def get_aero_refs(self):
xa_ref_c = []
xa_ref_2 = []
#Write the aerodynamic grid points coordinates into a list
with open(self.inflight_ref_shape_c) as f:
lines = f.readlines()
lines = [i.split() for i in lines]
for line in lines:
if all(isfloat(item) for item in line):
if len(line) == 3:
xa_ref_c.append(
[float(line[0]),
float(line[1]),
float(line[2])])
if len(line) == 6:
xa_ref_c.append(
[float(line[0]),
float(line[1]),
float(line[2])])
xa_ref_c.append(
[float(line[3]),
float(line[4]),
float(line[5])])
#Write the aerodynamic grid points coordinates into a list (excluding the root section)
with open(self.inflight_ref_shape_2) as f:
lines = f.readlines()
lines = [i.split() for i in lines]
for line in lines:
if all(isfloat(item) for item in line):
if len(line) == 3:
xa_ref_2.append(
[float(line[0]),
float(line[1]),
float(line[2])])
if len(line) == 6:
xa_ref_2.append(
[float(line[0]),
float(line[1]),
float(line[2])])
xa_ref_2.append(
[float(line[3]),
float(line[4]),
float(line[5])])
xa_ref_c = np.asarray(xa_ref_c)
xa_ref_2 = np.asarray(xa_ref_2)
aero_refs = {}
aero_refs['xa_ref_c'] = xa_ref_c
aero_refs['xa_ref_2'] = xa_ref_2
return aero_refs
def get_aero_params(self):
apoints_coord = []
#Write the aerodynamic grid points coordinates into a list (excluding the root section)
with open(self.jig_shape) as f:
lines = f.readlines()
lines = [i.split() for i in lines]
for line in lines:
if all(isfloat(item) for item in line):
if len(line) == 3:
apoints_coord.append(
[float(line[0]),
float(line[1]),
float(line[2])])
if len(line) == 6:
apoints_coord.append(
[float(line[0]),
float(line[1]),
float(line[2])])
apoints_coord.append(
[float(line[3]),
float(line[4]),
float(line[5])])
apoints_coord = np.asarray(apoints_coord)
aero_params = {}
aero_params['apoints_coord'] = apoints_coord
return aero_params
def get_aero_dimensions(self):
apoints_coord = []
network_info = []
#Write the aerodynamic grid points coordinates into a list
with open(self.aero_template) as f:
lines = f.readlines()
lines = [i.split() for i in lines]
points = 0
pans = 0
for line in lines:
#Get aerodynamic grid points coordinates
if all(isfloat(item) for item in line):
if len(line) == 3:
apoints_coord.append(
[float(line[0]),
float(line[1]),
float(line[2])])
if len(line) == 6:
apoints_coord.append(
[float(line[0]),
float(line[1]),
float(line[2])])
apoints_coord.append(
[float(line[3]),
float(line[4]),
float(line[5])])
#Get network information
if len(line) > 1:
if isint(line[0]):
network_info.append([
int(line[0]),
int(line[2]),
int(line[1]),
int(points),
int(pans)
])
points = points + int(line[2]) * int(line[1])
pans = pans + (int(line[2]) - 1) * (int(line[1]) - 1)
apoints_coord = np.asarray(apoints_coord)
na = len(apoints_coord)
apoints_coord_unique = np.unique(apoints_coord, axis=0)
na_unique = len(apoints_coord_unique)
#Dictionary containing aerodynamic problem data
aero_dimensions = {}
aero_dimensions['na'] = na
aero_dimensions['na_unique'] = na_unique
aero_dimensions['network_info'] = network_info
return aero_dimensions
def create_current_geom(self, params):
sym_plane_index = self.sym_plane_index
#Compute the coordinates of the displaced points
jig_coord = params['apoints_coord']
new_coord = jig_coord + params['delta']
#Enforce symmetry condition, if existing
if sym_plane_index is not None:
j = sym_plane_index - 1
for i in range(len(jig_coord)):
if jig_coord[i][j] == 0.:
new_coord[i][j] = 0.
with open(self.aero_template) as f:
lines = f.readlines()
split_lines = [i.split() for i in lines]
#Replace the old grid coordinates with the new ones
#Total aerodynamic grid point counter
j = 0
for l in range(len(split_lines)):
if all(isfloat(item) for item in split_lines[l]):
if len(split_lines[l]) == 3:
lines[l] = str(new_coord[j, 0]) + ' ' + str(
new_coord[j, 1]) + ' ' + str(new_coord[j,
2]) + '\n'
j += 1
if len(split_lines[l]) == 6:
lines[l] = str(new_coord[j, 0]) + ' ' + str(
new_coord[j, 1]) + ' ' + str(
new_coord[j, 2]) + ' ' + str(
new_coord[j + 1, 0]) + ' ' + str(
new_coord[j + 1, 1]) + ' ' + str(
new_coord[j + 1, 2]) + '\n'
j += 2
case_name = self.case_name
#Panin auxiliary file in a subdirectory for each case
current_shape = os.path.join(os.getcwd(), case_name,
self.current_shape)
#Create subdirectory if it does not exist
if not os.path.exists(os.path.dirname(current_shape)):
try:
os.makedirs(os.path.dirname(current_shape))
except OSError as exc: # Guard against race condition
if exc.errno != errno.EEXIST:
raise
#Write the new geometry file
with open(current_shape, 'w') as f:
for line in lines:
f.write(line)
def create_current_geom(self, params):
a=params['alpha']
print(a)
sym_plane_index = self.sym_plane_index
#Compute the coordinates of the displaced points
jig_coord = params['apoints_coord']
new_coord = jig_coord + params['delta']
#Enforce symmetry condition, if existing
if sym_plane_index is not None:
j = sym_plane_index - 1
for i in range(len(jig_coord)):
if jig_coord[i][j] == 0.:
new_coord[i][j] = 0.
with open(self.aero_template) as f:
lines = f.readlines()
split_lines = [i.split() for i in lines]
#Replace the old grid coordinates with the new ones
#Total aerodynamic grid point counter
j = 0
for l in range(len(split_lines)):
if all(isfloat(item) for item in split_lines[l]):
if len(split_lines[l]) == 3:
lines[l] = str(new_coord[j, 0])+' '+str(new_coord[j, 1])+' '+str(new_coord[j, 2])+'\n'
j += 1
if len(split_lines[l]) == 6:
lines[l] = str(new_coord[j, 0])+' '+str(new_coord[j, 1])+' '+str(new_coord[j, 2])+' '+str(new_coord[j+1, 0])+' '+str(new_coord[j+1, 1])+' '+str(new_coord[j+1, 2])+'\n'
j += 2
#Write the new geometry file
with open(self.current_shape, 'w') as f:
for line in lines:
f.write(line)
with open(pnh) as f:
lines = f.readlines()
lines = [i.split() for i in lines]
for i in range(len(lines)):
if len(lines[i]) > 1:
#Write nodal displacements onto u if the node belongs to the outer surface
if lines[i][1] == 'G':
displ[int(lines[i][0])] = [
float(lines[i][2]),
float(lines[i][3]),
float(lines[i][4])
]
if isint(lines[i][0]) and isfloat(lines[i][1]):
#Store stresses only if the element is of shell type:
if lines[i + 1][0] == '-CONT-' and lines[
i + 2][0] == '-CONT-' and lines[
i + 3][0] == '-CONT-' and lines[
i +
4][0] == '-CONT-' and lines[i +
5][0] == '-CONT-':
#Write shell principal stresses (upper and lower shell faces)
principal_stress_1[int(lines[i][0])] = (float(
lines[i + 1][3]), float(lines[i + 2][1]))
principal_stress_2[int(lines[i][0])] = (float(
lines[i + 4][2]), float(lines[i + 4][3]))
#Store the maximum von Mises stress between the upper and lower surface
for elm_id in elm.keys():
def get_output_data(self):
#Read the punch and output files only if they exist and their last modified date is older than input file one
while(not os.path.isfile(self.output_filepath)): pass
while(os.path.getmtime(self.output_filepath) <= os.path.getmtime(self.input_filepath)): pass
while(not os.path.isfile(self.output_file)): pass
while(os.path.getmtime(self.output_file) <= os.path.getmtime(self.input_filepath)): pass
u = np.zeros((self.ns,3))
shell_stress = []
mass = 0.
#Read the Nastran punch file (.pnh) and extract displacement and stress data
with open(self.output_filepath) as f:
lines = f.readlines()
lines = [i.split() for i in lines]
for i in range(len(lines)):
if len(lines[i]) > 1:
#Write nodal displacements onto u if the node belongs to the outer surface
if lines[i][0] in self.node_id and lines[i][1] == 'G':
u[self.node_id.index(lines[i][0])][0] = lines[i][2]
u[self.node_id.index(lines[i][0])][1] = lines[i][3]
u[self.node_id.index(lines[i][0])][2] = lines[i][4]
if isint(lines[i][0]) and isfloat(lines[i][1]):
if lines[i] is not lines[-2]:
if lines[i+2][0] == '-CONT-':
#Store stresses only if the element is of shell type:
if lines[i+1][0] == '-CONT-' and lines[i+2][0] == '-CONT-' and lines[i+3][0] == '-CONT-' and lines[i+4][0] == '-CONT-' and lines[i+5][0] == '-CONT-':
#Write shell principal stresses onto a list (upper and lower shell faces)
shell_stress.append(((float(lines[i+1][3]), float(lines[i+2][1])), (float(lines[i+4][2]), float(lines[i+4][3]))))
#Compute the Von Mises Stress on the structure
VM = []
for s in shell_stress:
VM.append(np.sqrt(s[0][0]**2 - s[0][0]*s[0][1] + s[0][1]**2))
VM.append(np.sqrt(s[1][0]**2 - s[1][0]*s[1][1] + s[1][1]**2))
VMStress = np.asarray(VM)
#Read the Nastran output file (.out) and extract the total mass of the structure (M)
with open(self.output_file) as f:
lines = f.readlines()
lines = [i.split() for i in lines]
for i in range(len(lines)):
if len(lines[i]) > 4:
if lines[i][4] == 'MASS' and lines[i][5] == 'X-C.G.':
mass = float(lines[i+1][1].replace('D', 'E'))
output_data = {}
output_data['u'] = u
output_data['VMStress'] = VMStress
output_data['mass'] = mass
return output_data
