def compute_after_cabin_arr(arg_class):
"""
compute after cabin numpy array
:param arg_class: argument class
:return: after_cabin_arr(numpy ndarray)
"""
# set required parameters
l1 = arg_class.l1 # section 1 length(cockpit)
l2 = arg_class.l2 # section 2 length(cabin)
l3 = arg_class.l3 # section 3 length(after cabin)
huf = arg_class.huf # height of upper at cabin(fuselage)
hau = arg_class.hau # height of upper at after cabin
hlf = arg_class.hlf # height of lower at cabin(fuselage)
hlc = arg_class.hlc # height of lower at cockpit
wa = arg_class.wa # width of after cabin
wf = arg_class.wf # width of cabin(fuselage)
# create bezier curve
bezier_zu = [] # z coord for upper line
bezier_zl = [] # z coord for lower line
bezier_y = [] # y coord for y line
# set array for bezier curve
qzu = np.array([[l1 + l2, huf], [l1 + l2 + 0.5 * l3, hau],
[l1 + l2 + l3, hau]])
qzl = np.array([[l1 + l2, -hlf], [l1 + l2 + l3, -hlc], [l1 + l2 + l3, 0]])
qy = np.array([[l1 + l2, wf], [l1 + l2 + l3, wa], [l1 + l2 + l3, 0]])
# compute bezier curve
for t in np.linspace(0, 1, 50):
bezier_zu.append(bezier(qzu.shape[0] - 1, t, qzu)[1])
bezier_zl.append(bezier(qzl.shape[0] - 1, t, qzl)[1])
bezier_y.append(bezier(qy.shape[0] - 1, t, qy)[1])
# compute after cabin array
after_cabin_arr = []
x = np.linspace(l1 + l2, l1 + l2 + l3, 50)
for xi, bzl, bzu, by in zip(x, bezier_zl, bezier_zu, bezier_y):
# set y range
y = np.linspace(-by, by, 30)
for yi in y:
zui = bzu * np.sqrt(1.0 - yi**2 / by**2)
zli = bzl * np.sqrt(1.0 - yi**2 / by**2)
# exception
if np.isnan(zui):
zui, zli = 0, 0
after_cabin_arr.append([xi, yi, zui])
after_cabin_arr.append([xi, yi, zli])
after_cabin_arr = np.array(after_cabin_arr)
return after_cabin_arr
def compute_cockpit_arr(arg_class):
"""
compute cockpit numpy array(3D)
:param arg_class: argument class
:return: cockpit_arr(numpy ndarray)
"""
# set required parameters
l1 = arg_class.l1 # section 1 length(cockpit)
huc = arg_class.huc # height of upper at cockpit
huf = arg_class.huf # height of upper at cabin(fuselage)
hlc = arg_class.hlc # height of lower at cockpit
hlf = arg_class.hlf # height of lower at cabin(fuselage)
uk = arg_class.uk # constant for bezier curve
wc = arg_class.wc # width of cockpit
wf = arg_class.wf # width of cabin(fuselage)
# array for bezier curve
qzu = np.array([[0, 0], [l1 * uk, huc], [l1, huf]])
qzl = np.array([[0, 0], [l1 * uk, -hlc], [l1, -hlf]])
qy = np.array([[0, 0], [l1 * uk, wc], [l1, wf]])
# compute bezier curve
bezier_zu = [] # z coords of upper line
bezier_zl = [] # z coord of lower line
bezier_y = [] # y coord
for t in np.linspace(0, 1, 50):
bezier_zu.append(bezier(qzu.shape[0] - 1, t, qzu)[1])
bezier_zl.append(bezier(qzl.shape[0] - 1, t, qzl)[1])
bezier_y.append(bezier(qy.shape[0] - 1, t, qy)[1])
# compute cockpit array
cockpit_arr = []
# set x range
x = np.linspace(0.0, l1, 50)
for xi, bzl, bzu, by in zip(x, bezier_zl, bezier_zu, bezier_y):
# set y range
y = np.linspace(-by, by, 30)
for yi in y:
# eclipse
if by == 0:
zui, zli = 0, 0
else:
zui = bzu * np.sqrt(1.0 - yi**2 / by**2)
zli = bzl * np.sqrt(1.0 - yi**2 / by**2)
cockpit_arr.append([xi, yi, zui])
cockpit_arr.append([xi, yi, zli])
cockpit_arr = np.array(cockpit_arr)
return cockpit_arr
cockpit_arr = []
bezier_zu = []
bezier_zl = []
uk = 0.5
qzu = np.array([[0, 0], [l1 * uk, huc], [l1, huf]])
qzl = np.array([[0, 0], [l1 * uk, -hlc], [l1, -hlf]])
bezier_y = []
qy = np.array([[0, 0], [l1 * uk, wc], [l1, wf]])
for t in np.linspace(0, 1, 50):
bezier_zu.append(bezier(2, t, qzu)[1])
bezier_zl.append(bezier(2, t, qzl)[1])
bezier_y.append(bezier(2, t, qy)[1])
for xi, bzl, bzu, by in zip(x, bezier_zl, bezier_zu, bezier_y):
y = np.linspace(-by, by, 30)
for yi in y:
zui = bzu * np.sqrt(1 - yi**2 / by**2)
zli = bzl * np.sqrt(1 - yi**2 / by**2)
cockpit_arr.append([xi, yi, zui])
cockpit_arr.append([xi, yi, zli])
cockpit_arr = np.array(cockpit_arr)
main_wing_arr = np.array(main_wing_arr)
# horizontal face
bezier_y1 = []
qy1 = np.array([[0, 0], [0, u1 * lb], [v1 * lb, u2 * lb],
[(b * 0.5 - st[1]) * np.tan(theta * np.pi / 180.0) + st[0],
b * 0.5]])
bezier_y2 = []
qy2 = np.array([[
(b * 0.5 - st[1]) * np.tan(theta * np.pi / 180.0) + st[0] + ctip, b * 0.5
], [croot + st[0], st[1]], [lb, u3 * lb], [lb, 0]])
for t in np.linspace(0, 1, 50):
bezier_y1.append(bezier(qy1.shape[0] - 1, t, qy1))
bezier_y2.append(bezier(qy2.shape[0] - 1, t, qy2))
xs = (b * 0.5 - st[1]) * np.tan(theta * np.pi / 180.0) + st[0]
xf = xs + ctip
interpolates = [np.array([xi, b * 0.5]) for xi in np.linspace(xs, xf, 5)]
# y coordinates
bezier_y = bezier_y1 + interpolates + bezier_y2
fuselage_arr = []
# xz plane
fuselage_line = []
for xi, yu in bezier_y:
xi /= lb
