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Optimization
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Context
This tutorial is the third part of the Asteroid Orbit Optimization example. This page reuses the Custom environment part of the example, without the explanation, after which an optimization is executed.
Problem recap
This aim of this tutorial is to illustrate the use of PyGMO to optimize an astrodynamics problem simulated with tudatpy. The problem describes the orbit design around a small body, the Itokawa asteroid.
The 4 design variables are:
initial values of the semi-major axis.
initial eccentricity.
initial inclination.
initial longitude of the ascending node.
The 2 objectives are:
good coverage (maximizing the mean value of the absolute longitude w.r.t. Itokawa over the full propagation).
good resolution (the mean value of the distance should be minimized).
The constraints are set on the altitude: all the sets of design variables leading to an orbit.
NOTE
It is assumed that the reader of this tutorial is already familiar with the content of this basic PyGMO tutorial. The full PyGMO documentation is available on this website. Be careful to read the correct the documentation webpage (there is also a similar one for previous yet now outdated versions here; as you can see, they can easily be confused). PyGMO is the Python counterpart of PAGMO.
Import statements
[1]:
# Load standard modules
import os
import numpy as np
# Uncomment the following to make plots interactive
# %matplotlib widget
from matplotlib import pyplot as plt
from itertools import combinations as comb
# Load tudatpy modules
from tudatpy.io import save2txt
from tudatpy.kernel import constants
from tudatpy.kernel.interface import spice
from tudatpy.kernel.astro import element_conversion
from tudatpy.kernel.astro import frame_conversion
from tudatpy.kernel import numerical_simulation
from tudatpy.kernel.numerical_simulation import environment_setup
from tudatpy.kernel.numerical_simulation import propagation_setup
import tudatpy.util as util
# Load pygmo library
import pygmo as pg
current_dir = os.path.abspath('')
Creation of Custom Environment
Itokawa rotation settings
[2]:
def get_itokawa_rotation_settings(itokawa_body_frame_name):
# Definition of initial Itokawa orientation conditions through the pole orientation
pole_declination = np.deg2rad(-66.30) # Declination
pole_right_ascension = np.deg2rad(90.53) # Right ascension
meridian_at_epoch = 0.0 # Meridian
# Define initial Itokawa orientation in inertial frame (equatorial plane)
initial_orientation_j2000 = frame_conversion.inertial_to_body_fixed_rotation_matrix(
pole_declination, pole_right_ascension, meridian_at_epoch)
# Get initial Itokawa orientation in inertial frame but in the Ecliptic plane
initial_orientation_eclipj2000 = np.matmul(spice.compute_rotation_matrix_between_frames(
"ECLIPJ2000", "J2000", 0.0), initial_orientation_j2000)
# Manually check the results, if desired
check_results = False
if check_results:
np.set_printoptions(precision=100)
print(initial_orientation_j2000)
print(initial_orientation_eclipj2000)
# Compute rotation rate
rotation_rate = np.deg2rad(712.143) / constants.JULIAN_DAY
# Set up rotational model for Itokawa with constant angular velocity
return environment_setup.rotation_model.simple(
"ECLIPJ2000", itokawa_body_frame_name, initial_orientation_eclipj2000, 0.0, rotation_rate)
Itokawa ephemeris settings
[3]:
def get_itokawa_ephemeris_settings(sun_gravitational_parameter):
# Define Itokawa initial Kepler elements
itokawa_kepler_elements = np.array([
1.324118017407799 * constants.ASTRONOMICAL_UNIT,
0.2801166461882852,
np.deg2rad(1.621303507642802),
np.deg2rad(162.8147699851312),
np.deg2rad(69.0803904880264),
np.deg2rad(187.6327516838828)])
# Convert mean anomaly to true anomaly
itokawa_kepler_elements[5] = element_conversion.mean_to_true_anomaly(
eccentricity=itokawa_kepler_elements[1],
mean_anomaly=itokawa_kepler_elements[5])
# Get epoch of initial Kepler elements (in Julian Days)
kepler_elements_reference_julian_day = 2459000.5
# Sets new reference epoch for Itokawa ephemerides (different from J2000)
kepler_elements_reference_epoch = (kepler_elements_reference_julian_day - constants.JULIAN_DAY_ON_J2000) \
* constants.JULIAN_DAY
# Sets the ephemeris model
return environment_setup.ephemeris.keplerian(
itokawa_kepler_elements,
kepler_elements_reference_epoch,
sun_gravitational_parameter,
"Sun",
"ECLIPJ2000")
Itokawa gravity field settings
[4]:
def get_itokawa_gravity_field_settings(itokawa_body_fixed_frame, itokawa_radius):
itokawa_gravitational_parameter = 2.36
normalized_cosine_coefficients = np.array([
[1.0, 0.0, 0.0, 0.0, 0.0],
[0.0, 0.0, 0.0, 0.0, 0.0],
[-0.145216, 0.0, 0.219420, 0.0, 0.0],
[0.036115, -0.028139, -0.046894, 0.069022, 0.0],
[0.087852, 0.034069, -0.123263, -0.030673, 0.150282]])
normalized_sine_coefficients = np.array([
[0.0, 0.0, 0.0, 0.0, 0.0],
[0.0, 0.0, 0.0, 0.0, 0.0],
[0.0, 0.0, 0.0, 0.0, 0.0],
[0.0, -0.006137, -0.046894, 0.033976, 0.0],
[0.0, 0.004870, 0.000098, -0.015026, 0.011627]])
return environment_setup.gravity_field.spherical_harmonic(
gravitational_parameter=itokawa_gravitational_parameter,
reference_radius=itokawa_radius,
normalized_cosine_coefficients=normalized_cosine_coefficients,
normalized_sine_coefficients=normalized_sine_coefficients,
associated_reference_frame=itokawa_body_fixed_frame)
Itokawa shape settings
[5]:
def get_itokawa_shape_settings(itokawa_radius):
# Creates spherical shape settings
return environment_setup.shape.spherical(itokawa_radius)
Simulation bodies
[6]:
def create_simulation_bodies(itokawa_radius):
### CELESTIAL BODIES ###
# Define Itokawa body frame name
itokawa_body_frame_name = "Itokawa_Frame"
# Create default body settings for selected celestial bodies
bodies_to_create = ["Sun", "Earth", "Jupiter", "Saturn", "Mars"]
# Create default body settings for bodies_to_create, with "Earth"/"J2000" as
# global frame origin and orientation. This environment will only be valid
# in the indicated time range [simulation_start_epoch --- simulation_end_epoch]
body_settings = environment_setup.get_default_body_settings(
bodies_to_create,
"SSB",
"ECLIPJ2000")
# Add Itokawa body
body_settings.add_empty_settings("Itokawa")
# Adds Itokawa settings
# Gravity field
body_settings.get("Itokawa").gravity_field_settings = get_itokawa_gravity_field_settings(itokawa_body_frame_name,
itokawa_radius)
# Rotational model
body_settings.get("Itokawa").rotation_model_settings = get_itokawa_rotation_settings(itokawa_body_frame_name)
# Ephemeris
body_settings.get("Itokawa").ephemeris_settings = get_itokawa_ephemeris_settings(
spice.get_body_gravitational_parameter( 'Sun') )
# Shape (spherical)
body_settings.get("Itokawa").shape_settings = get_itokawa_shape_settings(itokawa_radius)
# Create system of selected bodies
bodies = environment_setup.create_system_of_bodies(body_settings)
### VEHICLE BODY ###
# Create vehicle object
bodies.create_empty_body("Spacecraft")
bodies.get("Spacecraft").set_constant_mass(400.0)
# Create radiation pressure settings, and add to vehicle
reference_area_radiation = 4.0
radiation_pressure_coefficient = 1.2
radiation_pressure_settings = environment_setup.radiation_pressure.cannonball(
"Sun",
reference_area_radiation,
radiation_pressure_coefficient)
environment_setup.add_radiation_pressure_interface(
bodies,
"Spacecraft",
radiation_pressure_settings)
return bodies
Acceleration models
[7]:
def get_acceleration_models(bodies_to_propagate, central_bodies, bodies):
# Define accelerations acting on Spacecraft
accelerations_settings_spacecraft = dict(
Sun = [ propagation_setup.acceleration.cannonball_radiation_pressure(),
propagation_setup.acceleration.point_mass_gravity() ],
Itokawa = [ propagation_setup.acceleration.spherical_harmonic_gravity(3, 3) ],
Jupiter = [ propagation_setup.acceleration.point_mass_gravity() ],
Saturn = [ propagation_setup.acceleration.point_mass_gravity() ],
Mars = [ propagation_setup.acceleration.point_mass_gravity() ],
Earth = [ propagation_setup.acceleration.point_mass_gravity() ]
)
# Create global accelerations settings dictionary
acceleration_settings = {"Spacecraft": accelerations_settings_spacecraft}
# Create acceleration models
return propagation_setup.create_acceleration_models(
bodies,
acceleration_settings,
bodies_to_propagate,
central_bodies)
Termination settings
[8]:
def get_termination_settings(mission_initial_time,
mission_duration,
minimum_distance_from_com,
maximum_distance_from_com):
# Mission duration
time_termination_settings = propagation_setup.propagator.time_termination(
mission_initial_time + mission_duration,
terminate_exactly_on_final_condition=False
)
# Upper altitude
upper_altitude_termination_settings = propagation_setup.propagator.dependent_variable_termination(
dependent_variable_settings=propagation_setup.dependent_variable.relative_distance('Spacecraft', 'Itokawa'),
limit_value=maximum_distance_from_com,
use_as_lower_limit=False,
terminate_exactly_on_final_condition=False
)
# Lower altitude
lower_altitude_termination_settings = propagation_setup.propagator.dependent_variable_termination(
dependent_variable_settings=propagation_setup.dependent_variable.altitude('Spacecraft', 'Itokawa'),
limit_value=minimum_distance_from_com,
use_as_lower_limit=True,
terminate_exactly_on_final_condition=False
)
# Define list of termination settings
termination_settings_list = [time_termination_settings,
upper_altitude_termination_settings,
lower_altitude_termination_settings]
return propagation_setup.propagator.hybrid_termination(termination_settings_list,
fulfill_single_condition=True)
Dependent variables to save
[9]:
def get_dependent_variables_to_save():
dependent_variables_to_save = [
propagation_setup.dependent_variable.central_body_fixed_spherical_position(
"Spacecraft", "Itokawa"
)
]
return dependent_variables_to_save
Optimisation problem formulation
[10]:
class AsteroidOrbitProblem:
def __init__(self,
bodies,
propagator_settings,
mission_initial_time,
mission_duration,
design_variable_lower_boundaries,
design_variable_upper_boundaries):
# Sets input arguments as lambda function attributes
# NOTE: this is done so that the class is "pickable", i.e., can be serialized by pygmo
self.bodies_function = lambda: bodies
self.propagator_settings_function = lambda: propagator_settings
# Initialize empty dynamics simulator
self.dynamics_simulator_function = lambda: None
# Set other input arguments as regular attributes
self.mission_initial_time = mission_initial_time
self.mission_duration = mission_duration
self.mission_final_time = mission_initial_time + mission_duration
self.design_variable_lower_boundaries = design_variable_lower_boundaries
self.design_variable_upper_boundaries = design_variable_upper_boundaries
def get_bounds(self):
return (list(self.design_variable_lower_boundaries), list(self.design_variable_upper_boundaries))
def get_nobj(self):
return 2
def fitness(self,
orbit_parameters):
# Retrieves system of bodies
current_bodies = self.bodies_function()
# Retrieves Itokawa gravitational parameter
itokawa_gravitational_parameter = current_bodies.get("Itokawa").gravitational_parameter
# Reset the initial state from the design variable vector
new_initial_state = element_conversion.keplerian_to_cartesian_elementwise(
gravitational_parameter=itokawa_gravitational_parameter,
semi_major_axis=orbit_parameters[0],
eccentricity=orbit_parameters[1],
inclination=np.deg2rad(orbit_parameters[2]),
argument_of_periapsis=np.deg2rad(235.7),
longitude_of_ascending_node=np.deg2rad(orbit_parameters[3]),
true_anomaly=np.deg2rad(139.87))
# Retrieves propagator settings object
propagator_settings = self.propagator_settings_function()
# Reset the initial state
propagator_settings.initial_states = new_initial_state
# Propagate orbit
dynamics_simulator = numerical_simulation.create_dynamics_simulator(current_bodies,
propagator_settings)
# Update dynamics simulator function
self.dynamics_simulator_function = lambda: dynamics_simulator
# Retrieve dependent variable history
dependent_variables = dynamics_simulator.dependent_variable_history
dependent_variables_list = np.vstack(list(dependent_variables.values()))
# Retrieve distance
distance = dependent_variables_list[:, 0]
# Retrieve latitude
latitudes = dependent_variables_list[:, 1]
# Compute mean latitude
mean_latitude = np.mean(np.absolute(latitudes))
# Computes fitness as mean latitude
current_fitness = 1.0 / mean_latitude
# Exaggerate fitness value if the spacecraft has broken out of the selected distance range
current_penalty = 0.0
if (max(dynamics_simulator.dependent_variable_history.keys()) < self.mission_final_time):
current_penalty = 1.0E2
return [current_fitness + current_penalty, np.mean(distance) + current_penalty * 1.0E3]
def get_last_run_dynamics_simulator(self):
return self.dynamics_simulator_function()
Setup orbital simulation
Simulation settings
[11]:
# Load spice kernels
spice.load_standard_kernels()
# Set simulation start and end epochs
mission_initial_time = 0.0
mission_duration = 5.0 * constants.JULIAN_DAY
# Define Itokawa radius
itokawa_radius = 161.915
# Set altitude termination conditions
minimum_distance_from_com = 150.0 + itokawa_radius
maximum_distance_from_com = 5.0E3 + itokawa_radius
# Set boundaries on the design variables
design_variable_lb = (300, 0.0, 0.0, 0.0)
design_variable_ub = (2000, 0.3, 180, 360)
# Create simulation bodies
bodies = create_simulation_bodies(itokawa_radius)
# Define bodies to propagate and central bodies
bodies_to_propagate = ["Spacecraft"]
central_bodies = ["Itokawa"]
# Create acceleration models
acceleration_models = get_acceleration_models(bodies_to_propagate, central_bodies, bodies)
Dependent variables, termination settings, and orbit parameters
[12]:
# Define list of dependent variables to save
dependent_variables_to_save = get_dependent_variables_to_save()
# Create propagation settings
termination_settings = get_termination_settings(
mission_initial_time, mission_duration, minimum_distance_from_com, maximum_distance_from_com)
orbit_parameters = [1.20940330e+03, 2.61526215e-01, 7.53126558e+01, 2.60280587e+02]
Integrator and Propagator settings
[13]:
# Create numerical integrator settings
integrator_settings = propagation_setup.integrator.runge_kutta_variable_step_size(
initial_time_step=1.0,
coefficient_set=propagation_setup.integrator.CoefficientSets.rkf_78,
minimum_step_size=1.0E-6,
maximum_step_size=constants.JULIAN_DAY,
relative_error_tolerance=1.0E-8,
absolute_error_tolerance=1.0E-8)
# Get current propagator, and define translational state propagation settings
propagator = propagation_setup.propagator.cowell
# Define propagation settings
initial_state = np.zeros(6)
propagator_settings = propagation_setup.propagator.translational(central_bodies,
acceleration_models,
bodies_to_propagate,
initial_state,
mission_initial_time,
integrator_settings,
termination_settings,
propagator,
dependent_variables_to_save)
Optimisation run
From here on out the example is new compared to the Custom environment part of the example.
With the optimization problem and the simulation setup in hand, let’s now run our optimization using PyGMO.
Algorithm and problem definition
First, we define a fixed seed that PyGMO will use to generate random numbers. This ensures that the results can be reproduced.
Then, the optimization problem is defined using the AsteroidOrbitProblem class initiated with the values that have already been defined. This User Defined Problem (UDP) is then given to PyGMO trough the pg.problem() method.
Finally, the optimizer is selected to be the Multi-objective EA vith Decomposition (MOAD) algorithm that is implemented in PyGMO. See here for its documentation.
[14]:
# Fix seed for reproducibility
fixed_seed = 112987
# Instantiate orbit problem
orbitProblem = AsteroidOrbitProblem(bodies,
propagator_settings,
mission_initial_time,
mission_duration,
design_variable_lb,
design_variable_ub)
# Create pygmo problem using the UDP instantiated above
prob = pg.problem(orbitProblem)
# Select Moead algorithm from pygmo, with one generation
algo = pg.algorithm(pg.nsga2(gen=1, seed=fixed_seed))
Initial population
An initial population is now going to be generated by PyGMO, of a size of 48 individuals. This means that 48 orbital simulations will be run, and the fitness corresponding to the 48 individuals will be computed using the UDP.
[15]:
# Initialize pygmo population with 48 individuals
population_size = 48
pop = pg.population(prob, size=population_size, seed=fixed_seed)
Evolve population
We now want to make this population evolve, as to (hopefully) get closer to optimum solutions.
In a loop, we thus call algo.evolve(pop) 25 times to make the population evolve 25 times. During each generation, we also save the list of fitness and of design variables.
[16]:
# Set the number of evolutions
number_of_evolutions = 25
# Initialize containers
fitness_list = []
population_list = []
# Evolve the population recursively
for gen in range(number_of_evolutions):
print("Evolving population; at generation %i/%i" % (gen, number_of_evolutions-1), end="\r")
# Evolve the population
pop = algo.evolve(pop)
# Store the fitness values and design variables for all individuals
fitness_list.append(pop.get_f())
population_list.append(pop.get_x())
print("Evolving population is finished")
Evolving population is finishedion 24/24
Results analysis
With the population evolved, the optimization is finished. We can now analyse the results to see how our optimization was carried, and what our optimum solutions are.
Extract results
First of, we want to save the state and dependent variable history of the orbital simulations that were carried in the first and last generations. To do so, we extract the design variables of all the member of a given population, and we run the orbital simulation again, calling the orbitProblem.fitness() function. Then, we can extract the state and dependent variable history by calling the orbitProblem.get_last_run_dynamics_simulator() function.
[17]:
# Retrieve first and last generations for further analysis
pops_to_analyze = {0: 'initial',
number_of_evolutions - 1 : 'final'}
# Initialize containers
simulation_output = dict()
# Loop over first and last generations
for population_index, population_name in pops_to_analyze.items():
# Get population individuals from the given generation
current_population = population_list[population_index]
# Current generation's dictionary
generation_output = dict()
# Loop over all individuals of the populations
for individual in range(population_size):
# Retrieve orbital parameters
current_orbit_parameters = current_population[individual]
# Propagate orbit and compute fitness
orbitProblem.fitness(current_orbit_parameters)
# Retrieve state and dependent variable history
current_states = orbitProblem.get_last_run_dynamics_simulator().state_history
current_dependent_variables = orbitProblem.get_last_run_dynamics_simulator().dependent_variable_history
# Save results to dict
generation_output[individual] = [current_states, current_dependent_variables]
# Append to global dictionary
simulation_output[population_index] = [generation_output,
fitness_list[population_index],
population_list[population_index]]
Pareto fronts
As a first analysis of the optimization results, let’s plot the Pareto fronts, to represent the optimums.
This is done for the first and last generation, plotting the score of the two objectives for all of the population members. A colormap is also used to represent the value of the design variables selected by the optimiser. Finally, the Pareto front is plotted in green, showing the limit of the attainable optimum solutions.
These Pareto fronts show that both of the objectives were successfully improved after 25 generations, attaining lower values for both of them.
We can also notice that the population is packed closer to the Pareto front after 25 generations. At the opposite, the population was covering a higher area of the design space for the first generation.
[18]:
# Create dictionaries defining the design variables
design_variable_names = {0: 'Semi-major axis [m]',
1: 'Eccentricity',
2: 'Inclination [deg]',
3: 'Longitude of the node [deg]'}
design_variable_range = {0: [800.0, 1300.0],
1: [0.10, 0.17],
2: [90.0, 95.0],
3: [250.0, 270.0]}
design_variable_symbols = {0: r'$a$',
1: r'$e$',
2: r'$i$',
3: r'$\Omega$'}
design_variable_units = {0: r' m',
1: r' ',
2: r' deg',
3: r' deg'}
[19]:
# Loop over populations
for population_index in simulation_output.keys():
# Retrieve current population
current_generation = simulation_output[population_index]
# Plot Pareto fronts for all design variables
fig, axs = plt.subplots(2, 2, figsize=(9, 5))
fig.suptitle('Generation ' + str(population_index), fontweight='bold', y=0.95)
current_fitness = current_generation[1]
current_population = current_generation[2]
for ax_index, ax in enumerate(axs.flatten()):
# Plot all the population at given generation
cs = ax.scatter(np.deg2rad(current_fitness[:, 0]),
current_fitness[:, 1],
s=100,
c=current_population[:, ax_index],
marker='.',
cmap="plasma",
alpha=0.65)
# Plot the design variable using a colormap
cbar = fig.colorbar(cs, ax=ax)
cbar.ax.set_ylabel(design_variable_names[ax_index])
# Add a label only on the left-most and bottom-most axes
ax.grid('major')
if ax_index > 1:
ax.set_xlabel(r'Objective 1: coverage [$deg^{-1}$]')
if ax_index == 0 or ax_index == 2:
ax.set_ylabel(r'Objective 2: proximity [$m$]')
# Add the Pareto fron itself in green
optimum_mask = util.pareto_optimums(np.array([np.deg2rad(current_fitness[:, 0]), current_fitness[:, 1]]).T)
ax.step(
sorted(np.deg2rad(current_fitness[:, 0])[optimum_mask], reverse=True),
sorted(current_fitness[:, 1][optimum_mask], reverse=False),
color="#418F3E",
linewidth=2,
alpha=0.75)
# Show the figure
plt.tight_layout()
plt.show()
Design variables histogram
Plotting the histogram of the design variables for the final generation gives insights into what set of orbital parameters lead to optimum solutions. Possible optimum design variables values can then be detected by looking at the number of population members that use them. A high number of occurences in the final generation could indicate a better design variable. At least, this offers some leads into what to investigate further.
[20]:
# Plot histogram for last generation, semi-major axis
fig, axs = plt.subplots(2, 2, figsize=(9, 5))
fig.suptitle('Final orbits by design variable', fontweight='bold', y=0.95)
last_pop = simulation_output[number_of_evolutions - 1][2]
for ax_index, ax in enumerate(axs.flatten()):
ax.hist(last_pop[:, ax_index], bins=30)
# Prettify
ax.set_xlabel(design_variable_names[ax_index])
if ax_index % 2 == 0:
ax.set_ylabel('Occurrences in the population')
# Show the figure
plt.tight_layout()
plt.show()
Initial and final orbits visualisation
One may now want to see how much better the optimized orbits are compared to the ones of the random initial population. This can be done by plotting the orbit bundles from the initial and final generations.
The resulting 3D plot show the chaotic nature of the initial random population, where the last generation appears to use a handfull of variations of the similar design variables.
[21]:
# Plot orbits of initial and final generation
fig = plt.figure(figsize=(9, 5))
fig.suptitle('Initial and final orbit bundle', fontweight='bold', y=0.95)
title = {0: 'Initial orbit bundle',
1: 'Final orbit bundle'}
# Loop over populations
for ax_index, population_index in enumerate(simulation_output.keys()):
current_ax = fig.add_subplot(1, 2, 1 + ax_index, projection='3d')
# Retrieve current population
current_generation = simulation_output[population_index]
current_population = current_generation[2]
# Loop over individuals
for ind_index, individual in enumerate(current_population):
# Plot orbit
state_history = list(current_generation[0][ind_index][0].values())
state_history = np.vstack(state_history)
current_ax.plot(state_history[:, 0],
state_history[:, 1],
state_history[:, 2],
linewidth=0.5)
# Prettify
current_ax.set_xlabel('X [m]')
current_ax.set_ylabel('Y [m]')
current_ax.set_zlabel('Z [m]')
current_ax.set_title(title[ax_index], y=1.0, pad=15)
# Show the figure
plt.tight_layout()
plt.show()
Orbits visualization by design variable
Finally, we can visualize what range of design variables lead to which type of orbits. This is done by plotting the bundle of orbits for the last generation.
This plot one again shows that the orbits from the final population can be sub-categorized into disctinct orbital configurations.
[22]:
# Plot orbits of final generation divided by parameters
fig = plt.figure(figsize=(9, 5))
fig.suptitle('Final orbit bundle by design variable', fontweight='bold', y=0.95)
# Retrieve current population
current_generation = simulation_output[number_of_evolutions - 1]
# Plot Pareto fronts for all design variables
current_population = current_generation[2]
# Loop over design variables
for var in range(4):
# Create axis
current_ax = fig.add_subplot(2, 2, 1 + var, projection='3d')
# Loop over individuals
for ind_index, individual in enumerate(current_population):
# Set plot color according to boundaries
if individual[var] < design_variable_range[var][0]:
plt_color = 'r'
label = design_variable_symbols[var] + ' < ' + str(design_variable_range[var][0]) + \
design_variable_units[var]
elif design_variable_range[var][0] < individual[var] < design_variable_range[var][1]:
plt_color = 'b'
label = str(design_variable_range[var][0]) + ' < ' + \
design_variable_symbols[var] + \
' < ' + str(design_variable_range[var][1]) + design_variable_units[var]
else:
plt_color = 'g'
label = design_variable_symbols[var] + ' > ' + str(design_variable_range[var][1]) + \
design_variable_units[var]
# Plot orbit
state_history = list(current_generation[0][ind_index][0].values())
state_history = np.vstack(state_history)
current_ax.plot(state_history[:, 0],
state_history[:, 1],
state_history[:, 2],
color=plt_color,
linewidth=0.5,
label=label)
# Prettify
current_ax.set_xlabel('X [m]')
current_ax.set_ylabel('Y [m]')
current_ax.set_zlabel('Z [m]')
current_ax.set_title(design_variable_names[var], y=1.0, pad=10)
handles, design_variable_legend = current_ax.get_legend_handles_labels()
design_variable_legend, ids = np.unique(design_variable_legend, return_index=True)
handles = [handles[i] for i in ids]
current_ax.legend(handles, design_variable_legend, loc='lower right', bbox_to_anchor=(0.3, 0.6))
# Show the figure
plt.tight_layout()
plt.show()
