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

7 files changed, 336 insertions, 0 deletions

diff --git a/aircraftstudio/evaluator/__init__.py b/aircraftstudio/evaluator/__init__.py
new file mode 100644
index 0000000..a58168b
--- /dev/null
+++ b/aircraftstudio/evaluator/__init__.py
@@ -0,0 +1 @@
+from .evaluator import *
diff --git a/aircraftstudio/evaluator/dP.py b/aircraftstudio/evaluator/dP.py
new file mode 100644
index 0000000..b6aaa3b
--- /dev/null
+++ b/aircraftstudio/evaluator/dP.py
@@ -0,0 +1,18 @@
+def get_dx(self, component):
+    return [x - self.centroid[0] for x in component.x_start]
+
+
+def get_dz(self, component):
+    return [x - self.centroid[1] for x in component.x_start]
+
+
+def get_dP(self, xDist, zDist, V_x, V_z, area):
+    I_x = self.I_['x']
+    I_z = self.I_['z']
+    I_xz = self.I_['xz']
+    denom = float(I_x * I_z - I_xz**2)
+    z = float()
+    for _ in range(len(xDist)):
+        z += float(-area * xDist[_] * (I_x * V_x - I_xz * V_z) / denom -
+                   area * zDist[_] * (I_z * V_z - I_xz * V_x) / denom)
+    return z
diff --git a/aircraftstudio/evaluator/drag.py b/aircraftstudio/evaluator/drag.py
new file mode 100644
index 0000000..73a26fc
--- /dev/null
+++ b/aircraftstudio/evaluator/drag.py
@@ -0,0 +1,18 @@
+import random
+
+def get_drag(aircraft, drag):
+    # Transform semi-span integer into list
+    semi_span = [x for x in range(0, aircraft.wing.semi_span)]
+
+    # Drag increases after 80% of the semi_span
+    cutoff = round(0.8 * aircraft.wing.span)
+
+    # Drag increases by 25% after 80% of the semi_span
+    F_x = [drag for x in semi_span[0:cutoff]]
+    F_x.extend([1.25 * drag for x in semi_span[cutoff:]])
+    return F_x
+
+
+def get_drag_total(aircraft):
+    """Get total drag force acting on the aircraft."""
+    return random.random() * 100
diff --git a/aircraftstudio/evaluator/evaluator.py b/aircraftstudio/evaluator/evaluator.py
new file mode 100644
index 0000000..18bb692
--- /dev/null
+++ b/aircraftstudio/evaluator/evaluator.py
@@ -0,0 +1,195 @@
+"""
+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
diff --git a/aircraftstudio/evaluator/inertia.py b/aircraftstudio/evaluator/inertia.py
new file mode 100644
index 0000000..f047766
--- /dev/null
+++ b/aircraftstudio/evaluator/inertia.py
@@ -0,0 +1,66 @@
+def get_centroid(aircraft):
+    """Return the coordinates of the centroid."""
+    # stringer_area = aircraft.wing.stringers.area
+    # cap_area = aircraft.wing.spars.cap_area
+
+    # TODO: Fix this
+    # caps_x = [value for spar in aircraft.wing.spars.x for value in spar]
+    # caps_z = [value for spar in aircraft.wing.spars.z for value in spar]
+    # stringers_x = aircraft.wing.stringers.x
+    # stringers_z = aircraft.wing.stringers.z
+
+    # denominator = float(
+    #     len(caps_x) * cap_area + len(stringers_x) * stringer_area)
+
+    # centroid_x = float(
+    #     sum([x * cap_area
+    #          for x in caps_x]) + sum([x * stringer_area for x in stringers_x]))
+    # centroid_x = centroid_x / denominator
+
+    # centroid_z = float(
+    #     sum([z * cap_area
+    #          for z in caps_z]) + sum([z * stringer_area for z in stringers_z]))
+    # centroid_z = centroid_z / denominator
+
+    # return (centroid_x, centroid_z)
+    return (200, 420)
+
+
+def get_inertia_terms(self):
+    """Obtain all inertia terms."""
+    stringer_area = self.stringer.area
+    cap_area = self.spar.cap_area
+
+    # Adds upper and lower components' coordinates to list
+    x_stringers = self.stringer.x
+    z_stringers = self.stringer.z
+    x_spars = self.spar.x[:][0] + self.spar.x[:][1]
+    z_spars = self.spar.z[:][0] + self.spar.z[:][1]
+    stringer_count = range(len(x_stringers))
+    spar_count = range(len(self.spar.x))
+
+    # I_x is the sum of the contributions of the spar caps and stringers
+    # TODO: replace list indices with dictionary value
+    I_x = sum(
+        [cap_area * (z_spars[i] - self.centroid[1])**2 for i in spar_count])
+    I_x += sum([
+        stringer_area * (z_stringers[i] - self.centroid[1])**2
+        for i in stringer_count
+    ])
+
+    I_z = sum(
+        [cap_area * (x_spars[i] - self.centroid[0])**2 for i in spar_count])
+    I_z += sum([
+        stringer_area * (x_stringers[i] - self.centroid[0])**2
+        for i in stringer_count
+    ])
+
+    I_xz = sum([
+        cap_area * (x_spars[i] - self.centroid[0]) *
+        (z_spars[i] - self.centroid[1]) for i in spar_count
+    ])
+    I_xz += sum([
+        stringer_area * (x_stringers[i] - self.centroid[0]) *
+        (z_stringers[i] - self.centroid[1]) for i in stringer_count
+    ])
+    return (I_x, I_z, I_xz)
diff --git a/aircraftstudio/evaluator/lift.py b/aircraftstudio/evaluator/lift.py
new file mode 100644
index 0000000..516d649
--- /dev/null
+++ b/aircraftstudio/evaluator/lift.py
@@ -0,0 +1,30 @@
+import numpy as np
+from math import sqrt
+
+
+def _get_lift_rectangular(aircraft, lift=50):
+    L_prime = np.array([
+        lift / (aircraft.wing.semi_span * 2)
+        for _ in range(aircraft.wing.semi_span)
+    ])
+    return L_prime
+
+
+def _get_lift_elliptical(aircraft, L_0=3.2):
+    L_prime = np.array([
+        0.5 * L_0 / (aircraft.wing.semi_span * 2) *
+        sqrt(1 - (y / aircraft.wing.semi_span)**2)
+        for y in range(aircraft.wing.semi_span)
+    ])
+    return L_prime
+
+
+def get_lift_total(aircraft):
+    """Combination of rectangular and elliptical lift."""
+    # F_z = self._get_lift_rectangular(aircraft) + self._get_lift_elliptical(
+    #     aircraft)
+    # F_z = self._get_lift_rectangular(
+    #     aircraft) + self._get_lift_elliptical(aircraft) / 2
+    # F_z = [i + j for i, j in self._get_lift_rectangular]
+    # return F_z
+    return 400
diff --git a/aircraftstudio/evaluator/mass.py b/aircraftstudio/evaluator/mass.py
new file mode 100644
index 0000000..7edb926
--- /dev/null
+++ b/aircraftstudio/evaluator/mass.py
@@ -0,0 +1,8 @@
+def get_mass_distribution(self, total_mass):
+    F_z = [total_mass / self.semi_span for x in range(0, self.semi_span)]
+    return F_z
+
+
+def get_mass_total(aircraft):
+    """Get the total aircraft mass."""
+    return 2000