def test_create_branch(self):
"""Test the function 'create_branch'"""
tixi_handle = open_tixi(self.CPACS_IN_PATH)
update_branch = '/cpacs/header/updates/update'
new_branch = '/cpacs/header/updates/update[3]/test/test1/test2'
# This branch should be added
tixi = create_branch(tixi_handle, update_branch, True)
# This branch should not be added
tixi = create_branch(tixi, update_branch, False)
# 'new_branch' should be added
tixi = create_branch(tixi, new_branch)
# Save modified tixi in the output CPACS file
close_tixi(tixi, self.CPACS_OUT_PATH)
# Reopen the output CPACS file to check if branches have been added
tixi_out = open_tixi(self.CPACS_OUT_PATH)
# Check if the number of "update" child is equal to 3
namedchild_nb = tixi_out.getNamedChildrenCount('/cpacs/header/updates',
'update')
self.assertEqual(namedchild_nb, 3)
# Check if 'new_branch' has been added
branch_check = tixi_out.checkElement(new_branch)
self.assertEqual(branch_check, True)
def test_open_tigl(self):
"""Test the function 'open_tigl'"""
tixi_handle = open_tixi(self.CPACS_IN_PATH)
tigl_handle = open_tigl(tixi_handle)
self.assertIsNotNone(tigl_handle)
def test_fuse_nb(self):
'''Test if the number of fuselage is equal to 1'''
tixi_handle = open_tixi(self.CPACS_IN_PATH)
fuse_nb = tixi_handle.getNamedChildrenCount(
'/cpacs/vehicles/aircraft\
/model/fuselages', 'fuselage')
self.assertEqual(fuse_nb, 1)
def test_wing_nb(self):
'''Test if the number of wing is equal to 1'''
tixi_handle = open_tixi(self.CPACS_IN_PATH)
wing_nb = tixi_handle.getNamedChildrenCount(
'/cpacs/vehicles/aircraft\
/model/wings', 'wing')
self.assertEqual(wing_nb, 1)
def test_close_tixi(self):
"""Test the function 'close_tixi'"""
tixi_handle = open_tixi(self.CPACS_IN_PATH)
# Save unmodified tixi in the output CPACS file
close_tixi(tixi_handle, self.CPACS_OUT_PATH)
# Read Input and Ouput CPACS file as text, to compare them
with open(self.CPACS_IN_PATH) as file_in:
lines_cpacs_in = file_in.readlines()
with open(self.CPACS_OUT_PATH) as file_out:
lines_cpacs_out = file_out.readlines()
self.assertEqual(lines_cpacs_in, lines_cpacs_out)
def test_copy_branch(self):
"""Test the function 'copy_branch'"""
tixi_handle = open_tixi(self.CPACS_IN_PATH)
# Create a new 'header' branch and copy the original 'header' into it
xpath_new = '/cpacs/header'
xpath_from = '/cpacs/header[1]'
xpath_to = '/cpacs/header[2]'
tixi = create_branch(tixi_handle, xpath_new, True)
tixi = copy_branch(tixi, xpath_from, xpath_to)
# Check if a specific element has been copied
xpath_elem_from = '/cpacs/header[1]/updates/update[1]/timestamp'
xpath_elem_to = '/cpacs/header[2]/updates/update[1]/timestamp'
elem_from = tixi_handle.getTextElement(xpath_elem_from)
elem_to = tixi.getTextElement(xpath_elem_to)
self.assertEqual(elem_from, elem_to)
# Check if a specific attribute has been copied
attrib_text_from = tixi_handle.getTextAttribute(xpath_elem_from, 'uID')
attrib_text_to = tixi.getTextAttribute(xpath_elem_to, 'uID')
self.assertEqual(attrib_text_from, attrib_text_to)
def convert_cpacs_to_sumo(cpacs_path):
""" Function to convert a CPACS file geometry into a SUMO file geometry
Function 'convert_cpacs_to_sumo' open an input cpacs file with TIXI handle
and via two main loop, one for fuselage(s), one for wing(s) it convert
every element (as much as possible) in the SUMO (.smx) format, which is
also an xml file. Due to some differences between both format, some CPACS
definition could lead to issues. The output sumo file is saved in the
folder /ToolOutput
Source : CPACS documentation
ARGUMENTS
(str) cpacs_path -- Path to the CPACS file
RETURNS
(str) OUTPUT_SMX -- Path to the SUMO file
(./ToolOutput/Toolouput.smx)
"""
MODULE_DIR = os.path.dirname(os.path.abspath(__file__))
EMPTY_SMX = MODULE_DIR + '/files/sumo_empty.smx'
OUTPUT_SMX = MODULE_DIR + '/ToolOutput/ToolOutput.smx'
tixi = open_tixi(cpacs_path)
sumo = open_tixi(EMPTY_SMX)
# Fuslage(s) -----
FUSELAGES_PATH = '/cpacs/vehicles/aircraft/model/fuselages'
if tixi.checkElement(FUSELAGES_PATH):
fus_cnt = tixi.getNamedChildrenCount(FUSELAGES_PATH, 'fuselage')
log.info(str(fus_cnt) + ' fuselage has been found.')
else:
fus_cnt = 0
if fus_cnt == 0:
log.warning('No fuselage has been found in this CPACS file!')
for i_fus in range(fus_cnt):
fus_path = FUSELAGES_PATH + '/fuselage[' + str(i_fus+1) + ']'
fus_uid = tixi.getTextAttribute(fus_path, 'uID')
fus_transf = Transformation()
fus_transf.get_cpacs_transf(tixi, fus_path + '/transformation')
# Create new body (SUMO)
sumo.createElementAtIndex('/Assembly', 'BodySkeleton', i_fus+1)
body_path = '/Assembly/BodySkeleton[' + str(i_fus+1) + ']'
sumo.addTextAttribute(body_path, 'akimatg', 'false')
sumo.addTextAttribute(body_path, 'name', fus_uid)
body_tansf = Transformation()
body_tansf.translation = fus_transf.translation
# Convert angles
body_tansf.rotation = euler2fix(fus_transf.rotation)
# Add body rotation
body_rot_str = str(math.radians(body_tansf.rotation.x)) + ' ' \
+ str(math.radians(body_tansf.rotation.y)) + ' ' \
+ str(math.radians(body_tansf.rotation.z))
sumo.addTextAttribute(body_path, 'rotation', body_rot_str)
# Add body origin
body_ori_str = str(body_tansf.translation.x) + ' ' \
+ str(body_tansf.translation.y) + ' ' \
+ str(body_tansf.translation.z)
sumo.addTextAttribute(body_path, 'origin', body_ori_str)
# Positionings
if tixi.checkElement(fus_path + '/positionings'):
pos_cnt = tixi.getNamedChildrenCount(fus_path + '/positionings',
'positioning')
log.info(str(fus_cnt) + ' "Positionning" has been found : ')
pos_x_list = []
pos_y_list = []
pos_z_list = []
from_sec_list = []
to_sec_list = []
for i_pos in range(pos_cnt):
pos_path = fus_path + '/positionings/positioning[' \
+ str(i_pos+1) + ']'
length = tixi.getDoubleElement(pos_path + '/length')
sweep_deg = tixi.getDoubleElement(pos_path + '/sweepAngle')
sweep = math.radians(sweep_deg)
dihedral_deg = tixi.getDoubleElement(pos_path+'/dihedralAngle')
dihedral = math.radians(dihedral_deg)
# Get the corresponding translation of each positionning
pos_x_list.append(length * math.sin(sweep))
pos_y_list.append(length * math.cos(dihedral) * math.cos(sweep))
pos_z_list.append(length * math.sin(dihedral) * math.cos(sweep))
# Get which section are connected by the positionning
if tixi.checkElement(pos_path + '/fromSectionUID'):
from_sec = tixi.getTextElement(pos_path +'/fromSectionUID')
else:
from_sec = ''
from_sec_list.append(from_sec)
if tixi.checkElement(pos_path + '/toSectionUID'):
to_sec = tixi.getTextElement(pos_path + '/toSectionUID')
else:
to_sec = ''
to_sec_list.append(to_sec)
# Re-loop though the positionning to re-order them
for j_pos in range(pos_cnt):
if from_sec_list[j_pos] == '':
prev_pos_x = 0
prev_pos_y = 0
prev_pos_z = 0
elif from_sec_list[j_pos] == to_sec_list[j_pos-1]:
prev_pos_x = pos_x_list[j_pos-1]
prev_pos_y = pos_y_list[j_pos-1]
prev_pos_z = pos_z_list[j_pos-1]
else:
index_prev = to_sec_list.index(from_sec_list[j_pos])
prev_pos_x = pos_x_list[index_prev]
prev_pos_y = pos_y_list[index_prev]
prev_pos_z = pos_z_list[index_prev]
pos_x_list[j_pos] += prev_pos_x
pos_y_list[j_pos] += prev_pos_y
pos_z_list[j_pos] += prev_pos_z
else:
log.warning('No "positionings" have been found!')
pos_cnt = 0
#Sections
sec_cnt = tixi.getNamedChildrenCount(fus_path + '/sections', 'section')
log.info(" -" + str(sec_cnt) + ' fuselage sections have been found')
if pos_cnt == 0:
pos_x_list = [0.0] * sec_cnt
pos_y_list = [0.0] * sec_cnt
pos_z_list = [0.0] * sec_cnt
for i_sec in range(sec_cnt):
sec_path = fus_path + '/sections/section[' + str(i_sec+1) + ']'
sec_uid = tixi.getTextAttribute(sec_path, 'uID')
sec_transf = Transformation()
sec_transf.get_cpacs_transf(tixi, sec_path + '/transformation')
if (sec_transf.rotation.x
or sec_transf.rotation.y
or sec_transf.rotation.z):
log.warning('Sections "' + sec_uid + '" is rotated, it is \
not possible to take that into acount in SUMO !')
# Elements
elem_cnt = tixi.getNamedChildrenCount(sec_path + '/elements',
'element')
if elem_cnt > 1:
log.warning("Sections " + sec_uid + " contains multiple \
element, it could be an issue for the conversion \
to SUMO!")
for i_elem in range(elem_cnt):
elem_path = sec_path + '/elements/element[' \
+ str(i_elem + 1) + ']'
elem_uid = tixi.getTextAttribute(elem_path, 'uID')
elem_transf = Transformation()
elem_transf.get_cpacs_transf(tixi,elem_path +'/transformation')
if (elem_transf.rotation.x
or elem_transf.rotation.y
or elem_transf.rotation.z):
log.warning('Element "' + elem_uid + '" is rotated, it \
is not possible to take that into acount in \
SUMO !')
# Fuselage profiles
prof_uid = tixi.getTextElement(elem_path+'/profileUID')
prof_path = tixi.uIDGetXPath(prof_uid)
prof_vect_x_str = tixi.getTextElement(prof_path+'/pointList/x')
prof_vect_y_str = tixi.getTextElement(prof_path+'/pointList/y')
prof_vect_z_str = tixi.getTextElement(prof_path+'/pointList/z')
# Transform sting into list of float
prof_vect_x = []
for i, item in enumerate(prof_vect_x_str.split(';')):
if item:
prof_vect_x.append(float(item))
prof_vect_y = []
for i, item in enumerate(prof_vect_y_str.split(';')):
if item:
prof_vect_y.append(float(item))
prof_vect_z = []
for i, item in enumerate(prof_vect_z_str.split(';')):
if item:
prof_vect_z.append(float(item))
prof_size_y = (max(prof_vect_y) - min(prof_vect_y))/2
prof_size_z = (max(prof_vect_z) - min(prof_vect_z))/2
prof_vect_y[:] = [y / prof_size_y for y in prof_vect_y]
prof_vect_z[:] = [z / prof_size_z for z in prof_vect_z]
prof_min_y = min(prof_vect_y)
prof_max_y = max(prof_vect_y)
prof_min_z = min(prof_vect_z)
prof_max_z = max(prof_vect_z)
prof_vect_y[:] = [y - 1 - prof_min_y for y in prof_vect_y]
prof_vect_z[:] = [z - 1 - prof_min_z for z in prof_vect_z]
# Could be a problem if they are less positionings than secions
# TODO: solve that!
pos_y_list[i_sec] += (1 + prof_min_y) * prof_size_y
pos_z_list[i_sec] += (1 + prof_min_z) * prof_size_z
#To Plot a particular section
# if i_sec==30:
# plt.plot(prof_vect_z, prof_vect_y,'x')
# plt.xlabel('y')
# plt.ylabel('z')
# plt.grid(True)
# plt.show()
# Put value in SUMO format
body_frm_center_x = ( elem_transf.translation.x \
+ sec_transf.translation.x \
+ pos_x_list[i_sec]) \
* fus_transf.scale.x
body_frm_center_y = ( elem_transf.translation.y \
* sec_transf.scale.y \
+ sec_transf.translation.y \
+ pos_y_list[i_sec]) \
* fus_transf.scale.y
body_frm_center_z = ( elem_transf.translation.z \
* sec_transf.scale.z \
+ sec_transf.translation.z \
+ pos_z_list[i_sec]) \
* fus_transf.scale.z
body_frm_height = prof_size_z * 2 * elem_transf.scale.z \
* sec_transf.scale.z * fus_transf.scale.z
if body_frm_height < 0.01:
body_frm_height = 0.01
body_frm_width = prof_size_y * 2 * elem_transf.scale.y \
* sec_transf.scale.y * fus_transf.scale.y
if body_frm_width < 0.01:
body_frm_width = 0.01
# Convert the profile points in the SMX format
prof_str = ''
teta_list = []
teta_half = []
prof_vect_y_half = []
prof_vect_z_half = []
check_max = 0
check_min = 0
# Use polar angle to keep point in the correct order
for i, item in enumerate(prof_vect_y):
teta_list.append(math.atan2(prof_vect_z[i],prof_vect_y[i]))
for t, teta in enumerate(teta_list):
HALF_PI = math.pi/2
EPSILON = 0.04
if abs(teta) <= HALF_PI-EPSILON:
teta_half.append(teta)
prof_vect_y_half.append(prof_vect_y[t])
prof_vect_z_half.append(prof_vect_z[t])
elif abs(teta) < HALF_PI+EPSILON:
# Check if not the last element of the list
if not t == len(teta_list)-1:
next_val = prof_vect_z[t+1]
# Check if it is better to keep next point
if not abs(next_val) > abs(prof_vect_z[t]):
if prof_vect_z[t] > 0 and not check_max:
teta_half.append(teta)
# Force y=0, to get symmetrical profile
prof_vect_y_half.append(0)
prof_vect_z_half.append(prof_vect_z[t])
check_max = 1
elif prof_vect_z[t] < 0 and not check_min:
teta_half.append(teta)
# Force y=0, to get symmetrical profile
prof_vect_y_half.append(0)
prof_vect_z_half.append(prof_vect_z[t])
check_min = 1
# Sort points by teta value, to fit the SUMO profile format
teta_half, prof_vect_z_half, prof_vect_y_half = \
(list(t) for t in zip(*sorted(zip(teta_half,
prof_vect_z_half,
prof_vect_y_half))))
# Write profile as a string and add y=0 point at the begining
# and at the end to ensure symmmetry
if not check_min:
prof_str += str(0) + ' ' + str(prof_vect_z_half[0]) + ' '
for i, item in enumerate(prof_vect_z_half):
prof_str += str(round(prof_vect_y_half[i], 4)) + ' ' \
+ str(round(prof_vect_z_half[i], 4)) + ' '
if not check_max:
prof_str += str(0) + ' ' + str(prof_vect_z_half[i]) + ' '
# Write the SUMO file
sumo.addTextElementAtIndex(body_path, 'BodyFrame',
prof_str, i_sec+1)
frame_path = body_path + '/BodyFrame[' + str(i_sec+1) + ']'
body_center_str = str(body_frm_center_x) + ' ' + \
str(body_frm_center_y) + ' ' + \
str(body_frm_center_z)
sumo.addTextAttribute(frame_path, 'center', body_center_str)
sumo.addTextAttribute(frame_path,'height',str(body_frm_height))
sumo.addTextAttribute(frame_path, 'width', str(body_frm_width))
sumo.addTextAttribute(frame_path, 'name', sec_uid)
# To remove the default BodySkeleton
if fus_cnt == 0:
sumo.removeElement('/Assembly/BodySkeleton')
else:
sumo.removeElement('/Assembly/BodySkeleton[' + str(fus_cnt+1) + ']')
# Wing(s) -----
WINGS_PATH = '/cpacs/vehicles/aircraft/model/wings'
if tixi.checkElement(WINGS_PATH):
wing_cnt = tixi.getNamedChildrenCount(WINGS_PATH, 'wing')
log.info(str(wing_cnt) + ' wings has been found.')
else:
wing_cnt = 0
if wing_cnt == 0:
log.warning('No wings has been found in this CPACS file!')
for i_wing in range(wing_cnt):
wing_path = WINGS_PATH + '/wing[' + str(i_wing+1) + ']'
wing_uid = tixi.getTextAttribute(wing_path, 'uID')
wing_transf = Transformation()
wing_transf.get_cpacs_transf(tixi, wing_path + '/transformation')
# Create new wing (SUMO)
sumo.createElementAtIndex('/Assembly', 'WingSkeleton', i_wing+1)
wg_sk_path = '/Assembly/WingSkeleton[' + str(i_wing+1) + ']'
sumo.addTextAttribute(wg_sk_path, 'akimatg', 'false')
sumo.addTextAttribute(wg_sk_path, 'name', wing_uid)
# Create a class for the transformation of the WingSkeleton
wg_sk_tansf = Transformation()
# Convert WingSkeleton rotation and add it to SUMO
wg_sk_tansf.rotation = euler2fix(wing_transf.rotation)
wg_sk_rot_str = str(math.radians(wg_sk_tansf.rotation.x)) + ' ' \
+ str(math.radians(wg_sk_tansf.rotation.y)) + ' ' \
+ str(math.radians(wg_sk_tansf.rotation.z))
sumo.addTextAttribute(wg_sk_path, 'rotation', wg_sk_rot_str)
# Add WingSkeleton origin
wg_sk_tansf.translation = wing_transf.translation
wg_sk_ori_str = str(wg_sk_tansf.translation.x) + ' ' \
+ str(wg_sk_tansf.translation.y) + ' ' \
+ str(wg_sk_tansf.translation.z)
sumo.addTextAttribute(wg_sk_path, 'origin', wg_sk_ori_str)
if tixi.checkAttribute(wing_path, 'symmetry'):
if tixi.getTextAttribute(wing_path, 'symmetry') == 'x-z-plane':
sumo.addTextAttribute(wg_sk_path, 'flags',
'autosym,detectwinglet')
else:
sumo.addTextAttribute(wg_sk_path, 'flags', 'detectwinglet')
# Positionings
if tixi.checkElement(wing_path + '/positionings'):
pos_cnt = tixi.getNamedChildrenCount(wing_path + '/positionings',
'positioning')
log.info(str(wing_cnt) + ' "positionning" has been found : ')
pos_x_list = []
pos_y_list = []
pos_z_list = []
from_sec_list = []
to_sec_list = []
for i_pos in range(pos_cnt):
pos_path = wing_path + '/positionings/positioning[' \
+ str(i_pos+1) + ']'
length = tixi.getDoubleElement(pos_path + '/length')
sweep_deg = tixi.getDoubleElement(pos_path + '/sweepAngle')
sweep = math.radians(sweep_deg)
dihedral_deg = tixi.getDoubleElement(pos_path+'/dihedralAngle')
dihedral = math.radians(dihedral_deg)
# Get the corresponding translation of each positionning
pos_x_list.append(length * math.sin(sweep))
pos_y_list.append(length * math.cos(dihedral)*math.cos(sweep))
pos_z_list.append(length * math.sin(dihedral)*math.cos(sweep))
# Get which section are connected by the positionning
if tixi.checkElement(pos_path + '/fromSectionUID'):
from_sec = tixi.getTextElement(pos_path +'/fromSectionUID')
else:
from_sec = ''
from_sec_list.append(from_sec)
if tixi.checkElement(pos_path + '/toSectionUID'):
to_sec = tixi.getTextElement(pos_path + '/toSectionUID')
else:
to_sec = ''
to_sec_list.append(to_sec)
# Re-loop though the positionning to re-order them
for j_pos in range(pos_cnt):
if from_sec_list[j_pos] == '':
prev_pos_x = 0
prev_pos_y = 0
prev_pos_z = 0
elif from_sec_list[j_pos] == to_sec_list[j_pos-1]:
prev_pos_x = pos_x_list[j_pos-1]
prev_pos_y = pos_y_list[j_pos-1]
prev_pos_z = pos_z_list[j_pos-1]
else:
index_prev = to_sec_list.index(from_sec_list[j_pos])
prev_pos_x = pos_x_list[index_prev]
prev_pos_y = pos_y_list[index_prev]
prev_pos_z = pos_z_list[index_prev]
pos_x_list[j_pos] += prev_pos_x
pos_y_list[j_pos] += prev_pos_y
pos_z_list[j_pos] += prev_pos_z
else:
log.warning('No "positionings" have been found!')
pos_cnt = 0
#Sections
sec_cnt = tixi.getNamedChildrenCount(wing_path + '/sections','section')
log.info(" -" + str(sec_cnt) + ' wing sections have been found')
wing_sec_index = 1
if pos_cnt == 0:
pos_x_list = [0.0] * sec_cnt
pos_y_list = [0.0] * sec_cnt
pos_z_list = [0.0] * sec_cnt
for i_sec in reversed(range(sec_cnt)):
sec_path = wing_path + '/sections/section[' + str(i_sec+1) + ']'
sec_uid = tixi.getTextAttribute(sec_path, 'uID')
sec_transf = Transformation()
sec_transf.get_cpacs_transf(tixi, sec_path + '/transformation')
# Elements
elem_cnt = tixi.getNamedChildrenCount(sec_path + '/elements',
'element')
if elem_cnt > 1:
log.warning("Sections " + sec_uid + " contains multiple \
element, it could be an issue for the conversion \
to SUMO!")
for i_elem in range(elem_cnt):
elem_path = sec_path + '/elements/element[' \
+ str(i_elem + 1) + ']'
elem_uid = tixi.getTextAttribute(elem_path, 'uID')
elem_transf = Transformation()
elem_transf.get_cpacs_transf(tixi,elem_path +'/transformation')
# Wing profile (airfoil)
prof_uid = tixi.getTextElement(elem_path+'/airfoilUID')
prof_path = tixi.uIDGetXPath(prof_uid)
try:
tixi.checkElement(prof_path)
except:
log.error('No profile "' + prof_uid + '" has been found!')
prof_vect_x_str = tixi.getTextElement(prof_path+'/pointList/x')
prof_vect_y_str = tixi.getTextElement(prof_path+'/pointList/y')
prof_vect_z_str = tixi.getTextElement(prof_path+'/pointList/z')
# Transform airfoil points (string) into list of float
prof_vect_x = []
for i, item in enumerate(prof_vect_x_str.split(';')):
if item:
prof_vect_x.append(float(item))
prof_vect_y = []
for i, item in enumerate(prof_vect_y_str.split(';')):
if item:
prof_vect_y.append(float(item))
prof_vect_z = []
for i, item in enumerate(prof_vect_z_str.split(';')):
if item:
prof_vect_z.append(float(item))
if sum(prof_vect_z[0:len(prof_vect_z)//2]) \
< sum(prof_vect_z[len(prof_vect_z)//2:-1]):
log.info("Airfoil's points will be reversed.")
tmp_vect_x = []
tmp_vect_y = []
tmp_vect_z = []
for i in range(len(prof_vect_x)):
tmp_vect_x.append(prof_vect_x[len(prof_vect_x)-1-i])
tmp_vect_y.append(prof_vect_y[len(prof_vect_y)-1-i])
tmp_vect_z.append(prof_vect_z[len(prof_vect_z)-1-i])
prof_vect_x = tmp_vect_x
prof_vect_y = tmp_vect_y
prof_vect_z = tmp_vect_z
# Apply scaling
for i, item in enumerate(prof_vect_x):
prof_vect_x[i] = item * elem_transf.scale.x \
* sec_transf.scale.x * wing_transf.scale.x
for i, item in enumerate(prof_vect_y):
prof_vect_y[i] = item * elem_transf.scale.y \
* sec_transf.scale.y * wing_transf.scale.y
for i, item in enumerate(prof_vect_z):
prof_vect_z[i] = item * elem_transf.scale.z \
* sec_transf.scale.z * wing_transf.scale.z
# if (i_sec>8 and i_sec<=10):
# plt.plot(prof_vect_x, prof_vect_z,'x')
# plt.xlabel('x')
# plt.ylabel('z')
# plt.grid(True)
# plt.show()
prof_size_x = (max(prof_vect_x) - min(prof_vect_x))
prof_size_y = (max(prof_vect_y) - min(prof_vect_y))
prof_size_z = (max(prof_vect_z) - min(prof_vect_z))
if prof_size_y == 0:
prof_vect_x[:] = [x / prof_size_x for x in prof_vect_x]
prof_vect_z[:] = [z / prof_size_x for z in prof_vect_z]
# Is it correct to divide by prof_size_x ????
wg_sec_chord = prof_size_x
else:
log.error("An airfoil profile is not define correctly")
# SUMO variable for WingSection
wg_sec_center_x = ( elem_transf.translation.x \
+ sec_transf.translation.x \
+ pos_x_list[i_sec]) \
* wing_transf.scale.x
wg_sec_center_y = ( elem_transf.translation.y \
* sec_transf.scale.y \
+ sec_transf.translation.y \
+ pos_y_list[i_sec]) \
* wing_transf.scale.y
wg_sec_center_z = ( elem_transf.translation.z \
* sec_transf.scale.z \
+ sec_transf.translation.z \
+ pos_z_list[i_sec]) \
* wing_transf.scale.z
# Add roation from element and sections
# Adding the two angles: Maybe not work in every case!!!
add_rotation = SimpleNamespace()
add_rotation.x = elem_transf.rotation.x + sec_transf.rotation.x
add_rotation.y = elem_transf.rotation.y + sec_transf.rotation.y
add_rotation.z = elem_transf.rotation.z + sec_transf.rotation.z
# Get Section rotation for SUMO
wg_sec_rot = euler2fix(add_rotation)
wg_sec_dihed = math.radians(wg_sec_rot.x)
wg_sec_twist = math.radians(wg_sec_rot.y)
wg_sec_yaw = math.radians(wg_sec_rot.z)
# Convert point list into string
prof_str = ''
# Airfoil points order : shoud be from TE (1 0) to LE (0 0)
# then TE(1 0), but not reverse way.
# to avoid double zero, not accepted by SUMO
for i, item in (enumerate(prof_vect_x)):
# if not (prof_vect_x[i] == prof_vect_x[i-1] or \
# round(prof_vect_z[i],4) == round(prof_vect_z[i-1],4)):
if round(prof_vect_z[i],4) != round(prof_vect_z[i-1],4):
prof_str += str(round(prof_vect_x[i], 4)) + ' ' \
+ str(round(prof_vect_z[i], 4)) + ' '
sumo.addTextElementAtIndex(wg_sk_path, 'WingSection', prof_str,
wing_sec_index)
wg_sec_path = wg_sk_path + '/WingSection[' \
+ str(wing_sec_index) + ']'
sumo.addTextAttribute(wg_sec_path, 'airfoil', prof_uid)
sumo.addTextAttribute(wg_sec_path, 'name', sec_uid)
wg_sec_center_str = str(wg_sec_center_x) + ' ' + \
str(wg_sec_center_y) + ' ' + \
str(wg_sec_center_z)
sumo.addTextAttribute(wg_sec_path, 'center', wg_sec_center_str)
sumo.addTextAttribute(wg_sec_path, 'chord', str(wg_sec_chord))
sumo.addTextAttribute(wg_sec_path, 'dihedral',
str(wg_sec_dihed))
sumo.addTextAttribute(wg_sec_path, 'twist', str(wg_sec_twist))
sumo.addTextAttribute(wg_sec_path, 'yaw', str(wg_sec_yaw))
sumo.addTextAttribute(wg_sec_path, 'napprox', '-1')
sumo.addTextAttribute(wg_sec_path, 'reversed', 'false')
sumo.addTextAttribute(wg_sec_path, 'vbreak', 'false')
wing_sec_index += 1
# Add Wing caps
sumo.createElementAtIndex(wg_sk_path, "Cap", 1)
sumo.addTextAttribute(wg_sk_path+'/Cap[1]', 'height', '0')
sumo.addTextAttribute(wg_sk_path+'/Cap[1]', 'shape', 'LongCap')
sumo.addTextAttribute(wg_sk_path+'/Cap[1]', 'side', 'south')
sumo.createElementAtIndex(wg_sk_path, 'Cap', 2)
sumo.addTextAttribute(wg_sk_path+'/Cap[2]', 'height', '0')
sumo.addTextAttribute(wg_sk_path+'/Cap[2]', 'shape', 'LongCap')
sumo.addTextAttribute(wg_sk_path+'/Cap[2]', 'side', 'north')
# Save the SMX file
close_tixi(sumo, OUTPUT_SMX)
return OUTPUT_SMX
def create_config(cpacs_path, su2_path, config_file):
""" Function to create configuration file for SU2 calculation
Function 'create_config' create an SU2 configuration file from SU2 mesh data
(marker) and CPACS file specific related parameter (/toolSpecific).
For all other infomation the value from the default SU2 configuration file
are used.
Source : SU2 configuration file template
https://github.com/su2code/SU2/blob/master/config_template.cfg
ARGUMENTS
(str) cpacs_path -- Path to CPACS file
(str) su2_path -- Path to SU2 mesh
(str) config_file -- Path to default configuration file
RETURNS
()
Output
New configuration file save in /ToolOutput/ToolOutput.cfg
"""
MODULE_DIR = os.path.dirname(os.path.abspath(__file__))
CONFIG_FILE_OUTPUT = MODULE_DIR + '/ToolOutput/ToolOutput.cfg'
try:
config_file_object = open(config_file, 'r')
config_file_lines = config_file_object.readlines()
config_file_object.close()
log.info('Default configuration file has been found and read')
except Exception:
log.exception('Problem to open or read default configuration file')
# Create a dictionary with all the parameters from the default config file
config_dict = {}
for line in config_file_lines:
if '=' in line:
(key, val) = line.split('=')
if val.endswith('\n'):
val = val[:-1]
config_dict[key] = val
# Modify or add parameters -----------
tixi = open_tixi(cpacs_path)
config_dict_modif = config_dict
# General parmeters
config_dict_modif['MESH_FILENAME'] = su2_path
config_dict_modif['EXT_ITER'] = 300
# Get reference value
ref_len = get_value(tixi,
'/cpacs/vehicles/aircraft/model/reference/length')
ref_area = get_value(tixi, '/cpacs/vehicles/aircraft/model/reference/area')
config_dict_modif['REF_LENGTH'] = ref_len
config_dict_modif['REF_AREA'] = ref_area
# Flow conditions (from /toolSpecific?, possibility to have several cases)
aoa = 2.0
aos = 0.0
mach = 0.5
alt = 12000
Atm = get_atmosphere(alt)
pressure = Atm.pres
temp = Atm.temp
config_dict_modif['AOA'] = aoa
config_dict_modif['SIDESLIP_ANGLE'] = aos
config_dict_modif['MACH_NUMBER'] = mach
config_dict_modif['FREESTREAM_PRESSURE'] = pressure
config_dict_modif['FREESTREAM_TEMPERATURE'] = temp
# If calculation at CL fix (AOA will not be taken into account)
# Get value from /toolSpecific?, which one?
config_dict_modif['FIXED_CL_MODE'] = 'YES'
config_dict_modif['TARGET_CL'] = '0.5'
config_dict_modif['DCL_DALPHA'] = '0.1'
config_dict_modif['UPDATE_ALPHA'] = '8'
config_dict_modif['ITER_DCL_DALPHA'] = '80'
# Mesh Marker
marker_list = get_mesh_marker(su2_path)
euler_parts = '(' + ','.join(marker_list) + ')'
config_dict_modif['MARKER_EULER'] = euler_parts
config_dict_modif['MARKER_FAR'] = ' (Farfield)'
config_dict_modif['MARKER_SYM'] = ' (0)'
config_dict_modif['MARKER_PLOTTING'] = euler_parts
config_dict_modif['MARKER_MONITORING'] = euler_parts
config_dict_modif['MARKER_MOVING'] = euler_parts
# Change value if needed or add new parameters in the config file
for key, value in config_dict_modif.items():
line_nb = 0
# Double loop! There is probably a possibility to do something better.
for i, line in enumerate(config_file_lines):
if '=' in line:
(key_def, val_def) = line.split('=')
if key == key_def:
line_nb = i
break
if not line_nb:
config_file_lines.append(str(key) + ' = ' + str(value) + '\n')
else:
if val_def != config_dict_modif[key]:
config_file_lines[line_nb] = str(key) + ' = ' \
+ str(config_dict_modif[key]) + '\n'
config_file_new = open(CONFIG_FILE_OUTPUT, 'w')
config_file_new.writelines(config_file_lines)
config_file_new.close()
log.info('ToolOutput.cfg has been written in /ToolOutput.')
