import practised_ultimate as pu
import Airfoil_inertia as ai
print("------- Starting on shear calculation -------")
boom_area = pu.boom_area_all[0]
I_zz, I_yy, I_yz = pu.I_zz_sections, pu.I_yy_wing, pu.I_yz_wing
#print("The boom area", boom_area)
data_z_all_sec, data_y_upper_all_sec, data_y_lower_all_sec = ag.airfoil_geometry(
pu.N, pu.b, pu.calc_chord, pu.X_root)
airfoil_area, z_c_airfoil, y_c_airfoil = cw.get_skin_centroid(
pu.N, pu.b, pu.calc_chord, pu.dx)
z_centroid_all_sec, y_centroid_all_sec, y_loc_spar_up, y_loc_spar_low, y_loc_stiff_up, y_loc_stiff_low, y_vertical_spar, z_loc_stiff_up, spar_loc_sec, z_loc_stiff_low, spar_areas_verti = cw.wing_centroid(
boom_area, cw.spar_areas_hori, cw.t_spar_v, z_c_airfoil, y_c_airfoil,
cw.n_stiff_up, cw.n_stiff_low, pu.N, pu.b, pu.calc_chord, pu.X_root, pu.dx)
s_all_sec, ds_all_sec = ai.s_airfoil(pu.N, pu.b, pu.calc_chord, pu.X_root)
boom_loc_y = np.zeros((len(y_loc_spar_up), len(y_loc_stiff_up[0]) * 2 + 4))
boom_loc_z = np.zeros((len(y_loc_spar_up), len(y_loc_stiff_up[0]) * 2 + 4))
for i in range(len(y_loc_spar_up)):
for j in range(len(y_loc_stiff_up[0])):
boom_loc_y[i][j] = -(y_loc_stiff_up[i][j] - y_centroid_all_sec[i])
boom_loc_z[i][j] = z_loc_stiff_up[i][j] - z_centroid_all_sec[i]
boom_loc_y[i][j + 1] = -(y_loc_spar_up[i][1] - y_centroid_all_sec[i])
boom_loc_z[i][j + 1] = 0.55 * data_z_all_sec[i][-1] - z_centroid_all_sec[i]
def wing_price_weight(A_req_P, A_req_B, density, cost, N, t_skin, b, qcsweep,
dx):
Max_area, strut_volume, strut_mass, cost_strut = strut_cost(
A_req_P, A_req_B, density, cost)
airfoil_area, z_c_airfoil, y_c_airfoil = cw.get_skin_centroid(
N, b, prac.calc_chord, dx)
boom_area = prac.boom_area_all
print("boom area", boom_area)
X_root = np.arange(0, (b / 2) + dx, dx)
spar_areas_verti = cw.wing_centroid(boom_area, cw.spar_areas_hori,
cw.t_spar_v, z_c_airfoil, y_c_airfoil,
cw.n_stiff_up, cw.n_stiff_low, N, b,
prac.calc_chord, X_root, dx)[10]
spar_areas_hori = cw.spar_areas_hori
nr_stiff = cw.n_stiff_low + cw.n_stiff_up
Sweep_LE = m.atan(
m.tan(qcsweep) - 4 / prac.AR * (-0.25 * (1 - prac.taper) /
(1 + prac.taper))) # rad
# print(spar_areas_verti[0])
# print(spar_areas_hori)
# print(spar_areas_hori)
# print(spar_areas_verti[0])
# print(spar_areas_verti[1])
# print(len(spar_areas_verti[0]))
total_spar_volume = 0
for i in range(len(spar_areas_verti)):
spar_volume = 0
for j in range(len(spar_areas_verti[0])):
spar_volume += (spar_areas_verti[i][j] + spar_areas_hori[j] * 2)
total_spar_volume += spar_volume * prac.dx
total_boom_volume = np.zeros(len(prac.A_S_L))
for i in range(len(prac.A_S_L)):
if boom_area > 0:
total_boom_volume[i] = (boom_area *
nr_stiff) * (b / 2) / np.cos(Sweep_LE)
else:
total_boom_volume[i] = 0
# print("boom_area", boom_area)
boom_mass = total_boom_volume * density
boom_cost = boom_mass * cost
skin_volume = np.zeros(len(prac.X_root))
for i in range(len(prac.X_root) - 1):
skin_volume[i] = ai.s_airfoil(N, b, prac.calc_chord,
X_root)[0][i] * prac.dx * t_skin
# print(skin_volume)
skin_mass = sum(skin_volume) * density
skin_price = skin_mass * cost
spar_mass = total_spar_volume * density
spar_price = spar_mass * cost
total_price = np.zeros(len(prac.A_S_L))
total_mass = np.zeros(len(prac.A_S_L))
# print(spar_length, spar_volume, spar_mass, total_spar_area)
# print(skin_price, spar_price)
for i in range(len(prac.A_S_L)):
total_price[i] = (
skin_price + spar_price) * 2 + cost_strut[i] * 2 + boom_cost[i] * 2
total_mass[i] = (skin_mass +
spar_mass) * 2 + strut_mass[i] * 2 + boom_mass[i] * 2
return skin_mass, spar_mass, boom_mass, total_mass, total_price, boom_cost
def wing_stress(b, Mz, My, X_root):
# l_spar_h, t_spar_v, t_spar_h = cw.l_spar_h, cw.t_spar_v, cw.t_spar_h
N = prac.L_wing / prac.dx
# I_zz_spar, I_yy_spar, I_yz_spar = ai.I_zz_spars(l_spar_h, t_spar_v, t_spar_h, N, b ,prac.calc_chord,prac.boom_area_all)
# I_zz_req = pr.required_Izz(N, b, prac.calc_chord, Mz)
#
airfoil_area, z_c_airfoil, y_c_airfoil = cw.get_skin_centroid(
N, b, prac.calc_chord, prac.dx, cw.t_skin)
z_centroid_all_sec, y_centroid_all_sec, y_loc_spar_up, y_loc_spar_low, y_loc_stiff_up, y_loc_stiff_low, y_vertical_spar, z_loc_stiff_up, spar_loc_sec, z_loc_stiff_low, spar_areas_verti = cw.wing_centroid(
prac.boom_area_new, cw.spar_areas_hori, cw.t_spar_v, z_c_airfoil,
y_c_airfoil, cw.n_stiff_up, cw.n_stiff_low, N, b, prac.calc_chord,
X_root, prac.dx)
# print("the used boom area")
# print(prac.boom_area_all[0])
# print(z_centroid_all_sec)
# boom_area = ai.wing_geometry(I_zz_req, I_zz_spar, N, b, prac.calc_chord)[0][0]
# I_zz_wing, I_yy_wing, I_yz_wing = ai.inertia_wing(I_zz_spar, I_yy_spar, I_yz_spar, boom_area, N, b, prac.calc_chord)
I_yy_wing = prac.I_yy_wing
I_zz_wing = prac.I_zz_sections
I_yz_wing = prac.I_yz_wing
# I_yy_wing = inertia_wing(I_zz_spar, I_yy_spar, I_yz_spar, boom_area, N, b, c)
# I_zz_wing = inertia_wing(I_zz_spar, I_yy_spar, I_yz_spar, boom_area, N, b, c)
# I_zy_wing = inertia_wing(I_zz_spar, I_yy_spar, I_yz_spar, boom_area, N, b, c)
#
# z_centroid = wing_centroid(boom_area, spar_areas_hori, t_spar_v, z_c_airfoil, y_c_airfoil, n_stiff_up, n_stiff_low, N, b, c)
# y_centroid = wing_centroid(boom_area, spar_areas_hori, t_spar_v, z_c_airfoil, y_c_airfoil, n_stiff_up, n_stiff_low, N, b, c)
#
Mz_wing = Mz
My_wing = My
z_nodes = airfoil_geometry(N, b, prac.calc_chord,
X_root)[0] #adapt to centroid
y_up_nodes = airfoil_geometry(N, b, prac.calc_chord, X_root)[1] #adapt
y_low_nodes = airfoil_geometry(N, b, prac.calc_chord, X_root)[2]
local_stress_up = np.zeros((len(X_root), len(z_nodes[0])))
local_stress_low = np.zeros((len(X_root), len(z_nodes[0])))
z = np.zeros((len(X_root), len(z_nodes[0])))
y_up = np.zeros((len(X_root), len(y_up_nodes[0])))
y_low = np.zeros((len(X_root), len(y_low_nodes[0])))
# print(z_nodes)
# print(y_up_nodes[0])
for i in range(len(X_root)):
for j in range(len(z_nodes[0])):
z[i][j] = z_nodes[i][j] - z_centroid_all_sec[i]
y_up[i][j] = -(y_up_nodes[i][j] - y_centroid_all_sec[i])
y_low[i][j] = (y_centroid_all_sec[i] - y_low_nodes[i][j])
local_stress_up[i][j] = (
((-1) * My_wing[i] * I_zz_wing[i] +
(-1) * Mz_wing[i] * I_yz_wing[i]) * z[i][j] +
(Mz_wing[i] * I_yy_wing[i] + My_wing[i] * I_yz_wing[i]) *
y_up[i][j]) / (I_zz_wing[i] * I_yy_wing[i] - I_yz_wing[i]**2)
local_stress_low[i][j] = (
((-1) * My_wing[i] * I_zz_wing[i] +
(-1) * Mz_wing[i] * I_yz_wing[i]) * z[i][j] +
(Mz_wing[i] * I_yy_wing[i] + My_wing[i] * I_yz_wing[i]) *
y_low[i][j]) / (I_zz_wing[i] * I_yy_wing[i] - I_yz_wing[i]**2)
# print(I_zz_wing)
return z, local_stress_up, local_stress_low
# print(abs(boom_area_new - boom_area_old) )
z = 0
while abs(boom_area_new[0] - boom_area_old[0]) > 1 / 100000 or z < 5:
# print(abs(boom_area_new - boom_area_old) )
print("New iteration", z)
boom_area_old = boom_area_new
# boom_area_all = 0.0045
I_zz_spar, I_yy_spar, I_yz_spar = ai.I_zz_spars(l_spar_h, t_spar_v, t_spar_h, N, b ,calc_chord, boom_area_old, X_root, dx)
I_zz_req = pr.required_Izz(N, b, calc_chord, Mz_dist[idx], boom_area_old, X_root, dx)
boom_area_new = ai.wing_geometry(I_zz_req, I_zz_spar, N, b, calc_chord, boom_area_old,X_root, dx)
airfoil_area, z_c_airfoil, y_c_airfoil = cw.get_skin_centroid(N, b, calc_chord,dx, cw.t_skin)
z_centroid_all_sec, y_centroid_all_sec, y_loc_spar_up, y_loc_spar_low, y_loc_stiff_up, y_loc_stiff_low, y_vertical_spar, z_loc_stiff_up, spar_loc_sec, z_loc_stiff_low, spar_areas_verti = cw.wing_centroid(boom_area_new, cw.spar_areas_hori, cw.t_spar_v, z_c_airfoil, y_c_airfoil, cw.n_stiff_up, cw.n_stiff_low, N, b, calc_chord, X_root, dx)
#
#
# # print("I_zz_req",I_zz_req)
# boom_area = boom_area_new
# boom_area_all[idx] = max(boom_area_new) * 10000
print("Updated boom area for strut pos" + str(A_S_L[idx]))
#
print(max(boom_area_new) * 10000)
# print()
##
I_zz_sections, I_yy_wing, I_yz_wing = ai.inertia_wing(I_zz_spar, I_yy_spar, I_yz_spar, boom_area_new, N, b, calc_chord, X_root, dx)
#
# print("I_zz_sections",I_zz_sections)
def required_Izz(N, b, c, Mz, boom_area, X_root, dx):
data_y_all_sec_up = airfoil_geometry(N, b, c, X_root)[1]
data_y_all_sec_low = airfoil_geometry(N, b, c, X_root)[2]
airfoil_area, z_c_airfoil, y_c_airfoil = cw.get_skin_centroid(
N, b, c, dx, cw.t_skin)
z_centroid_all_sec, y_centroid_all_sec, y_loc_spar_up, y_loc_spar_low, y_loc_stiff_up, y_loc_stiff_low, y_vertical_spar, z_loc_stiff_up, spar_loc_sec, z_loc_stiff_low, spar_areas_verti = cw.wing_centroid(
boom_area, cw.spar_areas_hori, cw.t_spar_v, z_c_airfoil, y_c_airfoil,
cw.n_stiff_up, cw.n_stiff_low, N, b, c, X_root, dx)
I_zz_req_all_sec = np.zeros(len(X_root))
sigma_ult = 114 * 10**6
for i in range(len(X_root)):
y_up_max = -max(data_y_all_sec_up[i]) - (-1) * y_centroid_all_sec[i]
y_low_max = -min(data_y_all_sec_low[i]) - (-1) * y_centroid_all_sec[i]
# print(y_low_max)
# print(Mz[i])
y_max = max(abs(y_up_max), abs(y_low_max))
I_zz_req_all_sec[i] = abs(Mz[i]) * y_max / sigma_ult
# print("Mz",Mz[i])
# print("y_max",y_max)
# print("I_zz_req",I_zz_req_all_sec)
# print(y_max)
return I_zz_req_all_sec
def I_zz_spars(l_spar_h, t_spar_v, t_spar_h, N, b, c, boom_area, X_root, dx):
airfoil_area, z_c_airfoil, y_c_airfoil = cw.get_skin_centroid(
N, b, c, dx, cw.t_skin)
z_centroid_all_sec, y_centroid_all_sec, y_loc_spar_up, y_loc_spar_low, y_loc_stiff_up, y_loc_stiff_low, y_vertical_spar, z_loc_stiff_up, spar_loc_sec, z_loc_stiff_low, spar_areas_verti = cw.wing_centroid(
boom_area, cw.spar_areas_hori, cw.t_spar_v, z_c_airfoil, y_c_airfoil,
cw.n_stiff_up, cw.n_stiff_low, N, b, c, X_root, dx)
I_zz_spar = np.zeros((len(X_root), 1))
I_yy_spar = np.zeros((len(X_root), 1))
I_yz_spar = np.zeros((len(X_root), 1))
for j in range(len(X_root)):
I_zz_up = 0
I_yy_up = 0
I_yz_up = 0
I_zz_low = 0
I_yy_low = 0
I_yz_low = 0
I_zz_vertical = 0
I_yy_vertical = 0
I_yz_vertical = 0
# print(len(l_spar_h))
#
# print(len(cw.spar_areas_hori[0]))
for i in range(2):
I_zz_up += (1 / 12) * l_spar_h[j] * t_spar_h[i]**3 + l_spar_h[
j] * t_spar_h[i] * (-y_loc_spar_up[j][i] -
(-1) * y_centroid_all_sec[j])**2
I_yy_up += (1 / 12) * t_spar_h[i] * l_spar_h[j]**3 + l_spar_h[
j] * t_spar_h[i] * (spar_loc_sec[j][i] -
z_centroid_all_sec[j])**2
I_yz_up += l_spar_h[j] * t_spar_h[i] * (
-y_loc_spar_up[j][i] -
(-1) * y_centroid_all_sec[j]) * (spar_loc_sec[j][i] -
z_centroid_all_sec[j])
I_zz_low += (1 / 12) * l_spar_h[j] * t_spar_h[i]**3 + l_spar_h[
j] * t_spar_h[i] * (-y_loc_spar_low[j][i] -
(-1) * y_centroid_all_sec[j])**2
I_yy_low += (1 / 12) * t_spar_h[i] * l_spar_h[j]**3 + l_spar_h[
j] * t_spar_h[i] * (spar_loc_sec[j][i] -
z_centroid_all_sec[j])**2
I_yz_low += l_spar_h[j] * t_spar_h[i] * (
-y_loc_spar_low[j][i] -
(-1) * y_centroid_all_sec[j]) * (spar_loc_sec[j][i] -
z_centroid_all_sec[j])
l_spar_v = y_loc_spar_up[j][i] - y_loc_spar_low[j][i]
# print("l_spar_v", l_spar_v)
I_zz_vertical += (
1 /
12) * t_spar_v[i] * l_spar_v**3 + l_spar_v * t_spar_v[i] * (
-y_vertical_spar[j][i] - (-1) * y_centroid_all_sec[j])**2
I_yy_vertical += (1 / 12) * l_spar_v * t_spar_v[
i]**3 + l_spar_v * t_spar_v[i] * (spar_loc_sec[j][i] -
z_centroid_all_sec[j])**2
I_yz_vertical += l_spar_v * t_spar_v[i] * (
-y_vertical_spar[j][i] -
(-1) * y_centroid_all_sec[j]) * (spar_loc_sec[j][i] -
z_centroid_all_sec[j])
I_zz = I_zz_up + I_zz_low + I_zz_vertical
I_yy = I_yy_up + I_yy_low + I_yy_vertical
I_yz = I_yz_up + I_yz_low + I_yz_vertical
I_zz_spar[j] = I_zz
I_yy_spar[j] = I_yy
I_yz_spar[j] = I_yz
# print("I_zz in spar",I_zz_spar)
return I_zz_spar, I_yy_spar, I_yz_spar
def inertia_wing(I_zz_spar, I_yy_spar, I_yz_spar, boom_area, N, b, c, X_root,
dx):
airfoil_area, z_c_airfoil, y_c_airfoil = cw.get_skin_centroid(
N, b, c, dx, cw.t_skin)
z_centroid_all_sec, y_centroid_all_sec, y_loc_spar_up, y_loc_spar_low, y_loc_stiff_up, y_loc_stiff_low, y_vertical_spar, z_loc_stiff_up, spar_loc_sec, z_loc_stiff_low, spar_areas_verti = cw.wing_centroid(
boom_area, cw.spar_areas_hori, cw.t_spar_v, z_c_airfoil, y_c_airfoil,
cw.n_stiff_up, cw.n_stiff_low, N, b, c, X_root, dx)
# print("boom area in izz", boom_area)
I_zz = np.zeros(len(X_root))
I_yy = np.zeros(len(X_root))
I_yz = np.zeros(len(X_root))
for i in range(len(X_root)):
I_zz_booms = 0
I_yy_booms = 0
I_yz_booms = 0
I_zz_airfoil = 0
I_yy_airfoil = 0
I_yz_airfoil = 0
for j in range(len(y_loc_stiff_up[0])):
I_zz_booms += boom_area[i] * (-y_loc_stiff_up[i][j] -
(-1) * y_centroid_all_sec[i])**2
I_yy_booms += boom_area[i] * (z_loc_stiff_up[i][j] -
z_centroid_all_sec[i])**2
I_yz_booms += boom_area[i] * (-y_loc_stiff_up[i][j] -
(-1) * y_centroid_all_sec[i]) * (
z_loc_stiff_up[i][j] -
z_centroid_all_sec[i])
for k in range(len(y_loc_stiff_low[0])):
I_zz_booms += boom_area[i] * (-y_loc_stiff_low[i][k] -
(-1) * y_centroid_all_sec[i])**2
I_yy_booms += boom_area[i] * (z_loc_stiff_low[i][k] -
z_centroid_all_sec[i])**2
I_yz_booms += boom_area[i] * (-y_loc_stiff_low[i][k] -
(-1) * y_centroid_all_sec[i]) * (
z_loc_stiff_low[i][k] -
z_centroid_all_sec[i])
I_zz_airfoil += airfoil_area[i] * (-y_c_airfoil[i] -
(-1) * y_centroid_all_sec[i])**2
I_yy_airfoil += airfoil_area[i] * (z_c_airfoil[i] -
z_centroid_all_sec[i])**2
I_yz_airfoil += airfoil_area[i] * (-y_c_airfoil[i] -
(-1) * y_centroid_all_sec[i]) * (
z_c_airfoil[i] -
z_centroid_all_sec[i])
# print("boom_area", boom_area)
# print("I_zz_booms",I_zz_booms)
# print(I_zz_airfoil, I_yy_airfoil, I_yz_airfoil)
I_zz[i] = I_zz_booms + I_zz_spar[i][0] + I_zz_airfoil
I_yy[i] = I_yy_booms + I_yy_spar[i][0] + I_yy_airfoil
I_yz[i] = I_yz_booms + I_yz_spar[i][0] + I_yz_airfoil
# print("I_zz used",I_zz_spar[i][0])
#
# print("Izz wing",I_zz_airfoil)
# print("I_zz", I_zz[0])
return I_zz, I_yy, I_yz
def wing_geometry(I_zz_req, I_zz_spars, N, b, c, boom_area, X_root, dx):
# dx = 0.1
# print(X_root)
airfoil_area, z_c_airfoil, y_c_airfoil = cw.get_skin_centroid(
N, b, c, dx, cw.t_skin)
z_centroid_all_sec, y_centroid_all_sec, y_loc_spar_up, y_loc_spar_low, y_loc_stiff_up, y_loc_stiff_low, y_vertical_spar, z_loc_stiff_up, spar_loc_sec, z_loc_stiff_low, spar_areas_verti = cw.wing_centroid(
boom_area, cw.spar_areas_hori, cw.t_spar_v, z_c_airfoil, y_c_airfoil,
cw.n_stiff_up, cw.n_stiff_low, N, b, c, X_root, dx)
single_boom_area = np.zeros((len(X_root), 1))
# print(z_centroid_all_sec)
# print(y_centroid_all_sec)
# print(np.shape(I_zz_spars))
for i in range(len(X_root)):
y_2 = 0
I_zz_airfoil = 0
for k in range(len(y_loc_stiff_up[0])):
y_2 += (-y_loc_stiff_up[i][k] + y_centroid_all_sec[i])**2
for j in range(len(y_loc_stiff_low[0])):
y_2 += (-y_loc_stiff_low[i][j] + y_centroid_all_sec[i])**2
I_zz_airfoil += airfoil_area[i] * (-y_c_airfoil[i] -
(-1) * y_centroid_all_sec[i])**2
# I_yy_airfoil += airfoil_area[i]*(z_c_airfoil[i] - z_centroid_all_sec[i])**2
# I_yz_airfoil += airfoil_area[i]*(-y_c_airfoil[i] - (-1)*y_centroid_all_sec[i])*(z_c_airfoil[i] - z_centroid_all_sec[i])
# single_boom_area[i] = (I_zz_req[i] - I_zz_spars[i][0] - I_zz_airfoil)/y_2
if X_root[i] <= b / 2 - 16.05:
# single_boom_area = np.ones(len(X_root))*max(single_boom_area)
## print("locatie",np.argmax(max(single_boom_area)))
single_boom_area[i] = 0.018 - ((0.018 - 0.000) /
(b / 2)) * X_root[i]
elif X_root[i] > b / 2 - 16.05:
single_boom_area[
i] = 0.0 #0.0011 - ((0.0011-0.000)/(b/2))*X_root[i]
# if single_boom_area[i] <= 0:
# single_boom_area[i] = 0.
# elif single_boom_area[i] > 0:
# single_boom_area[i] = single_boom_area[i]
# plt.plot(X_root, single_boom_area)
# plt.show()
# print("single_boom_area",single_boom_area*10000, len(single_boom_area))
return single_boom_area