1
2
3
4
5
6
7
8
9
10
11
12
13
14
15
16
17
18
19
20
21
22
23
24
25
26
27
28
29
30
31
32
33
34
35
36
37
38
39
40
41
42
43
44
45
46
47
48
49
50
51
52
53
54
55
56
57
58
59
60
61
62
63
64
65
66
67
68
69
70
71
72
73
74
75
76
77
78
79
80
81
82
83
84
85
86
87
88
89
90
91
92
93
94
95
96
97
98
99
100
101
102
103
104
105
106
107
108
109
110
111
112
113
114
115
116
117
118
119
120
121
122
123
124
125
126
127
128
129
130
131
132
133
134
135
136
137
138
139
140
141
142
143
144
145
146
147
148
149
150
151
152
153
154
155
156
157
158
159
160
161
162
163
164
165
166
167
168
169
170
171
172
173
174
175
176
177
178
179
180
181
182
183
184
185
186
187
188
189
190
191
192
193
194
195
196
197
198
199
200
201
202
203
204
205
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
|
