def ipvPlot3DMoon(self):
import ipyvolume as ipv
lunarPositions = np.zeros((self.history.datetime.shape[0], 3))
for idx in range(0, self.history.datetime.shape[0]):
lunarPositions[idx, :] = models.lunarPositionAlmanac2013(
self.history.datetime[idx]) / 1e3
ipv.pylab.plot(lunarPositions[:, 0], lunarPositions[:, 2],
lunarPositions[:, 1])
ipv.pylab.scatter(np.array([lunarPositions[-1, 0]]),
np.array([lunarPositions[-1, 2]]),
np.array([lunarPositions[-1, 1]]),
color="gray",
marker="sphere")
def plot(self, item, itemHistory=None, **kwargs):
useDate = False
for key in kwargs:
if key == "useDate":
useDate = kwargs[key]
if item == "coe":
# PLOTTING CLASSICAL ORBITAL ELEMENTS
titles = ["a", "e", "i", "$\omega$", "$\Omega$", "$\\nu$"]
ylabels = ["[km]", "", "[°]", "[°]", "[°]", "[°]"]
timeAxis = self.history.datetime if useDate else self.history.t / 60 / 60 / 24
fig, axes = plt.subplots(3, 2, figsize=(10, 8), sharex=True)
for i in range(0, 6):
for j in range(0, len(self.history.maneuverIdxs) - 1):
maneuverSlice = slice(self.history.maneuverIdxs[j],
self.history.maneuverIdxs[j + 1])
if i in [2, 3, 4, 5]:
axes[int((i - i % 2) / 2), i % 2].plot(
timeAxis[maneuverSlice],
self.history.coe[maneuverSlice, i] * 180 / np.pi)
else:
if i == 0:
axes[int((i - i % 2) / 2), i % 2].plot(
timeAxis[maneuverSlice],
self.history.coe[maneuverSlice, i] / 1000)
else:
axes[int((i - i % 2) / 2), i % 2].plot(
timeAxis[maneuverSlice],
self.history.coe[maneuverSlice, i])
axes[int((i - i % 2) / 2),
i % 2].set_title(titles[i] + " " + ylabels[i])
if useDate:
fig.autofmt_xdate()
axes[int((i - i % 2) / 2),
i % 2].xaxis.set_major_formatter(
mdates.DateFormatter('%Y-%m-%d'))
else:
if i in [4, 5]:
axes[int((i - i % 2) / 2),
i % 2].set_xlabel("Tiempo [días]")
axes[int((i - i % 2) / 2),
i % 2].yaxis.get_major_formatter().set_scientific(False)
axes[int((i - i % 2) / 2),
i % 2].yaxis.get_major_formatter().set_useOffset(False)
axes[int((i - i % 2) / 2), i % 2].grid(b=True)
if i in [0, 1]:
axes[int((i - i % 2) / 2), i %
2].yaxis.get_major_formatter().set_scientific(True)
axes[int((i - i % 2) / 2),
i % 2].yaxis.get_major_formatter().set_useOffset(True)
if item == "secularCoe":
# PLOTTING CLASSICAL ORBITAL ELEMENTS
titles = ["a", "e", "i", "$\omega$", "$\Omega$", "$\\nu$"]
ylabels = ["[km]", "", "[°]", "[°]", "[°]", "[°]"]
timeAxis = self.history.datetime if useDate else self.history.tSecular / 60 / 60 / 24
fig, axes = plt.subplots(3, 2, figsize=(10, 8), sharex=True)
for i in range(0, 5):
if i in [2, 3, 4]:
axes[int((i - i % 2) / 2), i % 2].plot(
timeAxis, self.history.secularCoe[:, i] * 180 / np.pi)
else:
if i == 0:
axes[int((i - i % 2) / 2),
i % 2].plot(timeAxis,
self.history.secularCoe[:, i] / 1e3)
else:
axes[int((i - i % 2) / 2),
i % 2].plot(timeAxis, self.history.secularCoe[:,
i])
axes[int((i - i % 2) / 2),
i % 2].set_title(titles[i] + " " + ylabels[i])
if (useDate):
fig.autofmt_xdate()
axes[int((i - i % 2) / 2),
i % 2].xaxis.set_major_formatter(
mdates.DateFormatter('%Y-%m-%d'))
axes[int((i - i % 2) / 2),
i % 2].yaxis.get_major_formatter().set_scientific(False)
axes[int((i - i % 2) / 2),
i % 2].yaxis.get_major_formatter().set_useOffset(False)
axes[int((i - i % 2) / 2), i % 2].grid(b=True)
if item == "3d-trajectory":
for key in kwargs:
if key == "ax":
axExtern = kwargs["ax"]
#Plot 3D Trajectory
if 'axExtern' not in locals():
fig = plt.figure(figsize=(10, 10))
ax = fig.add_subplot(111, projection='3d')
else:
ax = axExtern
markers = np.zeros([len(self.history.maneuverIdxs) - 1, 3])
for i in range(0, len(self.history.maneuverIdxs) - 1):
maneuverSlice = slice(self.history.maneuverIdxs[i],
self.history.maneuverIdxs[i + 1])
ax.plot3D(self.history.r[maneuverSlice, 0] / 1000,
self.history.r[maneuverSlice, 1] / 1000,
self.history.r[maneuverSlice, 2] / 1000,
linewidth=1)
markers[i, :] = self.history.r[
self.history.maneuverIdxs[i], :] / 1000
ax.plot3D(markers[:, 0], markers[:, 1], markers[:, 2], "k.")
if 'axExtern' not in locals():
auxiliary.set_axes_equal(ax)
ax.set_aspect("equal")
scale_x = 1.2
scale_y = 1.2
scale_z = 1.2
ax.get_proj = lambda: np.dot(
Axes3D.get_proj(ax), np.diag(
[scale_x, scale_y, scale_z, 1]))
figXLim = ax.get_xlim()
figYLim = ax.get_ylim()
figZLim = ax.get_zlim()
xx, yy = np.meshgrid(figXLim, figYLim)
z = np.array([[0, 0], [0, 0]])
ax.plot_surface(xx, yy, z, alpha=0.3, color="lightgray")
ax.set_title("Satellite Trajectory [km]")
ax.set_xlabel("X [km]")
ax.set_ylabel("Y [km]")
ax.set_zlabel("Z [km]")
return ax
if item == "orbitalEnergy":
fig, ax = plt.subplots(figsize=(10, 4))
moonDistances = np.array([])
for num, date in enumerate(self.history.datetime):
moonVector = models.lunarPositionAlmanac2013(date)
moonDistances = np.append(
moonDistances,
np.linalg.norm(moonVector - self.history.r[num]))
earthEnergy = np.linalg.norm(
self.history.v, axis=1
)**2 / 2 - constants.mu_E / np.linalg.norm(self.history.r, axis=1)
moonEnergy = np.linalg.norm(
self.history.v, axis=1)**2 / 2 - constants.mu_M / moonDistances
ax.plot(self.history.datetime, earthEnergy, label="Earth Energy")
ax.plot(self.history.datetime, moonEnergy, label="Moon Energy")
fig.legend()
fig.autofmt_xdate()
ax.xaxis.set_major_formatter(mdates.DateFormatter('%Y-%m-%d'))
plt.grid()
#fig, ax = plt.subplots(figsize=(10,4))
#ax.plot(self.history.datetime,moonDistances);
if item == "energyUsage":
timeAxis = self.history.datetime if useDate else self.history.t / 60 / 60 / 24
fig, ax = plt.subplots(figsize=(10, 4))
PSolarPanels = np.diff(
self.history.energy["solar panels"]) / np.diff(self.history.t)
PThruster = np.diff(self.history.energy["thruster"]) / np.diff(
self.history.t)
POtherDevices = np.ones((len(self.history.t))) * (
self.spacecraft.solarPanels.nominalPower) * 0.6
EBattery = self.history.energy["battery"] / 60 / 60
ax.plot(timeAxis[:-1],
PSolarPanels,
linewidth=1,
label="Potencia Paneles Solares")
ax.plot(timeAxis[:-1],
PThruster,
linewidth=1,
label="Potencia Propulsor")
ax.plot(timeAxis,
POtherDevices,
linewidth=1,
label="Potencia Otros Dispositivos")
ax.set_ylabel("Potencia [W]")
#ax.set_ylim([-1,2])
if useDate:
fig.autofmt_xdate()
ax.xaxis.set_major_formatter(mdates.DateFormatter('%Y-%m-%d'))
else:
ax.set_xlabel("Tiempo [días]")
ax.yaxis.set_major_formatter(mticker.ScalarFormatter())
ax.yaxis.get_major_formatter().set_scientific(False)
ax.yaxis.get_major_formatter().set_useOffset(False)
ax2 = ax.twinx()
ax2.plot(timeAxis,
EBattery,
linewidth=1,
label="Energía Baterías",
color="purple")
ax2.set_ylabel("Energía [Wh]")
h1, l1 = ax.get_legend_handles_labels()
h2, l2 = ax2.get_legend_handles_labels()
ax2.legend(h1 + h2, l1 + l2)
ax2.set_ylim([-2, self.spacecraft.battery.energy + 2])
ax2.grid()
#ax2.set_ylim([-.5,.5])
if item == "singleItem":
timeAxis = self.history.datetime if useDate else self.history.t / 60 / 60 / 24
if np.isscalar(itemHistory) and itemHistory == None:
raise Exception("History Data not specified.")
else:
fig, ax = plt.subplots(figsize=(10, 4))
for i in range(0, len(self.history.maneuverIdxs) - 1):
maneuverSlice = slice(self.history.maneuverIdxs[i],
self.history.maneuverIdxs[i + 1])
ax.plot(timeAxis[maneuverSlice],
itemHistory[maneuverSlice],
linewidth=1)
if useDate:
fig.autofmt_xdate()
ax.xaxis.set_major_formatter(
mdates.DateFormatter('%Y-%m-%d'))
ax.yaxis.set_major_formatter(mticker.ScalarFormatter())
ax.yaxis.get_major_formatter().set_scientific(False)
ax.yaxis.get_major_formatter().set_useOffset(False)
else:
ax.set_xlabel("Time [days]")
plt.grid()
mplcursors.cursor(hover=True)
def calculatePerturbations(self, t, r, v, propMass):
p = [0, 0, 0]
if self._PERTURBATION_ATMDRAG_:
z = np.linalg.norm(r) - constants.Re
#Atmospheric Drag
vrel = v - np.cross(constants.wE, r)
rho = models.USSA76(z)
#rhoMin, rhoMax = models.HarrisPriester(z)
#rho = rhoMax
#rho = models.MSISE90(z,"mean")
#rhoMin = models.MSISE90(z,"low")
#rhoMax = models.MSISE90(z,"high")
#rho = models.mixAtmosphericModels(self.history.datetime[0]+timedelta(seconds=t),rhoMin,rhoMax)
Fd = -0.5 * rho * np.linalg.norm(vrel) * vrel * (
1 / self.spacecraft.BC(self.spacecraft.dryMass + propMass))
p = p + Fd
if self._PERTURBATION_J2_:
J2 = 0.00108263
zz = r[2]
rNorm = np.linalg.norm(r)
bigTerm = np.array([
1 / rNorm * (5 * zz**2 / rNorm**2 - 1),
1 / rNorm * (5 * zz**2 / rNorm**2 - 1),
1 / rNorm * (5 * zz**2 / rNorm**2 - 3)
])
#J2 Gravity Gradient
FJ2 = (
3 / 2
) * J2 * constants.mu_E * constants.Re**2 / rNorm**4 * bigTerm * r
p = p + FJ2
if self._PERTURBATION_SOLARPRESS_:
#u-hat vector pointing from Sun to Earth and Sun position vector
uhat, rS = models.solarPosition(self.history.datetime[0] +
timedelta(seconds=t))
#Solar Radiation Pressure
PSR = 4.56e-6
#Absorbing Area
As = self.spacecraft.area
#Shadow function
rSNorm = np.linalg.norm(rS)
rNorm = np.linalg.norm(r)
theta = np.arccos(np.dot(rS, r) / (rSNorm * rNorm))
theta1 = np.arccos(constants.Re / rNorm)
theta2 = np.arccos(constants.Re / rSNorm)
if (theta1 + theta2 > theta):
nu = 1
else:
nu = 0
#Radiation Pressure Coefficient (lies between 1 and 2)
Cr = self.spacecraft.Cr
#Spacecraft mass
mass = self.spacecraft.dryMass + propMass
#Radiation Pressure acceleration
FR = -nu * PSR * Cr * As / mass * uhat
p = p + FR
if self._PERTURBATION_MOON_:
r_m = models.lunarPositionAlmanac2013(self.history.datetime[0] +
timedelta(seconds=t))
r_ms = r_m - r
#pMoon = constants.mu_M*(r_ms/np.linalg.norm(r_ms)**3-r_m/np.linalg.norm(r_m)**3)
#F(q) formula from F.3 Appendix Curtis 2013
# c = b - a; a << b
# F = 1 - c**3/b**2
qq = np.dot(r, (2 * r_m - r)) / np.linalg.norm(r_m)**2
Fq = (qq**2 - 3 * qq + 3) * qq / (1 + (1 - qq)**(3 / 2))
pMoon = constants.mu_M / np.linalg.norm(r_ms)**3 * (Fq * r_m - r)
p = p + pMoon
if self._PERTURBATION_SUN_:
uhat, r_s = models.solarPosition(self.history.datetime[0] +
timedelta(seconds=t))
r_sunSat = r_s - r
#F(q) formula from F.3 Appendix Curtis 2013
# c = b - a; a << b
# F = 1 - c**3/b**2
qq = np.dot(r, (2 * r_s - r)) / np.linalg.norm(r_s)**2
Fq = (qq**2 - 3 * qq + 3) * qq / (1 + (1 - qq)**(3 / 2))
pSun = constants.mu_S / np.linalg.norm(r_sunSat)**3 * (Fq * r_s -
r)
p = p + pSun
return p