg
ss = Orbit.from_classical(Earth, aPoli, eccPoli, incPoli,
raanPoli, aopPoli, nuPoli)
op = OrbitPlotter2D()
op.plot(ss, label="Computed Orbit")
self.canvas.draw()
def test_plot_appends_data():
frame = OrbitPlotter2D()
assert len(frame._data) == 0
frame.plot(iss)
assert len(frame._data) == 1 + 1
plotOrbit((f_orbit.a.value), (f_orbit.ecc.value),
(f_orbit.inc.value), (f_orbit.raan.value),
(f_orbit.argp.value), (f_orbit.nu.value))
elif (opt_1 == '2'):
print("\n1.Find orbit using-")
print("1.Name.")
print("2.SPK id.")
opt_2 = input()
if (opt_2 == '1'):
print("Enter name:")
str_1 = input()
orbit = neows.orbit_from_name(str_1)
print(orbit)
print(orbit.rv())
frame = OrbitPlotter2D()
frame.plot(orbit, label=str_1)
print(
"\nPropagate to(Enter time in format='iso', scale='utc':")
p_t_s = input()
p_t_o = Time(p_t_s, format='iso', scale='utc')
print("")
final = orbit.propagate(p_t_o)
#final.plot()
print("Orbital elements:")
print(final.classical())
print("")
print("Final co-ordinates:")
print(final.rv())
print("")
f_orbit = final
observations = json.load(json_file)
sd_actual = []
sd_pred = []
es = []
r_actual = []
r_pred = []
ED_actual = []
ED_pred = []
v_actual = []
v_pred = []
ranges = []
speed_actual = []
speed_pred = []
orb = []
op = OrbitPlotter2D() # Initialiaze orbit plot
for epoch in range(num_epochs):
# Satellite-debris direction vectors
sd_actual.append(
observations['telemetry'][epoch]
['directionVector_actual']) # Actual satellite-debris direction vector
# Calculate predicted satellite-debris vector
K = np.array(observations['CameraCalibration'][epoch]
['intrinsics']) # camera intrinsics matrix
RT = np.array(observations['CameraCalibration'][epoch]
['extrinsics']) # camera extrinsics matrix
# Extract bounding box predictions
x = observations['bbox'][epoch]['Xcenter']
y = observations['bbox'][epoch]['Ycenter']
p = np.array([[x], [y],
[1]]) # convert location of bbox center to homogenous vector