def z_final_force_distribution(y, length_step, density, velocity):
value = lift_distribution(
y, length_step, density, velocity
) - weight_wing / surface_area * aerodynamic_data.chord_function(y)
if ((fuel_tank_start < y < fuel_tank_engine_stop) or
(fuel_tank_engine_start < y < fuel_tank_stop)) and include_fuel_tanks:
value -= (weight_fuel / fuel_tank_length) * fuel_tank_level
if spanwise_location_engine - length_step / 2 < y < spanwise_location_engine + length_step / 2 and include_engine:
value -= weight_engine
return value
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):
# Input end_points as [[x1,y1], [x2,y2]]
return ((end_points[0][0] - end_points[1][0])**2 +
(end_points[0][1] - end_points[1][1])**2)**0.5
# Get all plate dimensions by rearranging corner points
leading_spar_chord = [[
wingbox_corner_points[0][0], wingbox_corner_points[0][1]
], [wingbox_corner_points[3][0], wingbox_corner_points[3][1]]]
trailing_spar_chord = [[
wingbox_corner_points[1][0], wingbox_corner_points[1][1]
], [wingbox_corner_points[2][0], wingbox_corner_points[2][1]]]
leading_spar = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in leading_spar_chord
]
trailing_spar = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in trailing_spar_chord
]
# leading_spar_location = get_location(leading_spar)
# trailing_spar_location = get_location(trailing_spar)
# leading_spar_length = get_length(leading_spar)
# trailing_spar_length = get_length(trailing_spar)
spar_thickness = database_connector.load_wingbox_value('spar_thickness')
top_plate_chord = [[
wingbox_corner_points[0][0], wingbox_corner_points[0][1]
], [wingbox_corner_points[1][0], wingbox_corner_points[1][1]]]
bottom_plate_chord = [[
wingbox_corner_points[2][0], wingbox_corner_points[2][1]
], [wingbox_corner_points[3][0], wingbox_corner_points[3][1]]]
top_plate = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in top_plate_chord
]
bottom_plate = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in bottom_plate_chord
]
# top_plate_location = get_location(top_plate)
# bottom_plate_location = get_location(bottom_plate)
# top_plate_length = get_length(top_plate)
# bottom_plate_length = get_length(bottom_plate)
plate_thickness = database_connector.load_wingbox_value('plate_thickness')
# Get stringer locations along the top and bottom plate:
stringer_top_locations = np.transpose([
np.linspace(top_plate[0][0], top_plate[1][0],
get_amount_of_stringers(spanwise_location, True)),
np.linspace(top_plate[0][1], top_plate[1][1],
get_amount_of_stringers(spanwise_location, True))
])
stringer_top_distance_from_centroid = stringer_top_locations - centroid
stringer_bottom_locations = np.transpose([
np.linspace(bottom_plate[0][0], bottom_plate[1][0],
get_amount_of_stringers(spanwise_location, False)),
np.linspace(bottom_plate[0][1], bottom_plate[1][1],
get_amount_of_stringers(spanwise_location, False))
])
stringer_bottom_distance_from_centroid = stringer_bottom_locations - centroid
# END OF PROGRAM FROM REINIER
# importing the loading data
try:
with open("./data.pickle", 'rb') as file:
data = pickle.load(file)
except FileNotFoundError:
with open("../InertialLoadingCalculator/data.pickle", 'rb') as file:
data = pickle.load(file)
y_span_lst = data[0]
# TORQUE
torsion_lst = data[7]
torsion = sp.interpolate.interp1d(y_span_lst,
torsion_lst,
kind="cubic",
fill_value="extrapolate")
torque_y = torsion(spanwise_location)
# positive z is downwards
# LIFT
lift_lst = data[2]
v_force = sp.interpolate.interp1d(y_span_lst,
lift_lst,
kind="cubic",
fill_value="extrapolate")
v_force_y = v_force(spanwise_location)
# DRAG
drag_lst = data[5]
h_force = sp.interpolate.interp1d(y_span_lst,
drag_lst,
kind="cubic",
fill_value="extrapolate")
h_force_y = h_force(spanwise_location)
# importing constants
G = database_connector.load_wingbox_value("shear_modulus_pa")
wingbox_points = database_connector.load_wingbox_value("wingbox_points")
area_bottom_stringer = database_connector.load_wingbox_value(
"bottom_stringer_area")
area_top_stringer = database_connector.load_wingbox_value(
"top_stringer_area")
# thicknesses of spar and plates for torque calculations
t_12 = t_23 = t_45 = t_56 = database_connector.load_wingbox_value(
"plate_thickness")
t_34 = t_61 = t_25 = database_connector.load_wingbox_value(
"spar_thickness")
# PROCESSING OF RELEVANT DATA FOR SHEAR DUE TO TORQUE CALCULATIONS
# the 6 points are numbered from 1 to 6 from top left to bottom left in clockwise direction
distances_1 = (wingbox_points[0][0] - centroid[0],
wingbox_points[0][1] - centroid[1])
distances_2 = (wingbox_points[1][0] - centroid[0],
wingbox_points[1][1] - centroid[1])
distances_3 = (wingbox_points[2][0] - centroid[0],
wingbox_points[2][1] - centroid[1])
distances_4 = (wingbox_points[3][0] - centroid[0],
wingbox_points[3][1] - centroid[1])
distances_5 = (wingbox_points[4][0] - centroid[0],
wingbox_points[4][1] - centroid[1])
distances_6 = (wingbox_points[5][0] - centroid[0],
wingbox_points[5][1] - centroid[1])
chord_length = aerodynamic_data.chord_function(spanwise_location)
length_12 = abs(distances_1[0] - distances_2[0]) * chord_length
length_23 = abs(distances_2[0] - distances_3[0]) * chord_length
length_34 = abs(distances_3[1] - distances_4[1]) * chord_length
# length_45 = abs(distances_4[0] - distances_5[0]) * chord_length
# length_56 = abs(distances_5[0] - distances_6[0]) * chord_length
length_61 = abs(distances_6[1] - distances_1[1]) * chord_length
length_25 = abs(distances_2[1] - distances_5[1]) * chord_length
encl_area_1256 = (length_25 + length_61) * length_12 / 2
encl_area_2345 = (length_25 + length_34) * length_23 / 2
# PROCESSING OF RELEVANT DATA FOR SHEAR DUE TO VERTICAL FORCE CALCULATIONS
# q_b calculations for each boom
MoI_xx = area_top_stringer * (distances_1[1] ** 2 + distances_2[1] ** 2 + distances_3[1] ** 2) \
+ area_bottom_stringer * (distances_4[1] ** 2 + distances_5[1] ** 2 + distances_6[1] ** 2)
MoI_yy = area_top_stringer * (distances_1[0] ** 2 + distances_2[0] ** 2 + distances_3[0] ** 2) \
+ area_bottom_stringer * (distances_4[0] ** 2 + distances_5[0] ** 2 + distances_6[0] ** 2)
# The integral term for Lorezno
def q_b(distance_from_centroid, area):
return - (MoI_xx * h_force_y) / (MoI_xx * MoI_yy) * (area * distance_from_centroid[0]) - \
(MoI_yy * v_force_y) / (MoI_xx * MoI_yy) * (area * distance_from_centroid[1])
# BOTTOM FLANGES q_b
# q_b for the first cell (two flanges)
q_b_16 = q_b(distances_1, area_top_stringer)
integral_value_front_bottom = q_b_16
q_b_lst_bottom_surface_frontcell = []
# Bottom stringers of front cell (Change as you see fit Lorezno)
for stringer_index in range(
0, int(round(len(stringer_bottom_distance_from_centroid) / 2))):
integral_value_front_bottom += (
q_b(stringer_bottom_distance_from_centroid[stringer_index],
area_bottom_stringer) * get_length([
stringer_bottom_locations[stringer_index],
stringer_bottom_locations[stringer_index - 1]
])) / (plate_thickness * G)
q_b_lst_bottom_surface_frontcell.append(integral_value_front_bottom)
# q_b for the second cell (two flanges)
q_b_25 = q_b(distances_2, area_top_stringer)
integral_value_aft_bottom = q_b_25
q_b_lst_bottom_surface_aftcell = []
# Bottom stringers of aft cell (Change as you see fit)
for stringer_index in range(
int(round(len(stringer_bottom_distance_from_centroid) / 2)),
int(round(len(stringer_bottom_distance_from_centroid)))):
integral_value_aft_bottom += (
q_b(stringer_bottom_distance_from_centroid[stringer_index],
area_bottom_stringer) * get_length([
stringer_bottom_locations[stringer_index],
stringer_bottom_locations[stringer_index - 1]
])) / (plate_thickness * G)
q_b_lst_bottom_surface_aftcell.append(integral_value_aft_bottom)
# TOP FLANGES q_b
integral_value_front_top = q_b_lst_bottom_surface_frontcell[-1]
q_b_lst_top_surface_frontcell = []
# Bottom stringers of front cell (Change as you see fit Lorezno)
for stringer_index in range(
0, int(round(len(stringer_top_distance_from_centroid) / 2))):
integral_value_front_top += (
q_b(stringer_top_distance_from_centroid[stringer_index],
area_top_stringer) * get_length([
stringer_top_locations[stringer_index],
stringer_top_locations[stringer_index - 1]
])) / (plate_thickness * G)
q_b_lst_bottom_surface_frontcell.append(integral_value_front_top)
# q_b for the second cell (two flanges)
integral_value_aft_top = q_b_lst_bottom_surface_aftcell[-1]
q_b_lst_top_surface_aftcell = []
# Bottom stringers of aft cell (Change as you see fit)
for stringer_index in range(
int(round(len(stringer_top_distance_from_centroid) / 2)),
int(round(len(stringer_top_distance_from_centroid)))):
integral_value_aft_top += (
q_b(stringer_top_distance_from_centroid[stringer_index],
area_top_stringer) * get_length([
stringer_top_locations[stringer_index],
stringer_top_locations[stringer_index - 1]
])) / (plate_thickness * G)
q_b_lst_top_surface_aftcell.append(integral_value_aft_top)
inter_stringer_distance_bottom = get_length(
[[0, 0],
abs(stringer_bottom_distance_from_centroid[0] -
stringer_bottom_distance_from_centroid[1])])
inter_stringer_distance_top = get_length(
[[0, 0],
abs(stringer_top_distance_from_centroid[0] -
stringer_top_distance_from_centroid[1])])
p1 = np.array([centroid[0], centroid[1]])
p2 = np.array(stringer_bottom_distance_from_centroid[0])
p3 = np.array(stringer_bottom_distance_from_centroid[1])
moment_arm_bottom_surface_qbs = np.cross(p2 - p1,
p3 - p1) / np.linalg.norm(p2 - p1)
# moment generated by qbs and forces around point 2
## TO BE CHECKED WITH RASA
moment_due_to_forces = v_force_y * distances_2[
0] + h_force_y * distances_2[1]
## Direction to be checked
moment_due_to_bottom_surface_qbs_frontcell = integral_value_front_bottom * \
length_12 \
+ moment_arm_bottom_surface_qbs * \
sum(q_b_lst_bottom_surface_frontcell[:-1])
moment_due_to_bottom_surface_qbs_aftcell = moment_arm_bottom_surface_qbs * \
sum(q_b_lst_bottom_surface_aftcell[:-1]) + \
length_34 * \
q_b_lst_bottom_surface_aftcell[-1]
total_moment_forces_qbs_allcell = moment_due_to_forces - moment_due_to_bottom_surface_qbs_frontcell - \
moment_due_to_bottom_surface_qbs_aftcell
# line integrals functional to the equation with dthetha/dz
# bottom plates
line_integral_qb_frontcell_bottom = (
integral_value_front_bottom * length_61 +
q_b_lst_bottom_surface_frontcell[-1] * length_25) / (t_61 * G)
for element in q_b_lst_bottom_surface_frontcell[:-1]:
line_integral_qb_frontcell_bottom += element * inter_stringer_distance_bottom / (
t_56 * G)
line_integral_qb_aftcell_bottom = (
integral_value_aft_bottom * length_25 +
q_b_lst_bottom_surface_aftcell[-1] * length_34) / (t_25 * G)
for element in q_b_lst_bottom_surface_aftcell[:-1]:
line_integral_qb_aftcell_bottom += element * inter_stringer_distance_bottom / (
t_45 * G)
# top plates
line_integral_qb_frontcell_top = 0
for element in q_b_lst_top_surface_frontcell[:-1]:
line_integral_qb_frontcell_top += element * inter_stringer_distance_top / (
t_12 * G)
line_integral_qb_aftcell_top = 0
for element in q_b_lst_top_surface_aftcell[:-1]:
line_integral_qb_aftcell_top += element * inter_stringer_distance_top / (
t_23 * G)
dthetha_dz_contribution_qb_frontcell = (line_integral_qb_frontcell_bottom + line_integral_qb_frontcell_top) \
/ (2 * encl_area_1256)
dthetha_dz_contribution_qb_aftcell = (line_integral_qb_aftcell_bottom + line_integral_qb_aftcell_top) \
/ (2 * encl_area_1256)
# Matrix
matrix = np.array([[2 * encl_area_1256, 2 * encl_area_2345, 0],
[
1 / (2 * encl_area_1256 * G) *
(1 / t_12 + 1 / t_61 + 1 / t_25 + 1 / t_56),
1 / (2 * encl_area_1256 * G) * (-1 / t_25), -1
],
[
1 / (2 * encl_area_2345 * G) * (-1 / t_25),
1 / (2 * encl_area_2345 * G) *
(1 / t_23 + 1 / t_34 + 1 / t_45 + 1 / t_25), -1
]])
# SHEAR DUE TO TORQUE
solution_vector_t = np.array([torque_y, 0, 0])
q_t_1256, q_t_2345, dtheta_t = np.linalg.solve(matrix, solution_vector_t)
# SHEAR DUE TO VERTICAL and HORIZONTAL FORCE #tbf
solution_vector_s = np.array([
total_moment_forces_qbs_allcell, dthetha_dz_contribution_qb_frontcell,
dthetha_dz_contribution_qb_aftcell
])
q_s_s0_1256, q_s_s0_2345, dtheta_s = np.linalg.solve(
matrix, solution_vector_s)
# TOTAL SHEAR FORCE EVALUATION IN EACH SECTION
q_max_top_flange_value = 0
q_max_bottom_flange_value = 0
# top surface aftcell
for stringer_index in range(
int(round(len(stringer_top_distance_from_centroid) / 2)),
int(round(len(stringer_top_distance_from_centroid)))):
q_tot = abs(
q_b(stringer_top_distance_from_centroid[stringer_index],
area_top_stringer) + q_t_2345 + q_s_s0_2345)
if q_tot > q_max_top_flange_value:
q_max_top_flange_value = q_tot
if abs(q_t_1256 + q_s_s0_1256) > q_max_top_flange_value:
q_max_top_flange_value = abs(q_t_1256 + q_s_s0_1256)
if abs(q_t_2345 + q_s_s0_2345) > q_max_top_flange_value:
q_max_top_flange_value = abs(q_t_2345 + q_s_s0_2345)
# bottom surface aftcell
for stringer_index in range(
int(round(len(stringer_bottom_distance_from_centroid) / 2)),
int(round(len(stringer_bottom_distance_from_centroid)))):
q_tot = abs(
q_b(stringer_bottom_distance_from_centroid[stringer_index],
area_bottom_stringer) + q_t_2345 + q_s_s0_2345)
if q_tot > q_max_bottom_flange_value:
q_max_bottom_flange_value = q_tot
# top surface frontcell
for stringer_index in range(
0, int(round(len(stringer_top_distance_from_centroid) / 2))):
q_tot = abs(
q_b(stringer_top_distance_from_centroid[stringer_index],
area_top_stringer) + q_t_1256 + q_s_s0_1256)
if q_tot > q_max_top_flange_value:
q_max_top_flange_value = q_tot
# bottom surface frontcell
for stringer_index in range(
0, int(round(len(stringer_top_distance_from_centroid) / 2))):
q_tot = abs(
q_b(stringer_bottom_distance_from_centroid[stringer_index],
area_bottom_stringer) + q_t_1256 + q_s_s0_1256)
if q_tot > q_max_bottom_flange_value:
q_max_bottom_flange_value = q_tot
# front spar tot shear flow
q_tot_front_spar = abs(integral_value_front_bottom + q_t_1256 +
q_s_s0_1256)
# middle spar tot shear flow
q_tot_middle_spar = abs(
q_b(
stringer_bottom_distance_from_centroid[int(
round(len(stringer_bottom_distance_from_centroid) /
2))], area_top_stringer) + q_t_1256 + q_s_s0_1256 -
q_t_2345 - q_s_s0_2345)
# aft spar tot shear flow
#q_tot_aft_spar = abs(q_b(stringer_bottom_distance_from_centroid[len(stringer_top_distance_from_centroid) -1],
#area_top_stringer) + q_t_1256 + q_s_s0_1256 - q_t_2345 - q_s_s0_2345 + q_t_2345 + q_s_s0_2345)
return q_max_top_flange_value / t_12, q_max_bottom_flange_value / t_12, max(
q_tot_front_spar, q_tot_middle_spar) * t_61
def drag_distribution(y, length_step, density, velocity):
return load_factor * (drag_induced_function(y) + cd_0) * 0.5 * density * (
velocity**2) * aerodynamic_data.chord_function(y)
def pitching_moment_function(y, density, velocity, length_step):
# 0.5 rho V^2 S c
# print(aerodynamic_data.moment_coef_function_10(y))
return load_factor * moment_coef_function(y) * 0.5 * density * (velocity ** 2) * aerodynamic_data.chord_function(y) * \
aerodynamic_data.chord_function(y)
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
moment_arm_engine = (
0.25 + 0.2) * aerodynamic_data.chord_function(spanwise_location_engine)
moment_arm_thrust = 1.5 * radius_engine
global_length_step = 0.1 # [m]
# Define the flight conditions
test_velocity = 236.32 # m/s
test_density = 1.225 # kg/m^2
lift_coef_function = aerodynamic_data.lift_coef_function_10
drag_induced_function = aerodynamic_data.drag_induced_function_10
moment_coef_function = aerodynamic_data.moment_coef_function_10
def lift_distribution(y, length_step, density, velocity):
return load_factor * lift_coef_function(y) * 0.5 * density * (
velocity**2) * aerodynamic_data.chord_function(y)
def main_shear_stress(b):
#basics
list_coordinates = [(0.15, 0.06588533), (0.6, 0.0627513),
(0.6, -0.02702924), (0.15, -0.04083288)]
AC = AC_lenght(b)
lenghts = get_lenghts(list_coordinates)
slopes = get_slopes(list_coordinates)
Am = 0.5 * abs(
sum(x0 * y1 - x1 * y0 for ((x0, y0), (x1, y1)) in area_segments(
[x * aerodynamic_data.chord_function(b)
for x in list_coordinates])))
#******************************************************
if b <= 10:
topstr = database_connector.load_wingbox_value(
"top_number_of_stringers_1") #number of top stringers
botstr = database_connector.load_wingbox_value(
"bottom_number_of_stringers_1") #number of bottom stingers
if 10 < b <= 20:
topstr = database_connector.load_wingbox_value(
"top_number_of_stringers_2") #number of top stringers
botstr = database_connector.load_wingbox_value(
"bottom_number_of_stringers_2") #number of bottom stingers
if b > 20:
topstr = database_connector.load_wingbox_value(
"top_number_of_stringers_3") #number of top stringers
botstr = database_connector.load_wingbox_value(
"bottom_number_of_stringers_3") #number of bottom stingers
A1 = database_connector.load_wingbox_value(
"top_stringer_area") #area of corner stringers
A2 = database_connector.load_wingbox_value(
"top_stringer_area") #area of normal stringers
t_spar = database_connector.load_wingbox_value("spar_thickness")
t_skin = database_connector.load_wingbox_value("plate_thickness")
distances_btwn_stringers = distances(topstr, botstr, lenghts)
z_list = z(get_centroid(b), list_coordinates, topstr, botstr, lenghts,
slopes, distances_btwn_stringers, AC)
x_list = x(get_centroid(b), list_coordinates, topstr, botstr, lenghts,
slopes, distances_btwn_stringers, AC)
area_list = area_append(A1, A2, topstr, botstr)
# print(area_list)
# print(x_list)
# print(z_list)
#****** shear*****
qb_list = delta_q_and_qb(z_list, x_list, area_list, b, x_shear(b),
z_shear(b))
#print(qb_list)
q_so = qso(list_coordinates, qb_list, slopes, get_centroid(b), AC, b, Am,
x_shear(b), z_shear(b), lenghts, botstr)
#print(q_so)
q_t = qt(torsion(b), Am)
#print(q_t)
q_list = shear_flow(qb_list, q_t, q_so)
thicc_list = []
for i in range(botstr - 1):
thicc_list.append(t_skin)
thicc_list.append(t_spar)
for i in range(topstr - 1):
thicc_list.append(t_skin)
thicc_list.append(t_spar)
#print(thicc_list)
shear_stress = [i / j for i, j in zip(q_list, thicc_list)]
#max values
# max bottom
bottom_shear_list = []
for i in range(botstr - 1):
a = shear_stress[i]
bottom_shear_list.append(a)
# spars
spar_shear_stress_list = [shear_stress[botstr - 1], shear_stress[-1]]
top_plate_list = shear_stress[botstr:-1]
bottom_shear_list_abs = [abs(x) for x in bottom_shear_list]
spar_shear_stress_list_abs = [abs(x) for x in spar_shear_stress_list]
top_plate_list_abs = [abs(x) for x in top_plate_list]
max_tau_bottom_plate = max(bottom_shear_list_abs)
max_tau_top_plate = max(top_plate_list_abs)
max_tau_spars = max(spar_shear_stress_list_abs)
max_list = [max_tau_bottom_plate, max_tau_top_plate,
max_tau_spars] #<---------------------------
#print(q_list)
#shear_stress_max = max(shear_stress)
return max_list #shear_stress #_max
def get_polar_moment_of_inertia(spanwise_location):
"""
Calculates the polar moment of inertia of the wingbox around the centroid.
It uses a combination of rect subdivision and boom approximation to find this moment.
:param spanwise_location: The location of the cross-section along the span for which the polar moment of Inertia is calculated.
:return: The polar moment of Inertia of the wingbox cross-section in m4
"""
# Local coord system: x from LE to TE, y upwards
centroid = get_centroid(spanwise_location)
top_stringer_area = database_connector.load_wingbox_value(
'top_stringer_area')
bottom_stringer_area = database_connector.load_wingbox_value(
'bottom_stringer_area')
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):
# Input end_points as [[x1,y1], [x2,y2]]
return ((end_points[0][0] - end_points[1][0])**2 +
(end_points[0][1] - end_points[1][1])**2)**0.5
# Get all plate dimensions by rearranging corner points
leading_spar_chord = [[
wingbox_corner_points[0][0], wingbox_corner_points[0][1]
], [wingbox_corner_points[3][0], wingbox_corner_points[3][1]]]
trailing_spar_chord = [[
wingbox_corner_points[1][0], wingbox_corner_points[1][1]
], [wingbox_corner_points[2][0], wingbox_corner_points[2][1]]]
middle_spar_chord = [
[(wingbox_corner_points[0][0] + wingbox_corner_points[1][0]) / 2,
(wingbox_corner_points[0][1] + wingbox_corner_points[1][1]) / 2],
[(wingbox_corner_points[2][0] + wingbox_corner_points[3][0]) / 2,
(wingbox_corner_points[2][1] + wingbox_corner_points[3][1]) / 2]
]
leading_spar = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in leading_spar_chord
]
trailing_spar = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in trailing_spar_chord
]
middle_spar = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in middle_spar_chord
]
leading_spar_location = get_location(leading_spar)
trailing_spar_location = get_location(trailing_spar)
middle_spar_location = get_location(middle_spar)
leading_spar_length = get_length(leading_spar)
trailing_spar_length = get_length(trailing_spar)
middle_spar_length = get_length(middle_spar)
middle_spar_end = database_connector.load_wingbox_value('third_spar_end')
spar_thickness = database_connector.load_wingbox_value('spar_thickness')
top_plate_chord = [[
wingbox_corner_points[0][0], wingbox_corner_points[0][1]
], [wingbox_corner_points[1][0], wingbox_corner_points[1][1]]]
bottom_plate_chord = [[
wingbox_corner_points[2][0], wingbox_corner_points[2][1]
], [wingbox_corner_points[3][0], wingbox_corner_points[3][1]]]
top_plate = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in top_plate_chord
]
bottom_plate = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in bottom_plate_chord
]
top_plate_location = get_location(top_plate)
bottom_plate_location = get_location(bottom_plate)
top_plate_length = get_length(top_plate)
bottom_plate_length = get_length(bottom_plate)
plate_thickness = database_connector.load_wingbox_value('plate_thickness')
# Get stringer locations along the top and bottom plate:
stringer_top_locations = np.transpose([
np.linspace(top_plate[0][0], top_plate[1][0],
get_amount_of_stringers(spanwise_location, True)),
np.linspace(top_plate[0][1], top_plate[1][1],
get_amount_of_stringers(spanwise_location, True))
])
stringer_bottom_locations = np.transpose([
np.linspace(bottom_plate[0][0], bottom_plate[1][0],
get_amount_of_stringers(spanwise_location, False)),
np.linspace(bottom_plate[0][1], bottom_plate[1][1],
get_amount_of_stringers(spanwise_location, False))
])
def ll_axis_term(area, location):
# parallel axis term
return area * (location[0]**2 + location[1]**2)
def p_moi_rect(height, width, location):
# Standard formula and parallel axis term
# return (width * height * (width ** 2 + height ** 2)) / 12 + ll_axis_term(width * height, location)
return (width * height ** 3) / 12 + ll_axis_term(width * height, [location[0], 0]) + \
(height * width ** 3) / 12 + ll_axis_term(width * height, [0, location[1]])
def p_moi_point(area, location):
# Treat as point area and neglect terms except for parallel axis term
return ll_axis_term(area, [location[0], 0]) + ll_axis_term(
area, [0, location[1]])
polar_moment_of_inertia = 0
# Due to plates
polar_moment_of_inertia += p_moi_rect(leading_spar_length, spar_thickness,
leading_spar_location)
polar_moment_of_inertia += p_moi_rect(trailing_spar_length, spar_thickness,
trailing_spar_location)
polar_moment_of_inertia += p_moi_rect(plate_thickness, top_plate_length,
top_plate_location)
polar_moment_of_inertia += p_moi_rect(plate_thickness, bottom_plate_length,
bottom_plate_location)
if spanwise_location < middle_spar_end:
polar_moment_of_inertia += p_moi_rect(middle_spar_length,
spar_thickness,
middle_spar_location)
# Due to top stringers
for stringer_location in stringer_top_locations:
polar_moment_of_inertia += p_moi_point(top_stringer_area,
stringer_location)
# Due to bottom stringers
for stringer_location in stringer_bottom_locations:
polar_moment_of_inertia += p_moi_point(bottom_stringer_area,
stringer_location)
return polar_moment_of_inertia * 0.16
def get_torsional_constant(spanwise_location):
# centroid = get_centroid(spanwise_location)
wingbox_corner_points = database_connector.load_wingbox_value(
'wingbox_corner_points')
def get_length(end_points):
# Input end_points as [[x1,y1], [x2,y2]]
return ((end_points[0][0] - end_points[1][0])**2 +
(end_points[0][1] - end_points[1][1])**2)**0.5
# Get all plate dimensions by rearranging corner points
leading_spar_chord = [[
wingbox_corner_points[0][0], wingbox_corner_points[0][1]
], [wingbox_corner_points[3][0], wingbox_corner_points[3][1]]]
trailing_spar_chord = [[
wingbox_corner_points[1][0], wingbox_corner_points[1][1]
], [wingbox_corner_points[2][0], wingbox_corner_points[2][1]]]
middle_spar_chord = [
[(wingbox_corner_points[0][0] + wingbox_corner_points[1][0]) / 2,
(wingbox_corner_points[0][1] + wingbox_corner_points[1][1]) / 2],
[(wingbox_corner_points[2][0] + wingbox_corner_points[3][0]) / 2,
(wingbox_corner_points[2][1] + wingbox_corner_points[3][1]) / 2]
]
leading_spar = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in leading_spar_chord
]
trailing_spar = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in trailing_spar_chord
]
middle_spar = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in middle_spar_chord
]
leading_spar_length = get_length(leading_spar)
trailing_spar_length = get_length(trailing_spar)
spar_thickness = database_connector.load_wingbox_value('spar_thickness')
top_plate_chord = [[
wingbox_corner_points[0][0], wingbox_corner_points[0][1]
], [wingbox_corner_points[1][0], wingbox_corner_points[1][1]]]
bottom_plate_chord = [[
wingbox_corner_points[2][0], wingbox_corner_points[2][1]
], [wingbox_corner_points[3][0], wingbox_corner_points[3][1]]]
top_plate = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in top_plate_chord
]
bottom_plate = [
x * aerodynamic_data.chord_function(spanwise_location)
for x in bottom_plate_chord
]
top_plate_length = get_length(top_plate)
bottom_plate_length = get_length(bottom_plate)
plate_thickness = database_connector.load_wingbox_value('plate_thickness')
def area_segments(p):
return zip(p, p[1:] + [p[0]])
enclosed_area = 0.5 * abs(
sum(x0 * y1 - x1 * y0 for ((x0, y0), (x1, y1)) in area_segments([
x * aerodynamic_data.chord_function(spanwise_location)
for x in wingbox_corner_points
])))
integral_equivalent = top_plate_length / plate_thickness + bottom_plate_length / plate_thickness + leading_spar_length / spar_thickness + \
trailing_spar_length / spar_thickness
return (4 * enclosed_area**2) / integral_equivalent
def torque_shear_flow(AC, Torsion, b, list_coordinates):
Am = 0.5 * abs(
sum(x0 * y1 - x1 * y0 for ((x0, y0), (x1, y1)) in area_segments(
[x * aerodynamic_data.chord_function(b)
for x in list_coordinates])))
if b <= 10:
three_spars = True
else:
three_spars = False
if three_spars == True:
try:
with open("./data.pickle", 'rb') as file:
data = pickle.load(file)
except FileNotFoundError:
with open("../InertialLoadingCalculator/data.pickle",
'rb') as file:
data = pickle.load(file)
y_span_lst = data[0]
# TORQUE
spanwise_location = b
torsion_lst = data[7]
torsion = sp.interpolate.interp1d(y_span_lst,
torsion_lst,
kind="cubic",
fill_value="extrapolate")
torque_y = torsion(spanwise_location)
wingbox_points = database_connector.load_wingbox_value(
"wingbox_points")
G = database_connector.load_wingbox_value("shear_modulus_pa")
chord_length = aerodynamic_data.chord_function(spanwise_location)
centroid = get_centroid(spanwise_location)
distances_1 = (wingbox_points[0][0] - centroid[0],
wingbox_points[0][1] - centroid[1])
distances_2 = (wingbox_points[1][0] - centroid[0],
wingbox_points[1][1] - centroid[1])
distances_3 = (wingbox_points[2][0] - centroid[0],
wingbox_points[2][1] - centroid[1])
distances_4 = (wingbox_points[3][0] - centroid[0],
wingbox_points[3][1] - centroid[1])
distances_5 = (wingbox_points[4][0] - centroid[0],
wingbox_points[4][1] - centroid[1])
distances_6 = (wingbox_points[5][0] - centroid[0],
wingbox_points[5][1] - centroid[1])
length_12 = abs(distances_1[0] - distances_2[0]) * chord_length
length_23 = abs(distances_2[0] - distances_3[0]) * chord_length
length_34 = abs(distances_3[1] - distances_4[1]) * chord_length
length_61 = abs(distances_6[1] - distances_1[1]) * chord_length
length_25 = abs(distances_2[1] - distances_5[1]) * chord_length
t_12 = t_23 = t_45 = t_56 = database_connector.load_wingbox_value(
"plate_thickness")
t_34 = t_61 = t_25 = database_connector.load_wingbox_value(
"spar_thickness")
encl_area_1256 = (length_25 + length_61) * length_12 / 2
encl_area_2345 = (length_25 + length_34) * length_23 / 2
# Matrix
matrix = np.array([[2 * encl_area_1256, 2 * encl_area_2345, 0],
[
1 / (2 * encl_area_1256 * G) *
(1 / t_12 + 1 / t_61 + 1 / t_25 + 1 / t_56),
1 / (2 * encl_area_1256 * G) * (-1 / t_25), -1
],
[
1 / (2 * encl_area_2345 * G) * (-1 / t_25),
1 / (2 * encl_area_2345 * G) *
(1 / t_23 + 1 / t_34 + 1 / t_45 + 1 / t_25), -1
]])
# SHEAR DUE TO TORQUE
solution_vector_t = np.array([torque_y, 0, 0])
q_t_1256, q_t_2345, dtheta_t = np.linalg.solve(matrix,
solution_vector_t)
q_t = (q_t_1256, q_t_2345)
else:
q_t_a = Torsion / 2 * Am
q_t = (q_t_a, q_t_a)
return q_t
def get_centroid(spanwise_location, verbose=False):
"""
Calculates the X and Z component of the centroid.
:param spanwise_location: The location of the cross-section along the span for which the centroid is calculated
:param verbose: Print values while calculating
:return: The centroid of the cross-section as a list of [X, Z]
"""
chord_length = aerodynamic_data.chord_function(spanwise_location)
# wing box configuration
wingbox_corner_points = database_connector.load_wingbox_value(
"wingbox_corner_points")
left_top_corner_wingbox = wingbox_corner_points[0] * chord_length
left_bottom_corner_wingbox = wingbox_corner_points[3] * chord_length
right_top_corner_wingbox = wingbox_corner_points[1] * chord_length
right_bottom_corner_wingbox = wingbox_corner_points[2] * chord_length
length_top_plate = (math.sqrt(
(right_top_corner_wingbox[0] - left_top_corner_wingbox[0])**2 +
(left_top_corner_wingbox[1] - right_top_corner_wingbox[1])**2))
height_front_spar = (left_top_corner_wingbox[1] -
left_bottom_corner_wingbox[1])
height_back_spar = (right_top_corner_wingbox[1] -
right_bottom_corner_wingbox[1])
length_bottom_plate = (math.sqrt(
(right_top_corner_wingbox[0] - left_top_corner_wingbox[0])**2 +
(-left_bottom_corner_wingbox[1] + right_bottom_corner_wingbox[1])**2))
height_middle_spar = height_front_spar - math.sqrt(
(length_bottom_plate / 2)**2 - (length_top_plate / 2)**2)
# area_wingbox = length_top_plate * height_front_spar - (length_top_plate * (height_front_spar - height_back_spar))/2
plate_thickness = database_connector.load_wingbox_value("plate_thickness")
spar_thickness = database_connector.load_wingbox_value("spar_thickness")
area_front_spar = spar_thickness * height_front_spar
area_back_spar = spar_thickness * height_back_spar
area_middle_spar = spar_thickness * height_middle_spar
area_top_plate = plate_thickness * length_top_plate
area_bottom_plate = plate_thickness * length_bottom_plate
x_top_bottom_plate = (left_top_corner_wingbox[0] +
right_top_corner_wingbox[0]) * 1 / 2
x_front_spar = left_top_corner_wingbox[0]
x_back_spar = right_top_corner_wingbox[0]
x_middle_spar = (
left_top_corner_wingbox[0] +
(right_top_corner_wingbox[0] - left_top_corner_wingbox[0]) / 2)
z_top_plate = (left_top_corner_wingbox[1] +
right_top_corner_wingbox[1]) * 1 / 2
z_bottom_plate = (left_bottom_corner_wingbox[1] +
right_bottom_corner_wingbox[1]) * 1 / 2
z_front_spar = (left_top_corner_wingbox[1] +
left_bottom_corner_wingbox[1]) * 1 / 2
z_middle_spar = height_middle_spar / 2 + z_bottom_plate
z_back_spar = (right_top_corner_wingbox[1] +
right_bottom_corner_wingbox[1]) * 1 / 2
# Reinforcements: stringers
area_top_stringer = database_connector.load_wingbox_value(
"top_stringer_area")
area_bottom_stringer = database_connector.load_wingbox_value(
"bottom_stringer_area")
def get_x_coordinates_stringer(spanwise_location):
# get x-coordinates stringers
x_coordinates_stringers_top = []
x_coordinates_stringers_bottom = []
number_stringers_top = get_amount_of_stringers(spanwise_location,
"top")
number_stringers_bottom = get_amount_of_stringers(
spanwise_location, "bottom")
spacing_stringers_top = length_top_plate / (number_stringers_top + 1)
spacing_stringers_bottom = length_bottom_plate / (
number_stringers_bottom + 1)
for number_stringer in range(1, number_stringers_top + 1):
x_coordinate_current_stringer = left_top_corner_wingbox[
0] + number_stringer * spacing_stringers_top
x_coordinates_stringers_top.append(x_coordinate_current_stringer)
# print(number_stringer)
for number_stringer in range(1, number_stringers_bottom + 1):
x_coordinate_current_stringer = left_bottom_corner_wingbox[
0] + number_stringer * spacing_stringers_bottom
x_coordinates_stringers_bottom.append(
x_coordinate_current_stringer)
# print(number_stringer)
return x_coordinates_stringers_top, x_coordinates_stringers_bottom
def get_z_coordinates_stringer(spanwise_location):
z_coordinates_stringers_top = []
z_coordinates_stringers_bottom = []
number_stringers_top = get_amount_of_stringers(spanwise_location,
"top")
number_stringers_bottom = get_amount_of_stringers(
spanwise_location, "bottom")
spacing_stringers_top = length_top_plate / (number_stringers_top + 1)
spacing_stringers_bottom = length_bottom_plate / (
number_stringers_bottom + 1)
#top
sin_angle_top = (left_top_corner_wingbox[1] -
right_top_corner_wingbox[1]) / (length_top_plate)
for number_stringer in range(1, number_stringers_top + 1):
z_coordinate_current_top_stringer = left_top_corner_wingbox[
1] - number_stringer * sin_angle_top * spacing_stringers_top
z_coordinates_stringers_top.append(
z_coordinate_current_top_stringer)
#bottom
sin_angle_bottom = (-left_bottom_corner_wingbox[1] -
right_top_corner_wingbox[1]) / length_bottom_plate
for number_stringer in range(1, number_stringers_bottom + 1):
z_coordinate_current_bottom_stringer = left_bottom_corner_wingbox[
1] - number_stringer * sin_angle_bottom * spacing_stringers_bottom
z_coordinates_stringers_bottom.append(
z_coordinate_current_bottom_stringer)
# #z axis points up
# print(z_coordinates_stringers_top)
# print(z_coordinates_stringers_bottom)
return z_coordinates_stringers_top, z_coordinates_stringers_bottom
def calculate_x_coordinate_centroid(x_lst, area_lst):
AX_lst = []
for index in range(len(x_lst)):
AX_lst.append(x_lst[index] * area_lst[index])
# print(index)
sum_area = sum(area_lst)
sum_AX = sum(AX_lst)
return sum_AX / sum_area
def calculate_z_coordinate_centroid(z_lst, area_lst):
AZ_lst = []
for element in range(len(z_lst)):
AZ_lst.append(z_lst[element] * area_lst[element])
sum_area = sum(area_lst)
sum_AZ = sum(AZ_lst)
return sum_AZ / sum_area
def calculate_Ixz(x_lst, z_lst, area_lst):
IXZ_AXZ_lst = []
for element in range(len(x_lst)):
#print(z_lst[element])
IXZ_AXZ_lst.append(x_lst[element] * z_lst[element] *
area_lst[element])
#print(element)
I_XZ = sum(IXZ_AXZ_lst)
return I_XZ
area_lst = [
area_top_plate, area_bottom_plate, area_front_spar, area_middle_spar,
area_back_spar
]
x_coordinates_lst = [
x_top_bottom_plate, x_top_bottom_plate, x_front_spar, x_middle_spar,
x_back_spar
]
z_coordinates_lst = [
z_top_plate, z_bottom_plate, z_front_spar, z_middle_spar, z_back_spar
]
# coordinates centroid without ribs and stringers (wrt LE-chord intersection)
x_centroid_no_reinforcements = calculate_x_coordinate_centroid(
x_coordinates_lst[0:5], area_lst[0:5])
z_centroid_no_reinforcements = calculate_z_coordinate_centroid(
z_coordinates_lst[0:5], area_lst[0:5])
if verbose:
print(
"\nThe centroid w.r.t. the LE-chord without any ribs or stringers equals [x,z]: "
)
print([x_centroid_no_reinforcements, z_centroid_no_reinforcements])
# coordinates centroid with only stringers
x_coordinates_stringers_top, x_coordinates_stringers_bottom = get_x_coordinates_stringer(
spanwise_location)
z_coordinates_stringers_top, z_coordinates_stringers_bottom = get_z_coordinates_stringer(
spanwise_location)
x_coordinates_lst = x_coordinates_lst + x_coordinates_stringers_top + x_coordinates_stringers_bottom
z_coordinates_lst = z_coordinates_lst + z_coordinates_stringers_top + z_coordinates_stringers_bottom
for add_area in range(len(x_coordinates_stringers_top)):
area_lst.append(area_top_stringer)
for add_area in range(len(x_coordinates_stringers_bottom)):
area_lst.append(area_bottom_stringer)
x_centroid_stringers_only = calculate_x_coordinate_centroid(
x_coordinates_lst, area_lst)
z_centroid_stringers_only = calculate_z_coordinate_centroid(
z_coordinates_lst, area_lst)
if verbose:
print("\nThe centroid w.r.t. the LE-chord with stringers [x,z]: ")
print([x_centroid_stringers_only, z_centroid_stringers_only])
# print(x_coordinates_lst)
# print(len(x_coordinates_lst))
# print(z_coordinates_lst)
# print(len(z_coordinates_lst))
# print(len(area_lst))
return [x_centroid_stringers_only, z_centroid_stringers_only]
I_XZ = calculate_Ixz(x_coordinates_lst, z_coordinates_lst, area_lst)
return [x_centroid_stringers_only, z_centroid_stringers_only, I_XZ]