From 5e82dedea4c56eafc1bba4f3ec8677b15f51c03f Mon Sep 17 00:00:00 2001 From: blendoit Date: Sun, 20 Oct 2019 19:33:53 -0700 Subject: Commence declassification of Evaluator Pointless to have a separate object for the Evaluator when a collection of evaluator.py methods does the trick. --- evaluator/evaluator.py | 206 +++++++++++++++++++++++++++++++++++++++++++++++++ 1 file changed, 206 insertions(+) create mode 100644 evaluator/evaluator.py (limited to 'evaluator/evaluator.py') diff --git a/evaluator/evaluator.py b/evaluator/evaluator.py new file mode 100644 index 0000000..b2b6e18 --- /dev/null +++ b/evaluator/evaluator.py @@ -0,0 +1,206 @@ +""" +The evaluator.py module contains a single Evaluator class, +which knows all the attributes of a specified Aircraft instance, +and contains functions to analyse the airfoil's geometrical +& structural properties. +""" + +import sys +import os.path +import matplotlib.pyplot as plt +import concurrent.futures +import logging + +from . import drag, inertia, lift, mass +import generator + +logging.basicConfig(filename='log_eval.txt', + level=logging.DEBUG, + format='%(asctime)s - %(levelname)s - %(message)s') + + +class Evaluator: + """Performs structural evaluations on aircrafts. + Individual aircrafts must claim an Evaluator object as parent.""" + def __init__(self, name): + self.name = name + self.aircrafts = [] + self.results = [] + + self.I_ = {'x': 0, 'z': 0, 'xz': 0} + + def analyze(self, aircraft): + """Analyze a single aircraft.""" + aircraft.results.update({'Lift': lift.get_lift_total(aircraft)}) + aircraft.results.update({'Drag': drag.get_drag_total(aircraft)}) + aircraft.results.update({'Mass': mass.get_mass_total(aircraft)}) + aircraft.results.update({'Centroid': inertia.get_centroid(aircraft)}) + return aircraft.results + + def analyze_all(self): + """Perform all analysis calculations on a all aircraft in evaluator.""" + with concurrent.futures.ProcessPoolExecutor() as executor: + executor.map(self.analyze, self.aircrafts) + + 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, *aircrafts): + """Print the list of subcomponents.""" + name = f" TREE FOR {[i.name for i in aircrafts]} IN {self.name} " + num_of_dashes = len(name) + print(num_of_dashes * '-') + print(name) + for aircraft in aircrafts: + 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, + *aircrafts, + save_path='/home/blendux/Projects/Aircraft_Studio/save'): + """Save the evaluator's tree to a file.""" + for aircraft in aircrafts: + 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 -- cgit v1.2.3