Start work on optimized multiprocessing random a/c gen. & eval.HEADmaster

1 files changed, 0 insertions, 195 deletions

diff --git a/evaluator/evaluator.py b/evaluator/evaluator.py
deleted file mode 100644
index 18bb692..0000000
--- a/evaluator/evaluator.py
+++ /dev/null
@@ -1,195 +0,0 @@
-"""
-The evaluator.py module contains functions
-that return calculated data for an aircraft.
-Plotting aircraft components is also possible.
-"""
-
-import os.path
-import concurrent.futures
-import matplotlib.pyplot as plt
-
-from . import drag, inertia, lift, mass
-
-
-def analyze(aircraft):
-    """Analyze a single aircraft."""
-    results = {
-        'Lift': lift.get_lift_total(aircraft),
-        'Drag': drag.get_drag_total(aircraft),
-        'Mass': mass.get_mass_total(aircraft),
-        'Centroid': inertia.get_centroid(aircraft)
-    }
-    aircraft.results = results
-    return aircraft.name, results
-
-
-def analyze_all(population):
-    """Analyze all aircraft in a given population."""
-    # for aircraft in population.aircrafts:
-    #     print(analyze(aircraft))
-    with concurrent.futures.ProcessPoolExecutor() as executor:
-        results = executor.map(analyze, population.aircrafts)
-        for result in results:
-            print(result)
-    return None
-
-    # def analysis(self, V_x, V_z):
-    #     """Perform all analysis calculations and store in class instance."""
-
-    #     self.drag = self.get_drag(10)
-    #     self.lift_rectangular = self.get_lift_rectangular(13.7)
-    #     self.lift_elliptical = self.get_lift_elliptical(15)
-    #     self.lift_total = self.get_lift_total()
-    #     self.mass_dist = self.get_mass_distribution(self.mass_total)
-    #     self.centroid = self.get_centroid()
-    #     self.I_['x'] = self.get_inertia_terms()[0]
-    #     self.I_['z'] = self.get_inertia_terms()[1]
-    #     self.I_['xz'] = self.get_inertia_terms()[2]
-    #     spar_dx = self.get_dx(self.spar)
-    #     spar_dz = self.get_dz(self.spar)
-    #     self.spar.dP_x = self.get_dP(spar_dx, spar_dz, V_x, 0,
-    #                                  self.spar.cap_area)
-    #     self.spar.dP_z = self.get_dP(spar_dx, spar_dz, 0, V_z,
-    #                                  self.spar.cap_area)
-    #     print("yayyyyy")
-    #     return None
-
-    # print(f"Analysis results for {aircraft.name}:\n", results)
-    # self.results = self.get_lift_total(aircraft)
-
-    # self.drag = self.get_drag(10)
-    # self.lift_rectangular = self.get_lift_rectangular(13.7)
-    # self.lift_elliptical = self.get_lift_elliptical(15)
-    # self.lift_total = self.get_lift_total()
-    # self.mass_dist = self.get_mass_distribution(self.mass_total)
-    # self.centroid = self.get_centroid()
-    # self.I_['x'] = self.get_inertia_terms()[0]
-    # self.I_['z'] = self.get_inertia_terms()[1]
-    # self.I_['xz'] = self.get_inertia_terms()[2]
-    # spar_dx = self.get_dx(self.spar)
-    # spar_dz = self.get_dz(self.spar)
-    # self.spar.dP_x = self.get_dP(spar_dx, spar_dz, V_x, 0,
-    #                              self.spar.cap_area)
-    # self.spar.dP_z = self.get_dP(spar_dx, spar_dz, 0, V_z,
-    #                              self.spar.cap_area)
-    # return None
-
-    def tree_print(self, population):
-        """Print the list of subcomponents."""
-        name = f"    TREE FOR {[i.name for i in population.aircraft]} IN {self.name}    "
-        num_of_dashes = len(name)
-        print(num_of_dashes * '-')
-        print(name)
-        for aircraft in population:
-            print(".")
-            print(f"`-- {aircraft}")
-            print(f"    |--{aircraft.wing}")
-            print(f"    |   |-- {aircraft.wing.stringers}")
-            for spar in aircraft.wing.spars[:-1]:
-                print(f"    |   |-- {spar}")
-            print(f"    |   `-- {aircraft.wing.spars[-1]}")
-            print(f"    |-- {aircraft.fuselage}")
-            print(f"    `-- {aircraft.propulsion}")
-        print(num_of_dashes * '-')
-        return None
-
-    def tree_save(self,
-                  population,
-                  save_path='/home/blendux/Projects/Aircraft_Studio/save'):
-        """Save the evaluator's tree to a file."""
-        for aircraft in population.aircraft:
-            file_name = f"{aircraft.name}_tree.txt"
-            full_path = os.path.join(save_path, file_name)
-            with open(full_path, 'w') as f:
-                try:
-                    f.write(".\n")
-                    f.write(f"`-- {aircraft}\n")
-                    f.write(f"    |--{aircraft.wing}\n")
-                    for spar in aircraft.wing.spars[:-1]:
-                        f.write(f"    |   |-- {spar}\n")
-                    f.write(f"    |   `-- {aircraft.wing.spars[-1]}\n")
-                    f.write(f"    |-- {aircraft.fuselage}\n")
-                    f.write(f"    `-- {aircraft.propulsion}\n")
-                    logging.debug(f'Successfully wrote to file {full_path}')
-
-                except IOError:
-                    print(
-                        f'Unable to write {file_name} to specified directory.',
-                        'Was the full path passed to the function?')
-        return None
-
-
-def plot_geom(evaluator):
-    """This function plots analysis results over the airfoil's geometry."""
-    # Plot chord
-    x_chord = [0, evaluator.chord]
-    y_chord = [0, 0]
-    plt.plot(x_chord, y_chord, linewidth='1')
-    # Plot quarter chord
-    plt.plot(evaluator.chord / 4,
-             0,
-             '.',
-             color='g',
-             markersize=24,
-             label='Quarter-chord')
-    # Plot airfoil surfaces
-    x = [0.98 * x for x in evaluator.airfoil.x]
-    y = [0.98 * z for z in evaluator.airfoil.z]
-    plt.fill(x, y, color='w', linewidth='1', fill=False)
-    x = [1.02 * x for x in evaluator.airfoil.x]
-    y = [1.02 * z for z in evaluator.airfoil.z]
-    plt.fill(x, y, color='b', linewidth='1', fill=False)
-
-    # Plot spars
-    try:
-        for _ in range(len(evaluator.spar.x)):
-            x = (evaluator.spar.x[_])
-            y = (evaluator.spar.z[_])
-            plt.plot(x, y, '-', color='b')
-    except AttributeError:
-        print('No spars to plot.')
-    # Plot stringers
-    try:
-        for _ in range(0, len(evaluator.stringer.x)):
-            x = evaluator.stringer.x[_]
-            y = evaluator.stringer.z[_]
-            plt.plot(x, y, '.', color='y', markersize=12)
-    except AttributeError:
-        print('No stringers to plot.')
-
-    # Plot centroid
-    x = evaluator.centroid[0]
-    y = evaluator.centroid[1]
-    plt.plot(x, y, '.', color='r', markersize=24, label='centroid')
-
-    # Graph formatting
-    plt.xlabel('X axis')
-    plt.ylabel('Z axis')
-
-    plot_bound = max(evaluator.airfoil.x)
-    plt.xlim(-0.10 * plot_bound, 1.10 * plot_bound)
-    plt.ylim(-(1.10 * plot_bound / 2), (1.10 * plot_bound / 2))
-    plt.gca().set_aspect('equal', adjustable='box')
-    plt.gca().legend()
-    plt.grid(axis='both', linestyle=':', linewidth=1)
-    plt.show()
-    return None
-
-
-def plot_lift(evaluator):
-    x = range(evaluator.semi_span)
-    y_1 = evaluator.lift_rectangular
-    y_2 = evaluator.lift_elliptical
-    y_3 = evaluator.lift_total
-    plt.plot(x, y_1, '.', color='b', markersize=4, label='Rectangular lift')
-    plt.plot(x, y_2, '.', color='g', markersize=4, label='Elliptical lift')
-    plt.plot(x, y_3, '.', color='r', markersize=4, label='Total lift')
-
-    # Graph formatting
-    plt.xlabel('Semi-span location')
-    plt.ylabel('Lift')
-
-    plt.gca().legend()
-    plt.grid(axis='both', linestyle=':', linewidth=1)
-    plt.show()
-    return None