try:
from Database.database_functions import DatabaseConnector
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
database_connector = DatabaseConnector()
chord_r = database_connector.load_value("root_chord")
taper = database_connector.load_value("taper_ratio")
half_span = database_connector.load_value("wing_span") / 2
#Determines the chord length at every y position along the span
def chord_function(y):
return chord_r - chord_r*(1-taper)*(y/half_span)
from scipy import interpolate
try:
from Database.database_functions import DatabaseConnector
from Integrator import Integration
from MOIcalc.moicalc import inertia
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
from Integrator import Integration
from MOIcalc.moicalc import inertia
database_connector = DatabaseConnector()
wing_span = database_connector.load_value("wing_span") / 2
outer_diameter = database_connector.load_value("df,outer")
radius_fuselage = outer_diameter / 2
E_Modulus = 68.9E9
# function of Mx(span)
# whole function Mx(span)/Ixx(span)
# (-1/E)*(sp.integrate.quad(func, 0, y)) ? Also non linear functions
# first interval is (0 to y)
# second interval (0 to 26)
try:
from CentroidCalculator.centroid_funcs import get_amount_of_stringers
from CentroidCalculator.centroid_calculator import get_centroid
import Importer.xflr5 as aerodynamic_data
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
from CentroidCalculator.centroid_funcs import get_amount_of_stringers
from CentroidCalculator.centroid_calculator import get_centroid
import Importer.xflr5 as aerodynamic_data
database_connector = DatabaseConnector()
def shearflow_doublecell(spanwise_location):
centroid = get_centroid(spanwise_location)
# PROGRAM FROM REINIR TO GET STRINGER LOCATIONS
wingbox_corner_points = database_connector.load_wingbox_value(
'wingbox_corner_points')
def get_location(end_points):
# Input end_points as [[x1,y1], [x2,y2]]
return [(end_points[0][0] + end_points[1][0]) / 2 - centroid[0],
(end_points[0][1] + end_points[1][1]) / 2 - centroid[1]]
def get_length(end_points):
# Scroll all the way down for instructions
import numpy as np
import scipy as sp
from scipy import interpolate
import os
import inspect
try:
from Database.database_functions import DatabaseConnector
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
database_connector = DatabaseConnector()
aerodynamic_data_file_0 = '\\MainWing_a0.00_v10.00ms.txt'
aerodynamic_data_file_10 = '\\MainWing_a10.00_v10.00ms.txt'
"""
Output of this function is a numpy array, where [1] is the second data point, so in essence rows. In that data point:
[0] is the y-span, [1] is the chord, [2] the induced angle of attack, [3] the Cl, [4] the induced Cd, [5] is Cm around c/4
"""
def main_wing_xflr5(name):
main_wing = np.genfromtxt(name,
skip_header=40,
skip_footer=1029,
usecols=(0, 1, 2, 3, 5, 7))
return main_wing
from matplotlib import pyplot as plt
import numpy as np
import math
try:
from Database.database_functions import DatabaseConnector
from CentroidCalculator.centroid_calculator import get_centroid
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
from CentroidCalculator.centroid_calculator import get_centroid
database_connector = DatabaseConnector()
# COORDINATES:___________________________________________________
# list_coordinates = [(0.15, 0.0627513), (0.6, 0.0627513), (0.6, -0.02702924), (0.15, -0.04083288)]
# Class of Parts:
# ____________________________________________
class Part:
def __init__(self, length, thickness, area, angle):
self.LEN = length
self.T = thickness
self.AREA = area
self.ANGL = angle
from Integrator import Integration
from Database.database_functions import DatabaseConnector
from MOIcalc.moicalc import inertia
from CentroidCalculator.centroid_calculator import get_centroid
from WingData.chord_function import chord_function
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
from Integrator import Integration
from MOIcalc.moicalc import inertia
from CentroidCalculator.centroid_calculator import get_centroid
from WingData.chord_function import chord_function
database_connector = DatabaseConnector()
try:
with open("../InertialLoadingCalculator/data.pickle", 'rb') as file:
data = pickle.load(file)
except FileNotFoundError:
with open("./data.pickle", 'rb') as file:
data = pickle.load(file)
y_lst = data[0]
x_moment_lst = data[3]
z_moment_lst = data[6]
step = y_lst[1] - y_lst[0]
b = database_connector.load_value("wing_span") / 2
wingbox_points = database_connector.load_wingbox_value("wingbox_corner_points")
import pickle
try:
from Integrator import Integration
import Importer.xflr5 as aerodynamic_data
from Database.database_functions import DatabaseConnector
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
import Importer.xflr5 as aerodynamic_data
from Database.database_functions import DatabaseConnector
from Integrator import Integration
database_connector = DatabaseConnector()
# Import basic geometry
wing_span = database_connector.load_value("wing_span") / 2
outer_diameter = database_connector.load_value("df,outer")
radius_fuselage = outer_diameter / 2
surface_area = database_connector.load_value("surface_area") / 2
root_chord = database_connector.load_value("root_chord")
tip_chord = database_connector.load_value("tip_chord")
taper_ratio = database_connector.load_value("taper_ratio")
spanwise_location_engine = database_connector.load_value(
"engine_spanwise_location")
chord_at_engine_location = aerodynamic_data.chord_function(
spanwise_location_engine)
radius_engine = database_connector.load_value("d_engine") / 2
import numpy as np
import scipy as sp
try:
from Database.database_functions import DatabaseConnector
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
database_connector = DatabaseConnector()
wingbox_corner_points = database_connector.load_wingbox_value("wingbox_corner_points")
wingbox_centroid_location = [0.37216, 0.01494] # database_connector.load_wingbox_value("wingbox_centroid_location")
def spar_positions():
# x position of the spar
x_spar = wingbox_centroid_location[0]
slope_top_surface = (wingbox_corner_points[1][1] - wingbox_corner_points[0][1])/ (wingbox_corner_points[1][0] - wingbox_corner_points[0][0])
y_top = (x_spar - wingbox_corner_points[0][0]) * slope_top_surface + wingbox_corner_points[0][1]
slope_bottom_surface = (wingbox_corner_points[3][1] - wingbox_corner_points[2][1])/ (wingbox_corner_points[3][0] - wingbox_corner_points[2][0])
y_bottom = (x_spar - wingbox_corner_points[3][0]) * slope_bottom_surface + wingbox_corner_points[3][1]
return (x_spar, y_top), (x_spar, y_bottom)
import sys
import os
import inspect
from os import path
import scipy as sp
from scipy import interpolate
import numpy as np
try:
from Database.database_functions import DatabaseConnector
except ModuleNotFoundError:
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
# Init database connection
database_connector = DatabaseConnector()
# Locate wingbox file destination
wingbox_creator_folder = os.path.dirname(
os.path.abspath(inspect.getfile(inspect.currentframe())))
wingbox_file_destination = wingbox_creator_folder.replace(
"\\", "/").removesuffix("/WingboxCreator") + '/Database/wingbox.json'
halfspan = database_connector.load_value("wing_span") / 2
quarter_chord_sweep = database_connector.load_value("quarter_chord_sweep")
dihedral_angle = database_connector.load_value("dihedral_angle")
""" Determination of the wingbox coordinates """
def airfoil_definition_converter(
airfoil_file): # Previously 'text_to_array_converter'
from math import *
try:
from Database.database_functions import DatabaseConnector
from WingData.chord_function import chord_function
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
from WingData.chord_function import chord_function
database_connector = DatabaseConnector()
pois = database_connector.load_wingbox_value("poisson_ratio")
E = database_connector.load_wingbox_value("youngs_modulus_pa")
t = database_connector.load_wingbox_value("spar_thickness")
points = database_connector.load_wingbox_value("wingbox_corner_points")
def spar_crit_stress(y): #ks needs to be determined manually
if y <= 10:
ks = 9.8
if 10 < y <= 20:
ks = 9.5
if y > 20:
ks = 9.5
b = (points[1][1] - points[2][1]) * chord_function(y)
stress = (((pi**2) * ks * E) / (12 * (1 - (pois**2)))) * ((t / b)**2)
return stress
from Buckling.plate_crit import plate_crit_force
from Buckling.spar_crit import spar_crit_stress
from Buckling.Shear_flow_1cell import main_shear_stress
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
from Buckling.stringer_applied import string_stress_normal, string_stress_tension
from Buckling.stringer_crit import crit_stress_stringer
from Buckling.shear_flow_multicell import shearflow_doublecell
from Buckling.plate_crit import plate_crit_force
from Buckling.spar_crit import spar_crit_stress
from Buckling.Shear_flow_1cell import main_shear_stress
database_connector = DatabaseConnector()
try:
with open("../InertialLoadingCalculator/data.pickle", 'rb') as file:
data = pickle.load(file)
except FileNotFoundError:
with open("./data.pickle", 'rb') as file:
data = pickle.load(file)
y_lst = data[0][:-60]
strength = database_connector.load_wingbox_value("ultimate_strength")
crack_strength = 231400000
shear_strength = database_connector.load_wingbox_value('shear_strength')
def margin_safety_crit(applied, crit):
import matplotlib.pyplot as plt
try:
import Importer.xflr5 as aerodynamic_data
from Database.database_functions import DatabaseConnector
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
import Importer.xflr5 as aerodynamic_data
from Database.database_functions import DatabaseConnector
database_connector = DatabaseConnector()
# Import basic geometry
wing_span = database_connector.load_value("wing_span")
Outer_diameter = database_connector.load_value("df,outer")
radius_fuselage = Outer_diameter / 2
surface_area = database_connector.load_value("surface_area")
# Import weight and location of the engine
weight_engine = database_connector.load_value("engine_weight")
spanwise_location_engine = database_connector.load_value(
"engine_spanwise_location")
# Import the weight of the wing and fuel (Class II)
weight_wing = database_connector.load_value("wing_weight")
weight_fuel = database_connector.load_value("fuel_max")
def lift_distribution(y, density, velocity):
return aerodynamic_data.lift_coef_function_10(y) * 0.5 * density * (
velocity**2) * surface_area
import matplotlib.pyplot as plt
try:
from Database.database_functions import DatabaseConnector
from WingData.chord_function import chord_function
from Integrator import Integration
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
from WingData.chord_function import chord_function
from Integrator import Integration
database_connector = DatabaseConnector()
G = 26 * 10**9 # database_connector.load_value("shear_modulus_pa")
t1 = 0.035 # database_connector.load_wingbox_value("...") left and right spar
t2 = 0.035 # database_connector.load_wingbox_value("...") skin
t3 = 0.035 # database_connector.load_wingbox_value("...") mid spar
engine_pos = database_connector.load_value("engine_spanwise_location")
wingbox_points = database_connector.load_wingbox_value("wingbox_corner_points")
b_one = (wingbox_points[0][1] - wingbox_points[5][1])
b_two = (wingbox_points[2][1] - wingbox_points[3][1])
b_three = (wingbox_points[1][1] - wingbox_points[4][1])
a_one = sqrt((wingbox_points[0][1] - wingbox_points[1][1])**2 +
(wingbox_points[1][0] - wingbox_points[0][0])**2)
a_two = sqrt((wingbox_points[4][1] - wingbox_points[5][1])**2 +
from math import *
try:
from Database.database_functions import DatabaseConnector
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
database_connector = DatabaseConnector()
pois =
E = database_connector.load_wingbox_value("stringer_modulus")
k = 0 #Dont know yet
def plate_crit_force():
Fcr = ((pi**2)*k*E) / (12*(1-))
from math import *
import matplotlib.pyplot as plt
import numpy as np
try:
from Database.database_functions import DatabaseConnector
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
database_connector = DatabaseConnector()
#I = 0.00000158483 #Moment of inertia per stringer. This still needs to be determined.
I = 1.87875E-05
E = database_connector.load_wingbox_value("youngs_modulus_pa")
K = 4 #May vary per section in the wingbox. Needs to be determined manually per section.
def crit_stress_stringer(
y): #L is the wingbox section length, thus rib spacing.
if y <= 10:
L = 0.25
if 10 < y <= 20:
L = 1
if y > 20:
L = 1.7
sigma = (K * (pi**2) * E * I) / (L**2)
return sigma
from math import *
try:
from Database.database_functions import DatabaseConnector
from WingData.chord_function import chord_function
except ModuleNotFoundError:
import sys
from os import path
sys.path.append(path.dirname(path.dirname(path.abspath(__file__))))
from Database.database_functions import DatabaseConnector
from WingData.chord_function import chord_function
database_connector = DatabaseConnector()
pois = database_connector.load_wingbox_value("poisson_ratio")
E = database_connector.load_wingbox_value("youngs_modulus_pa")
kc = 7.3
t = database_connector.load_wingbox_value("plate_thickness")
points = database_connector.load_wingbox_value("wingbox_corner_points")
top_lim1 = database_connector.load_wingbox_value("top_stringer_lim_point_1")
top_lim2 = database_connector.load_wingbox_value("top_stringer_lim_point_2")
top_num_1 = database_connector.load_wingbox_value("top_number_of_stringers_1")
top_num_2 = database_connector.load_wingbox_value("top_number_of_stringers_2")
top_num_3 =database_connector.load_wingbox_value("top_number_of_stringers_3")
bot_lim1 = database_connector.load_wingbox_value("bottom_stringer_lim_point_1")
bot_lim2 = database_connector.load_wingbox_value("bottom_stringer_lim_point_2")
bot_num_1 = database_connector.load_wingbox_value("bottom_number_of_stringers_1")
bot_num_2 = database_connector.load_wingbox_value("bottom_number_of_stringers_2")
bot_num_3 =database_connector.load_wingbox_value("bottom_number_of_stringers_3")