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"""
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
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