def plot(self, state, osculating=True, label=None):
"""Plots state and osculating orbit in their plane.
"""
# TODO: This function needs a refactoring
if not self._frame:
self.set_frame(*state.pqw())
self._states.append(state)
lines = []
nu_vals = self._generate_vals(state)
# Compute PQW coordinates
r_pqw, _ = rv_pqw(state.attractor.k.to(u.km ** 3 / u.s ** 2).value,
state.p.to(u.km).value,
state.ecc.value,
nu_vals.value)
r_pqw = r_pqw * u.km
# Express on inertial frame
e_vec, p_vec, h_vec = state.pqw()
p_vec = np.cross(h_vec, e_vec) * u.one
rr = (r_pqw[:, 0, None].dot(e_vec[None, :]) +
r_pqw[:, 1, None].dot(p_vec[None, :]))
# Project on OrbitPlotter frame
# x_vec, y_vec, z_vec = self._frame
rr_proj = rr - rr.dot(self._frame[2])[:, None] * self._frame[2]
x = rr_proj.dot(self._frame[0])
y = rr_proj.dot(self._frame[1])
# Plot current position
l, = self.ax.plot(x[0].to(u.km).value, y[0].to(u.km).value,
'o', mew=0)
lines.append(l)
# Attractor
self.ax.add_patch(mpl.patches.Circle((0, 0),
state.attractor.R.to(u.km).value,
lw=0, color='#204a87')) # Earth
if osculating:
l, = self.ax.plot(x.to(u.km).value, y.to(u.km).value,
'--', color=l.get_color())
lines.append(l)
if label:
# This will apply the label to either the point or the osculating
# orbit depending on the last plotted line, as they share variable
l.set_label(label)
self.ax.set_title(state.epoch.iso)
self.ax.set_xlabel("$x$ (km)")
self.ax.set_ylabel("$y$ (km)")
self.ax.set_aspect(1)
self.ax.legend()
return lines
def plot(self, orbit, osculating=True, label=None):
"""Plots state and osculating orbit in their plane.
"""
# TODO: This function needs a refactoring
if not self._frame:
self.set_frame(*orbit.pqw())
# if new attractor radius is smaller, plot it
new_radius = max(orbit.attractor.R.to(u.km).value,
orbit.r_p.to(u.km).value / 6)
if not self._attractor_radius:
self.set_attractor(orbit)
elif new_radius < self._attractor_radius:
self.set_attractor(orbit)
lines = []
nu_vals = self._generate_vals(orbit.state)
# Compute PQW coordinates
r_pqw, _ = rv_pqw(orbit.attractor.k.to(u.km ** 3 / u.s ** 2).value,
orbit.p.to(u.km).value,
orbit.ecc.value,
nu_vals.value)
r_pqw = r_pqw * u.km
# Express on inertial frame
e_vec, p_vec, h_vec = orbit.pqw()
p_vec = np.cross(h_vec, e_vec) * u.one
rr = (r_pqw[:, 0, None].dot(e_vec[None, :]) +
r_pqw[:, 1, None].dot(p_vec[None, :]))
# Project on OrbitPlotter frame
# x_vec, y_vec, z_vec = self._frame
rr_proj = rr - rr.dot(self._frame[2])[:, None] * self._frame[2]
x = rr_proj.dot(self._frame[0])
y = rr_proj.dot(self._frame[1])
# Plot current position
l, = self.ax.plot(x[0].to(u.km).value, y[0].to(u.km).value,
'o', mew=0)
lines.append(l)
if osculating:
l, = self.ax.plot(x.to(u.km).value, y.to(u.km).value,
'--', color=l.get_color())
lines.append(l)
if label:
# This will apply the label to either the point or the osculating
# orbit depending on the last plotted line, as they share variable
l.set_label(label)
self.ax.legend()
self.ax.set_title(orbit.epoch.iso)
self.ax.set_xlabel("$x$ (km)")
self.ax.set_ylabel("$y$ (km)")
self.ax.set_aspect(1)
return lines
def plot(self, orbit, label=None):
"""Plots state and osculating orbit in their plane.
"""
# TODO: This function needs a refactoring
if not self._frame:
self.set_frame(*orbit.pqw())
# if new attractor radius is smaller, plot it
new_radius = max(
orbit.attractor.R.to(u.km).value,
orbit.r_p.to(u.km).value / 6)
if not self._attractor_radius:
self.set_attractor(orbit)
elif new_radius < self._attractor_radius:
self.set_attractor(orbit)
lines = []
nu_vals = self._generate_vals(orbit.state)
# Compute PQW coordinates
r_pqw, _ = rv_pqw(
orbit.attractor.k.to(u.km**3 / u.s**2).value,
orbit.p.to(u.km).value, orbit.ecc.value, nu_vals.value)
r_pqw = r_pqw * u.km
# Express on inertial frame
e_vec, p_vec, h_vec = orbit.pqw()
p_vec = np.cross(h_vec, e_vec) * u.one
rr = (r_pqw[:, 0, None].dot(e_vec[None, :]) +
r_pqw[:, 1, None].dot(p_vec[None, :]))
# Project on OrbitPlotter frame
# x_vec, y_vec, z_vec = self._frame
rr_proj = rr - rr.dot(self._frame[2])[:, None] * self._frame[2]
x = rr_proj.dot(self._frame[0])
y = rr_proj.dot(self._frame[1])
# Plot current position
l, = self.ax.plot(x[0].to(u.km).value, y[0].to(u.km).value, 'o', mew=0)
lines.append(l)
l, = self.ax.plot(x.to(u.km).value,
y.to(u.km).value,
'--',
color=l.get_color())
lines.append(l)
if label:
# This will apply the label to either the point or the osculating
# orbit depending on the last plotted line, as they share variable
handles = [] # type: List[mpl.lines.Line2D]
labels = [] # type: List[str]
orbit.epoch.out_subfmt = 'date_hm'
label = '{} ({})'.format(orbit.epoch.iso, label)
legends = self.ax.figure.legends
if legends:
handles = legends[0].get_lines()
labels = [text.get_text() for text in legends[0].get_texts()]
legends[0].remove()
handles.append(l)
labels.append(label)
self.ax.figure.legend(handles,
labels,
mode="expand",
loc="lower center",
fancybox=True,
title="Names and epochs")
self.ax.set_xlabel("$x$ (km)")
self.ax.set_ylabel("$y$ (km)")
self.ax.set_aspect(1)
return lines
def plot(self, state, osculating=True):
"""Plots state and osculating orbit in their plane.
"""
if not self._frame:
self.set_frame(*state.pqw())
self._states.append(state)
lines = []
# Generate points of the osculating orbit
if state.ecc >= 1.0:
# Select a sensible limiting value for non-closed orbits.
# This corresponds to r = 3p.
max_nu = np.arccos(-(1 - 1 / 3.) / state.ecc).to(u.rad).value
else:
max_nu = np.pi # rad
nu_vals = np.linspace(-max_nu, max_nu, self.num_points) # rad
# Insert state true anomaly into array
idx = np.searchsorted(nu_vals, state.nu.to(u.rad))
nu_vals = np.insert(nu_vals, idx,
state.nu.to(u.rad).value) * u.rad
# Compute PQW coordinates
r_pqw, _ = rv_pqw(state.attractor.k.to(u.km ** 3 / u.s ** 2).value,
state.p.to(u.km).value,
state.ecc.value,
nu_vals.value)
r_pqw = r_pqw * u.km
# Express on inertial frame
e_vec, p_vec, h_vec = state.pqw()
p_vec = np.cross(h_vec, e_vec) * u.one
rr = (r_pqw[:, 0, None].dot(e_vec[None, :]) +
r_pqw[:, 1, None].dot(p_vec[None, :]))
# Project on OrbitPlotter frame
# x_vec, y_vec, z_vec = self._frame
rr_proj = rr - rr.dot(self._frame[2])[:, None] * self._frame[2]
x = rr_proj.dot(self._frame[0])
y = rr_proj.dot(self._frame[1])
# Plot current position
l, = self.ax.plot(x[idx].to(u.km).value, y[idx].to(u.km).value,
'o', mew=0)
lines.append(l)
# Attractor
self.ax.add_patch(mpl.patches.Circle((0, 0),
state.attractor.R.to(u.km).value,
lw=0, color='#204a87')) # Earth
if osculating:
l, = self.ax.plot(x.to(u.km).value, y.to(u.km).value,
'--', color=l.get_color())
lines.append(l)
self.ax.set_title(state.epoch.iso)
self.ax.set_xlabel("$x$ (km)")
self.ax.set_ylabel("$y$ (km)")
self.ax.set_aspect(1)
return lines
