def test_plot_maneuver():
# Data from Vallado, example 6.1
alt_i = 191.34411 * u.km
alt_f = 35781.34857 * u.km
_a = 0 * u.deg
ss_i = Orbit.from_classical(
attractor=Earth,
a=Earth.R + alt_i,
ecc=0 * u.one,
inc=_a,
raan=_a,
argp=_a,
nu=_a,
)
# Create the maneuver
man = Maneuver.hohmann(ss_i, Earth.R + alt_f)
# Plot the maneuver
fig, ax = plt.subplots()
plotter = StaticOrbitPlotter(ax=ax)
plotter.plot(ss_i, label="Initial orbit", color="blue")
plotter.plot_maneuver(ss_i, man, label="Hohmann maneuver", color="red")
return fig
def test_plot_different_planes():
fig, ax = plt.subplots()
plotter = StaticOrbitPlotter(ax=ax)
plotter.plot(iss)
plotter.plot(molniya.change_plane(Planes.EARTH_ECLIPTIC))
return fig
def test_basic_orbit_and_trajectory_plotting():
fig, ax = plt.subplots()
plotter = StaticOrbitPlotter(ax=ax)
plotter.plot(iss)
plotter.plot_trajectory(molniya.sample(), label="Molniya")
return fig
def test_axes_labels_and_title():
ax = plt.gca()
op = StaticOrbitPlotter(ax)
ss = iss
op.plot(ss)
assert ax.get_xlabel() == "$x$ (km)"
assert ax.get_ylabel() == "$y$ (km)"
def test_set_frame_plots_same_colors():
# TODO: Review
op = StaticOrbitPlotter()
jupiter = Orbit.from_body_ephem(Jupiter)
op.plot(jupiter)
colors1 = [orb[2] for orb in op.trajectories]
op.set_frame(*jupiter.pqw())
colors2 = [orb[2] for orb in op.trajectories]
assert colors1 == colors2
def test_plot_trajectory_sets_label():
op = StaticOrbitPlotter()
earth = Orbit.from_body_ephem(Earth)
mars = Orbit.from_body_ephem(Mars)
trajectory = earth.sample()
op.plot(mars, label="Mars")
op.plot_trajectory(trajectory, label="Earth")
legend = plt.gca().get_legend()
assert legend.get_texts()[1].get_text() == "Earth"
def test_color():
op = StaticOrbitPlotter()
ss = iss
c = "#FF0000"
op.plot(ss, label="ISS", color=c)
ax = plt.gca()
assert ax.get_legend().get_lines()[0].get_c() == c
for element in ax.get_lines():
assert element.get_c() == c
def test_legend():
op = StaticOrbitPlotter()
ss = iss
op.plot(ss, label="ISS")
legend = plt.gca().get_legend()
ss.epoch.out_subfmt = "date_hm"
label = f"{ss.epoch.iso} (ISS)"
assert legend.get_texts()[0].get_text() == label
def test_redraw_keeps_trajectories():
# See https://github.com/poliastro/poliastro/issues/518
op = StaticOrbitPlotter()
earth = Orbit.from_body_ephem(Earth)
mars = Orbit.from_body_ephem(Mars)
trajectory = earth.sample()
op.plot(mars, label="Mars")
op.plot_trajectory(trajectory, label="Earth")
assert len(op.trajectories) == 2
op.set_frame(*mars.pqw())
assert len(op.trajectories) == 2
def test_number_of_lines_for_osculating_orbit():
op1 = StaticOrbitPlotter()
ss = iss
l1 = op1.plot(ss)
assert len(l1) == 2
def render(self, mode='live'):
# Render the environment to the screen
#plt.clf()
if mode == 'live':
if self.i <= self.n:
plt.figure()
op = StaticOrbitPlotter()
orb = [Orbit.from_vectors(Earth, r=(x[:3] / 1000) * u.km, v=(x[3:] / 1000) * u.km / u.s) for x in
self.x_true[self.i]]
orb1 = [Orbit.from_vectors(Earth, r=(x[:3] / 1000) * u.km, v=(x[3:] / 1000) * u.km / u.s) for x in
self.x_filter[self.i]]
palette = sns.color_palette("hls", len(orb))
for i, c in enumerate(orb):
new = op.plot(c, label="true", color=palette[i])
new[0].set_linestyle("-")
for j, d in enumerate(orb1):
op.plot(d, label="filtered", color=palette[j])
plt.pause(0.001)
plt.savefig('fig'+str(self.i)+'.png')
def test_trail_plotting():
fig, ax = plt.subplots()
plotter = StaticOrbitPlotter(ax=ax)
plotter.plot(iss, trail=True)
return fig
def test_basic_plotting():
fig, ax = plt.subplots()
plotter = StaticOrbitPlotter(ax=ax)
plotter.plot(iss)
return fig
# In[4]:
# Solving for direct (M=0) transfer long and short arcs
ss_short0, ss_long0 = lambert_transfer(earth_departure, mars_arrival, revs=0)
fig, ax = plt.subplots(figsize=(5, 10))
op = StaticOrbitPlotter(ax=ax)
ax.set_title("Direct arc transfer ($M=0$)")
orbit_set = {ss_short0: ["Short0", "black"], ss_long0: ["Long0", "grey"]}
op.plot_body_orbit(Earth, EPOCH_DPT)
op.plot_body_orbit(Mars, EPOCH_ARR)
for ss in orbit_set:
op.plot(ss, label=orbit_set[ss][0], color=orbit_set[ss][-1], trail=True)
# ### Solutions for M=1
# In[5]:
# Solving for M=1 long and short arc transfers
ss_short1, ss_long1 = lambert_transfer(earth_departure, mars_arrival, revs=1)
fig, ax = plt.subplots(figsize=(5, 10))
op = StaticOrbitPlotter(ax=ax)
ax.set_title("Direct arc transfer ($M=1$)")
orbit_set = {ss_short1: ["Short1", "black"], ss_long1: ["Long1", "grey"]}
op.plot_body_orbit(Earth, EPOCH_DPT)
"""
tru_anom = mean_anomaly + (2*eccentricity - (1/4)*eccentricity**3)*np.sin(mean_anomaly) + (5/4)*np.sin(2*mean_anomaly)*eccentricity**(2) + (13/12)*np.sin(3*mean_anomaly)*eccentricity**3 *3
return tru_anom
def dateUnpack(self, packed):
"""A package from mpcorgbet"""
yearcode = {"I":"18","J":"19","K":"20"}
daycode = "123456789ABCDEFGHIJKLMNOPQRSTUV"
year = yearcode[packed[0]]+packed[1:3]
month = daycode.index(packed[3])+1
day = daycode.index(packed[4])+1
return "%s/%s/%s" % (month, day, year)
###############################
#Main Execution
#Commands for getting mpcorgbet data
#first = mpcorbget.MPCORB("162269")
#epoch, mean_anomaly, argument_of_perihelion, longitude_of_ascendingnode, inclination, eccentricity, semimajor_axis,mean_daily_motion = returnOrbitalElements(first)
#Commands for getting eros data from txt file
i, e, a, ME, long, peri = ImportFromTxt('/home/alli/NugentResearch/eros.txt')
tru_anom = calculateTrueAnomaly(ME, e)
print(i, e, a, ME, long, peri)
#Creating poliastro orbit object
ss = Orbit.from_classical(Earth, a* u.AU, e* u.one, i* u.deg, long * u.deg, peri * u.deg, tru_anom * u.deg)
#Plotting Eros
plotter = StaticOrbitPlotter() #creating plotter class
plotter.plot(ss, label="Eros") #plotting Eros
plt.show()