def Get_xy_components(s1, s2, s3, s4, s5, qs12, qs23, qs35, qs56, qs61):
t_ys12 = np.array([])
x_coor_AC = 0.25 * Wing.Chordlength
# Moments from section 1 -> 2
for i in range(0, len(qs12) - 1):
t_y = qs12[i] / Wing.ThSpar1
t_ys12 = np.append(t_ys12, t_y.to(ureg("N/(m**2)")))
t_y = qs12L[-1] / Wing.ThSpar1
t_ys12 = np.append(t_ys12, t_y.to(ureg("N/(m**2)")))
# Moments from section 2 -> 3
t_xs23 = np.array([])
t_ys23 = np.array([])
for i in range(0, len(qs23) - 1):
x_loc_1, y_loc_1 = Wing.get_xy_from_perim(s2[i] / Wing.Chordlength,
Wing.ChSpar1)
x_loc_2, y_loc_2 = Wing.get_xy_from_perim(s2[i + 1] / Wing.Chordlength,
Wing.ChSpar1)
x_loc_1 *= Wing.Chordlength
x_loc_2 *= Wing.Chordlength
y_loc_1 *= Wing.Chordlength
y_loc_2 *= Wing.Chordlength
Force_angle = np.arctan2(y_loc_2 - y_loc_1, x_loc_2 - x_loc_1)
t_x = qs23[i] / Wing.ThSkin * np.cos(Force_angle)
t_y = qs23[i] / Wing.ThSkin * np.sin(Force_angle)
t_xs23 = np.append(t_xs23, t_x.to(ureg("N/(m**2)")))
t_ys23 = np.append(t_ys23, t_y.to(ureg("N/(m**2)")))
t_x = qs23[-1] / Wing.ThSkin * np.cos(Force_angle)
t_y = qs23[-1] / Wing.ThSkin * np.sin(Force_angle)
t_xs23 = np.append(t_xs23, t_x.to(ureg("N/(m**2)")))
t_ys23 = np.append(t_ys23, t_y.to(ureg("N/(m**2)")))
# Moments from section 3->5
t_ys35 = np.array([])
for i in range(0, len(qs35) - 1):
t_y = qs35[i] / Wing.ThSpar2
t_ys35 = np.append(t_ys35, t_y.to(ureg("N/(m**2)")))
t_y = qs35[-1] / Wing.ThSpar2
t_ys35 = np.append(t_ys35, t_y.to(ureg("N/(m**2)")))
# Moments from section 5 -> 6
t_xs56 = np.array([])
t_ys56 = np.array([])
for i in range(0, len(qs56) - 1):
x_loc_1, y_loc_1 = Wing.get_xy_from_perim(s4[i] / Wing.Chordlength,
Wing.ChSpar2,
reverse=True)
x_loc_2, y_loc_2 = Wing.get_xy_from_perim(s4[i + 1] / Wing.Chordlength,
Wing.ChSpar2,
reverse=True)
x_loc_1 *= Wing.Chordlength
x_loc_1 -= x_coor_AC
x_loc_2 *= Wing.Chordlength
x_loc_2 -= x_coor_AC
y_loc_1 *= Wing.Chordlength
y_loc_2 *= Wing.Chordlength
Force_angle = np.arctan2(y_loc_2 - y_loc_1, x_loc_2 - x_loc_1)
t_x = qs56[i] / Wing.ThSkin * np.cos(Force_angle)
t_y = qs56[i] / Wing.ThSkin * np.sin(Force_angle)
t_xs56 = np.append(t_xs56, t_x.to(ureg("N/(m**2)")))
t_ys56 = np.append(t_ys56, t_y.to(ureg("N/(m**2)")))
t_x = qs56[-1] / Wing.ThSkin * np.cos(Force_angle)
t_y = qs56[-1] / Wing.ThSkin * np.sin(Force_angle)
t_xs56 = np.append(t_xs56, t_x.to(ureg("N/(m**2)")))
t_ys56 = np.append(t_ys56, t_y.to(ureg("N/(m**2)")))
# Moment 6 -> 1
t_ys61 = np.array([])
for i in range(0, len(qs61) - 1):
t_y = qs61[i] / Wing.ThSpar1
t_ys61 = np.append(t_ys61, t_y.to(ureg("N/(m**2)")))
t_y = qs61[-1] / Wing.ThSpar1
t_ys61 = np.append(t_ys61, t_y.to(ureg("N/(m**2)")))
t_xs23 *= ureg("N/(m**2)")
t_xs56 *= ureg("N/(m**2)")
t_ys12 *= ureg("N/(m**2)")
t_ys23 *= ureg("N/(m**2)")
t_ys35 *= ureg("N/(m**2)")
t_ys56 *= ureg("N/(m**2)")
t_ys61 *= ureg("N/(m**2)")
return t_xs23, t_xs56, t_ys12, t_ys23, t_ys35, t_ys56, t_ys61
def Calc_base_shear_flow(boom_areas, n):
"""
:param boom_areas: Return variable from Boom_area function
:param n: Number of sections that divides the perimiter
:return: Arrays with s's and qs's, seperated for L and D
"""
strs_x_coords, strs_y_coords, _ = Wing.x_y_angle_coords
strs_x_coords.ito(ureg("m"))
strs_y_coords.ito(ureg("m"))
strs_x_coords = np.append(strs_x_coords, np.flip(strs_x_coords, 0))
strs_x_coords *= ureg('m')
strs_y_coords = np.append(strs_y_coords, np.flip(-1 * strs_y_coords, 0))
strs_y_coords *= ureg('m')
S_x = WingStress.D
S_y = WingStress.L
Ixx = Inertia.Ixx_wb
Iyy = Inertia.Iyy_wb
## section 1 2
ds = Wing.HSpar1 / (2 * n)
qs12L = np.array([])
qs12D = np.array([])
qs12L = np.append(qs12L, 0)
qs12D = np.append(qs12D, 0)
s1 = np.array([])
s1 = np.append(s1, 0)
s = Q_("0 m")
q_loc_L = 0
q_loc_D = 0
x = (Wing.ChSpar1 - Wing.centroid
) * Wing.Chordlength # x_coordinate of Spar 1 w.r.t. the centroid
for _ in range(n - 1):
s += ds
y = s
s1 = np.append(s1, s)
# Lift
q_loc_L += -(S_y / Ixx) * Wing.ThSpar1 * y * ds
qs12L = np.append(qs12L, q_loc_L.to(ureg("N/m")))
# Drag
q_loc_D += -(S_x / Iyy) * Wing.ThSpar1 * x * ds
qs12D = np.append(qs12D, q_loc_D.to(ureg("N/m")))
s += ds
y = s
s1 = np.append(s1, s)
# Lift
q_loc_L += -(S_y / Ixx) * (Wing.ThSpar1 * y * ds +
boom_areas[0] * Wing.HSpar1 / 2)
qs12L = np.append(qs12L, q_loc_L.to(ureg("N/m")))
# Drag
q_loc_D += -(S_x / Iyy) * (Wing.ThSpar1 * x * ds + boom_areas[0] * x)
qs12D = np.append(qs12D, q_loc_D.to(ureg("N/m")))
## section 2 3
ds = (Wing.skin_length) / n
s = Q_("0 m")
qs23L = np.array([])
qs23L = np.append(qs23L, qs12L[-1])
qs23D = np.array([])
qs23D = np.append(qs23D, qs12D[-1])
s2 = np.array([])
s2 = np.append(s2, s)
str_counter = 0
for _ in range(n):
s = np.add(ds, s)
s2 = np.append(s2, s)
x_coor, y_coor = Wing.get_xy_from_perim(s / Wing.Chordlength,
Wing.ChSpar1) # RELATIVE!!
# Lift
q_loc_L += -(S_y / Ixx) * (Wing.ThSkin * y_coor * Wing.Chordlength *
ds)
# Drag
q_loc_D += -(S_x / Iyy) * (Wing.ThSkin * (x_coor - Wing.centroid) *
Wing.Chordlength * ds)
if (np.sqrt(
(x_coor * Wing.Chordlength - strs_x_coords[str_counter])**2 +
(y_coor * Wing.Chordlength - strs_y_coords[str_counter])**2) <
Q_("1 cm")):
print("s2:", strs_x_coords[str_counter])
q_loc_L += -(S_y /
Ixx) * Wing.A_stringer * strs_y_coords[str_counter]
q_loc_D += -(S_x / Iyy) * Wing.A_stringer * (
strs_x_coords[str_counter] / Wing.Chordlength -
Wing.centroid) * Wing.Chordlength
str_counter += 1
qs23L = np.append(qs23L, q_loc_L.to(ureg("N/m")))
qs23D = np.append(qs23D, q_loc_D.to(ureg("N/m")))
## Section 3 5
ds = Wing.HSpar2 / n
qs35L = np.array([])
qs35D = np.array([])
qs35L = np.append(qs35L, qs23L[-1])
qs35D = np.append(qs35D, qs23D[-1])
s3 = np.array([])
s3 = np.append(s3, 0)
s = Q_("0 m")
x = (Wing.ChSpar2 - Wing.centroid
) * Wing.Chordlength # x_coordinate of Spar 1 w.r.t. the centroid
for _ in range(n):
s += ds
y = Wing.HSpar2 / 2 - s
s3 = np.append(s3, s)
# Lift
q_loc_L += -(S_y / Ixx) * Wing.ThSpar2 * y * ds
qs35L = np.append(qs35L, q_loc_L.to(ureg("N/m")))
# Drag
q_loc_D += -(S_x / Iyy) * Wing.ThSpar2 * x * ds
qs35D = np.append(qs35D, q_loc_D.to(ureg("N/m")))
## section 5 6
ds = (Wing.skin_length) / n
s = Q_("0 m")
qs56L = np.array([])
qs56L = np.append(qs56L, qs35L[-1])
qs56D = np.array([])
qs56D = np.append(qs56D, qs35D[-1])
s4 = np.array([])
s4 = np.append(s4, s)
for _ in range(n):
s = np.add(ds, s)
s4 = np.append(s4, s)
x_coor, y_coor = Wing.get_xy_from_perim(s / Wing.Chordlength,
Wing.ChSpar2,
reverse=True) # RELATIVE!!
# Lift
q_loc_L += -(S_y / Ixx) * (Wing.ThSkin * y_coor * Wing.Chordlength *
ds)
# Drag
q_loc_D += -(S_x / Iyy) * (Wing.ThSkin * (x_coor - Wing.centroid) *
Wing.Chordlength * ds)
if (str_counter < Wing.N_stringers):
if (abs(x_coor * Wing.Chordlength - strs_x_coords[str_counter]) <
Q_("1 cm")):
q_loc_L += -(
S_y / Ixx) * Wing.A_stringer * strs_y_coords[str_counter]
print(strs_x_coords[str_counter])
q_loc_D += -(S_x / Iyy) * Wing.A_stringer * (
strs_x_coords[str_counter] / Wing.Chordlength -
Wing.centroid) * Wing.Chordlength
str_counter += 1
qs56L = np.append(qs56L, q_loc_L.to(ureg("N/m")))
qs56D = np.append(qs56D, q_loc_D.to(ureg("N/m")))
## section 6 1
ds = Wing.HSpar1 / (2 * n)
qs61L = np.array([])
qs61D = np.array([])
qs61L = np.append(qs61L, qs56L[-1])
qs61D = np.append(qs61D, qs56D[-1])
s5 = np.array([])
s5 = np.append(s5, 0)
s = Q_("0 m")
x = (Wing.ChSpar1 - Wing.centroid
) * Wing.Chordlength # x_coordinate of Spar 1 w.r.t. the centroid
y = -Wing.HSpar1 / 2
# Lift
s5 = np.append(s5, 0)
q_loc_L += -(S_y / Ixx) * (Wing.ThSpar1 * y * ds + boom_areas[-1] * y)
qs61L = np.append(qs61L, q_loc_L.to(ureg("N/m")))
# Drag
q_loc_D += -(S_x / Iyy) * (Wing.ThSpar1 * x * ds + boom_areas[-1] * x)
qs61D = np.append(qs61D, q_loc_D.to(ureg("N/m")))
for _ in range(n - 1):
s += ds
y = -Wing.HSpar1 / 2 + s # x_coordinate of Spar 1 w.r.t. the centroid
s5 = np.append(s5, s)
# Lift
q_loc_L += -(S_y / Ixx) * Wing.ThSpar1 * y * ds
qs61L = np.append(qs61L, q_loc_L.to(ureg("N/m")))
# Drag
q_loc_D += -(S_x / Iyy) * Wing.ThSpar1 * x * ds
qs61D = np.append(qs61D, q_loc_D.to(ureg("N/m")))
s1 *= ureg("m")
s2 *= ureg("m")
s3 *= ureg("m")
s4 *= ureg("m")
s5 *= ureg("m")
qs12L *= ureg("N/m")
qs12D *= ureg("N/m")
qs23L *= ureg("N/m")
qs23D *= ureg("N/m")
qs35L *= ureg("N/m")
qs35D *= ureg("N/m")
qs56L *= ureg("N/m")
qs56D *= ureg("N/m")
qs61L *= ureg("N/m")
qs61D *= ureg("N/m")
return s1, s2, s3, s4, s5, qs12L, qs23L, qs35L, qs56L, qs61L, qs12D, qs23D, qs35D, qs56D, qs61D
def Calc_moment_due_to_shear(s1, s2, s3, s4, s5, qs12L, qs23L, qs35L, qs56L,
qs61L):
x_coor_AC = 0.25 * Wing.Chordlength
Moment_L = 0
# Moments from section 1 -> 2
for i in range(0, len(qs12L) - 1):
q_loc = (qs12L[i] + qs12L[i + 1]) / 2
s_loc = (s1[i] + s1[i + 1]) / 2
ds = s1[i + 1] - s1[i]
x_loc = Wing.ChSpar1 * Wing.Chordlength - x_coor_AC
F_y = q_loc * ds
Moment_L += F_y * x_loc
# Moments from section 2 -> 3
for i in range(0, len(qs23L) - 1):
q_loc = (qs23L[i] + qs23L[i + 1]) / 2
s_loc = (s2[i] + s2[i + 1]) / 2
ds = s2[i + 1] - s2[i]
x_loc_1, y_loc_1 = Wing.get_xy_from_perim(s2[i] / Wing.Chordlength,
Wing.ChSpar1)
x_loc_2, y_loc_2 = Wing.get_xy_from_perim(s2[i + 1] / Wing.Chordlength,
Wing.ChSpar1)
x_loc_1 *= Wing.Chordlength
x_loc_2 *= Wing.Chordlength
y_loc_1 *= Wing.Chordlength
y_loc_2 *= Wing.Chordlength
Force_angle = np.arctan2(y_loc_2 - y_loc_1, x_loc_2 - x_loc_1)
x_loc_1 -= x_coor_AC
x_loc_2 -= x_coor_AC
F_x = q_loc * ds * np.cos(Force_angle)
F_y = q_loc * ds * np.sin(Force_angle)
Moment_L += -F_x * (y_loc_2 + y_loc_1) / 2 + F_y * (x_loc_2 +
x_loc_1) / 2
# Moments from section 3->5
t_ys35 = np.array([])
for i in range(0, len(qs35L) - 1):
q_loc = (qs35L[i] + qs35L[i + 1]) / 2
s_loc = (s3[i] + s3[i + 1]) / 2
ds = s3[i + 1] - s3[i]
x_loc = Wing.ChSpar2 * Wing.Chordlength - x_coor_AC
F_y = q_loc * ds
Moment_L += -F_y * x_loc
# Moments from section 5 -> 6
for i in range(0, len(qs56L) - 1):
q_loc = (qs56L[i] + qs56L[i + 1]) / 2
s_loc = (s4[i] + s4[i + 1]) / 2
ds = s4[i + 1] - s4[i]
x_loc_1, y_loc_1 = Wing.get_xy_from_perim(s4[i] / Wing.Chordlength,
Wing.ChSpar2,
reverse=True)
x_loc_2, y_loc_2 = Wing.get_xy_from_perim(s4[i + 1] / Wing.Chordlength,
Wing.ChSpar2,
reverse=True)
x_loc_1 *= Wing.Chordlength
x_loc_1 -= x_coor_AC
x_loc_2 *= Wing.Chordlength
x_loc_2 -= x_coor_AC
y_loc_1 *= Wing.Chordlength
y_loc_2 *= Wing.Chordlength
Force_angle = np.arctan2(y_loc_2 - y_loc_1, x_loc_2 - x_loc_1)
F_x = q_loc * ds * np.cos(Force_angle)
F_y = q_loc * ds * np.sin(Force_angle)
Moment_L += -F_x * (y_loc_2 + y_loc_1) / 2 + F_y * (x_loc_2 +
x_loc_1) / 2
# Moment 6 -> 1
for i in range(0, len(qs61L) - 1):
q_loc = (qs61L[i] + qs61L[i + 1]) / 2
s_loc = (s5[i] + s5[i + 1]) / 2
ds = s5[i + 1] - s5[i]
x_loc = Wing.ChSpar1 * Wing.Chordlength - x_coor_AC
F_y = q_loc * ds
Moment_L += F_y * x_loc
return Moment_L