def test_get_value_or_default():
"""Test the function 'get_value_or_default'"""
tixi = open_tixi(CPACS_IN_PATH)
# Check if the correct value (float) is return from an xpath
xpath = '/cpacs/vehicles/aircraft/model/reference/area'
tixi, value = get_value_or_default(tixi, xpath, 2.0)
assert value == 1.0
# Check if the correct value (text) is return from an xpath
xpath = '/cpacs/vehicles/aircraft/model/name'
tixi, value = get_value_or_default(tixi, xpath, 'name')
assert value == 'Cpacs2Test'
# Check if a non exitant xpath leads to its creation (integer)
xpath = '/cpacs/vehicles/aircraft/model/reference/newSpan'
tixi, value = get_value_or_default(tixi, xpath, 100)
assert value == 100
new_elem = tixi.getDoubleElement(xpath)
assert new_elem == 100
# Check if a non exitant xpath leads to its creation (float)
xpath = '/cpacs/vehicles/aircraft/model/reference/newArea'
tixi, value = get_value_or_default(tixi, xpath, 1000.0)
assert value == 1000.0
new_elem = tixi.getDoubleElement(xpath)
assert new_elem == 1000.0
# Check if a non exitant xpath leads to its creation (text)
xpath = '/cpacs/vehicles/aircraft/model/reference/newRef'
tixi, value = get_value_or_default(tixi, xpath, 'test')
assert value == 'test'
new_elem = tixi.getTextElement(xpath)
assert new_elem == 'test'
def get_inside_dim(self, cpacs_path):
""" Get user input from the CPACS file
The function 'get_inside_dim' extracts from the CPACS file the required
aircraft inside dimension, the code will use the default value when they are
missing.
Args:
cpacs_path (str): Path to CPACS file
"""
tixi = open_tixi(cpacs_path)
# Get inside dimension from the CPACS file if exit
self.seat_width = get_value_or_default(tixi, GEOM_XPATH + '/seatWidth',
0.525)
self.seat_length = get_value_or_default(tixi,
GEOM_XPATH + '/seatLength',
self.seat_length)
self.aisle_width = get_value_or_default(tixi,
GEOM_XPATH + '/aisleWidth',
0.42)
self.fuse_thick = get_value_or_default(tixi, GEOM_XPATH + '/fuseThick',
6.63)
self.toilet_length = get_value_or_default(tixi,
GEOM_XPATH + '/toiletLength',
self.toilet_length)
close_tixi(tixi, cpacs_path)
def add_skin_friction(cpacs_path, cpacs_out_path):
""" Function to add the skin frinction drag coeffienct to the CPACS file
Function 'add_skin_friction' add the skin friction drag 'cd0' to the CPACS
file, then it could be added to the drag coeffienct obtain with Euler
calcualtions or other methods
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str): Path to CPACS output file
"""
tixi = open_tixi(cpacs_path)
tigl = open_tigl(tixi)
wing_area_max, wing_span_max = get_largest_wing_dim(tixi, tigl)
analysis_xpath = '/cpacs/toolspecific/CEASIOMpy/geometry/analysis'
range_xpath = '/cpacs/toolspecific/CEASIOMpy/ranges'
# Requiered input data from CPACS
wetted_area = get_value(tixi, analysis_xpath + '/wettedArea')
# Not requiered input data (a default value will be used if no
# value has been found in the CPACS file)
wing_area_xpath = analysis_xpath + '/wingArea'
tixi, wing_area = get_value_or_default(tixi, wing_area_xpath,
wing_area_max)
if wing_area != wing_area_max:
log.warning('Wing area found in the CPACS file /toolspecific is \
different from the one calculated from geometry, \
/toolspecific value will be used')
wing_span_xpath = analysis_xpath + '/wingSpan'
tixi, wing_span = get_value_or_default(tixi, wing_span_xpath,
wing_span_max)
if wing_span != wing_span_max:
log.warning('Wing span found in the CPACS file /toolspecific is \
different from the one calculated from geometry, \
/toolspecific value will be used')
cruise_alt_xpath = range_xpath + '/cruiseAltitude'
tixi, cruise_alt = get_value_or_default(tixi, cruise_alt_xpath, 12000)
cruise_mach_xpath = range_xpath + '/cruiseMach'
tixi, cruise_mach = get_value_or_default(tixi, cruise_mach_xpath, 0.78)
# Calculate Cd0
cd0 = estimate_skin_friction_coef(wetted_area,wing_area,wing_span, \
cruise_mach,cruise_alt)
# Save Cd0 in the CPACS file
cd0_xpath = '/cpacs/toolspecific/CEASIOMpy/aerodynamics/skinFriction/cd0'
tixi = create_branch(tixi, cd0_xpath)
tixi.updateDoubleElement(cd0_xpath, cd0, '%g')
log.info('Skin friction drag coeffienct (cd0) has been saved in the \
CPACS file')
close_tixi(tixi, cpacs_out_path)
def get_user_inputs(self, cpacs_path):
"""Take user inputs from the GUI."""
tixi = cpsf.open_tixi(CPACS_OPTIM_PATH)
# Problem setup
objectives = cpsf.get_value_or_default(tixi, OPTIM_XPATH + 'objective',
'cl')
self.objective = objectives.split(';')
self.minmax = cpsf.get_value_or_default(tixi, OPTIM_XPATH + 'minmax',
'max')
# Global parameters
self.driver = cpsf.get_value_or_default(
tixi, OPTIM_XPATH + 'parameters/driver', 'COBYLA')
self.max_iter = int(
cpsf.get_value_or_default(tixi, OPTIM_XPATH + 'iterationNB', 200))
self.tol = float(
cpsf.get_value_or_default(tixi, OPTIM_XPATH + 'tolerance', 1e-3))
self.save_iter = int(
cpsf.get_value_or_default(tixi, OPTIM_XPATH + 'saving/perIter', 1))
# Specific DoE parameters
self.doedriver = cpsf.get_value_or_default(
tixi, OPTIM_XPATH + 'parameters/DoE/driver', 'uniform')
self.samplesnb = int(
cpsf.get_value_or_default(tixi,
OPTIM_XPATH + 'parameters/DoE/sampleNB',
3))
# User specified configuration file path
self.user_config = cpsf.get_value_or_default(
tixi, OPTIM_XPATH + 'Config/filepath',
'../Optimisation/Default_config.csv')
cpsf.close_tixi(tixi, CPACS_OPTIM_PATH)
def get_cl(cpacs_path, cpacs_out_path):
""" Function to calculate CL requiered as a function of the parameter found
in the CPACS file.
Function 'get_cl' find input value in the CPACS file, calculate the
requiered CL (with calculate_cl) and save the CL value in
/cpacs/toolspecific/CEASIOMpy/aerodynamics/su2/targetCL
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str): Path to CPACS output file
"""
tixi = open_tixi(cpacs_path)
# XPath definition
model_xpath = '/cpacs/vehicles/aircraft/model'
ref_area_xpath = model_xpath + '/reference/area'
mtom_xpath = model_xpath + '/analyses/massBreakdown/designMasses/mTOM/mass'
range_xpath = '/cpacs/toolspecific/CEASIOMpy/ranges'
cruise_alt_xpath = range_xpath + '/cruiseAltitude'
cruise_mach_xpath = range_xpath + '/cruiseMach'
load_fact_xpath = range_xpath + '/loadFactor'
su2_xpath = '/cpacs/toolspecific/CEASIOMpy/aerodynamics/su2'
# Requiered input data from CPACS
ref_area = get_value(tixi, ref_area_xpath)
mtom = get_value(tixi, mtom_xpath)
# Requiered input data that could be replace by a default value if missing
cruise_alt = get_value_or_default(tixi, cruise_alt_xpath, 12000.0)
cruise_mach = get_value_or_default(tixi, cruise_mach_xpath, 0.78)
load_fact = get_value_or_default(tixi, load_fact_xpath, 1.05)
# Get atmosphere from cruise altitude
Atm = get_atmosphere(cruise_alt)
# CL calculation
target_cl = calculate_cl(ref_area, cruise_alt, cruise_mach, mtom,
load_fact)
# Save TargetCL
create_branch(tixi, su2_xpath)
create_branch(tixi, su2_xpath + '/targetCL')
create_branch(tixi, su2_xpath + '/fixedCL')
tixi.updateDoubleElement(su2_xpath + '/targetCL', target_cl, '%g')
tixi.updateTextElement(su2_xpath + '/fixedCL', 'YES')
log.info('Target CL has been saved in the CPACS file')
close_tixi(tixi, cpacs_out_path)
def get_user_inputs(self, cpacs_path):
"""Take user inputs from the GUI."""
tixi = cpsf.open_tixi(CPACS_PREDICT_PATH)
self.objectives = cpsf.get_value_or_default(
tixi, PREDICT_XPATH + 'objective', ['cl'])
self.user_config = cpsf.get_value_or_default(
tixi, PREDICT_XPATH + 'Config/filepath', 'Variable_history.csv')
self.aeromap_case = cpsf.get_value_or_default(
tixi, PREDICT_XPATH + 'aeromap_case/IsCase', False)
self.doedriver = cpsf.get_value_or_default(
tixi, PREDICT_XPATH + 'aeromap_case/DoEdriver', 'LatinHypercube')
self.samplesnb = cpsf.get_value_or_default(
tixi, PREDICT_XPATH + 'aeromap_case/sampleNB', 3)
def get_wkdir_or_create_new(tixi):
""" Function get the wkdir path from CPACS or create a new one
Function 'get_wkdir_or_create_new' checks in the CPACS file if a working
directory already exit for this run, if not, a new one is created and
return.
Args:
tixi (handle): TIXI handle
Returns:
wkdir_path (str): Path to the active working directory
"""
WKDIR_XPATH = '/cpacs/toolspecific/CEASIOMpy/filesPath/wkdirPath'
wkdir_path = cpsf.get_value_or_default(tixi, WKDIR_XPATH, '')
if wkdir_path is '':
wkdir_path = create_new_wkdir()
cpsf.create_branch(tixi, WKDIR_XPATH)
tixi.updateTextElement(WKDIR_XPATH, wkdir_path)
else:
# Check if the directory really exists
if not os.path.isdir(wkdir_path):
wkdir_path = create_new_wkdir()
cpsf.create_branch(tixi, WKDIR_XPATH)
tixi.updateTextElement(WKDIR_XPATH, wkdir_path)
return wkdir_path
def load_surrogate(tixi):
"""Load a surrogate model object from file
Using the pickle module, a surrogate model object is retrieved from a file
provided by the user.
Args:
tixi (Tixi handle): Handle of the current CPACS.
Returns:
sm (object): The surrogate model.
"""
file = cpsf.get_value_or_default(tixi, SMUSE_XPATH + 'modelFile', '')
log.info('Trying to open file' + file)
try:
f = open(file, 'rb')
except:
raise IOError('File could not be opened')
Model = pickle.load(f)
return Model
def test_get_value_or_default():
"""Test the function 'get_value_or_default'"""
tixi = cpsf.open_tixi(CPACS_IN_PATH)
# Check if the correct value (float) is return from an xpath
xpath = '/cpacs/vehicles/aircraft/model/reference/area'
value = cpsf.get_value_or_default(tixi, xpath, 2.0)
assert value == 1.0
# Check if the correct value (text) is return from an xpath
xpath = '/cpacs/vehicles/aircraft/model/name'
value = cpsf.get_value_or_default(tixi, xpath, 'name')
assert value == 'Cpacs2Test'
# Check if boolean are returned from an xpath or default value
xpath = '/cpacs/toolspecific/testUtils/testCPACSFunctions/testBoolTrue'
value = cpsf.get_value_or_default(tixi, xpath, False)
assert value == True
xpath = '/cpacs/toolspecific/testUtils/testCPACSFunctions/testBoolFalse'
value = cpsf.get_value_or_default(tixi, xpath, True)
assert value == False
xpath = '/cpacs/toolspecific/testUtils/testCPACSFunctions/notExistTrue'
value = cpsf.get_value_or_default(tixi, xpath, True)
assert value == True
xpath = '/cpacs/toolspecific/testUtils/testCPACSFunctions/notExistFalse'
value = cpsf.get_value_or_default(tixi, xpath, False)
assert value == False
# Check if a non exitant xpath leads to its creation (integer)
xpath = '/cpacs/vehicles/aircraft/model/reference/newSpan'
value = cpsf.get_value_or_default(tixi, xpath, 100)
assert value == 100
new_elem = tixi.getDoubleElement(xpath)
assert new_elem == 100
# Check if a non exitant xpath leads to its creation (float)
xpath = '/cpacs/vehicles/aircraft/model/reference/newArea'
value = cpsf.get_value_or_default(tixi, xpath, 1000.0)
assert value == 1000.0
new_elem = tixi.getDoubleElement(xpath)
assert new_elem == 1000.0
# Check if a non exitant xpath leads to its creation (text)
xpath = '/cpacs/vehicles/aircraft/model/reference/newRef'
value = cpsf.get_value_or_default(tixi, xpath, 'test')
assert value == 'test'
new_elem = tixi.getTextElement(xpath)
assert new_elem == 'test'
def check_aeromap(tixi):
"""Check if aeromap is not used to train the model.
To avoid re-writting results on the aeromap that was used to train the
model, the uid of the training aeromap is compared to the one that is
given by the user to be computed. Stops the program if they match.
Args:
tixi (Tixi handle): Handle of the current CPACS.
Returns:
None.
"""
am_uid_use = cpsf.get_value_or_default(tixi, SMUSE_XPATH+'aeroMapUID', '')
am_uid_train = cpsf.get_value_or_default(tixi, SMTRAIN_XPATH+'aeroMapUID', '')
if am_uid_train == am_uid_use:
sys.exit('Same aeromap that was used to create the model')
def get_normal_param(tixi, entry, outputs):
"""Add a variable to the optimisation dictionnary.
It is checked if the variable has a user-specified initial value, else it
will assign a default value or the variable will be excluded from the
problem.
Args:
tixi (Tixi3 handle): Handle of the current CPACS file.
entry (object): Current parameter object.
Returns:
None.
"""
value = '-'
xpath = entry.xpath
def_val = entry.default_value
if not def_val:
if entry.var_type in [float, int]:
def_val = 0.0
else:
def_val = '-'
if entry.var_name not in banned_entries:
value = cpsf.get_value_or_default(tixi, xpath, def_val)
if entry.var_type == int:
value = int(value)
if not tls.is_digit(value):
log.info('Not a digital value')
value = '-'
elif entry.var_type == bool:
log.info('Boolean, not implemented yet')
value = '-'
# Ignores values that are not int or float
if value != '-':
value = str(value)
tixi.updateTextElement(xpath, value)
var['init'].append(value)
var['xpath'].append(xpath)
var['Name'].append(entry.var_name)
tls.add_type(entry, outputs, objective, var)
tls.add_bounds(value, var)
log.info('Value : {}'.format(value))
log.info('Added to variable file')
def get_user_inputs(self):
"""Take user inputs from the GUI."""
cpacs_path = mif.get_toolinput_file_path('SMTrain')
tixi = cpsf.open_tixi(cpacs_path)
# Search working directory
self.wkdir = cpsf.get_value_or_default(tixi, OPTWKDIR_XPATH, '')
if self.wkdir == '':
self.wkdir = ceaf.get_wkdir_or_create_new(tixi) + '/SM'
if not os.path.isdir(self.wkdir):
os.mkdir(self.wkdir)
self.type = cpsf.get_value_or_default(tixi,
SMTRAIN_XPATH + 'modelType',
'KRG')
obj = cpsf.get_value_or_default(tixi, SMTRAIN_XPATH + 'objective',
'cl')
self.objectives = re.split(';|,', obj)
self.user_file = cpsf.get_value_or_default(tixi,
SMTRAIN_XPATH + 'trainFile',
'')
if self.user_file == '':
path = cpsf.get_value_or_default(tixi, OPTWKDIR_XPATH, '')
if path != '':
self.user_file = path + '/Variable_history.csv'
self.data_repartition = cpsf.get_value_or_default(
tixi, SMTRAIN_XPATH + 'trainingPercentage', 0.9)
self.show_plots = cpsf.get_value_or_default(
tixi, SMTRAIN_XPATH + 'showPlots', False)
self.aeromap_case = cpsf.get_value_or_default(
tixi, SMTRAIN_XPATH + 'useAeromap', False)
self.aeromap_uid = cpsf.get_value_or_default(
tixi, SMTRAIN_XPATH + 'aeroMapUID', '')
cpsf.close_tixi(tixi, cpacs_path)
def check_aeromap(tixi, aeromap_uid):
""" Check an aeroMap and add missing nodes
Function 'check_aeromap' is similar to 'create_empty_aeromap' but for existing
aeroMap. It will make sur that all node exist and create the missing ones.
Args:
tixi (handles): TIXI Handle of the CPACS file
aeromap_uid (str): UID of the aeroPerformanceMap to create
"""
seconds = time.time()
local_time = time.ctime(seconds)
# If this aeroMap UID did not exist a new one will be create
if not tixi.uIDCheckExists(aeromap_uid):
log.warning(aeromap_uid + ' aeroMap has not been found!')
log.warning('An empty one will be created')
description = 'AeroMap created by CEASIOMpy ' + str(local_time)
create_empty_aeromap(tixi, aeromap_uid, description)
else:
aeromap_xpath = tixi.uIDGetXPath(aeromap_uid)
log.info('The aeroMap to check as been found')
# Check name, description and boundary conditions
cpsf.get_value_or_default(tixi, aeromap_xpath + '/name', aeromap_uid)
description = 'AeroMap checked and utdated by CEASIOMpy ' + str(
local_time)
cpsf.get_value_or_default(tixi, aeromap_xpath + '/description',
description)
aeromap_bc_xpath = aeromap_xpath + '/boundaryConditions'
cpsf.create_branch(tixi, aeromap_bc_xpath)
cpsf.get_value_or_default(tixi, aeromap_bc_xpath + '/atmosphericModel',
'ISA')
# Check AeroPerformanceMap, parameters and coefficients nodes
apm_xpath = aeromap_xpath + '/aeroPerformanceMap'
cpsf.create_branch(tixi, apm_xpath)
#TODO: Replace by a for loop
cpsf.create_branch(tixi, apm_xpath + '/altitude')
cpsf.create_branch(tixi, apm_xpath + '/machNumber')
cpsf.create_branch(tixi, apm_xpath + '/angleOfAttack')
cpsf.create_branch(tixi, apm_xpath + '/angleOfSideslip')
cpsf.create_branch(tixi, apm_xpath + '/cl')
cpsf.create_branch(tixi, apm_xpath + '/cd')
cpsf.create_branch(tixi, apm_xpath + '/cs')
cpsf.create_branch(tixi, apm_xpath + '/cml')
cpsf.create_branch(tixi, apm_xpath + '/cmd')
cpsf.create_branch(tixi, apm_xpath + '/cms')
def add_entries(tixi, module_list):
"""Add the entries of all the modules.
Search all the entries that can be used as problem parameters and fills the
variable dictionary with the valid entries.
Args:
tixi (Tixi3 handler): Tixi handle of the CPACS file.
"""
use_am = cpsf.get_value_or_default(tixi, smu.SMUSE_XPATH+'AeroMapOnly', False)
if 'SMUse' in module_list and use_am:
get_aero_param(tixi)
else:
for mod_name, specs in mif.get_all_module_specs().items():
if specs and mod_name in module_list:
if mod_name == 'SMUse':
get_sm_vars(tixi)
else:
get_module_vars(tixi, specs)
def __init__(self, tabs, tixi, module_name):
"""Tab class
Note:
A tab will only be created if the module actually has
any settings which are to be shown
Args:
tabs (TODO): TODO
tixi (handle): Tixi handle
module_name (str): String of the module name for which a tab is to be created
"""
self.var_dict = {}
self.group_dict = {}
self.module_name = module_name
self.tabs = tabs
self.tixi = tixi
self.tab = tk.Frame(tabs, borderwidth=1)
tabs.add(self.tab, text=module_name)
# Get GUI dict from specs
specs = mif.get_specs_for_module(module_name)
self.gui_dict = specs.cpacs_inout.get_gui_dict()
#canvas has replaced self.tab in the following lines
space_label = tk.Label(self.tab, text=' ')
space_label.grid(column=0, row=0)
row_pos = 1
for key, (name, def_value, dtype, unit, xpath, description, group) in self.gui_dict.items():
# Create a LabelFrame for new groupe
if group:
if not group in self.group_dict:
self.labelframe = tk.LabelFrame(self.tab, text=group)
self.labelframe.grid(column=0, row=row_pos, columnspan=3,sticky= tk.W, padx=5, pady=5)
self.group_dict[group] = self.labelframe
parent = self.group_dict[group]
else: # if not a group, use tab as parent
parent = self.tab
# Name label for variable
if (name is not '__AEROMAP_SELECTION' and name is not '__AEROMAP_CHECHBOX'):
self.name_label = tk.Label(parent, text= name)
self.name_label.grid(column=0, row=row_pos, sticky= tk.W, padx=5, pady=5)
# Type and Value
if dtype is bool:
self.var_dict[key] = tk.BooleanVar()
value = cpsf.get_value_or_default(self.tixi,xpath,def_value)
self.var_dict[key].set(value)
bool_entry = tk.Checkbutton(parent, text='', variable=self.var_dict[key])
bool_entry.grid(column=1, row=row_pos, padx=5, pady=5)
elif dtype is int:
value = cpsf.get_value_or_default(self.tixi, xpath, def_value)
self.var_dict[key] = tk.IntVar()
self.var_dict[key].set(int(value))
value_entry = tk.Entry(parent, bd=2, textvariable=self.var_dict[key])
value_entry.grid(column=1, row=row_pos, padx=5, pady=5)
elif dtype is float:
value = cpsf.get_value_or_default(self.tixi, xpath, def_value)
self.var_dict[key] = tk.DoubleVar()
self.var_dict[key].set(value)
value_entry = tk.Entry(parent, bd=2, textvariable=self.var_dict[key])
value_entry.grid(column=1, row=row_pos, padx=5, pady=5)
elif dtype is 'pathtype':
value = cpsf.get_value_or_default(self.tixi,xpath,def_value)
self.var_dict[key] = tk.StringVar()
self.var_dict[key].set(value)
value_entry = tk.Entry(parent, textvariable=self.var_dict[key])
value_entry.grid(column=1, row=row_pos, padx=5, pady=5)
self.key = key
self.browse_button = tk.Button(parent, text="Browse", command=self._browse_file)
self.browse_button.grid(column=2, row=row_pos, padx=5, pady=5)
elif dtype is list:
if name == '__AEROMAP_SELECTION':
# Get the list of all AeroMaps
self.aeromap_uid_list = apm.get_aeromap_uid_list(self.tixi)
# Try to get the pre-selected AeroMap from the xpath
try:
selected_aeromap = cpsf.get_value(self.tixi,xpath)
selected_aeromap_index = self.aeromap_uid_list.index(selected_aeromap)
except:
selected_aeromap = ''
selected_aeromap_index = 0
self.labelframe = tk.LabelFrame(parent, text='Choose an AeroMap')
self.labelframe.grid(column=0, row=row_pos, columnspan=3, sticky=tk.W, padx=5, pady=5)
# The Combobox is directly use as the varaible
self.var_dict[key] = ttk.Combobox(self.labelframe, values=self.aeromap_uid_list)
self.var_dict[key].current(selected_aeromap_index)
self.var_dict[key].grid(column=1, row=row_pos, padx=5, pady=5)
elif name == '__AEROMAP_CHECHBOX':
# Just to find back the name when data are saved
self.var_dict[key] = None
# __AEROMAP_CHECHBOX is a bit different, data are saved in their own dictionary
self.aeromap_var_dict = {}
# Get the list of all AeroMaps
self.aeromap_uid_list = apm.get_aeromap_uid_list(self.tixi)
self.labelframe = tk.LabelFrame(parent, text='Selecte AeroMap(s)')
self.labelframe.grid(column=0, row=row_pos, columnspan=3, sticky=tk.W, padx=5, pady=5)
# Try to get pre-selected AeroMaps from the xpath
try:
selected_aeromap = cpsf.get_string_vector(self.tixi,xpath)
except:
selected_aeromap = ''
# Create one checkbox for each AeroMap
for aeromap in self.aeromap_uid_list:
self.aeromap_var_dict[aeromap] = tk.BooleanVar()
#if aeromap in selected_aeromap:
# For now, set all to True
self.aeromap_var_dict[aeromap].set(True)
aeromap_entry = tk.Checkbutton(self.labelframe,text=aeromap,variable=self.aeromap_var_dict[aeromap])
aeromap_entry.pack()#side=tk.TOP, anchor='w')
else: # Other kind of list (not aeroMap)
# 'def_value' will be the list of possibilies in this case
# Try to get the pre-selected AeroMap from the xpath
try: # TODO Should be retested...
selected_value = cpsf.get_value(self.tixi,xpath)
selected_value_index = def_value.index(selected_value)
except:
selected_value = ''
selected_value_index = 0
# The Combobox is directly use as the varaible
self.var_dict[key] = ttk.Combobox(parent, values=def_value)
self.var_dict[key].current(selected_value_index)
self.var_dict[key].grid(column=1, row=row_pos, padx=5, pady=5)
else:
value = cpsf.get_value_or_default(self.tixi,xpath,def_value)
self.var_dict[key] = tk.StringVar()
self.var_dict[key].set(value)
value_entry = tk.Entry(parent, textvariable=self.var_dict[key])
value_entry.grid(column=1, row=row_pos, padx=5, pady=5)
# Units
if unit and unit != '1':
unit_label = tk.Label(parent, text=pretty_unit(unit))
unit_label.grid(column=2, row=row_pos, padx=5, pady=5)
row_pos += 1
def create_config(cpacs_path, cpacs_out_path, su2_mesh_path,
config_output_path):
""" 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. A new configuration file will be saved in
/ToolOutput/ToolOutput.cfg
Source:
* SU2 configuration file template
https://github.com/su2code/SU2/blob/master/config_template.cfg
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str): Path to CPACS output file
su2_mesh_path (str): Path to SU2 mesh
config_output_path (str): Path to the output configuration file
"""
DEFAULT_CONFIG_PATH = MODULE_DIR + '/files/DefaultConfig_v6.cfg'
# Get value from CPACS
tixi = open_tixi(cpacs_path)
su2_xpath = '/cpacs/toolspecific/CEASIOMpy/aerodynamics/su2'
# Reference values
ref_xpath = '/cpacs/vehicles/aircraft/model/reference'
ref_len = get_value(tixi, ref_xpath + '/length')
ref_area = get_value(tixi, ref_xpath + '/area')
# Fixed CL parameters
fixed_cl_xpath = su2_xpath + '/fixedCL'
target_cl_xpath = su2_xpath + '/targetCL'
tixi, fixed_cl = get_value_or_default(tixi, fixed_cl_xpath, 'NO')
tixi, target_cl = get_value_or_default(tixi, target_cl_xpath, 1.0)
if fixed_cl == 'NO':
# Get value from the aeroMap (1 point)
active_aeroMap_xpath = su2_xpath + '/aeroMapUID'
aeroMap_uid = get_value(tixi, active_aeroMap_xpath)
aeroMap_path = tixi.uIDGetXPath(aeroMap_uid)
apm_path = aeroMap_path + '/aeroPerformanceMap'
#State = get_states(tixi,apm_path)
#alt = State.alt_list
alt = get_value(tixi, apm_path + '/altitude')
mach = get_value(tixi, apm_path + '/machNumber')
aoa = get_value(tixi, apm_path + '/angleOfAttack')
aos = get_value(tixi, apm_path + '/angleOfSideslip')
else:
range_xpath = '/cpacs/toolspecific/CEASIOMpy/ranges'
cruise_alt_xpath = range_xpath + '/cruiseAltitude'
cruise_mach_xpath = range_xpath + '/cruiseMach'
# value corresponding to fix CL calulation
aoa = 0.0 # Will not be used
aos = 0.0
tixi, mach = get_value_or_default(tixi, cruise_mach_xpath, 0.78)
tixi, alt = get_value_or_default(tixi, cruise_alt_xpath, 12000)
Atm = get_atmosphere(alt)
pressure = Atm.pres
temp = Atm.temp
# Settings
settings_xpath = '/cpacs/toolspecific/CEASIOMpy/aerodynamics/su2/settings'
max_iter_xpath = settings_xpath + '/maxIter'
cfl_nb_xpath = settings_xpath + '/cflNumber'
mg_level_xpath = settings_xpath + '/multigridLevel'
tixi, max_iter = get_value_or_default(tixi, max_iter_xpath, 200)
tixi, cfl_nb = get_value_or_default(tixi, cfl_nb_xpath, 1.0)
tixi, mg_level = get_value_or_default(tixi, mg_level_xpath, 3)
# Mesh Marker
bc_wall_xpath = '/cpacs/toolspecific/CEASIOMpy/aerodynamics/su2/boundaryConditions/wall'
bc_wall_list = get_mesh_marker(su2_mesh_path)
tixi = create_branch(tixi, bc_wall_xpath)
bc_wall_str = ';'.join(bc_wall_list)
tixi.updateTextElement(bc_wall_xpath, bc_wall_str)
close_tixi(tixi, cpacs_out_path)
# Open default configuration file
try:
config_file_object = open(DEFAULT_CONFIG_PATH, '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
config_dict_modif = config_dict
# General parmeters
config_dict_modif['MESH_FILENAME'] = su2_mesh_path
config_dict_modif['REF_LENGTH'] = ref_len
config_dict_modif['REF_AREA'] = ref_area
# Settings
config_dict_modif['EXT_ITER'] = int(max_iter)
config_dict_modif['CFL_NUMBER'] = cfl_nb
config_dict_modif['MGLEVEL'] = int(mg_level)
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)
config_dict_modif['FIXED_CL_MODE'] = fixed_cl
config_dict_modif['TARGET_CL'] = target_cl
config_dict_modif['DCL_DALPHA'] = '0.1'
config_dict_modif['UPDATE_ALPHA'] = '8'
config_dict_modif['ITER_DCL_DALPHA'] = '80'
# Mesh Marker
bc_wall_str = '(' + ','.join(bc_wall_list) + ')'
config_dict_modif['MARKER_EULER'] = bc_wall_str
config_dict_modif['MARKER_FAR'] = ' (Farfield)'
config_dict_modif['MARKER_SYM'] = ' (0)'
config_dict_modif['MARKER_PLOTTING'] = bc_wall_str
config_dict_modif['MARKER_MONITORING'] = bc_wall_str
config_dict_modif['MARKER_MOVING'] = bc_wall_str
# 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_output_path, 'w')
config_file_new.writelines(config_file_lines)
config_file_new.close()
log.info('ToolOutput.cfg has been written in /ToolOutput.')
def run_mesh_deformation(tixi, wkdir):
"""Function to run all the configuration files with SU2_DEF.
Function 'run_mesh_deformation' will check in all config file directory and run
SU2_DEF for each config file in order.
Args:
tixi (handles): TIXI Handle
wkdir (str): Path to the working directory
"""
log.info('All mesh deromation will be preformed.')
mesh_dir = os.path.join(wkdir, 'MESH')
if not os.path.exists(mesh_dir):
raise OSError('The MESH directory : ' + mesh_dir + 'does not exit!')
os.chdir(mesh_dir)
su2_def_mesh_list = []
ted_dir_list = [dir for dir in os.listdir(mesh_dir) if '_TED_' in dir]
# Get number of proc to use
nb_proc = cpsf.get_value_or_default(tixi, SU2_XPATH + '/settings/nbProc',
1)
# Iterate in all TED directory
for dir in sorted(ted_dir_list):
ted_dir = os.path.join(mesh_dir, dir)
os.chdir(ted_dir)
cfg_file_list = [
file for file in os.listdir(ted_dir) if 'Config' in file
]
# Run all the config file in the directory with SU2_DEF, in alphabetical
# order to respect the order of execution (DEF,ROT_,ROT_sym)
for cfg_file in sorted(cfg_file_list):
if os.path.isfile(cfg_file):
su2f.run_soft('SU2_DEF', cfg_file, ted_dir, nb_proc)
else:
raise ValueError("Not correct configuration file to run!")
tmp_su2_mesh_list = [
file for file in os.listdir(ted_dir) if '.su2' in file
]
# Copy in the completly deform mesh in the MESH directory
for su2_mesh in tmp_su2_mesh_list:
if not su2_mesh.startswith('_'):
shutil.copyfile(su2_mesh, os.path.join('..', su2_mesh))
log.info(su2_mesh + ' mesh has been copied in the MESH dir.')
su2_def_mesh_list.append(su2_mesh)
# Remove all SU2 mesh from the config folder (to save space)
os.remove(su2_mesh)
log.info(su2_mesh + ' mesh has been deleted from the temp mesh.')
# Add the list of available SU2 deformed mesh in the CPACS file
su2_def_mesh_xpath = SU2_XPATH + '/availableDeformedMesh'
cpsf.add_string_vector(tixi, su2_def_mesh_xpath, su2_def_mesh_list)
def generate_su2_config(cpacs_path, cpacs_out_path, wkdir):
"""Function to create SU2 confif file.
Function 'generate_su2_config' reads data in the CPACS file and generate
configuration files for one or multible flight conditions (alt,mach,aoa,aos)
Source:
* SU2 config template: https://github.com/su2code/SU2/blob/master/config_template.cfg
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str):Path to CPACS output file
wkdir (str): Path to the working directory
"""
# Get value from CPACS
tixi = cpsf.open_tixi(cpacs_path)
tigl = cpsf.open_tigl(tixi)
# Get SU2 mesh path
su2_mesh_xpath = '/cpacs/toolspecific/CEASIOMpy/filesPath/su2Mesh'
su2_mesh_path = cpsf.get_value(tixi,su2_mesh_xpath)
# Get reference values
ref_xpath = '/cpacs/vehicles/aircraft/model/reference'
ref_len = cpsf.get_value(tixi,ref_xpath + '/length')
ref_area = cpsf.get_value(tixi,ref_xpath + '/area')
ref_ori_moment_x = cpsf.get_value_or_default(tixi,ref_xpath+'/point/x',0.0)
ref_ori_moment_y = cpsf.get_value_or_default(tixi,ref_xpath+'/point/y',0.0)
ref_ori_moment_z = cpsf.get_value_or_default(tixi,ref_xpath+'/point/z',0.0)
# Get SU2 settings
settings_xpath = SU2_XPATH + '/settings'
max_iter_xpath = settings_xpath + '/maxIter'
max_iter = cpsf.get_value_or_default(tixi, max_iter_xpath,200)
cfl_nb_xpath = settings_xpath + '/cflNumber'
cfl_nb = cpsf.get_value_or_default(tixi, cfl_nb_xpath,1.0)
mg_level_xpath = settings_xpath + '/multigridLevel'
mg_level = cpsf.get_value_or_default(tixi, mg_level_xpath,3)
# Mesh Marker
bc_wall_xpath = SU2_XPATH + '/boundaryConditions/wall'
bc_wall_list = su2f.get_mesh_marker(su2_mesh_path)
cpsf.create_branch(tixi, bc_wall_xpath)
bc_wall_str = ';'.join(bc_wall_list)
tixi.updateTextElement(bc_wall_xpath,bc_wall_str)
# Fixed CL parameters
fixed_cl_xpath = SU2_XPATH + '/fixedCL'
fixed_cl = cpsf.get_value_or_default(tixi, fixed_cl_xpath,'NO')
target_cl_xpath = SU2_XPATH + '/targetCL'
target_cl = cpsf.get_value_or_default(tixi, target_cl_xpath,1.0)
if fixed_cl == 'NO':
active_aeroMap_xpath = SU2_XPATH + '/aeroMapUID'
aeromap_uid = cpsf.get_value(tixi,active_aeroMap_xpath)
log.info('Configuration file for ""' + aeromap_uid + '"" calculation will be created.')
# Get parameters of the aeroMap (alt,ma,aoa,aos)
Param = apmf.get_aeromap(tixi,aeromap_uid)
param_count = Param.get_count()
if param_count >= 1:
alt_list = Param.alt
mach_list = Param.mach
aoa_list = Param.aoa
aos_list = Param.aos
else:
raise ValueError('No parametre have been found in the aeroMap!')
else: # if fixed_cl == 'YES':
log.info('Configuration file for fixed CL calculation will be created.')
range_xpath = '/cpacs/toolspecific/CEASIOMpy/ranges'
# Parameters fixed CL calulation
param_count = 1
# These parameters will not be used
aoa_list = [0.0]
aos_list = [0.0]
cruise_mach_xpath= range_xpath + '/cruiseMach'
mach = cpsf.get_value_or_default(tixi,cruise_mach_xpath,0.78)
mach_list = [mach]
cruise_alt_xpath= range_xpath + '/cruiseAltitude'
alt = cpsf.get_value_or_default(tixi,cruise_alt_xpath,12000)
alt_list = [alt]
aeromap_uid = 'aeroMap_fixedCL_SU2'
description = 'AeroMap created for SU2 fixed CL value of: ' + str(target_cl)
apmf.create_empty_aeromap(tixi, aeromap_uid, description)
Parameters = apmf.AeroCoefficient()
Parameters.alt = alt_list
Parameters.mach = mach_list
Parameters.aoa = aoa_list
Parameters.aos = aos_list
apmf.save_parameters(tixi,aeromap_uid,Parameters)
tixi.updateTextElement(SU2_XPATH+ '/aeroMapUID',aeromap_uid)
# Get and modify the default configuration file
cfg = su2f.read_config(DEFAULT_CONFIG_PATH)
# General parmeters
cfg['REF_LENGTH'] = ref_len
cfg['REF_AREA'] = ref_area
cfg['REF_ORIGIN_MOMENT_X'] = ref_ori_moment_x
cfg['REF_ORIGIN_MOMENT_Y'] = ref_ori_moment_y
cfg['REF_ORIGIN_MOMENT_Z'] = ref_ori_moment_z
# Settings
cfg['INNER_ITER'] = int(max_iter)
cfg['CFL_NUMBER'] = cfl_nb
cfg['MGLEVEL'] = int(mg_level)
# Fixed CL mode (AOA will not be taken into account)
cfg['FIXED_CL_MODE'] = fixed_cl
cfg['TARGET_CL'] = target_cl
cfg['DCL_DALPHA'] = '0.1'
cfg['UPDATE_AOA_ITER_LIMIT'] = '50'
cfg['ITER_DCL_DALPHA'] = '80'
# TODO: correct value for the 3 previous parameters ??
# Mesh Marker
bc_wall_str = '(' + ','.join(bc_wall_list) + ')'
cfg['MARKER_EULER'] = bc_wall_str
cfg['MARKER_FAR'] = ' (Farfield)' # TODO: maybe make that a variable
cfg['MARKER_SYM'] = ' (0)' # TODO: maybe make that a variable?
cfg['MARKER_PLOTTING'] = bc_wall_str
cfg['MARKER_MONITORING'] = bc_wall_str
cfg['MARKER_MOVING'] = '( NONE )' # TODO: when do we need to define MARKER_MOVING?
cfg['DV_MARKER'] = bc_wall_str
# Parameters which will vary for the different cases (alt,mach,aoa,aos)
for case_nb in range(param_count):
cfg['MESH_FILENAME'] = su2_mesh_path
alt = alt_list[case_nb]
mach = mach_list[case_nb]
aoa = aoa_list[case_nb]
aos = aos_list[case_nb]
Atm = get_atmosphere(alt)
pressure = Atm.pres
temp = Atm.temp
cfg['MACH_NUMBER'] = mach
cfg['AOA'] = aoa
cfg['SIDESLIP_ANGLE'] = aos
cfg['FREESTREAM_PRESSURE'] = pressure
cfg['FREESTREAM_TEMPERATURE'] = temp
cfg['ROTATION_RATE'] = '0.0 0.0 0.0'
config_file_name = 'ConfigCFD.cfg'
case_dir_name = ''.join(['Case',str(case_nb).zfill(2),
'_alt',str(alt),
'_mach',str(round(mach,2)),
'_aoa',str(round(aoa,1)),
'_aos',str(round(aos,1))])
case_dir_path = os.path.join(wkdir,case_dir_name)
if not os.path.isdir(case_dir_path):
os.mkdir(case_dir_path)
config_output_path = os.path.join(wkdir,case_dir_name,config_file_name)
su2f.write_config(config_output_path,cfg)
# Damping derivatives
damping_der_xpath = SU2_XPATH + '/options/clalculateDampingDerivatives'
damping_der = cpsf.get_value_or_default(tixi,damping_der_xpath,False)
if damping_der:
rotation_rate_xpath = SU2_XPATH + '/options/rotationRate'
rotation_rate = cpsf.get_value_or_default(tixi,rotation_rate_xpath,1.0)
cfg['GRID_MOVEMENT'] = 'ROTATING_FRAME'
cfg['ROTATION_RATE'] = str(rotation_rate) + ' 0.0 0.0'
os.mkdir(os.path.join(wkdir,case_dir_name+'_dp'))
config_output_path = os.path.join(wkdir,case_dir_name+'_dp',config_file_name)
su2f.write_config(config_output_path,cfg)
cfg['ROTATION_RATE'] = '0.0 ' + str(rotation_rate) + ' 0.0'
os.mkdir(os.path.join(wkdir,case_dir_name+'_dq'))
config_output_path = os.path.join(wkdir,case_dir_name+'_dq',config_file_name)
su2f.write_config(config_output_path,cfg)
cfg['ROTATION_RATE'] = '0.0 0.0 ' + str(rotation_rate)
os.mkdir(os.path.join(wkdir,case_dir_name+'_dr'))
config_output_path = os.path.join(wkdir,case_dir_name+'_dr',config_file_name)
su2f.write_config(config_output_path,cfg)
log.info('Damping derivatives cases directory has been created.')
# Control surfaces deflections
control_surf_xpath = SU2_XPATH + '/options/clalculateCotrolSurfacesDeflections'
control_surf = cpsf.get_value_or_default(tixi,control_surf_xpath,False)
if control_surf:
# Get deformed mesh list
su2_def_mesh_xpath = SU2_XPATH + '/availableDeformedMesh'
if tixi.checkElement(su2_def_mesh_xpath):
su2_def_mesh_list = cpsf.get_string_vector(tixi,su2_def_mesh_xpath)
else:
log.warning('No SU2 deformed mesh has been found!')
su2_def_mesh_list = []
for su2_def_mesh in su2_def_mesh_list:
mesh_path = os.path.join(wkdir,'MESH',su2_def_mesh)
config_dir_path = os.path.join(wkdir,case_dir_name+'_'+su2_def_mesh.split('.')[0])
os.mkdir(config_dir_path)
cfg['MESH_FILENAME'] = mesh_path
config_file_name = 'ConfigCFD.cfg'
config_output_path = os.path.join(wkdir,config_dir_path,config_file_name)
su2f.write_config(config_output_path,cfg)
# TODO: change that, but if it is save in tooloutput it will be erease by results...
cpsf.close_tixi(tixi,cpacs_path)
def main():
log.info("Running PyTornado...")
# ===== CPACS inout and output paths =====
MODULE_DIR = os.path.dirname(os.path.abspath(__file__))
cpacs_in_path = mi.get_toolinput_file_path(MODULE_NAME)
cpacs_out_path = mi.get_tooloutput_file_path(MODULE_NAME)
# ===== Delete old working directories =====
settings_from_CPACS = get_pytornado_settings_from_CPACS(cpacs_in_path)
if settings_from_CPACS is not None:
if settings_from_CPACS.get('deleteOldWKDIRs', False):
wkdirs = glob(os.path.join(DIR_MODULE, 'wkdir_*'))
for wkdir in wkdirs:
shutil.rmtree(wkdir, ignore_errors=True)
# ===== Paths =====
dir_pyt_wkdir = os.path.join(DIR_MODULE, 'wkdir_temp')
dir_pyt_aircraft = os.path.join(dir_pyt_wkdir, 'aircraft')
dir_pyt_settings = os.path.join(dir_pyt_wkdir, 'settings')
dir_pyt_results = os.path.join(dir_pyt_wkdir, '_results')
file_pyt_aircraft = os.path.join(dir_pyt_aircraft, 'ToolInput.xml')
file_pyt_settings = os.path.join(dir_pyt_settings, 'cpacs_run.json')
# ===== Make directories =====
Path(dir_pyt_wkdir).mkdir(parents=True, exist_ok=True)
Path(dir_pyt_aircraft).mkdir(parents=True, exist_ok=True)
Path(dir_pyt_settings).mkdir(parents=True, exist_ok=True)
Path(dir_pyt_results).mkdir(parents=True, exist_ok=True)
# ===== Setup =====
shutil.copy(src=cpacs_in_path, dst=file_pyt_aircraft)
mi.check_cpacs_input_requirements(cpacs_in_path)
# ===== Get PyTornado settings =====
cpacs_settings = get_pytornado_settings(cpacs_in_path)
with open(file_pyt_settings, "w") as fp:
dump_pretty_json(cpacs_settings, fp)
# ===== PyTornado analysis =====
pytornado = import_pytornado('pytornado.stdfun.run')
#pytornado.standard_run(args=pytornado.StdRunArgs(run=file_pyt_settings, verbose=True))
results = pytornado.standard_run(
args=pytornado.StdRunArgs(run=file_pyt_settings, verbose=True))
# ===== Extract load =====
tixi = cpsf.open_tixi(cpacs_in_path)
extract_loads_xpath = '/cpacs/toolspecific/pytornado/save_results/extractLoads'
extract_loads = cpsf.get_value_or_default(tixi, extract_loads_xpath, False)
if extract_loads:
_get_load_fields(results, dir_pyt_results)
# ===== Clean up =====
shutil.copy(src=file_pyt_aircraft, dst=cpacs_out_path)
wkdir = ceaf.get_wkdir_or_create_new(tixi)
dst_pyt_wkdir = os.path.join(
wkdir, 'CFD', 'PyTornado',
f"wkdir_{datetime.strftime(datetime.now(), '%F_%H%M%S')}")
shutil.copytree(src=dir_pyt_wkdir, dst=dst_pyt_wkdir)
shutil.rmtree(dir_pyt_wkdir, ignore_errors=True)
log.info("PyTornado analysis completed")
def dynamic_stability_analysis(cpacs_path, cpacs_out_path):
"""Function to analyse a full Aeromap
Function 'dynamic_stability_analysis' analyses longitudinal dynamic
stability and directionnal dynamic.
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str):Path to CPACS output file
plot (boolean): Choise to plot graph or not
Returns: (#TODO put that in the documentation)
* Adrvertisements certifying if the aircraft is stable or Not
* In case of longitudinal dynamic UNstability or unvalid test on data:
- Plot cms VS aoa for constant Alt, Mach and different aos
- Plot cms VS aoa for const alt and aos and different mach
- plot cms VS aoa for constant mach, AOS and different altitudes
* In case of directionnal dynamic UNstability or unvalid test on data:
- Pcot cml VS aos for constant Alt, Mach and different aoa
- Plot cml VS aos for const alt and aoa and different mach
- plot cml VS aos for constant mach, AOA and different altitudes
* Plot one graph of cruising angles of attack for different mach and altitudes
Make the following tests:
* Check the CPACS path
* For longitudinal dynamic stability analysis:
- If there is more than one angle of attack for a given altitude, mach, aos
- If cml values are only zeros for a given altitude, mach, aos
- If there one aoa value which is repeated for a given altitude, mach, aos
* For directionnal dynamic stability analysis:
- If there is more than one angle of sideslip for a given altitude, mach, aoa
- If cms values are only zeros for a given altitude, mach, aoa
- If there one aos value which is repeated for a given altitude, mach, aoa
"""
# XPATH definition
aeromap_uid_xpath = DYNAMIC_ANALYSIS_XPATH + '/aeroMapUid'
aircraft_class_xpath = DYNAMIC_ANALYSIS_XPATH + '/class' # Classes 1 2 3 4 small, heavy ...
aircraft_cathegory_xpath = DYNAMIC_ANALYSIS_XPATH + '/category' # flight phase A B C
selected_mass_config_xpath = DYNAMIC_ANALYSIS_XPATH + '/massConfiguration'
longi_analysis_xpath = DYNAMIC_ANALYSIS_XPATH + '/instabilityModes/longitudinal'
direc_analysis_xpath = DYNAMIC_ANALYSIS_XPATH + '/instabilityModes/lateralDirectional'
show_plot_xpath = DYNAMIC_ANALYSIS_XPATH + '/showPlots'
save_plot_xpath = DYNAMIC_ANALYSIS_XPATH + '/savePlots'
model_xpath = '/cpacs/vehicles/aircraft/model'
ref_area_xpath = model_xpath + '/reference/area'
ref_length_xpath = model_xpath + '/reference/length'
flight_qualities_case_xpath = model_xpath + '/analyses/flyingQualities/fqCase'
masses_location_xpath = model_xpath + '/analyses/massBreakdown/designMasses'
# aircraft_class_xpath = flight_qualities_case_xpath + '/class' # Classes 1 2 3 4 small, heavy ...
# aircraft_cathegory_xpath = flight_qualities_case_xpath + '/cathegory' # flight phase A B C
# Ask user flight path angles : gamma_e
thrust_available = None # Thrust data are not available
flight_path_angle_deg = [
0
] # [-15,-10,-5,0,5,10,15] # The user should have the choice to select them !!!!!!!!!!!!!!!!!!!!
flight_path_angle = [
angle * (np.pi / 180) for angle in flight_path_angle_deg
] # flight_path_angle in [rad]
tixi = cpsf.open_tixi(cpacs_path)
# Get aeromap uid
aeromap_uid = cpsf.get_value(tixi, aeromap_uid_xpath)
log.info('The following aeroMap will be analysed: ' + aeromap_uid)
# Mass configuration: (Maximum landing mass, Maximum ramp mass (the maximum weight authorised for the ground handling), Take off mass, Zero Fuel mass)
mass_config = cpsf.get_value(tixi, selected_mass_config_xpath)
log.info('The aircraft mass configuration used for analysis is: ' +
mass_config)
# Analyses to do : longitudinal / Lateral-Directional
longitudinal_analysis = cpsf.get_value(tixi, longi_analysis_xpath)
lateral_directional_analysis = False
# lateral_directional_analysis = cpsf.get_value(tixi, direc_analysis_xpath )
# Plots configuration with Setting GUI
show_plots = cpsf.get_value_or_default(tixi, show_plot_xpath, False)
save_plots = cpsf.get_value_or_default(tixi, save_plot_xpath, False)
mass_config_xpath = masses_location_xpath + '/' + mass_config
if tixi.checkElement(mass_config_xpath):
mass_xpath = mass_config_xpath + '/mass'
I_xx_xpath = mass_config_xpath + '/massInertia/Jxx'
I_yy_xpath = mass_config_xpath + '/massInertia/Jyy'
I_zz_xpath = mass_config_xpath + '/massInertia/Jzz'
I_xz_xpath = mass_config_xpath + '/massInertia/Jxz'
else:
raise ValueError(
'The mass configuration : {} is not defined in the CPACS file !!!'.
format(mass_config))
s = cpsf.get_value(
tixi, ref_area_xpath
) # Wing area : s for non-dimonsionalisation of aero data.
mac = cpsf.get_value(
tixi, ref_length_xpath
) # ref length for non dimensionalisation, Mean aerodynamic chord: mac,
# TODO: check that
b = s / mac
# TODO: find a way to get that
xh = 10 # distance Aircaft cg-ac_horizontal-tail-plane.
m = cpsf.get_value(tixi, mass_xpath) # aircraft mass dimensional
I_xx = cpsf.get_value(tixi, I_xx_xpath) # X inertia dimensional
I_yy = cpsf.get_value(tixi, I_yy_xpath) # Y inertia dimensional
I_zz = cpsf.get_value(tixi, I_zz_xpath) # Z inertia dimensional
I_xz = cpsf.get_value(tixi, I_xz_xpath) # XZ inertia dimensional
aircraft_class = cpsf.get_value(
tixi, aircraft_class_xpath) # aircraft class 1 2 3 4
flight_phase = cpsf.get_string_vector(
tixi, aircraft_cathegory_xpath)[0] # Flight phase A B C
Coeffs = apmf.get_aeromap(
tixi, aeromap_uid
) # Warning: Empty uID found! This might lead to unknown errors!
alt_list = Coeffs.alt
mach_list = Coeffs.mach
aoa_list = Coeffs.aoa
aos_list = Coeffs.aos
cl_list = Coeffs.cl
cd_list = Coeffs.cd
cs_list = Coeffs.cs
cml_list = Coeffs.cml
cms_list = Coeffs.cms
cmd_list = Coeffs.cmd
dcsdrstar_list = Coeffs.dcsdrstar
dcsdpstar_list = Coeffs.dcsdpstar
dcldqstar_list = Coeffs.dcldqstar
dcmsdqstar_list = Coeffs.dcmsdqstar
dcddqstar_list = Coeffs.dcddqstar
dcmldqstar_list = Coeffs.dcmldqstar
dcmddpstar_list = Coeffs.dcmddpstar
dcmldpstar_list = Coeffs.dcmldpstar
dcmldrstar_list = Coeffs.dcmldrstar
dcmddrstar_list = Coeffs.dcmddrstar
# All different vallues with only one occurence
alt_unic = get_unic(alt_list)
mach_unic = get_unic(mach_list)
aos_unic = get_unic(aos_list)
aoa_unic = get_unic(aoa_list)
# TODO get from CPACS
incrementalMap = False
for alt in alt_unic:
idx_alt = [i for i in range(len(alt_list)) if alt_list[i] == alt]
Atm = get_atmosphere(alt)
g = Atm.grav
a = Atm.sos
rho = Atm.dens
for mach in mach_unic:
print('Mach : ', mach)
idx_mach = [
i for i in range(len(mach_list)) if mach_list[i] == mach
]
u0, m_adim, i_xx, i_yy, i_zz, i_xz = adimensionalise(
a, mach, rho, s, b, mac, m, I_xx, I_yy, I_zz,
I_xz) # u0 is V0 in Cook
# Hyp: trim condition when: ( beta = 0 and dCm/dalpha = 0) OR ( aos=0 and dcms/daoa = 0 )
if 0 not in aos_unic:
log.warning(
'The aircraft can not be trimmed (requiring symetric flight condition) as beta never equal to 0 for Alt = {}, mach = {}'
.format(alt, mach))
else:
idx_aos = [i for i in range(len(aos_list)) if aos_list[i] == 0]
find_index = get_index(idx_alt, idx_mach, idx_aos)
# If there is only one data at (alt, mach, aos) then dont make stability anlysis
if len(find_index) <= 1:
log.warning(
'Not enough data at : Alt = {} , mach = {}, aos = 0, can not perform stability analysis'
.format(alt, mach))
# If there is at leat 2 data at (alt, mach, aos) then, make stability anlysis
else:
# Calculate trim conditions
cms = []
aoa = []
cl = []
for index in find_index:
cms.append(cms_list[index])
aoa.append(aoa_list[index] * np.pi / 180)
cl.append(cl_list[index])
cl_required = (m * g) / (0.5 * rho * u0**2 * s)
(trim_aoa, idx_trim_before, idx_trim_after,
ratio) = trim_condition(
alt,
mach,
cl_required,
cl,
aoa,
)
if trim_aoa:
trim_aoa_deg = trim_aoa * 180 / np.pi
trim_cms = interpolation(cms, idx_trim_before,
idx_trim_after, ratio)
pitch_moment_derivative_rad = (
cms[idx_trim_after] - cms[idx_trim_before]) / (
aoa[idx_trim_after] - aoa[idx_trim_before])
pitch_moment_derivative_deg = pitch_moment_derivative_rad / (
180 / np.pi)
# Find incremental cms
if incrementalMap:
for index, mach_number in enumerate(mach_unic, 0):
if mach_number == mach:
mach_index = index
dcms_before = dcms_list[mach_index * len(aoa_unic)
+ idx_trim_before]
dcms_after = dcms_list[mach_index * len(aoa_unic) +
idx_trim_after]
dcms = dcms_before + ratio * (dcms_after -
dcms_before)
trim_elevator = -trim_cms / dcms # Trim elevator deflection in [°]
else:
dcms = None
trim_elevator = None
else:
trim_aoa_deg = None
trim_cms = None
pitch_moment_derivative_deg = None
dcms = None
trim_elevator = None
# Longitudinal dynamic stability,
# Stability analysis
if longitudinal_analysis and trim_cms:
cl = []
cd = []
dcldqstar = []
dcddqstar = []
dcmsdqstar = []
for index in find_index:
cl.append(cl_list[index])
cd.append(cd_list[index])
dcldqstar.append(dcldqstar_list[index])
dcddqstar.append(dcddqstar_list[index])
dcmsdqstar.append(dcmsdqstar_list[index])
# Trimm variables
cd0 = interpolation(cd, idx_trim_before,
idx_trim_after,
ratio) # Dragg coeff at trim
cl0 = interpolation(cl, idx_trim_before,
idx_trim_after,
ratio) # Lift coeff at trim
cl_dividedby_cd_trim = cl0 / cd0 # cl/cd ratio at trim, at trim aoa
# Lift & drag coefficient derivative with respect to AOA at trimm
cl_alpha0 = (cl[idx_trim_after] - cl[idx_trim_before]
) / (aoa[idx_trim_after] -
aoa[idx_trim_before])
cd_alpha0 = (cd[idx_trim_after] - cd[idx_trim_before]
) / (aoa[idx_trim_after] -
aoa[idx_trim_before])
print(idx_trim_before, idx_trim_after, ratio)
dcddqstar0 = interpolation(dcddqstar, idx_trim_before,
idx_trim_after,
ratio) # x_q
dcldqstar0 = interpolation(dcldqstar, idx_trim_before,
idx_trim_after,
ratio) # z_q
dcmsdqstar0 = interpolation(dcmsdqstar,
idx_trim_before,
idx_trim_after,
ratio) # m_q
cm_alpha0 = trim_cms
# Speed derivatives if there is at least 2 distinct mach values
if len(mach_unic) >= 2:
dcddm0 = speed_derivative_at_trim(
cd_list, mach, mach_list, mach_unic, idx_alt,
aoa_list, aos_list, idx_trim_before,
idx_trim_after, ratio)
if dcddm0 == None:
dcddm0 = 0
log.warning(
'Not enough data to determine dcddm or (Cd_mach) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: dcddm = 0'
.format(alt, mach, round(trim_aoa_deg, 2)))
dcldm0 = speed_derivative_at_trim(
cl_list, mach, mach_list, mach_unic, idx_alt,
aoa_list, aos_list, idx_trim_before,
idx_trim_after, ratio)
if dcldm0 == None:
dcldm0 = 0
log.warning(
'Not enough data to determine dcldm (Cl_mach) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: dcldm = 0'
.format(alt, mach, round(trim_aoa_deg, 2)))
else:
dcddm0 = 0
dcldm0 = 0
log.warning(
'Not enough data to determine dcddm (Cd_mach) and dcldm (Cl_mach) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: dcddm = dcldm = 0'
.format(alt, mach, round(trim_aoa_deg, 2)))
# Controls Derivatives to be found in the CPACS (To be calculated)
dcddeta0 = 0
dcldeta0 = 0
dcmsdeta0 = 0
dcddtau0 = 0
dcldtau0 = 0
dcmsdtau0 = 0
# Traduction Ceasiom -> Theory
Ue = u0 * np.cos(
trim_aoa
) # *np.cos(aos) as aos = 0 at trim, cos(aos)=1
We = u0 * np.sin(
trim_aoa
) # *np.cos(aos) as aos = 0 at trim, cos(aos)=1
# Dimentionless State Space variables,
# In generalised body axes coordinates ,
# simplifications: Ue=V0, We=0, sin(Theta_e)=0 cos(Theta_e)=0
if thrust_available: # If power data
X_u = -(2 * cd0 + mach * dcddm0) + 1 / (
0.5 * rho * s * a ^ 2
) * dtaudm0 # dtaudm dimensional Thrust derivative at trim conditions, P340 Michael V. Cook
else: # Glider Mode
X_u = -(2 * cd0 + mach * dcddm0)
Z_u = -(2 * cl0 + mach * dcldm0)
M_u = 0 # Negligible for subsonic conditions or better with P289 Yechout (cm_u+2cm0)
X_w = (cl0 - cd_alpha0)
Z_w = -(cl_alpha0 + cd0)
M_w = cm_alpha0
X_q = dcddqstar0 # Normally almost = 0
Z_q = dcldqstar0
M_q = -dcmsdqstar0
X_dotw = 0 # Negligible
Z_dotw = 1 / 3 * M_q / u0 / (
xh / mac
) # Thumb rule : M_alpha_dot = 1/3 Mq , ( not true for 747 :caughey P83,M_alpha_dot = 1/6Mq )
M_dotw = 1 / 3 * M_q / u0 # Thumb rule : M_alpha_dot = 1/3 Mq
# Controls:
X_eta = dcddeta0 # To be found from the cpacs file, and defined by the user!
Z_eta = dcldeta0 # To be found from the cpacs file, and defined by the user!
M_eta = dcmsdeta0 # To be found from the cpacs file, and defined by the user!
X_tau = dcddtau0 # To be found from the cpacs file, and defined by the user!
Z_tau = dcldtau0 # To be found from the cpacs file, and defined by the user!
M_tau = dcmsdtau0 # To be found from the cpacs file, and defined by the user!
# ----------------- Traduction Ceasiom -> Theory END -----------------------------------
# Sign check (Ref: Thomas Yechout Book, P304)
check_sign_longi(cd_alpha0, M_w, cl_alpha0, M_dotw,
Z_dotw, M_q, Z_q, M_eta, Z_eta)
# Laterl-Directional
if lateral_directional_analysis:
cml = [] # N
cmd = [] # L
aos = []
aoa = [] # For Ue We
cs = [] # For y_v
dcsdpstar = [] # y_p
dcmddpstar = [] # l_p
dcmldpstar = [] # n_p
dcsdrstar = [] # y_r
dcmldrstar = [] # n_r
dcmddrstar = [] # l_r
for index in find_index:
cml.append(cml_list[index]) # N , N_v
cmd.append(cmd_list[index]) # L , L_v
aos.append(aos_list[index] * np.pi / 180)
aoa.append(aoa_list[index]) # For Ue We
cs.append(cs_list[index])
dcsdpstar.append(dcsdpstar_list[index]) # y_p
dcmddpstar.append(dcmddpstar_list[index]) # l_p
dcmldpstar.append(dcmldpstar_list[index]) # n_p
dcsdrstar.append(dcsdrstar_list[index]) # y_r
dcmldrstar.append(dcmldrstar_list[index]) # n_r
dcmddrstar.append(dcmddrstar_list[index]) # l_r
#Trimm condition calculation
# speed derivatives : y_v / l_v / n_v / Must be devided by speed given that the hyp v=Beta*U
if len(aos_unic) >= 2:
print('Mach : ', mach, ' and idx_mach : ',
idx_mach)
cs_beta0 = speed_derivative_at_trim_lat(
cs_list, aos_list, aos_unic, idx_alt, idx_mach,
aoa_list, idx_trim_before, idx_trim_after,
ratio) # y_v
if cs_beta0 == None:
cs_beta0 = 0
log.warning(
'Not enough data to determine cs_beta (Y_v) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: cs_beta = 0'
.format(alt, mach, round(trim_aoa_deg, 2)))
cmd_beta0 = speed_derivative_at_trim_lat(
cmd_list, aos_list, aos_unic, idx_alt,
idx_mach, aoa_list, idx_trim_before,
idx_trim_after, ratio) # l_v
if cmd_beta0 == None:
cmd_beta0 = 0
log.warning(
'Not enough data to determine cmd_beta (L_v) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: cmd_beta = 0'
.format(alt, mach, round(trim_aoa_deg, 2)))
cml_beta0 = speed_derivative_at_trim_lat(
cml_list, aos_list, aos_unic, idx_alt,
idx_mach, aoa_list, idx_trim_before,
idx_trim_after, ratio) # n_v
if cml_beta0 == None:
cml_beta0 = 0
log.warning(
'Not enough data to determine cml_beta (N_v) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: cml_beta = 0'
.format(alt, mach, round(trim_aoa_deg, 2)))
else:
cs_beta0 = 0
cmd_beta0 = 0
cml_beta0 = 0
log.warning(
'Not enough data to determine cs_beta (Y_v), cmd_beta (L_v) and cml_beta (N_v) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: cs_beta = cmd_beta = cml_beta = 0'
.format(alt, mach, round(trim_aoa_deg, 2)))
dcsdpstar0 = interpolation(dcsdpstar, idx_trim_before,
idx_trim_after,
ratio) # y_p
dcmddpstar0 = interpolation(dcmddpstar,
idx_trim_before,
idx_trim_after,
ratio) # l_p
dcmldpstar0 = interpolation(dcmldpstar,
idx_trim_before,
idx_trim_after,
ratio) # n_p
dcsdrstar0 = interpolation(dcsdrstar, idx_trim_before,
idx_trim_after,
ratio) # y_r
dcmldrstar0 = interpolation(dcmldrstar,
idx_trim_before,
idx_trim_after,
ratio) # n_r
dcmddrstar0 = interpolation(dcmddrstar,
idx_trim_before,
idx_trim_after,
ratio) # l_r
# TODO: calculate that and find in the cpacs
dcsdxi0 = 0
dcmddxi0 = 0
dcmldxi0 = 0
dcsdzeta0 = 0
dcmddzeta0 = 0
dcmldzeta0 = 0
# Traduction Ceasiom -> Theory
Y_v = cs_beta0
L_v = cmd_beta0
N_v = cml_beta0
Y_p = -dcsdpstar0 * mac / b
L_p = -dcmddpstar0 * mac / b
N_p = dcmldpstar0 * mac / b
Y_r = dcsdrstar0 * mac / b
N_r = -dcmldrstar0 * mac / b # mac/b :Because coefficients in ceasiom are nondimensionalised by the mac instead of the span
L_r = dcmddrstar0 * mac / b
# Controls:
# Ailerons
Y_xi = dcsdxi0 # To be found from the cpacs file, and defined by the user!
L_xi = dcmddxi0 # To be found from the cpacs file, and defined by the user!
N_xi = dcmldxi0 # To be found from the cpacs file, and defined by the user!
# Rudder
Y_zeta = dcsdzeta0 # To be found from the cpacs file, and defined by the user!
L_zeta = dcmddzeta0 # To be found from the cpacs file, and defined by the user!
N_zeta = dcmldzeta0 # To be found from the cpacs file, and defined by the user!
Ue = u0 * np.cos(
trim_aoa
) # *np.cos(aos) as aos = 0 at trim, cos(aos)=1
We = u0 * np.sin(
trim_aoa
) # *np.cos(aos) as aos = 0 at trim, cos(aos)=1
# Sign check (Ref: Thomas Yechout Book, P304)
check_sign_lat(Y_v, L_v, N_v, Y_p, L_p, Y_r, L_r, N_r,
L_xi, Y_zeta, L_zeta, N_zeta)
if trim_aoa:
for angles in flight_path_angle:
theta_e = angles + trim_aoa
if longitudinal_analysis:
(A_longi, B_longi, x_u,z_u,m_u,x_w,z_w,m_w, x_q,z_q,m_q,x_theta,z_theta,m_theta,x_eta,z_eta,m_eta, x_tau,z_tau,m_tau)\
= concise_derivative_longi(X_u,Z_u,M_u,X_w,Z_w,M_w,\
X_q,Z_q,M_q,X_dotw,Z_dotw,M_dotw,X_eta,Z_eta,M_eta,\
X_tau,Z_tau,M_tau, g, theta_e, u0,We,Ue,mac,m_adim,i_yy)
C_longi = np.identity(4)
D_longi = np.zeros((4, 2))
# Identify longitudinal roots
if longi_root_identification(
A_longi
)[0] == None: # If longitudinal root not complex conjugate raise warning and plot roots
eg_value_longi = longi_root_identification(
A_longi)[1]
log.warning(
'Longi : charcateristic equation roots are not complex conjugate : {}'
.format(eg_value_longi))
legend = [
'Root1', 'Root2', 'Root3', 'Root4'
]
plot_title = 'S-plane longitudinal characteristic equation roots at (Alt = {}, Mach= {}, trimed at aoa = {}°)'.format(
alt, mach, trim_aoa)
plot_splane(eg_value_longi, plot_title,
legend, show_plots, save_plots)
else: # Longitudinal roots are complex conjugate
(sp1, sp2, ph1, ph2, eg_value_longi , eg_vector_longi, eg_vector_longi_magnitude)\
= longi_root_identification(A_longi)
legend = ['sp1', 'sp2', 'ph1', 'ph2']
plot_title = 'S-plane longitudinal characteristic equation roots at (Alt = {}, Mach= {}, trimed at aoa = {}°)'.format(
alt, mach, trim_aoa)
plot_splane(eg_value_longi, plot_title,
legend, show_plots, save_plots)
# Modes parameters : damping ratio, frequence, CAP, time tou double amplitude
Z_w_dimensional = Z_w * (
0.5 * rho * s * u0**2
) # Z_w* (0.5*rho*s*u0**2) is the dimensional form of Z_w, Z_w = -(cl_alpha0 + cd0) P312 Yechout
z_alpha = Z_w_dimensional * u0 / m # alpha = w/u0 hence, z_alpha = Z_w_dimensional * u0 [Newton/rad/Kg : m/s^2 /rad]
load_factor = -z_alpha / g # number of g's/rad (1g/rad 2g/rad 3g/rad)
(sp_freq, sp_damp, sp_cap, ph_freq, ph_damp, ph_t2)\
= longi_mode_characteristic(sp1,sp2,ph1,ph2,load_factor)
# Rating
sp_damp_rate = short_period_damping_rating(
aircraft_class, sp_damp)
sp_freq_rate = short_period_frequency_rating(
flight_phase, aircraft_class, sp_freq,
load_factor)
# Plot SP freq vs Load factor
legend = 'Alt = {}, Mach= {}, trim aoa = {}°'.format(
alt, mach, trim_aoa)
if flight_phase == 'A':
plot_sp_level_a([load_factor],
[sp_freq], legend,
show_plots, save_plots)
elif flight_phase == 'B':
plot_sp_level_b(
x_axis, y_axis, legend, show_plots,
save_plots)
else:
plot_sp_level_c(
x_axis, y_axis, legend, show_plots,
save_plots)
sp_cap_rate = cap_rating(
flight_phase, sp_cap, sp_damp)
ph_rate = phugoid_rating(ph_damp, ph_t2)
# Raise warning if unstable mode in the log file
if sp_damp_rate == None:
log.warning(
'ShortPeriod UNstable at Alt = {}, Mach = {} , due to DampRatio = {} '
.format(alt, mach,
round(sp_damp, 4)))
if sp_freq_rate == None:
log.warning(
'ShortPeriod UNstable at Alt = {}, Mach = {} , due to UnDampedFreq = {} rad/s '
.format(alt, mach,
round(sp_freq, 4)))
if sp_cap_rate == None:
log.warning(
'ShortPeriod UNstable at Alt = {}, Mach = {} , with CAP evaluation, DampRatio = {} , CAP = {} '
.format(alt, mach,
round(sp_damp, 4),
round(sp_cap, 4)))
if ph_rate == None:
log.warning(
'Phugoid UNstable at Alt = {}, Mach = {} , DampRatio = {} , UnDampedFreq = {} rad/s'
.format(alt, mach,
round(ph_damp, 4),
round(ph_freq, 4)))
# TODO
# Compute numerator TF for (Alt, mach, flight_path_angle, aoa_trim, aos=0
if lateral_directional_analysis:
(A_direc, B_direc,y_v,l_v,n_v,y_p,y_phi,y_psi,l_p,l_phi,l_psi,n_p,y_r,l_r,n_r,n_phi,n_psi, y_xi,l_xi,n_xi, y_zeta,l_zeta,n_zeta)\
= concise_derivative_lat(Y_v,L_v,N_v,Y_p,L_p,N_p,Y_r,L_r,N_r,\
Y_xi,L_xi,N_xi, Y_zeta,L_zeta,N_zeta,\
g, b, theta_e, u0,We,Ue,m_adim,i_xx,i_zz,i_xz )
C_direc = np.identity(5)
D_direc = np.zeros((5, 2))
if direc_root_identification(
A_direc
)[0] == None: # Lateral-directional roots are correctly identified
eg_value_direc = direc_root_identification(
A_direc)[1]
print(
'Lat-Dir : charcateristic equation roots are not complex conjugate : {}'
.format(eg_value_direc))
legend = [
'Root1', 'Root2', 'Root3', 'Root4'
]
plot_title = 'S-plane lateral characteristic equation roots at (Alt = {}, Mach= {}, trimed at aoa = {}°)'.format(
alt, mach, trim_aoa)
plot_splane(eg_value_direc, plot_title,
legend, show_plots, save_plots)
else: # Lateral-directional roots are correctly identified
(roll, spiral, dr1, dr2, eg_value_direc, eg_vector_direc, eg_vector_direc_magnitude)\
= direc_root_identification(A_direc)
legend = ['roll', 'spiral', 'dr1', 'dr2']
plot_title = 'S-plane lateralcharacteristic equation roots at (Alt = {}, Mach= {}, trimed at aoa = {}°)'.format(
alt, mach, trim_aoa)
plot_splane(eg_value_direc, plot_title,
legend, show_plots, save_plots)
(roll_timecst, spiral_timecst, spiral_t2,
dr_freq, dr_damp,
dr_damp_freq) = direc_mode_characteristic(
roll, spiral, dr1, dr2)
# Rating
roll_rate = roll_rating(
flight_phase, aircraft_class,
roll_timecst)
spiral_rate = spiral_rating(
flight_phase, spiral_timecst,
spiral_t2)
dr_rate = dutch_roll_rating(
flight_phase, aircraft_class, dr_damp,
dr_freq, dr_damp_freq)
# Raise warning in the log file if unstable mode
if roll_rate == None:
log.warning(
'Roll mode UNstable at Alt = {}, Mach = {} , due to roll root = {}, roll time contatant = {} s'
.format(alt, mach,
round(roll_root, 4),
round(roll_timecst, 4)))
if spiral_rate == None:
log.warning(
'Spiral mode UNstable at Alt = {}, Mach = {} , spiral root = {}, time_double_ampl = {}'
.format(alt, mach,
round(spiral_root, 4),
round(spiral_t2, 4)))
if dr_rate == None:
log.warning(
'Dutch Roll UNstable at Alt = {}, Mach = {} , Damping Ratio = {} , frequency = {} rad/s '
.format(alt, mach,
round(dr_damp, 4),
round(dr_freq, 4)))
def get_su2_results(cpacs_path, cpacs_out_path, wkdir):
""" Function to write SU2 results in a CPACS file.
Function 'get_su2_results' get available results from the latest SU2
calculation and put it at the correct place in the CPACS file.
'/cpacs/vehicles/aircraft/model/analyses/aeroPerformance/aerpMap[n]/aeroPerformanceMap'
Args:
cpacs_path (str): Path to input CPACS file
cpacs_out_path (str): Path to output CPACS file
wkdir (str): Path to the working directory
"""
tixi = cpsf.open_tixi(cpacs_path)
# TODO Check and reactivate that
# save_timestamp(tixi,SU2_XPATH) <-- ceaf.replace by get get_execution_date()
if not os.path.exists(wkdir):
raise OSError('The working directory : ' + wkdir + 'does not exit!')
os.chdir(wkdir)
dir_list = os.listdir(wkdir)
# Get and save Wetted area
wetted_area = get_wetted_area(wkdir)
wetted_area_xpath = '/cpacs/toolspecific/CEASIOMpy/geometry/analysis/wettedArea'
cpsf.create_branch(tixi, wetted_area_xpath)
tixi.updateDoubleElement(wetted_area_xpath, wetted_area, '%g')
# Get and save CL/CD ratio
fixed_cl_xpath = SU2_XPATH + '/fixedCL'
fixed_cl = cpsf.get_value_or_default(tixi, fixed_cl_xpath, 'NO')
# TODO
# if fixed_cl == 'YES':
# find force_file_name = 'forces_breakdown.dat'
# cl_cd = get_efficiency(force_path)
# lDRatio_xpath = '/cpacs/toolspecific/CEASIOMpy/ranges/lDRatio' # TODO: probalby change xpath and name
# cpsf.create_branch(tixi, lDRatio_xpath)
# tixi.updateDoubleElement(lDRatio_xpath,cl_cd,'%g')
# Save aeroPerformanceMap
su2_aeromap_xpath = SU2_XPATH + '/aeroMapUID'
aeromap_uid = cpsf.get_value(tixi, su2_aeromap_xpath)
# Check if loads shoud be extracted
check_extract_loads_xpath = SU2_XPATH + '/results/extractLoads'
check_extract_loads = cpsf.get_value_or_default(tixi,
check_extract_loads_xpath,
False)
# Create an oject to store the aerodynamic coefficients
apmf.check_aeromap(tixi, aeromap_uid)
# TODO: create a function to earase previous results...
Coef2 = apmf.get_aeromap(tixi, aeromap_uid)
Coef = apmf.AeroCoefficient()
Coef.alt = Coef2.alt
Coef.mach = Coef2.mach
Coef.aoa = Coef2.aoa
Coef.aos = Coef2.aos
case_dir_list = [dir for dir in dir_list if 'Case' in dir]
for config_dir in sorted(case_dir_list):
if os.path.isdir(config_dir):
os.chdir(config_dir)
force_file_name = 'forces_breakdown.dat'
if not os.path.isfile(force_file_name):
raise OSError('No result force file have been found!')
# Read result file
with open(force_file_name) as f:
for line in f.readlines():
if 'Total CL:' in line:
cl = float(line.split(':')[1].split('|')[0])
if 'Total CD:' in line:
cd = float(line.split(':')[1].split('|')[0])
if 'Total CSF:' in line:
cs = float(line.split(':')[1].split('|')[0])
# TODO: Check which axis name corespond to waht: cml, cmd, cms
if 'Total CMx:' in line:
cmd = float(line.split(':')[1].split('|')[0])
if 'Total CMy:' in line:
cms = float(line.split(':')[1].split('|')[0])
if 'Total CMz:' in line:
cml = float(line.split(':')[1].split('|')[0])
if ('Free-stream velocity' in line and 'm/s' in line):
velocity = float(line.split(' ')[7])
# Damping derivatives
rotation_rate_xpath = SU2_XPATH + '/options/rotationRate'
rotation_rate = cpsf.get_value_or_default(tixi,
rotation_rate_xpath, 1.0)
ref_xpath = '/cpacs/vehicles/aircraft/model/reference'
ref_len = cpsf.get_value(tixi, ref_xpath + '/length')
adim_rot_rate = rotation_rate * ref_len / velocity
if '_dp' in config_dir:
dcl = (cl - Coef.cl[-1]) / adim_rot_rate
dcd = (cd - Coef.cd[-1]) / adim_rot_rate
dcs = (cs - Coef.cs[-1]) / adim_rot_rate
dcml = (cml - Coef.cml[-1]) / adim_rot_rate
dcmd = (cmd - Coef.cmd[-1]) / adim_rot_rate
dcms = (cms - Coef.cms[-1]) / adim_rot_rate
Coef.damping_derivatives.add_damping_der_coef(
dcl, dcd, dcs, dcml, dcmd, dcms, '_dp')
elif '_dq' in config_dir:
dcl = (cl - Coef.cl[-1]) / adim_rot_rate
dcd = (cd - Coef.cd[-1]) / adim_rot_rate
dcs = (cs - Coef.cs[-1]) / adim_rot_rate
dcml = (cml - Coef.cml[-1]) / adim_rot_rate
dcmd = (cmd - Coef.cmd[-1]) / adim_rot_rate
dcms = (cms - Coef.cms[-1]) / adim_rot_rate
Coef.damping_derivatives.add_damping_der_coef(
dcl, dcd, dcs, dcml, dcmd, dcms, '_dq')
elif '_dr' in config_dir:
dcl = (cl - Coef.cl[-1]) / adim_rot_rate
dcd = (cd - Coef.cd[-1]) / adim_rot_rate
dcs = (cs - Coef.cs[-1]) / adim_rot_rate
dcml = (cml - Coef.cml[-1]) / adim_rot_rate
dcmd = (cmd - Coef.cmd[-1]) / adim_rot_rate
dcms = (cms - Coef.cms[-1]) / adim_rot_rate
Coef.damping_derivatives.add_damping_der_coef(
dcl, dcd, dcs, dcml, dcmd, dcms, '_dr')
elif '_TED_' in config_dir:
config_dir_split = config_dir.split('_')
ted_idx = config_dir_split.index('TED')
ted_uid = config_dir_split[ted_idx + 1]
defl_angle = float(config_dir.split('_defl')[1])
try:
print(Coef.IncrMap.dcl)
except AttributeError:
Coef.IncrMap = apmf.IncrementMap(ted_uid)
# TODO: still in development, for now only 1 ted and 1 defl
print(ted_uid, defl_angle)
dcl = (cl - Coef.cl[-1])
dcd = (cd - Coef.cd[-1])
dcs = (cs - Coef.cs[-1])
dcml = (cml - Coef.cml[-1])
dcmd = (cmd - Coef.cmd[-1])
dcms = (cms - Coef.cms[-1])
control_parameter = -1
Coef.IncrMap.add_cs_coef(dcl, dcd, dcs, dcml, dcmd, dcms,
ted_uid, control_parameter)
else: # No damping derivative or control surfaces case
Coef.add_coefficients(cl, cd, cs, cml, cmd, cms)
if check_extract_loads:
results_files_dir = os.path.join(wkdir, config_dir)
extract_loads(results_files_dir)
os.chdir(wkdir)
# Save object Coef in the CPACS file
apmf.save_coefficients(tixi, aeromap_uid, Coef)
cpsf.close_tixi(tixi, cpacs_out_path)
def create_SU2_mesh(cpacs_path, cpacs_out_path):
""" Function to create a simple SU2 mesh form an SUMO file (.smx)
Function 'create_mesh' is used to generate an unstructured mesh with SUMO
(which integrage Tetgen for the volume mesh) using a SUMO (.smx) geometry
file as input.
Meshing option could be change manually (only in the script for now)
Source :
* sumo help, tetgen help (in the folder /doc)
Args:
cpacs_path (str): Path to the CPACS file
cpacs_out_path (str): Path to the output CPACS file
"""
tixi = cpsf.open_tixi(cpacs_path)
wkdir = ceaf.get_wkdir_or_create_new(tixi)
sumo_dir = os.path.join(wkdir, 'SUMO')
if not os.path.isdir(sumo_dir):
os.mkdir(sumo_dir)
su2_mesh_path = os.path.join(sumo_dir, 'ToolOutput.su2')
meshdir = os.path.join(wkdir, 'MESH')
if not os.path.isdir(meshdir):
os.mkdir(meshdir)
original_dir = os.getcwd()
os.chdir(sumo_dir)
sumo_file_xpath = '/cpacs/toolspecific/CEASIOMpy/filesPath/sumoFilePath'
sumo_file_path = cpsf.get_value_or_default(tixi, sumo_file_xpath, '')
if sumo_file_path == '':
raise ValueError('No SUMO file to use to create a mesh')
# Set mesh parameters
log.info('Mesh parameter will be set')
refine_level_xpath = '/cpacs/toolspecific/CEASIOMpy/mesh/sumoOptions/refinementLevel'
refine_level = cpsf.get_value_or_default(tixi, refine_level_xpath, 0.0)
log.info('Refinement level is {}'.format(refine_level))
add_mesh_parameters(sumo_file_path, refine_level)
# Check current Operating System
current_os = platform.system()
if current_os == 'Darwin':
log.info('Your OS is Mac\n\n')
log.info(
'!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!')
log.info('On MacOS the mesh has to be generated manually.')
log.info('To create a SU2Mesh you have to :')
log.info('Open the .smx geometry that you will find there:')
log.info(sumo_file_path)
log.info('Click on the button "Mesh"')
log.info('Click on "Create Mesh"')
log.info('Click on "Volume Mesh"')
log.info('Click on "Run"')
log.info('When the mesh generation is completed, click on "Close"')
log.info('Go to the Menu "Mesh" -> "Save volume mesh..."')
log.info('Chose "SU2 (*.su2)" as File Type"')
log.info('Copy/Paste the following line as File Name')
log.info(su2_mesh_path)
log.info('Click on "Save"')
log.info('You can now close SUMO, your workflow will continue.')
log.info(
'More information: https://ceasiompy.readthedocs.io/en/latest/user_guide/modules/SUMOAutoMesh/index.html'
)
log.info(
'!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!!\n\n'
)
# For now, I did not find a way to run "sumo -batch" on Mac...
# The command just open SUMO GUI, the mesh has to be generate and save manually
command = ['open', '/Applications/SUMO/dwfsumo.app/']
os.system(' '.join(command))
elif current_os == 'Linux':
log.info('Your OS is Linux')
# Check if SUMO is installed
soft_dict = ceaf.get_install_path(['sumo'])
# Run SUMO in batch
output = '-output=su2'
options = '-tetgen-options=pq1.16VY' # See Tetgen help for more options, maybe transform that as an input
# Command line to run: sumo -batch -output=su2 -tetgen-options=pq1.16VY ToolOutput.smx
command = [
soft_dict['sumo'], '-batch', output, options, sumo_file_path
]
os.system(' '.join(command))
elif current_os == 'Windows':
log.info('Your OS is Windows')
# TODO: develop this part
log.warning('OS not supported yet by SUMOAutoMesh!')
raise OSError('OS not supported yet!')
else:
raise OSError('OS not recognize!')
# Copy the mesh in the MESH directory
aircraft_name = cpsf.aircraft_name(tixi)
su2_mesh_name = aircraft_name + '_baseline.su2'
su2_mesh_new_path = os.path.join(meshdir, su2_mesh_name)
shutil.copyfile(su2_mesh_path, su2_mesh_new_path)
if os.path.isfile(su2_mesh_new_path):
log.info('An SU2 Mesh has been correctly generated.')
su2_mesh_xpath = '/cpacs/toolspecific/CEASIOMpy/filesPath/su2Mesh'
cpsf.create_branch(tixi, su2_mesh_xpath)
tixi.updateTextElement(su2_mesh_xpath, su2_mesh_new_path)
os.remove(su2_mesh_path)
else:
raise ValueError('No SU2 Mesh file has been generated!')
cpsf.close_tixi(tixi, cpacs_out_path)
os.chdir(original_dir)
def create_SU2_mesh(cpacs_path, cpacs_out_path):
""" Function to create a simple SU2 mesh form an SUMO file (.smx)
Function 'create_mesh' is used to generate an unstructured mesh with SUMO
(which integrage Tetgen for the volume mesh) using a SUMO (.smx) geometry
file as input.
Meshing option could be change manually (only in the script for now)
Source :
* sumo help, tetgen help (in the folder /doc)
Args:
cpacs_path (str): Path to the CPACS file
cpacs_out_path (str): Path to the output CPACS file
"""
tixi = cpsf.open_tixi(cpacs_path)
wkdir = ceaf.get_wkdir_or_create_new(tixi)
sumo_dir = os.path.join(wkdir, 'SUMO')
if not os.path.isdir(sumo_dir):
os.mkdir(sumo_dir)
mesh_dir = os.path.join(wkdir, 'MESH')
if not os.path.isdir(mesh_dir):
os.mkdir(mesh_dir)
original_dir = os.getcwd()
os.chdir(sumo_dir)
sumo_file_xpath = '/cpacs/toolspecific/CEASIOMpy/filesPath/sumoFilePath'
sumo_file_path = cpsf.get_value_or_default(tixi, sumo_file_xpath, '')
if sumo_file_path == '':
raise ValueError('No SUMO file to use to create a mesh')
# Check if SUMO is installed
soft_dict = ceaf.get_install_path(['sumo'])
# Run SUMO to create a create a mesh
# sumo - batch -output=su2 -tetgen-options=pq1.16VY mesh.smx
sumo_output = '-output=su2' # For now, must be SU2
tetgen_options = '-tetgen-options=pq1.16VY' # See Tetgen help for more options, maybe transform that as an input
command_line = [
soft_dict['sumo'], '-batch', sumo_output, tetgen_options,
sumo_file_path
]
# print(' '.join(command_line))
os.system(' '.join(command_line))
# Copy the mesh in the MESH directory
su2_mesh_path = os.path.join(sumo_dir, 'ToolOutput.su2')
aircraft_name = cpsf.aircraft_name(tixi)
su2_mesh_name = aircraft_name + '_baseline.su2'
su2_mesh_new_path = os.path.join(mesh_dir, su2_mesh_name)
shutil.copyfile(su2_mesh_path, su2_mesh_new_path)
if os.path.isfile(su2_mesh_new_path):
log.info('An SU2 Mesh has been correctly generated.')
su2_mesh_xpath = '/cpacs/toolspecific/CEASIOMpy/filesPath/su2Mesh'
cpsf.create_branch(tixi, su2_mesh_xpath)
tixi.updateTextElement(su2_mesh_xpath, su2_mesh_new_path)
os.remove(su2_mesh_path)
else:
raise ValueError('No SU2 Mesh file has been generated!')
cpsf.close_tixi(tixi, cpacs_out_path)
os.chdir(original_dir)
def get_user_inputs(ed, ui, adui, cpacs_in):
"""Function to extract from the xml file the required input data,
the code will use the default value when they are missing.
Function 'get_user_inputs' ...
Args:
ed (int): EngineData class.
ui (class): UserInputs class
adui (str): AdvancedInputs class.
cpacs_in (str): Path to the CPACS file
Returns:
ed (int): Updated ngineData class.
ui (class): Updated UserInputs class
adui (str): Updated AdvancedInputs class.
"""
log.info('Starting data extraction from CPACS file')
tixi = cpsf.open_tixi(cpacs_in)
# toolspecific
CEASIOM_XPATH = '/cpacs/toolspecific/CEASIOMpy'
GEOM_XPATH = CEASIOM_XPATH + '/geometry'
RANGE_XPATH = CEASIOM_XPATH + '/ranges'
WEIGHT_XPATH = CEASIOM_XPATH + '/weight'
CREW_XPATH = WEIGHT_XPATH + '/crew'
PILOTS_PATH = CREW_XPATH + '/pilots'
CAB_CREW_XPATH = CREW_XPATH + '/cabinCrewMembers'
PASS_XPATH = WEIGHT_XPATH + '/passengers'
ML_XPATH = WEIGHT_XPATH + '/massLimits'
PROP_XPATH = CEASIOM_XPATH + '/propulsion'
FUEL_XPATH = '/cpacs/toolspecific/CEASIOMpy/fuels'
cpsf.create_branch(tixi, FUEL_XPATH, False)
cpsf.create_branch(tixi, GEOM_XPATH, False)
cpsf.create_branch(tixi, RANGE_XPATH, False)
cpsf.create_branch(tixi, PILOTS_PATH, False)
cpsf.create_branch(tixi, CAB_CREW_XPATH, False)
cpsf.create_branch(tixi, PASS_XPATH, False)
cpsf.create_branch(tixi, ML_XPATH, False)
cpsf.create_branch(tixi, PROP_XPATH, False)
# cpacs/vehicles
MC_XPATH = '/cpacs/vehicles/aircraft/model/analyses/massBreakdown/payload/mCargo/massDescription'
F_XPATH = '/cpacs/vehicles/fuels/fuel'
cpsf.create_branch(tixi, MC_XPATH, False)
cpsf.create_branch(tixi, F_XPATH, False)
cpsf.add_uid(tixi, F_XPATH, 'kerosene')
# Gathering data =========================================================
# Geometry ===============================================================
if not tixi.checkElement(GEOM_XPATH + '/description'):
tixi.createElement(GEOM_XPATH, 'description')
tixi.updateTextElement(GEOM_XPATH + '/description', 'User '\
+ 'geometry input')
ui.FLOORS_NB = cpsf.get_value_or_default(tixi,GEOM_XPATH + '/floorsNb', ui.FLOORS_NB)
adui.VRT_THICK = cpsf.get_value_or_default(tixi,GEOM_XPATH + '/virtualThick', 0.00014263)
adui.VRT_STR_DENSITY = cpsf.get_value_or_default(tixi,GEOM_XPATH + '/virtualDensity', 2700.0)
ui.H_LIM_CABIN = cpsf.get_value_or_default(tixi,GEOM_XPATH + '/cabinHeight', 2.3)
# People =================================================================
# Pilots user input data
adui.PILOT_NB = cpsf.get_value_or_default(tixi,PILOTS_PATH + '/pilotNb', 2)
adui.MASS_PILOT = cpsf.get_value_or_default(tixi,PILOTS_PATH + '/pilotMass', 102.0)
adui.MASS_CABIN_CREW = cpsf.get_value_or_default(tixi,CAB_CREW_XPATH + '/cabinCrewMemberMass', 68.0)
adui.MASS_PASS = cpsf.get_value_or_default(tixi,PASS_XPATH + '/passMass', 105.0)
adui.PASS_BASE_DENSITY = cpsf.get_value_or_default(tixi,PASS_XPATH + '/passDensity', 1.66)
adui.PASS_PER_TOILET = cpsf.get_value_or_default(tixi,PASS_XPATH + '/passPerToilet', 50)
# what to to with this input
if tixi.checkElement(PASS_XPATH + '/passNb'):
temp = tixi.getIntegerElement(PASS_XPATH+ '/passNb')
if temp != ui.MAX_PASS and temp > 0:
ui.MAX_PASS = temp
# Fuel ===================================================================
adui.FUEL_DENSITY = cpsf.get_value_or_default(tixi,F_XPATH + '/density', 800)
adui.RES_FUEL_PERC = cpsf.get_value_or_default(tixi,F_XPATH + '/resFuelPerc', 0.06)
# Weight =================================================================
# Mass limits data
if not tixi.checkElement(ML_XPATH + '/description'):
tixi.createElement(ML_XPATH, 'description')
tixi.updateTextElement(ML_XPATH + '/description', 'Desired max fuel '\
+ 'volume [m^3] and payload mass [kg]')
ui.MAX_PAYLOAD = cpsf.get_value_or_default(tixi,ML_XPATH + '/maxPayload', 0.0)
ui.MAX_FUEL_VOL = cpsf.get_value_or_default(tixi,ML_XPATH + '/maxFuelVol', 0.0)
ui.MASS_CARGO = cpsf.get_value_or_default(tixi,MC_XPATH + '/massCargo', 0.0)
# If the cargo mass is defined in the UserInputs class will be added
# in the CPACS file after the analysis.
# Flight =================================================================
ed.TSFC_CRUISE = cpsf.get_value_or_default(tixi,PROP_XPATH + '/tSFC', 0.5)
# TODO: These data should be taken from aeroMaps...
if not tixi.checkElement(RANGE_XPATH + '/lDRatio'):
tixi.createElement(RANGE_XPATH, 'lDRatio')
tixi.updateDoubleElement(RANGE_XPATH + '/lDRatio',\
ui.LD, '%g')
else:
temp = tixi.getIntegerElement(RANGE_XPATH + '/lDRatio')
if temp != ui.LD and temp > 0:
ui.LD = temp
if not tixi.checkElement(RANGE_XPATH + '/cruiseSpeed'):
tixi.createElement(RANGE_XPATH, 'cruiseSpeed')
tixi.updateDoubleElement(RANGE_XPATH + '/cruiseSpeed',\
ui.CRUISE_SPEED, '%g')
else:
temp = tixi.getIntegerElement(RANGE_XPATH + '/cruiseSpeed')
if temp != ui.CRUISE_SPEED and temp > 0:
ui.CRUISE_SPEED = temp
# TODO: see how to enter input for Engines
if not tixi.checkElement(PROP_XPATH + '/userEngineOption'):
tixi.createElement(PROP_XPATH, 'userEngineOption')
if ui.USER_ENGINES:
tixi.updateTextElement(PROP_XPATH + '/userEngineOption', 'True')
else:
tixi.updateTextElement(PROP_XPATH + '/userEngineOption', 'False')
else:
temp = tixi.getTextElement(PROP_XPATH + '/userEngineOption')
if temp == 'False':
ui.USER_ENGINES = False
else:
ui.USER_ENGINES = True
if not tixi.checkElement(PROP_XPATH + '/singleHydraulics'):
tixi.createElement(PROP_XPATH, 'singleHydraulics')
if adui.SINGLE_HYDRAULICS:
tixi.updateTextElement(PROP_XPATH + '/singleHydraulics', 'True')
else:
tixi.updateTextElement(PROP_XPATH + '/singleHydraulics', 'False')
else:
temp = tixi.getTextElement(PROP_XPATH + '/singleHydraulics')
if temp == 'False':
adui.SINGLE_HYDRAULICS = False
else:
adui.SINGLE_HYDRAULICS = True
log.info('Data from CPACS file succesfully extracted')
cpsf.close_tixi(tixi, cpacs_in)
return(ed, ui, adui)
None.
"""
am_uid_use = cpsf.get_value_or_default(tixi, SMUSE_XPATH + 'aeroMapUID',
'')
am_uid_train = cpsf.get_value_or_default(tixi,
SMTRAIN_XPATH + 'aeroMapUID', '')
if am_uid_train == am_uid_use:
sys.exit('Same aeromap that was used to create the model')
if __name__ == "__main__":
log.info('----- Start of ' + os.path.basename(__file__) + ' -----')
# Load the model
tixi = cpsf.open_tixi(cpacs_path)
Model = load_surrogate(tixi)
check_aeromap(tixi)
if cpsf.get_value_or_default(tixi, SMUSE_XPATH + 'AeroMapOnly', False):
aeromap_calculation(Model.sm, tixi)
else:
predict_output(Model)
cpsf.close_tixi(tixi, cpacs_path_out)
log.info('----- End of ' + os.path.basename(__file__) + ' -----')
def get_user_inputs(self, cpacs_path):
""" Get user input from the CPACS file
The function 'get_user_inputs' extracts from the CPACS file the required
input data, the code will use the default value when they are missing.
Args:
cpacs_path (str): Path to CPACS file
"""
tixi = open_tixi(cpacs_path)
description = 'User geometry input'
get_value_or_default(tixi, GEOM_XPATH + '/description', description)
self.IS_DOUBLE_FLOOR = get_value_or_default(
tixi, GEOM_XPATH + '/isDoubleFloor', 0)
self.PILOT_NB = get_value_or_default(tixi, pilots_xpath + '/pilotNb',
2)
self.MASS_PILOT = get_value_or_default(tixi,
pilots_xpath + '/pilotMass',
102)
self.MASS_CABIN_CREW = get_value_or_default(
tixi, CC_XPATH + '/cabinCrewMemberMass', 68)
self.MASS_PASS = get_value_or_default(tixi, PASS_XPATH + '/passMass',
105)
self.PASS_PER_TOILET = get_value_or_default(
tixi, PASS_XPATH + '/passPerToilet', 50)
description = 'Desired max fuel volume [m^3] and payload mass [kg]'
get_value_or_default(tixi, ML_XPATH + '/description', description)
self.MAX_PAYLOAD = get_value_or_default(tixi, ML_XPATH + '/maxPayload',
0)
self.MAX_FUEL_VOL = get_value_or_default(tixi,
ML_XPATH + '/maxFuelVol', 0)
self.MASS_CARGO = get_value_or_default(tixi, MC_XPATH + '/mass', 0.0)
self.FUEL_DENSITY = get_value_or_default(tixi, F_XPATH + '/density',
800)
self.TURBOPROP = get_value_or_default(tixi, PROP_XPATH + '/turboprop',
False)
self.RES_FUEL_PERC = get_value_or_default(tixi,
FUEL_XPATH + '/resFuelPerc',
0.06)
add_uid(tixi, F_XPATH, 'kerosene')
close_tixi(tixi, cpacs_path)
def plot_aero_coef(cpacs_path, cpacs_out_path):
"""Plot Aero coefficients from the chosen aeroMap in the CPACS file
Function 'plot_aero_coef' can plot one or several aeromap from the CPACS
file according to some user option, these option will be shown in the the
SettingGUI or default values will be used.
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str):Path to CPACS output file
"""
# Open TIXI handle
tixi = cpsf.open_tixi(cpacs_path)
aircraft_name = cpsf.aircraft_name(tixi)
# Get aeroMap list to plot
aeromap_to_plot_xpath = PLOT_XPATH + '/aeroMapToPlot'
aeromap_uid_list = []
# Option to select aeromap manualy
manual_selct = cpsf.get_value_or_default(tixi,
PLOT_XPATH + '/manualSelection',
False)
if manual_selct:
aeromap_uid_list = call_select_aeromap(tixi)
cpsf.create_branch(tixi, aeromap_to_plot_xpath)
cpsf.add_string_vector(tixi, aeromap_to_plot_xpath, aeromap_uid_list)
else:
try:
aeromap_uid_list = cpsf.get_string_vector(tixi,
aeromap_to_plot_xpath)
except:
# If aeroMapToPlot is not define, select manualy anyway
aeromap_uid_list = call_select_aeromap(tixi)
cpsf.create_branch(tixi, aeromap_to_plot_xpath)
cpsf.add_string_vector(tixi, aeromap_to_plot_xpath,
aeromap_uid_list)
# Create DataFrame from aeromap(s)
aeromap_df_list = []
for aeromap_uid in aeromap_uid_list:
aeromap_df = apmf.get_datafram_aeromap(tixi, aeromap_uid)
aeromap_df['uid'] = aeromap_uid
aeromap_df_list.append(aeromap_df)
aeromap = pd.concat(aeromap_df_list, ignore_index=True)
if len(aeromap_uid_list) > 1:
uid_crit = None
else:
uid_crit = aeromap_uid_list[0]
# Default options
title = aircraft_name
criterion = pd.Series([True] * len(aeromap.index))
groupby_list = ['uid', 'mach', 'alt', 'aos']
# Get criterion from CPACS
crit_xpath = PLOT_XPATH + '/criterion'
alt_crit = cpsf.get_value_or_default(tixi, crit_xpath + '/alt', 'None')
mach_crit = cpsf.get_value_or_default(tixi, crit_xpath + '/mach', 'None')
aos_crit = cpsf.get_value_or_default(tixi, crit_xpath + '/aos', 'None')
cpsf.close_tixi(tixi, cpacs_out_path)
# Modify criterion and title according to user option
if len(aeromap['alt'].unique()) == 1:
title += ' - Alt = ' + str(aeromap['alt'].loc[0])
groupby_list.remove('alt')
elif alt_crit not in NONE_LIST:
criterion = criterion & (aeromap.alt == alt_crit)
title += ' - Alt = ' + str(alt_crit)
groupby_list.remove('alt')
if len(aeromap['mach'].unique()) == 1:
title += ' - Mach = ' + str(aeromap['mach'].loc[0])
groupby_list.remove('mach')
elif mach_crit not in NONE_LIST:
criterion = criterion & (aeromap.mach == mach_crit)
title += ' - Mach = ' + str(mach_crit)
groupby_list.remove('mach')
if len(aeromap['aos'].unique()) == 1:
title += ' - AoS = ' + str(aeromap['aos'].loc[0])
groupby_list.remove('aos')
elif aos_crit not in NONE_LIST:
criterion = criterion & (aeromap.aos == aos_crit)
title += ' - AoS = ' + str(aos_crit)
groupby_list.remove('aos')
if uid_crit is not None and len(groupby_list) > 1:
criterion = criterion & (aeromap.uid == uid_crit)
title += ' - ' + uid_crit
groupby_list.remove('uid')
# Plot settings
fig, axs = plt.subplots(2, 3)
fig.suptitle(title, fontsize=14)
fig.set_figheight(8)
fig.set_figwidth(15)
fig.subplots_adjust(left=0.06)
axs[0, 1].axhline(y=0.0, color='k', linestyle='-') # Line at Cm=0
# Plot aerodynamic coerfficients
for value, grp in aeromap.loc[criterion].groupby(groupby_list):
legend = write_legend(groupby_list, value)
axs[0, 0].plot(grp['aoa'], grp['cl'], 'x-', label=legend)
axs[1, 0].plot(grp['aoa'], grp['cd'], 'x-')
axs[0, 1].plot(grp['aoa'], grp['cms'], 'x-')
axs[1, 1].plot(grp['aoa'], grp['cl'] / grp['cd'], 'x-')
axs[0, 2].plot(grp['cd'], grp['cl'], 'x-')
axs[1, 2].plot(grp['cl'], grp['cl'] / grp['cd'], 'x-')
# Set subplot options
subplot_options(axs[0, 0], 'CL', 'AoA')
subplot_options(axs[1, 0], 'CD', 'AoA')
subplot_options(axs[0, 1], 'Cm', 'AoA')
subplot_options(axs[1, 1], 'CL/CD', 'AoA')
subplot_options(axs[0, 2], 'CL', 'CD')
subplot_options(axs[1, 2], 'CL/CD', 'CL')
fig.legend(loc='upper right')
plt.show()
def generate_mesh_def_config(tixi, wkdir, ted_uid, wing_uid, sym_dir,
defl_list):
"""Function to create config file for a TED.
Function 'generate_mesh_def_config' will create SU2 configuration files to
create SU2 deformed mesh for a specific Trailing Edge Device (TED) at several
deflection angle (from defl_list)
Args:
tixi (handle): TIXI handle
wkdir (str): Path to the working directory
ted_uid (str): uID of the TED
wing_uid (str): uID of the coresponding wing
sym_dir (str): Direction of the axis of symmetry ('x','y','z' or '')
defl_list (str): List of deflction angles to generate
"""
tigl = cpsf.open_tigl(tixi)
aircraft_name = cpsf.aircraft_name(tixi)
DEFAULT_CONFIG_PATH = MODULE_DIR + '/files/DefaultConfig_v7.cfg'
cfg = su2f.read_config(DEFAULT_CONFIG_PATH)
config_dir_name = aircraft_name + '_TED_' + ted_uid
# TODO: add check or remove if alread exist?
os.mkdir(os.path.join(wkdir, 'MESH', config_dir_name))
# Get TED and hinge line definition
ted_corner = get_ted_corner(tixi, tigl, ted_uid)
ted_corner_list, ted_corner_sym_list = get_ffd_box(ted_corner, sym_dir)
ted_hinge = get_ted_hinge(tixi, tigl, ted_uid)
hinge_list, hinge_sym_list = get_hinge_lists(ted_hinge, sym_dir)
# General parmeters
ref_len = cpsf.get_value(tixi, REF_XPATH + '/length')
ref_area = cpsf.get_value(tixi, REF_XPATH + '/area')
ref_ori_moment_x = cpsf.get_value_or_default(tixi, REF_XPATH + '/point/x',
0.0)
ref_ori_moment_y = cpsf.get_value_or_default(tixi, REF_XPATH + '/point/y',
0.0)
ref_ori_moment_z = cpsf.get_value_or_default(tixi, REF_XPATH + '/point/z',
0.0)
cfg['REF_LENGTH'] = ref_len
cfg['REF_AREA'] = ref_area
cfg['REF_ORIGIN_MOMENT_X'] = ref_ori_moment_x
cfg['REF_ORIGIN_MOMENT_Y'] = ref_ori_moment_y
cfg['REF_ORIGIN_MOMENT_Z'] = ref_ori_moment_z
cfg['GRID_MOVEMENT'] = 'NONE'
cfg['ROTATION_RATE'] = '0.0 0.0 0.0'
# TODO: is it the best way or should be pass as arg?
mesh_dir = os.path.join(wkdir, 'MESH')
su2_mesh_path = os.path.join(mesh_dir, aircraft_name + '_baseline.su2')
cfg['MESH_FILENAME'] = '../' + aircraft_name + '_baseline.su2'
# Mesh Marker
bc_wall_list = su2f.get_mesh_marker(su2_mesh_path)
bc_wall_str = '(' + ','.join(bc_wall_list) + ')'
cfg['MARKER_EULER'] = bc_wall_str
cfg['MARKER_FAR'] = ' (Farfield)'
cfg['MARKER_SYM'] = ' (0)'
cfg['MARKER_PLOTTING'] = bc_wall_str
cfg['MARKER_MONITORING'] = bc_wall_str
cfg['MARKER_MOVING'] = '( NONE )'
cfg['DV_MARKER'] = bc_wall_str
# FFD BOX definition
cfg['DV_KIND'] = 'FFD_SETTING'
cfg['DV_MARKER'] = '( ' + wing_uid + ')'
cfg['FFD_CONTINUITY'] = '2ND_DERIVATIVE'
cfg['FFD_DEFINITION'] = '( ' + ted_uid + ', ' + ','.join(
ted_corner_list) + ')'
cfg['FFD_DEGREE'] = '( 6, 10, 3 )' # TODO: how to chose/calculate these value?
if sym_dir:
cfg['FFD_DEFINITION'] += '; (' + ted_uid + '_sym, ' + ','.join(
ted_corner_sym_list) + ')'
cfg['FFD_DEGREE'] += ';( 6, 10, 3 )' # TODO: how to chose/calculate these value?
cfg['MESH_OUT_FILENAME'] = '_mesh_ffd_box.su2'
# Write Config definition for FFD box
config_file_name = 'ConfigDEF.cfg'
config_path = os.path.join(wkdir, 'MESH', config_dir_name,
config_file_name)
su2f.write_config(config_path, cfg)
log.info(config_path + ' have has been written.')
# FFD BOX rotation
for defl in defl_list:
cfg['DV_KIND'] = 'FFD_ROTATION'
cfg['DV_MARKER'] = '( ' + wing_uid + ')'
cfg['DV_PARAM'] = '( ' + ted_uid + ', ' + ','.join(hinge_list) + ')'
cfg['DV_VALUE'] = str(defl / 1000) # SU2 use 1/1000 degree...
cfg['MESH_FILENAME'] = '_mesh_ffd_box.su2'
defl_mesh_name = aircraft_name + '_TED_' + ted_uid + '_defl' + str(
defl) + '.su2'
if sym_dir:
defl_mesh_name = '_' + defl_mesh_name
cfg['MESH_OUT_FILENAME'] = defl_mesh_name
# Write Config rotation for FFD box
config_file_name = 'ConfigROT_defl' + str(defl) + '.cfg'
config_path = os.path.join(wkdir, 'MESH', config_dir_name,
config_file_name)
su2f.write_config(config_path, cfg)
log.info(config_path + ' have has been written.')
if sym_dir:
# TODO: add a condition for anti symetric deflection (e.g. ailerons)
cfg['DV_MARKER'] = '( ' + wing_uid + ')'
cfg['DV_PARAM'] = '( ' + ted_uid + '_sym, ' + ','.join(
hinge_sym_list) + ')'
cfg['DV_VALUE'] = str(defl / 1000) # SU2 use 1/1000 degree...
cfg['MESH_FILENAME'] = defl_mesh_name
defl_mesh_sym_name = aircraft_name + '_TED_' + ted_uid + '_defl' + str(
defl) + '_sym.su2'
cfg['MESH_OUT_FILENAME'] = defl_mesh_sym_name
config_file_name = 'ConfigROT_sym_defl' + str(defl) + '.cfg'
config_path = os.path.join(wkdir, 'MESH', config_dir_name,
config_file_name)
su2f.write_config(config_path, cfg)
log.info(config_path + ' have has been written.')
def add_skin_friction(cpacs_path, cpacs_out_path):
""" Function to add the skin frinction drag coeffienct to aerodynamic coefficients
Function 'add_skin_friction' add the skin friction drag 'cd0' to the
SU2 and pyTornado aeroMap, if their UID is not geven, it will add skin
friction to all aeroMap. For each aeroMap it creates a new aeroMap where
the skin friction drag coeffienct is added with the correct projcetions.
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str): Path to CPACS output file
"""
tixi = cpsf.open_tixi(cpacs_path)
tigl = cpsf.open_tigl(tixi)
wing_area_max, wing_span_max = get_largest_wing_dim(tixi, tigl)
analyses_xpath = '/cpacs/toolspecific/CEASIOMpy/geometry/analysis'
# Requiered input data from CPACS
wetted_area = cpsf.get_value(tixi, analyses_xpath + '/wettedArea')
# Wing area/span, default values will be calated if no value found in the CPACS file
wing_area_xpath = analyses_xpath + '/wingArea'
wing_area = cpsf.get_value_or_default(tixi, wing_area_xpath, wing_area_max)
wing_span_xpath = analyses_xpath + '/wingSpan'
wing_span = cpsf.get_value_or_default(tixi, wing_span_xpath, wing_span_max)
aeromap_uid_list = []
# Try to get aeroMapToCalculate
aeroMap_to_clculate_xpath = SF_XPATH + '/aeroMapToCalculate'
if tixi.checkElement(aeroMap_to_clculate_xpath):
aeromap_uid_list = cpsf.get_string_vector(tixi,
aeroMap_to_clculate_xpath)
else:
aeromap_uid_list = []
# If no aeroMap in aeroMapToCalculate, get all existing aeroMap
if len(aeromap_uid_list) == 0:
try:
aeromap_uid_list = apmf.get_aeromap_uid_list(tixi)
except:
raise ValueError(
'No aeroMap has been found in this CPACS file, skin friction cannot be added!'
)
# Get unique aeroMap list
aeromap_uid_list = list(set(aeromap_uid_list))
new_aeromap_uid_list = []
# Add skin friction to all listed aeroMap
for aeromap_uid in aeromap_uid_list:
log.info('adding skin friction coefficients to: ' + aeromap_uid)
# Get orignial aeroPerformanceMap
AeroCoef = apmf.get_aeromap(tixi, aeromap_uid)
AeroCoef.complete_with_zeros()
# Create new aeroCoefficient object to store coef with added skin friction
AeroCoefSF = apmf.AeroCoefficient()
AeroCoefSF.alt = AeroCoef.alt
AeroCoefSF.mach = AeroCoef.mach
AeroCoefSF.aoa = AeroCoef.aoa
AeroCoefSF.aos = AeroCoef.aos
# Iterate over all cases
case_count = AeroCoef.get_count()
for case in range(case_count):
# Get parameters for this case
alt = AeroCoef.alt[case]
mach = AeroCoef.mach[case]
aoa = AeroCoef.aoa[case]
aos = AeroCoef.aos[case]
# Calculate Cd0 for this case
cd0 = estimate_skin_friction_coef(wetted_area,wing_area,wing_span, \
mach,alt)
# Projection of cd0 on cl, cd and cs axis
#TODO: Should Cd0 be projected or not???
aoa_rad = math.radians(aoa)
aos_rad = math.radians(aos)
cd0_cl = cd0 * math.sin(aoa_rad)
cd0_cd = cd0 * math.cos(aoa_rad) * math.cos(aos_rad)
cd0_cs = cd0 * math.sin(aos_rad)
# Update aerodynamic coefficients
cl = AeroCoef.cl[case] + cd0_cl
cd = AeroCoef.cd[case] + cd0_cd
cs = AeroCoef.cs[case] + cd0_cs
# Shoud we change something? e.i. if a force is not apply at aero center...?
if len(AeroCoef.cml):
cml = AeroCoef.cml[case]
else:
cml = 0.0 # Shoud be change, just to test pyTornado
if len(AeroCoef.cmd):
cmd = AeroCoef.cmd[case]
else:
cmd = 0.0
if len(AeroCoef.cms):
cms = AeroCoef.cms[case]
else:
cms = 0.0
# Add new coefficients into the aeroCoefficient object
AeroCoefSF.add_coefficients(cl, cd, cs, cml, cmd, cms)
# Create new aeroMap UID
aeromap_sf_uid = aeromap_uid + '_SkinFriction'
new_aeromap_uid_list.append(aeromap_sf_uid)
# Create new description
description_xpath = tixi.uIDGetXPath(aeromap_uid) + '/description'
sf_description = cpsf.get_value(
tixi,
description_xpath) + ' Skin friction has been add to this AeroMap.'
apmf.create_empty_aeromap(tixi, aeromap_sf_uid, sf_description)
# Save aeroCoefficient object Coef in the CPACS file
apmf.save_parameters(tixi, aeromap_sf_uid, AeroCoefSF)
apmf.save_coefficients(tixi, aeromap_sf_uid, AeroCoefSF)
# Get aeroMap list to plot
plot_xpath = '/cpacs/toolspecific/CEASIOMpy/aerodynamics/plotAeroCoefficient'
aeromap_to_plot_xpath = plot_xpath + '/aeroMapToPlot'
if tixi.checkElement(aeromap_to_plot_xpath):
aeromap_uid_list = cpsf.get_string_vector(tixi, aeromap_to_plot_xpath)
new_aeromap_to_plot = aeromap_uid_list + new_aeromap_uid_list
new_aeromap_to_plot = list(set(new_aeromap_to_plot))
cpsf.add_string_vector(tixi, aeromap_to_plot_xpath,
new_aeromap_to_plot)
else:
cpsf.create_branch(tixi, aeromap_to_plot_xpath)
cpsf.add_string_vector(tixi, aeromap_to_plot_xpath,
new_aeromap_uid_list)
log.info('AeroMap "' + aeromap_uid + '" has been added to the CPACS file')
cpsf.close_tixi(tixi, cpacs_out_path)
def generate_config_deformed_mesh(cpacs_path,
cpacs_out_path,
skip_config=False,
skip_su2=False):
"""Function to generate all deform meshes with SU2 from CPACS data
Function 'generate_config_deformed_mesh' reads data in the CPACS file
and generate all the corresponding directory and config file which allow to
generate deformed meshes.
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str):Path to CPACS output file
skip_config (bool):
skip_su2 (bool):
"""
tixi = cpsf.open_tixi(cpacs_path)
wkdir = ceaf.get_wkdir_or_create_new(tixi)
# Get SU2 mesh path
su2_mesh_xpath = '/cpacs/toolspecific/CEASIOMpy/filesPath/su2Mesh'
su2_mesh_path = cpsf.get_value(tixi, su2_mesh_xpath)
if wkdir in su2_mesh_path:
log.info('The Baseline SU2 mesh is already in the working directory.')
else:
mesh_dir = os.path.join(wkdir, 'MESH')
if not os.path.isdir(mesh_dir):
os.mkdir(mesh_dir)
aircraft_name = cpsf.aircraft_name(tixi)
su2_mesh_new_path = os.path.join(mesh_dir,
aircraft_name + '_baseline.su2')
shutil.copyfile(su2_mesh_path, su2_mesh_new_path)
tixi.updateTextElement(su2_mesh_xpath, su2_mesh_new_path)
if not skip_config:
# Control surfaces deflections
control_surf_xpath = SU2_XPATH + '/options/clalculateCotrolSurfacesDeflections'
control_surf = cpsf.get_value_or_default(tixi, control_surf_xpath,
False)
if not control_surf:
log.warning(
'The CPACS file indicate that Control surface deflection should not be calculated!'
)
active_ted_list = []
else:
ted_df = get_ted_list(tixi)
# TODO: option to calculate only TED selected in cpacs
# if ...
# active_ted_xpath = SU2_XPATH + '/options/....'
# # check element
# active_ted_list = cpsf.get_string_vector(tixi,active_ted_xpath)
# else: calculate all TED adn all deflections from CPACS
# active_ted_list = ted_list
for i, row in ted_df.iterrows():
# Unwrap TED data from the dataframe
ted_uid = row['ted_uid']
wing_uid = row['wing_uid']
sym_dir = row['sym_dir']
defl_list = row['defl_list']
generate_mesh_def_config(tixi, wkdir, ted_uid, wing_uid,
sym_dir, defl_list)
if not skip_su2:
run_mesh_deformation(tixi, wkdir)
cpsf.close_tixi(tixi, cpacs_out_path)
