diff options
Diffstat (limited to 'creator')
| -rw-r--r-- | creator/__init__.py | 4 | ||||
| -rw-r--r-- | creator/__init__.pyc | bin | 311 -> 0 bytes | |||
| -rw-r--r-- | creator/base.py | 93 | ||||
| -rw-r--r-- | creator/fuselage.py | 0 | ||||
| -rw-r--r-- | creator/log_base.txt | 0 | ||||
| -rw-r--r-- | creator/propulsion.py | 0 | ||||
| -rw-r--r-- | creator/wing.py | 312 |
7 files changed, 0 insertions, 409 deletions
diff --git a/creator/__init__.py b/creator/__init__.py deleted file mode 100644 index 818c7b2..0000000 --- a/creator/__init__.py +++ /dev/null @@ -1,4 +0,0 @@ -from . import base -from . import fuselage -from . import propulsion -from . import wing diff --git a/creator/__init__.pyc b/creator/__init__.pyc Binary files differdeleted file mode 100644 index 022f493..0000000 --- a/creator/__init__.pyc +++ /dev/null diff --git a/creator/base.py b/creator/base.py deleted file mode 100644 index 130add3..0000000 --- a/creator/base.py +++ /dev/null @@ -1,93 +0,0 @@ -"""The base.py module contains parent classes for components.""" - -import numpy as np -import os.path -import random -import logging - -import creator - -logging.basicConfig(filename='log_base.txt', - level=logging.DEBUG, - format='%(asctime)s - %(levelname)s - %(message)s') - - -class Aircraft: - """This class tracks all sub-components and is fed to the evaluator.""" - name = None - fuselage = None - propulsion = None - wing = None - properties = {} - - def __init__(self): - self.results = {} - - def __str__(self): - return self.name - - @classmethod - def from_default(cls): - aircraft = creator.base.Aircraft() - aircraft.name = 'default_aircraft_' + str(random.randrange(1000, 9999)) - airfoil = creator.wing.Airfoil(aircraft, 'default_airfoil') - airfoil.add_naca(2412) - soar1 = creator.wing.Spar(airfoil, 'default_spar_1', 0.30) - soar2 = creator.wing.Spar(airfoil, 'default_spar_2', 0.60) - stringer = creator.wing.Stringer(airfoil, 'default_stringer') - return aircraft - - -class Component: - """Basic component providing coordinates, tools and a component tree.""" - def __init__(self, parent, name): - self.parent = parent - self.name = name - self.x = np.array([]) - self.z = np.array([]) - self.y = np.array([]) - self.material = None - self.mass = float() - self.properties = {} - - def __str__(self): - return self.name - - def info_print(self, round): - """Print all the component's coordinates to the terminal.""" - name = f' CREATOR DATA FOR {str(self).upper()} ' - num_of_dashes = len(name) - print(num_of_dashes * '-') - print(name) - for k, v in self.__dict__.items(): - if type(v) is not np.ndarray: - print(f'{k}:\n', v) - print(num_of_dashes * '-') - for k, v in self.__dict__.items(): - if type(v) is np.ndarray: - print(f'{k}:\n', np.around(v, round)) - return None - - def info_save(self, - save_path='/home/blendux/Projects/Aircraft_Studio/save'): - """Save all the object's coordinates (must be full path).""" - file_name = f'{self.name}_info.txt' - full_path = os.path.join(save_path, file_name) - try: - with open(full_path, 'w') as f: - for k, v in self.__dict__.items(): - if type(v) is not np.ndarray: - f.write(f'{k}=\n') - f.write(str(v)) - f.write("\n") - # print(num_of_dashes * '-') - for k, v in self.__dict__.items(): - if type(v) is np.ndarray: - f.write(f'{k}=\n') - f.write(str(v)) - f.write("\n") - logging.debug(f'Successfully wrote to file {full_path}') - except IOError: - print(f'Unable to write {file_name} to specified directory.\n', - 'Was the full path passed to the function?') - return None diff --git a/creator/fuselage.py b/creator/fuselage.py deleted file mode 100644 index e69de29..0000000 --- a/creator/fuselage.py +++ /dev/null diff --git a/creator/log_base.txt b/creator/log_base.txt deleted file mode 100644 index e69de29..0000000 --- a/creator/log_base.txt +++ /dev/null diff --git a/creator/propulsion.py b/creator/propulsion.py deleted file mode 100644 index e69de29..0000000 --- a/creator/propulsion.py +++ /dev/null diff --git a/creator/wing.py b/creator/wing.py deleted file mode 100644 index 01aa6ff..0000000 --- a/creator/wing.py +++ /dev/null @@ -1,312 +0,0 @@ -""" -The wing.py module contains class definitions for and various components -we add to an airfoil (spars, stringers, and ribs). - -Classes: - Airfoil: instantiated with class method to provide coordinates to heirs. - Spar: inherits from Airfoil. - Stringer: also inherits from Airfoil. - -Functions: - plot_geom(airfoil): generates a 2D plot of the airfoil & any components. -""" - -import logging -import numpy as np -from math import sin, cos, atan -import bisect as bi -import matplotlib.pyplot as plt - -import creator.base as base -import resources.materials as mt - - -class Airfoil(base.Component): - """This class represents a single NACA airfoil. - - The coordinates are saved as two np.arrays - for the x- and z-coordinates. The coordinates start at - the leading edge, travel over the airfoil's upper edge, - then loop back to the leading edge via the lower edge. - - This method was chosen for easier future exports - to 3D CAD packages like SolidWorks, which can import such - geometry as coordinates written in a CSV file. - """ - def __init__(self, - parent, - name, - chord=68, - semi_span=150, - material=mt.aluminium): - super().__init__(parent, name) - parent.wing = self - if chord > 20: - self.chord = chord - else: - self.chord = 20 - logging.debug('Chord too small, using minimum value of 20.') - parent - self.semi_span = semi_span - self.material = material - self.spars = [] - self.stringers = [] - - def add_naca(self, naca_num=2412): - """Generate surface geometry for a NACA airfoil. - - The nested functions perform the required steps to generate geometry, - and can be called to solve the geometry y-coordinate for any 'x' input. - Equation coefficients were retrieved from Wikipedia.org. - - Parameters: - naca_num: 4-digit NACA wing - - Return: - None - """ - self.naca_num = naca_num - # Variables extracted from naca_num argument passed to the function - m = int(str(naca_num)[0]) / 100 - p = int(str(naca_num)[1]) / 10 - t = int(str(naca_num)[2:]) / 100 - # x-coordinate of maximum camber - p_c = p * self.chord - - def get_camber(x): - """ - Returns camber z-coordinate from 1 'x' along the airfoil chord. - """ - z_c = float() - if 0 <= x < p_c: - z_c = (m / (p**2)) * (2 * p * (x / self.chord) - - (x / self.chord)**2) - elif p_c <= x <= self.chord: - z_c = (m / - ((1 - p)**2)) * ((1 - 2 * p) + 2 * p * - (x / self.chord) - (x / self.chord)**2) - return (z_c * self.chord) - - def get_thickness(x): - """Return thickness from 1 'x' along the airfoil chord.""" - x = 0 if x < 0 else x - z_t = 5 * t * self.chord * (+0.2969 * - (x / self.chord)**0.5 - 0.1260 * - (x / self.chord)**1 - 0.3516 * - (x / self.chord)**2 + 0.2843 * - (x / self.chord)**3 - 0.1015 * - (x / self.chord)**4) - return z_t - - def get_theta(x): - dz_c = float() - if 0 <= x < p_c: - dz_c = ((2 * m) / p**2) * (p - x / self.chord) - elif p_c <= x <= self.chord: - dz_c = (2 * m) / ((1 - p)**2) * (p - x / self.chord) - - theta = atan(dz_c) - return theta - - def get_coord_u(x): - x = x - get_thickness(x) * sin(get_theta(x)) - z = get_camber(x) + get_thickness(x) * cos(get_theta(x)) - return (x, z) - - def get_coord_l(x): - x = x + get_thickness(x) * sin(get_theta(x)) - z = get_camber(x) - get_thickness(x) * cos(get_theta(x)) - return (x, z) - - # Densify x-coordinates 10 times for first 1/4 chord length - x_chord_25_percent = round(self.chord / 4) - x_chord = [i / 10 for i in range(x_chord_25_percent * 10)] - x_chord.extend(i for i in range(x_chord_25_percent, self.chord + 1)) - # Generate our airfoil skin geometry from previous sub-functions - self.x_c = np.array([]) - self.z_c = np.array([]) - # Upper surface and camber line - for x in x_chord: - self.x_c = np.append(self.x_c, x) - self.z_c = np.append(self.z_c, get_camber(x)) - self.x = np.append(self.x, get_coord_u(x)[0]) - self.z = np.append(self.z, get_coord_u(x)[1]) - # Lower surface - for x in x_chord[::-1]: - self.x = np.append(self.x, get_coord_l(x)[0]) - self.z = np.append(self.z, get_coord_l(x)[1]) - return None - - -class Spar(base.Component): - """Contains a single spar's data.""" - def __init__(self, parent, name, loc_percent=0.30, material=mt.aluminium): - """Set spar location as percent of chord length.""" - super().__init__(parent, name) - parent.spars.append(self) - self.material = material - self.cap_area = float() - # bi.bisect_left: returns index of first value in parent.x > loc - # This ensures that spar geom intersects with airfoil geom. - loc = loc_percent * parent.chord - # Spar upper coordinates - spar_u = bi.bisect_left(parent.x, loc) - 1 - self.x = np.append(self.x, parent.x[spar_u]) - self.z = np.append(self.z, parent.z[spar_u]) - # Spar lower coordinates - spar_l = bi.bisect_left(parent.x[::-1], loc) - self.x = np.append(self.x, parent.x[-spar_l]) - self.z = np.append(self.z, parent.z[-spar_l]) - return None - - def set_cap_area(self, cap_area): - self.cap_area = cap_area - return None - - def set_mass(self, mass): - self.mass = mass - return None - - -class Stringer(base.Component): - """Contains the coordinates of all stringers.""" - def __init__(self, - parent, - name, - den_u_1=4, - den_u_2=4, - den_l_1=4, - den_l_2=4): - """Add equally distributed stringers to four airfoil locations - (upper nose, lower nose, upper surface, lower surface). - - den_u_1: upper nose number of stringers - den_u_2: upper surface number of stringers - den_l_1: lower nose number of stringers - den_l_2: lower surface number of stringers - """ - super().__init__(parent, name) - parent.stringers = self - self.x_start = [] - self.x_end = [] - self.z_start = [] - self.z_end = [] - self.diameter = float() - self.area = float() - - # Find distance between leading edge and first upper stringer - # interval = self.parent.spars[0].x[0] / (den_u_1 + 1) - interval = 2 - # initialise first self.stringer_x at first interval - x = interval - # Add upper stringers from leading edge until first spar. - for _ in range(0, den_u_1): - # Index of the first value of airfoil.x > x - i = bi.bisect_left(self.parent.x, x) - self.x = np.append(self.x, self.parent.x[i]) - self.z = np.append(self.z, self.parent.z[i]) - x += interval - # Add upper stringers from first spar until last spar - interval = (self.parent.spars[-1].x[0] - - self.parent.spars[0].x[0]) / (den_u_2 + 1) - x = interval + self.parent.spars[0].x[0] - for _ in range(0, den_u_2): - i = bi.bisect_left(self.parent.x, x) - self.x = np.append(self.x, self.parent.x[i]) - self.z = np.append(self.z, self.parent.z[i]) - x += interval - - # Find distance between leading edge and first lower stringer - interval = self.parent.spars[0].x[1] / (den_l_1 + 1) - x = interval - # Add lower stringers from leading edge until first spar. - for _ in range(0, den_l_1): - i = bi.bisect_left(self.parent.x[::-1], x) - self.x = np.append(self.x, self.parent.x[-i]) - self.z = np.append(self.z, self.parent.z[-i]) - x += interval - # Add lower stringers from first spar until last spar - interval = (self.parent.spars[-1].x[1] - - self.parent.spars[0].x[1]) / (den_l_2 + 1) - x = interval + self.parent.spars[0].x[1] - for _ in range(0, den_l_2): - i = bi.bisect_left(self.parent.x[::-1], x) - self.x = np.append(self.x, self.parent.x[-i]) - self.z = np.append(self.z, self.parent.z[-i]) - x += interval - return None - - def add_area(self, area): - self.area = area - return None - - def add_mass(self, mass): - self.mass = len(self.x) * mass + len(self.x) * mass - return None - - def add_webs(self, thickness): - """Add webs to stringers.""" - for _ in range(len(self.x) // 2): - self.x_start.append(self.x[_]) - self.x_end.append(self.x[_ + 1]) - self.z_start.append(self.z[_]) - self.z_end.append(self.z[_ + 1]) - self.thickness = thickness - return None - - def info_print(self, round=2): - super().info_print(round) - print('Stringer Area:\n', np.around(self.area, round)) - return None - - -def plot_geom(airfoil): - """This function plots the airfoil's + sub-components' geometry.""" - fig, ax = plt.subplots() - - # Plot chord - x = [0, airfoil.chord] - y = [0, 0] - ax.plot(x, y, linewidth='1') - # Plot quarter chord - ax.plot(airfoil.chord / 4, - 0, - '.', - color='g', - markersize=24, - label='Quarter-chord') - # Plot mean camber line - ax.plot(airfoil.x_c, - airfoil.z_c, - '-.', - color='r', - linewidth='2', - label='Mean camber line') - # Plot airfoil surfaces - ax.plot(airfoil.x, airfoil.z, color='b', linewidth='1') - - try: # Plot spars - for spar in airfoil.spars: - x = (spar.x) - y = (spar.z) - ax.plot(x, y, '-', color='y', linewidth='4') - except AttributeError: - print('No spars to plot.') - try: # Plot stringers - for i in range(len(airfoil.stringers.x)): - x = airfoil.stringers.x[i] - y = airfoil.stringers.z[i] - ax.plot(x, y, '.', color='y', markersize=12) - except AttributeError: - print('No stringers to plot.') - - ax.set(title='NACA ' + str(airfoil.naca_num) + ' airfoil', - xlabel='X axis', - ylabel='Z axis') - - plt.grid(axis='both', linestyle=':', linewidth=1) - plt.gca().set_aspect('equal', adjustable='box') - plt.gca().legend(bbox_to_anchor=(1, 1), - bbox_transform=plt.gcf().transFigure) - plt.show() - return fig, ax |