def toolspecific_update(fus_nb, awg, mw, out, cpacs_out_path):
""" The function that update the cpacs file after the Weight_unc_main
program.
Args:
fus_nb (integer): Number of fuselage [-].
awg (class): AircraftWingGeometry class.
mw (class): Masses and Weights class.
out (class): Output class.
cpacs_out_path (str): Path of the output file.
"""
tixi = open_tixi(cpacs_out_path)
# Path creation
create_branch(tixi, CREW_XPATH + "/cabinCrewMembers", False)
create_branch(tixi, PASS_XPATH, False)
# Path update
if not tixi.checkElement(CREW_XPATH +
"/cabinCrewMembers/cabinCrewMemberNb"):
tixi.createElement(CREW_XPATH + "/cabinCrewMembers",
"cabinCrewMemberNb")
tixi.updateDoubleElement(
CREW_XPATH + "/cabinCrewMembers/cabinCrewMemberNb", out.cabin_crew_nb,
"%g")
if not tixi.checkElement(PASS_XPATH + "/passNb"):
tixi.createElement(PASS_XPATH, "passNb")
tixi.updateIntegerElement(PASS_XPATH + "/passNb", out.pass_nb, "%i")
if not tixi.checkElement(PASS_XPATH + "/mass"):
tixi.createElement(PASS_XPATH, "mass")
tixi.updateDoubleElement(PASS_XPATH + "/mass", mw.mass_pass, "%g")
if not tixi.checkElement(PASS_XPATH + "/toiletNb"):
tixi.createElement(PASS_XPATH, "toiletNb")
tixi.updateIntegerElement(PASS_XPATH + "/toiletNb", int(out.toilet_nb),
"%i")
if not tixi.checkElement(PASS_XPATH + "/fuelMassMaxpass"):
tixi.createElement(PASS_XPATH, "fuelMassMaxpass")
FMP_PATH = PASS_XPATH + "/fuelMassMaxpass"
if not tixi.checkElement(FMP_PATH + "/description"):
tixi.createElement(FMP_PATH, "description")
tixi.updateTextElement(
FMP_PATH + "/description",
"Maximum amount of " + "fuel with maximum payload [kg]")
if not tixi.checkElement(FMP_PATH + "/mass"):
tixi.createElement(FMP_PATH, "mass")
tixi.updateDoubleElement(FMP_PATH + "/mass", mw.mass_fuel_maxpass, "%g")
tixi.save(cpacs_out_path)
return ()
def _save_quit(self):
# Iterate over all existing tabs
for tab in self.tab_list:
# Iterate in Variable dictionary of each tab
for key, var in tab.var_dict.items():
# Get the XPath from the GUI setting dictionary and crate a branch
name = tab.gui_dict[key][0]
xpath = tab.gui_dict[key][4]
create_branch(self.cpacs.tixi, xpath)
if name == "__AEROMAP_CHECHBOX":
aeromap_uid_list_str = ""
for aeromap_uid, aeromap_bool in tab.aeromap_var_dict.items():
if aeromap_bool.get():
aeromap_uid_list_str += aeromap_uid + ";"
if aeromap_uid_list_str == "":
messagebox.showerror(
"ValueError",
'In the Tab "'
+ tab.module_name
+ '", no value has been selected for "'
+ name
+ '" ',
)
raise TypeError("No value has been selected for " + name + " !")
self.cpacs.tixi.updateTextElement(xpath, aeromap_uid_list_str)
# '__AEROMAP_SELECTION' and list Type value will be saved as any other variable
else:
if str(var.get()) == "":
# Not working when it expect an 'int' or a 'float'
messagebox.showerror(
"ValueError",
'In the Tab "'
+ tab.module_name
+ '", no value has been entered for "'
+ name
+ '" ',
)
raise TypeError("No value has been entered for " + name + " !")
try:
self.cpacs.tixi.updateTextElement(xpath, str(var.get()))
except:
messagebox.showerror(
"TypeError",
'In the Tab "'
+ tab.module_name
+ '", the value "'
+ name
+ '" has not the correct type!',
)
raise TypeError(name + " has not the correct type!")
self.cpacs.save_cpacs(self.cpacs_out_path, overwrite=True)
self.quit()
def get_user_fuel(fus_nb, ui, cpacs_in):
""" Function to extract from the xml file the required input data,
the code will use the default value when they are missing.
INPUT
(int) fus_nb --Arg.: Number of fuselage.
(class) ui --Arg.: UserInputs class.
##======= Classes are defined in the InputClasses folder =======##
(char) cpacs_in --Arg.: Relative location of the xml file in the
ToolInput folder (cpacs option) or
relative location of the temp. xml file in
the ToolOutput folder (input option).
OUTPUT
(class) ui --Out.: UserInputs class.
(file) cpacs_in --Out.: Updated cpasc file
"""
log.info("Starting data extraction from CPACS file")
# Path creation ==========================================================
tixi = open_tixi(cpacs_in)
FUEL_PATH = "/cpacs/toolspecific/CEASIOMpy/fuels"
create_branch(tixi, FUEL_PATH, False)
if fus_nb:
for i in range(0, fus_nb):
if fus_nb > 1:
F = "fuelOnCabin" + str(i + 1)
else:
F = "fuelOnCabin"
if not tixi.checkElement(FUEL_PATH + "/" + F):
tixi.createElement(FUEL_PATH, F)
tixi.updateDoubleElement(FUEL_PATH + "/" + F, ui.F_FUEL[i],
"%g")
else:
ui.F_FUEL[i] = tixi.getDoubleElement(FUEL_PATH + "/" + F)
else:
if not tixi.checkElement(FUEL_PATH + "/fuelOnCabin"):
tixi.createElement(FUEL_PATH, "fuelOnCabin")
tixi.updateDoubleElement(FUEL_PATH + "/fuelOnCabin", ui.FUEL_ON_CABIN,
"%g")
# Modif Aidan: this code seems useless
# else:
# temp = tixi.updateDoubleElement(FUEL_PATH + '/fuelOnCabin',\
# ui.FUEL_ON_CABIN, '%g')
# if temp != ui.FUEL_ON_CABIN and temp > 0:
# ui.FUEL_ON_CABIN = temp
log.info("Data from CPACS file succesfully extracted")
# # Saving and closing the cpacs file --------------------------------------
tixi.save(cpacs_in)
return ui
def get_user_fuel(fus_nb, ui, cpacs_in):
"""Function to extract fuel data from a CPACS file
Function 'get_user_fuel' extracts fuel data from the CPACS file, the code
will use the default value when they are missing.
Args:
fus_nb (int): Number of fuselage.
ui (class): UserInputs class
cpacs_in (str): Path to the CPACS file
Returns:
ui (class): Modified UserInputs class
"""
log.info("Starting data extraction from CPACS file")
tixi = open_tixi(cpacs_in)
create_branch(tixi, FUEL_XPATH, False)
if fus_nb:
for i in range(0, fus_nb):
if fus_nb > 1:
F = "fuelOnCabin" + str(i + 1)
else:
F = "fuelOnCabin"
if not tixi.checkElement(FUEL_XPATH + "/" + F):
tixi.createElement(FUEL_XPATH, F)
tixi.updateDoubleElement(FUEL_XPATH + "/" + F, ui.F_FUEL[i],
"%g")
else:
ui.F_FUEL[i] = tixi.getDoubleElement(FUEL_XPATH + "/" + F)
else:
if not tixi.checkElement(FUEL_XPATH + "/fuelOnCabin"):
tixi.createElement(FUEL_XPATH, "fuelOnCabin")
tixi.updateDoubleElement(FUEL_XPATH + "/fuelOnCabin",
ui.FUEL_ON_CABIN, "%g")
else:
temp = tixi.updateDoubleElement(FUEL_XPATH + "/fuelOnCabin",
ui.FUEL_ON_CABIN, "%g")
if temp != ui.FUEL_ON_CABIN and temp > 0:
ui.FUEL_ON_CABIN = temp
log.info("Data from CPACS file succesfully extracted")
tixi.save(cpacs_in)
return ui
def cpacs_engine_update(ui, ed, mw, cpacs_out_path):
""" The function that update the cpacs file after the Weight_unc_main
program.
Args:
mw (class): MassesWeihts class.
ui (class): UserInputs class.
ed (class): EngineData class.
cpacs_out_path (str): Path of the CPACS output file.
"""
tixi = open_tixi(cpacs_out_path)
EN_XPATH = "/cpacs/vehicles/engines"
if tixi.checkElement(EN_XPATH):
tixi.removeElement(EN_XPATH)
for e in range(0, ed.NE):
EN_XPATH = "/cpacs/vehicles/engines/engine" + str(e + 1)
create_branch(tixi, EN_XPATH, True)
EN_UID = "EngineuID_" + str(e + 1)
add_uid(tixi, EN_XPATH, EN_UID)
tixi.createElement(EN_XPATH, "name")
if not ed.EN_NAME[e]:
EN_NAME = "Engine_" + str(e + 1)
tixi.updateTextElement(EN_XPATH + "/name", EN_NAME)
else:
tixi.updateTextElement(EN_XPATH + "/name", ed.EN_NAME[e])
ENA_XPATH = EN_XPATH + "/analysis/mass"
create_branch(tixi, ENA_XPATH, False)
add_uid(tixi, EN_XPATH, EN_UID + "_mass")
tixi.createElement(ENA_XPATH, "mass")
tixi.updateDoubleElement(ENA_XPATH + "/mass", ed.en_mass, "%g")
ENT_XPATH = EN_XPATH + "/analysis"
tixi.createElement(ENT_XPATH, "thrust00")
tixi.updateDoubleElement(ENT_XPATH + "/thrust00", ed.max_thrust, "%g")
tixi.save(cpacs_out_path)
return ()
def create_default_toolspecific():
"""Create a default XML /toolspecific based on all __spec__ xpath and
default values. Two CPACS file are created and saved in /utils/doc/
"""
CPACS_PATH = "./doc/empty_cpacs.xml"
tixi_in = open_tixi(CPACS_PATH)
tixi_out = open_tixi(CPACS_PATH)
for mod_name, specs in get_all_module_specs().items():
if specs is not None:
# Inputs
for entry in specs.cpacs_inout.inputs:
xpath = entry.xpath
if xpath.endswith("/"):
xpath = xpath[:-1]
value_name = xpath.split("/")[-1]
xpath_parent = xpath[:-(len(value_name) + 1)]
if not tixi_in.checkElement(xpath):
create_branch(tixi_in, xpath_parent)
if entry.default_value is not None:
value = str(entry.default_value)
else:
value = "No default value"
tixi_in.addTextElement(xpath_parent, value_name, value)
# Outputs
for entry in specs.cpacs_inout.outputs:
xpath = entry.xpath
create_branch(tixi_out, xpath)
TOOLSPECIFIC_INPUT_PATH = "./doc/input_toolspecifics.xml"
TOOLSPECIFIC_OUTPUT_PATH = "./doc/output_toolspecifics.xml"
tixi_in.save(TOOLSPECIFIC_INPUT_PATH)
tixi_out.save(TOOLSPECIFIC_OUTPUT_PATH)
def write_inouts(v, inout, tixi):
"""Write inputs or outputs to cpacs.
Write the specified input or the predicted output of the model to the
CPACS file.
Args:
v (DataFrame): Contains the inout, locations.
inout (np.array): Values of the inout.
Returns:
None.
"""
v.fillna("-", inplace=True)
for i, name in enumerate(v.index):
if v.loc[name, "setcmd"] != "-":
exec("{} = {}".format(name, inout[0][i]))
eval(v.loc[name, "setcmd"])
elif v.loc[name, "getcmd"] != "-":
xpath = v.loc[name, "getcmd"]
create_branch(tixi, xpath)
tixi.updateDoubleElement(xpath, inout[0][i], "%g")
def cpacs_update(mass_pass, out, mw, out_xml):
""" The function updates the cpacs file after the range analysis.
INPUT
(float) mass_pass --Arg.: Passenger mass, countig also the
extra mass.
(class) out --Arg.: RangeOutput class.
##======== Class is defined in the InputClasses folder =======##
(class) mw --Arg.: MassesWeights class.
##======= Class is defined in the InputClasses folder =======##
(char) out_xml --Arg.: Path of the output file.
OUTPUT
(file) cpacs.xml --Out.: Updated cpacs file.
"""
tixi = open_tixi(out_xml)
# PATH CHECKS ==========================================================
CEASIOM_PATH = "/cpacs/toolspecific/CEASIOMpy"
# Ranges
RANGE_PATH = CEASIOM_PATH + "/ranges"
R_DES_MAXP_PATH = RANGE_PATH + "/rangeMaxP/rangeDescription"
R_DES_MAXF_PATH = RANGE_PATH + "/rangeMaxF/rangeDescription"
R_DES_MAXIMUM_PATH = RANGE_PATH + "/rangeMaximum/rangeDescription"
create_branch(tixi, R_DES_MAXP_PATH + "/range", False)
create_branch(tixi, R_DES_MAXP_PATH + "/payload", False)
create_branch(tixi, R_DES_MAXF_PATH + "/range", False)
create_branch(tixi, R_DES_MAXF_PATH + "/payload", False)
create_branch(tixi, R_DES_MAXIMUM_PATH + "/range", False)
create_branch(tixi, R_DES_MAXIMUM_PATH + "/payload", False)
# Fuel consumption
FCONS_PATH = "/cpacs/toolspecific/CEASIOMpy/fuelConsumption"
FDES_PATH = FCONS_PATH + "/description"
FTO_PATH = FCONS_PATH + "/fuelForTakeOff"
FC_PATH = FCONS_PATH + "/fuelForClimb"
FCR_PATH = FCONS_PATH + "/fuelForCruise"
FL_PATH = FCONS_PATH + "/fuelForLoiter"
FLD_PATH = FCONS_PATH + "/fuelForLanding"
FAL_PATH = FCONS_PATH + "/fuelRemained"
create_branch(tixi, FDES_PATH, False)
create_branch(tixi, FTO_PATH, False)
create_branch(tixi, FC_PATH, False)
create_branch(tixi, FCR_PATH, False)
create_branch(tixi, FL_PATH, False)
create_branch(tixi, FLD_PATH, False)
create_branch(tixi, FAL_PATH, False)
# RANGES ===============================================================
# Max payload max range ------------------------------------------------
add_uid(tixi, R_DES_MAXP_PATH,
"Maximum_range_[km]" + "_with_maximum_payload_[kg]")
tixi.updateDoubleElement(R_DES_MAXP_PATH + "/range", out.ranges[1], "%g")
tixi.updateDoubleElement(R_DES_MAXP_PATH + "/payload", out.payloads[1],
"%g")
# Max fuel range with some payload -------------------------------------
add_uid(tixi, R_DES_MAXF_PATH,
"Range_[km]_with_" + "maximum_fuel_and_some_payload_[kg]")
tixi.updateDoubleElement(R_DES_MAXF_PATH + "/range", out.ranges[2], "%g")
tixi.updateDoubleElement(R_DES_MAXF_PATH + "/payload", out.payloads[2],
"%g")
# Maximum range, no payload and max fuel -------------------------------
add_uid(tixi, R_DES_MAXIMUM_PATH,
"Maximum_range_[km]_with_" + "max_fuel_and_no_payload_[kg]")
tixi.updateDoubleElement(R_DES_MAXIMUM_PATH + "/range", out.ranges[3],
"%g")
tixi.updateDoubleElement(R_DES_MAXIMUM_PATH + "/payload", out.payloads[3],
"%g")
# FUEL CONSUMPTION =====================================================
add_uid(
tixi, FDES_PATH,
"Fuel required for each flight phase " + "[kg], with maximum payload.")
tixi.updateDoubleElement(FTO_PATH, mw.mf_for_to, "%g")
tixi.updateDoubleElement(FC_PATH, mw.mf_for_climb, "%g")
tixi.updateDoubleElement(FCR_PATH, mw.mf_for_cruise, "%g")
tixi.updateDoubleElement(FL_PATH, mw.mf_for_loiter, "%g")
tixi.updateDoubleElement(FLD_PATH, mw.mf_for_landing, "%g")
tixi.updateDoubleElement(FAL_PATH, mw.mf_after_land, "%g")
# Saving and closing the new cpacs file inside the ToolOutput folder ---
tixi.save(out_xml)
return out_xml
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 = open_tixi(cpacs_in)
create_branch(tixi, FUEL_XPATH, False)
create_branch(tixi, GEOM_XPATH, False)
create_branch(tixi, RANGE_XPATH, False)
create_branch(tixi, PILOTS_XPATH, False)
create_branch(tixi, CAB_CREW_XPATH, False)
create_branch(tixi, PASS_XPATH, False)
create_branch(tixi, ML_XPATH, False)
create_branch(tixi, PROP_XPATH, False)
# cpacs/vehicles
MC_XPATH = MASSBREAKDOWN_XPATH + "/payload/mCargo/massDescription"
create_branch(tixi, MC_XPATH, False)
create_branch(tixi, F_XPATH, False)
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 = get_value_or_default(tixi, GEOM_XPATH + "/floorsNb",
ui.FLOORS_NB)
adui.VRT_THICK = get_value_or_default(tixi, GEOM_XPATH + "/virtualThick",
0.00014263)
adui.VRT_STR_DENSITY = get_value_or_default(tixi,
GEOM_XPATH + "/virtualDensity",
2700.0)
ui.H_LIM_CABIN = get_value_or_default(tixi, GEOM_XPATH + "/cabinHeight",
2.3)
# People =================================================================
# Pilots user input data
adui.PILOT_NB = get_value_or_default(tixi, PILOTS_XPATH + "/pilotNb", 2)
adui.MASS_PILOT = get_value_or_default(tixi, PILOTS_XPATH + "/pilotMass",
102.0)
adui.MASS_CABIN_CREW = get_value_or_default(
tixi, CAB_CREW_XPATH + "/cabinCrewMemberMass", 68.0)
adui.MASS_PASS = get_value_or_default(tixi, PASS_XPATH + "/passMass",
105.0)
adui.PASS_BASE_DENSITY = get_value_or_default(tixi,
PASS_XPATH + "/passDensity",
1.66)
adui.PASS_PER_TOILET = 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 = get_value_or_default(tixi, F_XPATH + "/density", 800)
adui.RES_FUEL_PERC = 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 = get_value_or_default(tixi, ML_XPATH + "/maxPayload", 0.0)
ui.MAX_FUEL_VOL = get_value_or_default(tixi, ML_XPATH + "/maxFuelVol", 0.0)
ui.MASS_CARGO = 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 = 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")
tixi.save(cpacs_in)
return (ed, ui, adui)
def get_engine_inputs(ui, ed, cpacs_in):
""" Function to extract from the xml file the required input data,
the code will use the default value when they are missing.
INPUT
(class) ui --Arg.: UserInputs class.
(class) ed --Arg.: EngineData class.
##======= Class ares defined in the InputClasses folder =======##
(char) cpacs_in --Arg.: Relative location of the xml file in the
ToolInput folder (cpacs option) or
relative location of the temp. xml file in
the ToolOutput folder (input option).
OUTPUT
(class) ed --Out.: EngineData class.
(file) cpacs_in --Out.: Updated cpasc file
"""
log.info("Starting engine data extraction from CPACS file")
tixi = open_tixi(cpacs_in)
create_branch(tixi, PROP_XPATH, False)
# Propulsion =============================================================
if not tixi.checkElement(PROP_XPATH + "/turboprop"):
create_branch(tixi, PROP_XPATH, False)
tixi.createElement(PROP_XPATH, "turboprop")
if ed.TURBOPROP:
tixi.updateTextElement(PROP_XPATH + "/turboprop", "True")
else:
tixi.updateTextElement(PROP_XPATH + "/turboprop", "False")
else:
temp = tixi.getTextElement(PROP_XPATH + "/turboprop")
if temp == "False":
ed.TURBOPROP = False
else:
ed.TURBOPROP = True
if not tixi.checkElement(PROP_XPATH + "/auxiliaryPowerUnit"):
tixi.createElement(PROP_XPATH, "auxiliaryPowerUnit")
if ed.APU:
tixi.updateTextElement(PROP_XPATH + "/auxiliaryPowerUnit", "True")
else:
tixi.updateTextElement(PROP_XPATH + "/auxiliaryPowerUnit", "False")
else:
temp = tixi.getTextElement(PROP_XPATH + "/auxiliaryPowerUnit")
if temp == "False":
ed.APU = False
else:
ed.APU = True
if not tixi.checkElement(PROP_XPATH + "/engineNumber"):
tixi.createElement(PROP_XPATH, "engineNumber")
tixi.updateIntegerElement(PROP_XPATH + "/engineNumber", ed.NE, "%i")
else:
ed.NE = tixi.getIntegerElement(PROP_XPATH + "/engineNumber")
# Engines (TODO: check this _XPATH)
mp = []
tp = []
EN_XPATH = "/cpacs/vehicles/engines"
if tixi.checkElement(EN_XPATH):
for e in range(0, ed.NE - 1):
if ed.NE > 1:
EN_XPATH += "/engine" + str(e + 1)
else:
EN_XPATH += "/engine"
if not tixi.checkElement(EN_XPATH):
raise Exception("Engine definition inclomplete, missing" +
" one or more engines in the cpacs file")
if not tixi.checkElement(EN_XPATH + "/name"):
ed.EN_NAME.append("Engine_" + str(e + 1))
tixi.createElement(EN_XPATH, "name")
tixi.updateTextElement(EN_XPATH + "/name", ed.EN_NAME[e])
else:
if e > len(ed.EN_NAME):
ed.EN_NAME.append(tixi.getTextElement(EN_XPATH + "/name"))
ENA_XPATH = EN_XPATH + "/analysis/mass"
if tixi.checkElement(ENA_XPATH + "/mass"):
ed.en_mass = tixi.getDoubleElement(ENA_XPATH + "/mass")
mp.append(ed.en_mass)
if e > 0 and ed.en_mass != mp[e - 1]:
raise Exception("The engines have different masses, this" +
" can lead to an unbalanced aircraft")
elif ed.en_mass:
tixi.createElement(ENA_XPATH, "mass")
tixi.updateDoubleElement(ENA_XPATH + "/mass", ed.en_mass, "%g")
else:
raise Exception("Engine definition inclomplete, missing" +
" engine mass in the cpacs file")
if tixi.checkElement(EN_XPATH + "/analysis/thrust00"):
ed.max_thrust = tixi.getDoubleElement(EN_XPATH +
"/analysis/thrust00")
tp.append(ed.max_thrust)
if e > 0 and ed.max_thrust != tp[e - 1]:
raise Exception("The engines have different thrust, this")
# + ' can lead to an unbalanced flight')
elif ed.max_thrust:
tixi.createElement(EN_XPATH, "/analysisthrust00")
tixi.updateDoubleElement(EN_XPATH + "/analysis/thrust00",
ed.max_thrust, "%g")
else:
raise Exception("Engine definition inclomplete, missing" +
" engine thrust in the cpacs file")
log.info("Data from CPACS file succesfully extracted")
tixi.save(cpacs_in)
return ed
def get_data(ui, bi, mw, ed, cpacs_in):
""" The function extracts from the xml file the required input data,
the code will use the default value when they are missing.
INPUT
(class) ui --Arg.: UserInputs class.
(class) bi --Arg.: BalanceInputs class.
(class) mw --Arg.: MassesWeight class.
(class) ed --Arg.: EngineData class.
##======= Classes are defined in the InputClasses folder =======##
(char) cpacs_in --Arg.: Relative location of the xml file in the
ToolInput folder (cpacs option) or
relative location of the temp. xml file in
the ToolOutput folder (input option).
OUTPUT
(class) mw --Out.: MassesWeight class updated.
(class) ed --Out.: EngineData class updated.
(file) cpacs_in --Out.: Updated cpasc file.
"""
log.info("CPACS file path check")
# path definition ========================================================
# Opening CPACS file
tixi = open_tixi(cpacs_in)
TSPEC_PATH = "/cpacs/toolspecific/CEASIOMpy"
GEOM_PATH = TSPEC_PATH + "/geometry"
FMP_PATH = TSPEC_PATH + "/weight/passengers/fuelMassMaxpass/mass"
PROP_PATH = TSPEC_PATH + "/propulsion"
MASS_PATH = "/cpacs/vehicles/aircraft/model/analyses/massBreakdown"
MTOM_PATH = MASS_PATH + "/designMasses/mTOM/mass"
F_PATH = MASS_PATH + "/fuel/massDescription/mass"
OEM_PATH = MASS_PATH + "/mOEM/massDescription/mass"
PAY_PATH = MASS_PATH + "/payload/massDescription/mass"
EN_PATH = "/cpacs/vehicles/engines/engine1/analysis/mass/mass"
BC_PATH = TSPEC_PATH + "/balance/userBalance"
create_branch(tixi, BC_PATH, False)
# Compulsory path checks =================================================
if not tixi.checkElement(TSPEC_PATH):
raise Exception("Missing required toolspecific path. Run " +
"Weight_unc_main.py," +
" in the 4Weight_unc_module folder.")
elif not tixi.checkElement(MASS_PATH):
raise Exception("Missing required massBreakdown path. Run " +
"Weight_unc_main.py," +
" in the 4Weight_unc_module folder.")
elif not tixi.checkElement(MTOM_PATH):
raise Exception("Missing required mTOM/mass path. Run " +
"Weight_unc_main.py," +
" in the 4Weight_unc_module folder.")
elif not tixi.checkElement(FMP_PATH):
raise Exception("Missing required fuelMassMaxpass/mass path. Run " +
"Weight_unc_main.py," +
" in the 4Weight_unc_module folder.")
elif not tixi.checkElement(OEM_PATH):
raise Exception("Missing required mOEM/massDescription/mass " +
"path. Run Weight_unc_main.py," +
" in the 4Weight_unc_module folder.")
elif not tixi.checkElement(PAY_PATH):
raise Exception("Missing required payload/massDescription/mass " +
"path. Run Weight_unc_main.py," +
" in the 4Weight_unc_module folder.")
elif not tixi.checkElement(F_PATH):
raise Exception("Missing required /fuel/massDescription/mass " +
"path. Run Weight_unc_main.py," +
" in the 4Weight_unc_module folder.")
elif not tixi.checkElement(EN_PATH):
raise Exception("Missing required /cpacs/vehicles/engines/engine1" +
"/analysis/mass path. Run Weight_unc_main.py," +
" in the 4Weight_unc_module folder.")
else:
log.info("All path correctly defined in the toolinput.xml file, " +
"beginning data extracction.")
# Gathering data =========================================================
# Geometry Data
if not tixi.checkElement(GEOM_PATH + "/floorsNb"):
tixi.createElement(GEOM_PATH, "floorsNb")
tixi.updateDoubleElement(GEOM_PATH + "/floorsNb", ui.FLOORS_NB, "%g")
else:
temp = tixi.getDoubleElement(GEOM_PATH + "/floorsNb")
if temp != ui.FLOORS_NB and temp > 0:
ui.FLOORS_NB = temp
if not tixi.checkElement(GEOM_PATH + "/cabinHeight"):
tixi.createElement(GEOM_PATH, "cabinHeight")
tixi.updateDoubleElement(GEOM_PATH + "/cabinHeight", ui.H_LIM_CABIN,
"%g")
else:
temp = tixi.getDoubleElement(GEOM_PATH + "/cabinHeight")
if temp != ui.H_LIM_CABIN and temp > 0:
ui.H_LIM_CABIN = temp
# User Case Balance
if not tixi.checkElement(BC_PATH + "/userCase"):
tixi.createElement(BC_PATH, "userCase")
if bi.USER_CASE:
tixi.updateTextElement(BC_PATH + "/userCase", "True")
else:
tixi.updateTextElement(BC_PATH + "/userCase", "False")
else:
temp = tixi.getTextElement(BC_PATH + "/userCase")
if temp == "False":
bi.USER_CASE = False
else:
bi.USER_CASE = True
if bi.USER_CASE:
if tixi.checkElement(BC_PATH + "/fuelPercentage"):
bi.F_PERC = tixi.getDoubleElement(BC_PATH + "/fuelPercentage")
elif bi.F_PERC:
tixi.createElement(BC_PATH, "fuelPercentage")
tixi.updateDoubleElement(BC_PATH + "/fuelPercentage", bi.F_PERC,
"%g")
else:
raise Exception("User balance option defined" +
" True but no fuel percentage data in the" +
" CPACS file or in th BalanceInput class.")
if tixi.checkElement(BC_PATH + "/payloadPercentage"):
bi.P_PERC = tixi.getDoubleElement(BC_PATH + "/payloadPercentage")
elif bi.P_PERC:
tixi.createElement(BC_PATH, "payloadPercentage")
tixi.updateDoubleElement(BC_PATH + "/payloadPercentage", bi.P_PERC,
"%g")
else:
raise Exception("User balance option defined" +
" True but no payload percentage data in" +
" the CPACS file or in th BalanceInput class.")
# Engines Data
ed.en_mass = tixi.getDoubleElement(EN_PATH)
if not tixi.checkElement(PROP_PATH + "/wingMountedEngine"):
create_branch(tixi, PROP_PATH, False)
tixi.createElement(PROP_PATH, "wingMountedEngine")
if ed.WING_MOUNTED:
tixi.updateTextElement(PROP_PATH + "/wingMountedEngine", "True")
else:
tixi.updateTextElement(PROP_PATH + "/wingMountedEngine", "False")
else:
temp = tixi.getTextElement(PROP_PATH + "/wingMountedEngine")
if temp == "False":
ed.WING_MOUNTED = False
else:
ed.WING_MOUNTED = True
if not tixi.checkElement(PROP_PATH + "/userEnginePlacement"):
tixi.createElement(PROP_PATH, "userEnginePlacement")
if bi.USER_EN_PLACEMENT:
tixi.updateTextElement(PROP_PATH + "/userEnginePlacement", "True")
else:
tixi.updateTextElement(PROP_PATH + "/userEnginePlacement", "False")
else:
temp = tixi.getTextElement(PROP_PATH + "/userEnginePlacement")
if temp == "False":
bi.USER_EN_PLACEMENT = False
else:
bi.USER_EN_PLACEMENT = True
if not tixi.checkElement(PROP_PATH + "/engineNumber"):
create_branch(tixi, PROP_PATH, False)
tixi.createElement(PROP_PATH, "engineNumber")
tixi.updateIntegerElement(PROP_PATH + "/engineNumber", ed.NE, "%i")
else:
ed.NE = tixi.getIntegerElement(PROP_PATH + "/engineNumber")
# User Engine Placement
tp = []
ed.EN_NAME = []
if tixi.checkElement(EN_PATH):
for e in range(0, ed.NE):
EN_PATH = "/cpacs/vehicles/engines"
if ed.NE > 1:
EN_PATH += "/engine" + str(e + 1)
else:
EN_PATH += "/engine"
if not tixi.checkElement(EN_PATH):
raise Exception("Engine definition inclomplete, missing" +
" one or more engines in the cpacs file")
if not tixi.checkElement(EN_PATH + "/name"):
ed.EN_NAME.append("Engine_" + str(e + 1))
else:
ed.EN_NAME.append(tixi.getTextElement(EN_PATH + "/name"))
ENA_PATH = EN_PATH + "/analysis/mass"
if tixi.checkElement(ENA_PATH):
ed.en_mass = tixi.getDoubleElement(ENA_PATH + "/mass")
tp.append(ed.en_mass)
if e > 0 and ed.en_mass != tp[e - 1]:
log.warning("The engines have different masses," +
"this can lead to an unbalanced aircraft")
elif ed.en_mass:
tixi.createElement(ENA_PATH, "mass")
tixi.updateDoubleElement(ENA_PATH + "/mass", ed.en_mass, "%g")
else:
raise Exception("Engine definition inclomplete, missing" +
" engine mass in the cpacs file")
s = np.shape(ed.EN_PLACEMENT)
warn = False
if not ed.NE:
raise Exception("No engine defined for the aircraft")
elif s[0] < ed.NE or s[1] < 3 or np.any(ed.EN_PLACEMENT) == False:
warn = True
else:
log.info("EngineData class defined correctly.")
s = ed.EN_PLACEMENT
if bi.USER_EN_PLACEMENT:
ed.EN_PLACEMENT = []
for e in range(1, ed.NE + 1):
if ed.NE > 1:
ENLOC_PATH = "/cpacs/vehicles/engines/engine" + str(
e) + "/analysis/mass/location"
else:
ENLOC_PATH = "/cpacs/vehicles/engines/engine/analysis/mass/location"
if not tixi.checkElement(ENLOC_PATH) and warn:
raise Exception("User engine Placement option defined" +
" True but no engine placement data in the" +
" CPACS file.")
if not tixi.checkElement(ENLOC_PATH) and not warn:
create_branch(tixi, ENLOC_PATH, False)
tixi.createElement(ENLOC_PATH, "x")
tixi.createElement(ENLOC_PATH, "y")
tixi.createElement(ENLOC_PATH, "z")
tixi.updateDoubleElement(ENLOC_PATH + "/x", s[e - 1][0], "%g")
tixi.updateDoubleElement(ENLOC_PATH + "/y", s[e - 1][1], "%g")
tixi.updateDoubleElement(ENLOC_PATH + "/z", s[e - 1][2], "%g")
ed.EN_PLACEMENT.append([s[e - 1][0], s[e - 1][1], s[e - 1][2]])
else:
x = tixi.getDoubleElement(ENLOC_PATH + "/x")
y = tixi.getDoubleElement(ENLOC_PATH + "/y")
z = tixi.getDoubleElement(ENLOC_PATH + "/z")
ed.EN_PLACEMENT.append([x, y, z])
ed.EN_PLACEMENT = np.array(ed.EN_PLACEMENT)
# REQUIRED TOOLSPECIFIC DATA ============================================
# Fuel
mw.mass_fuel_maxpass = tixi.getDoubleElement(FMP_PATH)
# REQUIRED MASSBREAKDOWN DATA ===========================================
mw.maximum_take_off_mass = tixi.getDoubleElement(MTOM_PATH)
mw.operating_empty_mass = tixi.getDoubleElement(OEM_PATH)
mw.mass_payload = tixi.getDoubleElement(PAY_PATH)
mw.mass_fuel_tot = tixi.getDoubleElement(F_PATH)
log.info("Data from CPACS file succesfully extracted")
# # Saving and closing the cpacs file ======================================
tixi.save(cpacs_in)
return (mw, ed)
def generate_su2_cfd_config(cpacs_path, cpacs_out_path, wkdir):
"""Function to create SU2 confif file.
Function 'generate_su2_cfd_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
cpacs = CPACS(cpacs_path)
# Get SU2 mesh path
su2_mesh_path = get_value(cpacs.tixi, SU2MESH_XPATH)
# Get SU2 settings
max_iter_xpath = SU2_XPATH + "/settings/maxIter"
max_iter = get_value_or_default(cpacs.tixi, max_iter_xpath, 200)
cfl_nb_xpath = SU2_XPATH + "/settings/cflNumber"
cfl_nb = get_value_or_default(cpacs.tixi, cfl_nb_xpath, 1.0)
mg_level_xpath = SU2_XPATH + "/settings/multigridLevel"
mg_level = get_value_or_default(cpacs.tixi, mg_level_xpath, 3)
# Mesh Marker
bc_wall_xpath = SU2_XPATH + "/boundaryConditions/wall"
bc_farfield_xpath = SU2_XPATH + "/boundaryConditions/farfield"
bc_wall_list, engine_bc_list = get_mesh_marker(su2_mesh_path)
create_branch(cpacs.tixi, bc_wall_xpath)
bc_wall_str = ";".join(bc_wall_list)
cpacs.tixi.updateTextElement(bc_wall_xpath, bc_wall_str)
create_branch(cpacs.tixi, bc_farfield_xpath)
bc_farfiled_str = ";".join(engine_bc_list)
cpacs.tixi.updateTextElement(bc_farfield_xpath, bc_farfiled_str)
# Fixed CL parameters
fixed_cl_xpath = SU2_XPATH + "/fixedCL"
fixed_cl = get_value_or_default(cpacs.tixi, fixed_cl_xpath, "NO")
target_cl_xpath = SU2_XPATH + "/targetCL"
target_cl = get_value_or_default(cpacs.tixi, target_cl_xpath, 1.0)
if fixed_cl == "NO":
active_aeroMap_xpath = SU2_XPATH + "/aeroMapUID"
aeromap_uid = get_value(cpacs.tixi, active_aeroMap_xpath)
log.info(
f'Configuration file for "{aeromap_uid}" calculation will be created.'
)
active_aeromap = cpacs.get_aeromap_by_uid(aeromap_uid)
# Get parameters of the aeroMap (altitude, machNumber, angleOfAttack, angleOfSideslip)
alt_list = active_aeromap.get("altitude").tolist()
mach_list = active_aeromap.get("machNumber").tolist()
aoa_list = active_aeromap.get("angleOfAttack").tolist()
aos_list = active_aeromap.get("angleOfSideslip").tolist()
param_count = len(alt_list)
else: # if fixed_cl == 'YES':
log.info(
"Configuration file for fixed CL calculation will be created.")
# Parameters fixed CL calulation
param_count = 1
# Create a new aeroMap
fix_cl_aeromap = cpacs.create_aeromap("aeroMap_fixedCL_SU2")
fix_cl_aeromap.description = "AeroMap created for SU2 fixed CL value of: " + str(
target_cl)
# Get cruise mach and altitude
cruise_mach_xpath = RANGE_XPATH + "/cruiseMach"
mach = get_value_or_default(cpacs.tixi, cruise_mach_xpath, 0.78)
cruise_alt_xpath = RANGE_XPATH + "/cruiseAltitude"
alt = get_value_or_default(cpacs.tixi, cruise_alt_xpath, 12000)
# Add new parameters to the aeroMap and save it
fix_cl_aeromap.add_row(alt=alt, mach=mach, aos=0.0, aoa=0.0)
fix_cl_aeromap.save()
# Parameter lists
alt_list = [alt]
mach_list = [mach]
aoa_list = [0.0]
aos_list = [0.0]
# Get and modify the default configuration file
cfg = ConfigFile(DEFAULT_CONFIG_PATH)
# General parmeters
cfg["REF_LENGTH"] = cpacs.aircraft.ref_lenght
cfg["REF_AREA"] = cpacs.aircraft.ref_area
cfg["REF_ORIGIN_MOMENT_X"] = cpacs.aircraft.ref_point_x
cfg["REF_ORIGIN_MOMENT_Y"] = cpacs.aircraft.ref_point_y
cfg["REF_ORIGIN_MOMENT_Z"] = cpacs.aircraft.ref_point_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, " + ",".join(engine_bc_list) + ")"
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 = Atmosphere(alt)
cfg["MACH_NUMBER"] = mach
cfg["AOA"] = aoa
cfg["SIDESLIP_ANGLE"] = aos
cfg["FREESTREAM_PRESSURE"] = Atm.pressure[0]
cfg["FREESTREAM_TEMPERATURE"] = Atm.temperature[0]
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)
cfg.write_file(config_output_path, overwrite=True)
# Damping derivatives
damping_der_xpath = SU2_XPATH + "/options/clalculateDampingDerivatives"
damping_der = get_value_or_default(cpacs.tixi, damping_der_xpath,
False)
if damping_der:
rotation_rate_xpath = SU2_XPATH + "/options/rotationRate"
rotation_rate = get_value_or_default(cpacs.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)
cfg.write_file(config_output_path, overwrite=True)
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)
cfg.write_file(config_output_path, overwrite=True)
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)
cfg.write_file(config_output_path, overwrite=True)
log.info("Damping derivatives cases directory has been created.")
# Control surfaces deflections
control_surf_xpath = SU2_XPATH + "/options/clalculateCotrolSurfacesDeflections"
control_surf = get_value_or_default(cpacs.tixi, control_surf_xpath,
False)
if control_surf:
# Get deformed mesh list
su2_def_mesh_xpath = SU2_XPATH + "/availableDeformedMesh"
if cpacs.tixi.checkElement(su2_def_mesh_xpath):
su2_def_mesh_list = get_string_vector(cpacs.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)
cfg.write_file(config_output_path, overwrite=True)
# TODO: change that, but if it is save in tooloutput it will be erease by results...
cpacs.save_cpacs(cpacs_out_path, overwrite=True)
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 = open_tixi(cpacs_path)
sumo_dir = get_results_directory("SUMOAutoMesh")
su2_mesh_path = os.path.join(sumo_dir, "ToolOutput.su2")
sumo_file_xpath = "/cpacs/toolspecific/CEASIOMpy/filesPath/sumoFilePath"
sumo_file_path = 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 = 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
with change_working_dir(sumo_dir):
command = ["open", "/Applications/SUMO/dwfsumo.app/"]
# /Applications/SUMO/dwfsumo.app/Contents/MacOS/dwfsumo
# -batch output=su2 -tetgen-options=pq1.16VY ToolOutput.smx
os.system(" ".join(command))
input("Press ENTER to continue...")
elif current_os == "Linux":
log.info("Your OS is Linux")
# Check if SUMO is installed
soft_dict = get_install_path(["sumo"])
# Run SUMO in batch
output = "-output=su2"
options = "-tetgen-options=pq1.16VY" # See Tetgen help for more options
# Command line to run: sumo -batch -output=su2 -tetgen-options=pq1.16VY ToolOutput.smx
command = [
soft_dict["sumo"], "-batch", output, options, sumo_file_path
]
with change_working_dir(sumo_dir):
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 NotImplementedError("OS not supported yet!")
else:
raise OSError("OS not recognize!")
# Copy the mesh in the MESH directory
su2_mesh_name = aircraft_name(tixi) + "_baseline.su2"
su2_mesh_new_path = os.path.join(sumo_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.")
create_branch(tixi, SU2MESH_XPATH)
tixi.updateTextElement(SU2MESH_XPATH, su2_mesh_new_path)
os.remove(su2_mesh_path)
else:
raise ValueError("No SU2 Mesh file has been generated!")
tixi.save(cpacs_out_path)
def get_data(mw, ri, cpacs_in):
""" The function extracts from the xml file the required input data,
the code will use the default value when they are missing.
INPUT
(class) mw --Arg.: MassesWeight class updated
(class) ri --Arg.: RangeInput class updated
##======= Classes are defined in the Input_classes folder =======##
(char) opt --Arg.: Cpacs or input option
(char) cpacs_in --Arg.: Relative location of the xml file in the
ToolInput folder (cpacs option) or
relative location of the temp. xml file in
the ToolOutput folder (input option).
OUTPUT
(class) mw --Out.: MassesWeight class updated.
(class) ri --Out.: RangeInput class updated.
(file) cpacs_in --Out.: Updated cpasc file.
"""
log.info("CPACS file path check")
# path definition ========================================================
# Opening CPACS file
tixi = open_tixi(cpacs_in)
TSPEC_PATH = "/cpacs/toolspecific/CEASIOMpy"
W_PATH = TSPEC_PATH + "/weight"
C_PATH = W_PATH + "/crew"
P_PATH = C_PATH + "/pilots"
CC_PATH = C_PATH + "/cabinCrewMembers"
PASS_PATH = W_PATH + "/passengers"
FMP_PATH = PASS_PATH + "/fuelMassMaxpass/mass"
PROP_PATH = TSPEC_PATH + "/propulsion"
RANGE_PATH = TSPEC_PATH + "/ranges"
MASS_PATH = "/cpacs/vehicles/aircraft/model/analyses/massBreakdown"
DM_PATH = MASS_PATH + "/designMasses"
MTOM_PATH = DM_PATH + "/mTOM/mass"
F_PATH = MASS_PATH + "/fuel/massDescription/mass"
OEM_PATH = MASS_PATH + "/mOEM/massDescription/mass"
PAY_PATH = MASS_PATH + "/payload/massDescription/mass"
F1_PATH = "/cpacs/vehicles/fuels/fuel"
F2_PATH = TSPEC_PATH + "/fuels"
TSFC_PATH = PROP_PATH + "/tSFC"
create_branch(tixi, TSFC_PATH, False)
create_branch(tixi, RANGE_PATH, False)
create_branch(tixi, P_PATH, False)
create_branch(tixi, F1_PATH, False)
create_branch(tixi, F2_PATH, False)
add_uid(tixi, F1_PATH, "kerosene")
# Compulsory path checks =================================================
if not tixi.checkElement(TSPEC_PATH):
raise Exception("Missing required toolspecific path.")
elif not tixi.checkElement(CC_PATH + "/cabinCrewMemberNb"):
raise Exception("Missing required cabinCrewMemberNb path.")
elif not tixi.checkElement(MASS_PATH):
raise Exception("Missing required massBreakdown path.")
elif not tixi.checkElement(DM_PATH):
raise Exception("Missing required designMasses path.")
elif not tixi.checkElement(MTOM_PATH):
raise Exception("Missing required mTOM/mass path.")
elif not tixi.checkElement(F_PATH):
raise Exception("Missing required fuel/massDescription/mass path.")
elif not tixi.checkElement(FMP_PATH):
raise Exception("Missing required fuelMassMaxpass/mass path.")
elif not tixi.checkElement(OEM_PATH):
raise Exception("Missing required mOEM/massDescription/mass path.")
elif not tixi.checkElement(PAY_PATH):
raise Exception("Missing required payload/massDescription/mass path.")
else:
log.info("All path correctly defined in the toolinput.xml file, " +
"beginning data extracction.")
# Gathering data =========================================================
# TOOLSPECIFIC ----------------------------------------------------------
if not tixi.checkElement(RANGE_PATH + "/lDRatio"):
tixi.createElement(RANGE_PATH, "lDRatio")
tixi.updateDoubleElement(RANGE_PATH + "/lDRatio", ri.LD, "%g")
else:
temp = tixi.getIntegerElement(RANGE_PATH + "/lDRatio")
if temp != ri.LD and temp > 0:
ri.LD = temp
if not tixi.checkElement(RANGE_PATH + "/cruiseSpeed"):
tixi.createElement(RANGE_PATH, "cruiseSpeed")
tixi.updateDoubleElement(RANGE_PATH + "/cruiseSpeed", ri.CRUISE_SPEED,
"%g")
else:
temp = tixi.getIntegerElement(RANGE_PATH + "/cruiseSpeed")
if temp != ri.CRUISE_SPEED and temp > 0:
ri.CRUISE_SPEED = temp
if not tixi.checkElement(RANGE_PATH + "/loiterTime"):
tixi.createElement(RANGE_PATH, "loiterTime")
tixi.updateDoubleElement(RANGE_PATH + "/loiterTime", ri.LOITER_TIME,
"%g")
else:
temp = tixi.getIntegerElement(RANGE_PATH + "/loiterTime")
if temp != ri.LOITER_TIME and temp > 0:
ri.LOITER_TIME = temp
if not tixi.checkElement(TSPEC_PATH + "/geometry/winglet"):
tixi.createElement(TSPEC_PATH + "/geometry", "winglet")
tixi.updateIntegerElement(TSPEC_PATH + "/geometry/winglet", ri.WINGLET,
"%i")
else:
temp = tixi.getIntegerElement(TSPEC_PATH + "/geometry/winglet")
if temp != ri.WINGLET:
ri.WINGLET = temp
if not tixi.checkElement(P_PATH + "/pilotNb"):
tixi.createElement(P_PATH, "pilotNb")
tixi.updateIntegerElement(P_PATH + "/pilotNb", ri.pilot_nb, "%i")
else:
temp = tixi.getIntegerElement(P_PATH + "/pilotNb")
if temp != ri.pilot_nb and temp > 0:
ri.pilot_nb = temp
# Pilots user input data
if not tixi.checkElement(P_PATH + "/pilotMass"):
tixi.createElement(P_PATH, "pilotMass")
tixi.updateDoubleElement(P_PATH + "/pilotMass", ri.MASS_PILOT, "%g")
else:
temp = tixi.getDoubleElement(P_PATH + "/pilotMass")
if temp != ri.MASS_PILOT and temp > 0:
ri.MASS_PILOT = temp
# Cabin crew user input data
if not tixi.checkElement(CC_PATH + "/cabinCrewMemberMass"):
tixi.createElement(CC_PATH, "cabinCrewMemberMass")
tixi.updateDoubleElement(CC_PATH + "/cabinCrewMemberMass",
ri.MASS_CABIN_CREW, "%g")
else:
temp = tixi.getDoubleElement(CC_PATH + "/cabinCrewMemberMass")
if temp != ri.MASS_CABIN_CREW and temp > 0:
ri.MASS_CABIN_CREW = temp
# Passengers input
if not tixi.checkElement(PASS_PATH + "/passMass"):
tixi.createElement(PASS_PATH, "passMass")
tixi.updateDoubleElement(PASS_PATH + "/passMass", ri.MASS_PASS, "%g")
else:
temp = tixi.getDoubleElement(PASS_PATH + "/passMass")
if temp != ri.MASS_PASS and temp > 0:
ri.MASS_PASS = temp
# Propulsion and Fuel
if not tixi.checkElement(PROP_PATH + "/turboprop"):
create_branch(tixi, PROP_PATH, False)
tixi.createElement(PROP_PATH, "turboprop")
if ri.TURBOPROP:
tixi.updateTextElement(PROP_PATH + "/turboprop", "True")
else:
tixi.updateTextElement(PROP_PATH + "/turboprop", "False")
else:
temp = tixi.getTextElement(PROP_PATH + "/turboprop")
if temp == "False":
ri.TURBOPROP = False
else:
ri.TURBOPROP = True
if not tixi.checkElement(F2_PATH + "/resFuelPerc"):
tixi.createElement(F2_PATH, "resFuelPerc")
tixi.updateDoubleElement(F2_PATH + "/resFuelPerc", ri.RES_FUEL_PERC,
"%g")
else:
temp = tixi.getDoubleElement(F2_PATH + "/resFuelPerc")
if temp != ri.RES_FUEL_PERC and temp > 0:
ri.RES_FUEL_PERC = temp
if not tixi.checkElement(TSFC_PATH + "/tsfcCruise"):
tixi.createElement(TSFC_PATH, "tsfcCruise")
tixi.updateDoubleElement(TSFC_PATH + "/tsfcCruise", ri.TSFC_CRUISE,
"%g")
else:
temp = tixi.getDoubleElement(TSFC_PATH + "/tsfcCruise")
if temp != ri.TSFC_CRUISE and temp > 0:
ri.TSFC_CRUISE = temp
if not tixi.checkElement(TSFC_PATH + "/tsfcLoiter"):
tixi.createElement(TSFC_PATH, "tsfcLoiter")
tixi.updateDoubleElement(TSFC_PATH + "/tsfcLoiter", ri.TSFC_LOITER,
"%g")
else:
temp = tixi.getDoubleElement(TSFC_PATH + "/tsfcLoiter")
if temp != ri.TSFC_LOITER and temp > 0:
ri.TSFC_LOITER = temp
# REQUIRED DATA =========================================================
# Cabin Crew
ri.cabin_crew_nb = tixi.getIntegerElement(CC_PATH + "/cabinCrewMemberNb")
# Fuel
mw.mass_fuel_maxpass = tixi.getDoubleElement(FMP_PATH)
# REQUIRED MASSBREAKDOWN DATA ===========================================
mw.maximum_take_off_mass = tixi.getDoubleElement(MTOM_PATH)
mw.operating_empty_mass = tixi.getDoubleElement(OEM_PATH)
mw.mass_payload = tixi.getDoubleElement(PAY_PATH)
mw.mass_fuel_max = tixi.getDoubleElement(F_PATH)
log.info("Data from CPACS file succesfully extracted")
# Saving and closing the cpacs file ======================================
tixi.save(cpacs_in)
return (mw, ri)
def convert_cpacs_to_sumo(cpacs_path, cpacs_out_path):
"""Function to convert a CPACS file geometry into a SUMO file geometry.
Function 'convert_cpacs_to_sumo' open an input cpacs file with TIXI handle
and via two main loop, one for fuselage(s), one for wing(s) it convert
every element (as much as possible) in the SUMO (.smx) format, which is
also an xml file. Due to some differences between both format, some CPACS
definition could lead to issues. The output sumo file is saved in the
folder /ToolOutput
Source:
* CPACS documentation: https://www.cpacs.de/pages/documentation.html
Args:
cpacs_path (str): Path to the CPACS file
Returns:
sumo_output_path (str): Path to the SUMO file
"""
EMPTY_SMX = MODULE_DIR + "/files/sumo_empty.smx"
tixi = open_tixi(cpacs_path)
sumo = open_tixi(EMPTY_SMX)
# Fuslage(s) ---------------------------------------------------------------
if tixi.checkElement(FUSELAGES_XPATH):
fus_cnt = tixi.getNamedChildrenCount(FUSELAGES_XPATH, "fuselage")
log.info(str(fus_cnt) + " fuselage has been found.")
else:
fus_cnt = 0
log.warning("No fuselage has been found in this CPACS file!")
for i_fus in range(fus_cnt):
fus_xpath = FUSELAGES_XPATH + "/fuselage[" + str(i_fus + 1) + "]"
fus_uid = tixi.getTextAttribute(fus_xpath, "uID")
fus_transf = Transformation()
fus_transf.get_cpacs_transf(tixi, fus_xpath)
# Create new body (SUMO)
sumo.createElementAtIndex("/Assembly", "BodySkeleton", i_fus + 1)
body_xpath = "/Assembly/BodySkeleton[" + str(i_fus + 1) + "]"
sumo.addTextAttribute(body_xpath, "akimatg", "false")
sumo.addTextAttribute(body_xpath, "name", fus_uid)
body_tansf = Transformation()
body_tansf.translation = fus_transf.translation
# Convert angles
body_tansf.rotation = euler2fix(fus_transf.rotation)
# Add body rotation
body_rot_str = (str(math.radians(body_tansf.rotation.x)) + " " +
str(math.radians(body_tansf.rotation.y)) + " " +
str(math.radians(body_tansf.rotation.z)))
sumo.addTextAttribute(body_xpath, "rotation", body_rot_str)
# Add body origin
body_ori_str = (str(body_tansf.translation.x) + " " +
str(body_tansf.translation.y) + " " +
str(body_tansf.translation.z))
sumo.addTextAttribute(body_xpath, "origin", body_ori_str)
# Positionings
if tixi.checkElement(fus_xpath + "/positionings"):
pos_cnt = tixi.getNamedChildrenCount(fus_xpath + "/positionings",
"positioning")
log.info(str(fus_cnt) + ' "Positionning" has been found : ')
pos_x_list = []
pos_y_list = []
pos_z_list = []
from_sec_list = []
to_sec_list = []
for i_pos in range(pos_cnt):
pos_xpath = fus_xpath + "/positionings/positioning[" + str(
i_pos + 1) + "]"
length = tixi.getDoubleElement(pos_xpath + "/length")
sweep_deg = tixi.getDoubleElement(pos_xpath + "/sweepAngle")
sweep = math.radians(sweep_deg)
dihedral_deg = tixi.getDoubleElement(pos_xpath +
"/dihedralAngle")
dihedral = math.radians(dihedral_deg)
# Get the corresponding translation of each positionning
pos_x_list.append(length * math.sin(sweep))
pos_y_list.append(length * math.cos(dihedral) *
math.cos(sweep))
pos_z_list.append(length * math.sin(dihedral) *
math.cos(sweep))
# Get which section are connected by the positionning
if tixi.checkElement(pos_xpath + "/fromSectionUID"):
from_sec = tixi.getTextElement(pos_xpath +
"/fromSectionUID")
else:
from_sec = ""
from_sec_list.append(from_sec)
if tixi.checkElement(pos_xpath + "/toSectionUID"):
to_sec = tixi.getTextElement(pos_xpath + "/toSectionUID")
else:
to_sec = ""
to_sec_list.append(to_sec)
# Re-loop though the positionning to re-order them
for j_pos in range(pos_cnt):
if from_sec_list[j_pos] == "":
prev_pos_x = 0
prev_pos_y = 0
prev_pos_z = 0
elif from_sec_list[j_pos] == to_sec_list[j_pos - 1]:
prev_pos_x = pos_x_list[j_pos - 1]
prev_pos_y = pos_y_list[j_pos - 1]
prev_pos_z = pos_z_list[j_pos - 1]
else:
index_prev = to_sec_list.index(from_sec_list[j_pos])
prev_pos_x = pos_x_list[index_prev]
prev_pos_y = pos_y_list[index_prev]
prev_pos_z = pos_z_list[index_prev]
pos_x_list[j_pos] += prev_pos_x
pos_y_list[j_pos] += prev_pos_y
pos_z_list[j_pos] += prev_pos_z
else:
log.warning('No "positionings" have been found!')
pos_cnt = 0
# Sections
sec_cnt = tixi.getNamedChildrenCount(fus_xpath + "/sections",
"section")
log.info(" -" + str(sec_cnt) + " fuselage sections have been found")
if pos_cnt == 0:
pos_x_list = [0.0] * sec_cnt
pos_y_list = [0.0] * sec_cnt
pos_z_list = [0.0] * sec_cnt
for i_sec in range(sec_cnt):
sec_xpath = fus_xpath + "/sections/section[" + str(i_sec + 1) + "]"
sec_uid = tixi.getTextAttribute(sec_xpath, "uID")
sec_transf = Transformation()
sec_transf.get_cpacs_transf(tixi, sec_xpath)
if sec_transf.rotation.x or sec_transf.rotation.y or sec_transf.rotation.z:
log.warning('Sections "' + sec_uid + '" is rotated, it is \
not possible to take that into acount in SUMO !')
# Elements
elem_cnt = tixi.getNamedChildrenCount(sec_xpath + "/elements",
"element")
if elem_cnt > 1:
log.warning("Sections " + sec_uid + " contains multiple \
element, it could be an issue for the conversion \
to SUMO!")
for i_elem in range(elem_cnt):
elem_xpath = sec_xpath + "/elements/element[" + str(i_elem +
1) + "]"
elem_uid = tixi.getTextAttribute(elem_xpath, "uID")
elem_transf = Transformation()
elem_transf.get_cpacs_transf(tixi, elem_xpath)
if elem_transf.rotation.x or elem_transf.rotation.y or elem_transf.rotation.z:
log.warning('Element "' + elem_uid + '" is rotated, it \
is not possible to take that into acount in \
SUMO !')
# Fuselage profiles
prof_uid = tixi.getTextElement(elem_xpath + "/profileUID")
prof_vect_x, prof_vect_y, prof_vect_z = get_profile_coord(
tixi, prof_uid)
prof_size_y = (max(prof_vect_y) - min(prof_vect_y)) / 2
prof_size_z = (max(prof_vect_z) - min(prof_vect_z)) / 2
prof_vect_y[:] = [y / prof_size_y for y in prof_vect_y]
prof_vect_z[:] = [z / prof_size_z for z in prof_vect_z]
prof_min_y = min(prof_vect_y)
prof_min_z = min(prof_vect_z)
prof_vect_y[:] = [y - 1 - prof_min_y for y in prof_vect_y]
prof_vect_z[:] = [z - 1 - prof_min_z for z in prof_vect_z]
# Could be a problem if they are less positionings than secions
# TODO: solve that!
pos_y_list[i_sec] += (
(1 + prof_min_y) * prof_size_y) * elem_transf.scaling.y
pos_z_list[i_sec] += (
(1 + prof_min_z) * prof_size_z) * elem_transf.scaling.z
# #To Plot a particular section
# if i_sec==5:
# plt.plot(prof_vect_z, prof_vect_y,'x')
# plt.xlabel('y')
# plt.ylabel('z')
# plt.grid(True)
# plt.show
# Put value in SUMO format
body_frm_center_x = (elem_transf.translation.x +
sec_transf.translation.x +
pos_x_list[i_sec]) * fus_transf.scaling.x
body_frm_center_y = (
elem_transf.translation.y * sec_transf.scaling.y +
sec_transf.translation.y +
pos_y_list[i_sec]) * fus_transf.scaling.y
body_frm_center_z = (
elem_transf.translation.z * sec_transf.scaling.z +
sec_transf.translation.z +
pos_z_list[i_sec]) * fus_transf.scaling.z
body_frm_height = (prof_size_z * 2 * elem_transf.scaling.z *
sec_transf.scaling.z * fus_transf.scaling.z)
if body_frm_height < 0.01:
body_frm_height = 0.01
body_frm_width = (prof_size_y * 2 * elem_transf.scaling.y *
sec_transf.scaling.y * fus_transf.scaling.y)
if body_frm_width < 0.01:
body_frm_width = 0.01
# Convert the profile points in the SMX format
prof_str = ""
teta_list = []
teta_half = []
prof_vect_y_half = []
prof_vect_z_half = []
check_max = 0
check_min = 0
# Use polar angle to keep point in the correct order
for i, item in enumerate(prof_vect_y):
teta_list.append(math.atan2(prof_vect_z[i],
prof_vect_y[i]))
for t, teta in enumerate(teta_list):
HALF_PI = math.pi / 2
EPSILON = 0.04
if abs(teta) <= HALF_PI - EPSILON:
teta_half.append(teta)
prof_vect_y_half.append(prof_vect_y[t])
prof_vect_z_half.append(prof_vect_z[t])
elif abs(teta) < HALF_PI + EPSILON:
# Check if not the last element of the list
if not t == len(teta_list) - 1:
next_val = prof_vect_z[t + 1]
# Check if it is better to keep next point
if not abs(next_val) > abs(prof_vect_z[t]):
if prof_vect_z[t] > 0 and not check_max:
teta_half.append(teta)
# Force y=0, to get symmetrical profile
prof_vect_y_half.append(0)
prof_vect_z_half.append(prof_vect_z[t])
check_max = 1
elif prof_vect_z[t] < 0 and not check_min:
teta_half.append(teta)
# Force y=0, to get symmetrical profile
prof_vect_y_half.append(0)
prof_vect_z_half.append(prof_vect_z[t])
check_min = 1
# Sort points by teta value, to fit the SUMO profile format
teta_half, prof_vect_z_half, prof_vect_y_half = (
list(t) for t in zip(*sorted(
zip(teta_half, prof_vect_z_half, prof_vect_y_half))))
# Write profile as a string and add y=0 point at the begining
# and at the end to ensure symmmetry
if not check_min:
prof_str += str(0) + " " + str(prof_vect_z_half[0]) + " "
for i, item in enumerate(prof_vect_z_half):
prof_str += (str(round(prof_vect_y_half[i], 4)) + " " +
str(round(prof_vect_z_half[i], 4)) + " ")
if not check_max:
prof_str += str(0) + " " + str(prof_vect_z_half[i]) + " "
# Write the SUMO file
sumo.addTextElementAtIndex(body_xpath, "BodyFrame", prof_str,
i_sec + 1)
frame_xpath = body_xpath + "/BodyFrame[" + str(i_sec + 1) + "]"
body_center_str = (str(body_frm_center_x) + " " +
str(body_frm_center_y) + " " +
str(body_frm_center_z))
sumo.addTextAttribute(frame_xpath, "center", body_center_str)
sumo.addTextAttribute(frame_xpath, "height",
str(body_frm_height))
sumo.addTextAttribute(frame_xpath, "width",
str(body_frm_width))
sumo.addTextAttribute(frame_xpath, "name", sec_uid)
# Fuselage symmetry (mirror copy)
if tixi.checkAttribute(fus_xpath, "symmetry"):
if tixi.getTextAttribute(fus_xpath, "symmetry") == "x-z-plane":
sumo_mirror_copy(sumo, body_xpath, fus_uid, False)
# To remove the default BodySkeleton
if fus_cnt == 0:
sumo.removeElement("/Assembly/BodySkeleton")
else:
sumo.removeElement("/Assembly/BodySkeleton[" + str(fus_cnt + 1) + "]")
# Wing(s) ------------------------------------------------------------------
if tixi.checkElement(WINGS_XPATH):
wing_cnt = tixi.getNamedChildrenCount(WINGS_XPATH, "wing")
log.info(str(wing_cnt) + " wings has been found.")
else:
wing_cnt = 0
log.warning("No wings has been found in this CPACS file!")
for i_wing in range(wing_cnt):
wing_xpath = WINGS_XPATH + "/wing[" + str(i_wing + 1) + "]"
wing_uid = tixi.getTextAttribute(wing_xpath, "uID")
wing_transf = Transformation()
wing_transf.get_cpacs_transf(tixi, wing_xpath)
# Create new wing (SUMO)
sumo.createElementAtIndex("/Assembly", "WingSkeleton", i_wing + 1)
wg_sk_xpath = "/Assembly/WingSkeleton[" + str(i_wing + 1) + "]"
sumo.addTextAttribute(wg_sk_xpath, "akimatg", "false")
sumo.addTextAttribute(wg_sk_xpath, "name", wing_uid)
# Create a class for the transformation of the WingSkeleton
wg_sk_tansf = Transformation()
# Convert WingSkeleton rotation and add it to SUMO
wg_sk_tansf.rotation = euler2fix(wing_transf.rotation)
wg_sk_rot_str = (str(math.radians(wg_sk_tansf.rotation.x)) + " " +
str(math.radians(wg_sk_tansf.rotation.y)) + " " +
str(math.radians(wg_sk_tansf.rotation.z)))
sumo.addTextAttribute(wg_sk_xpath, "rotation", wg_sk_rot_str)
# Add WingSkeleton origin
wg_sk_tansf.translation = wing_transf.translation
wg_sk_ori_str = (str(wg_sk_tansf.translation.x) + " " +
str(wg_sk_tansf.translation.y) + " " +
str(wg_sk_tansf.translation.z))
sumo.addTextAttribute(wg_sk_xpath, "origin", wg_sk_ori_str)
if tixi.checkAttribute(wing_xpath, "symmetry"):
if tixi.getTextAttribute(wing_xpath, "symmetry") == "x-z-plane":
sumo.addTextAttribute(wg_sk_xpath, "flags",
"autosym,detectwinglet")
else:
sumo.addTextAttribute(wg_sk_xpath, "flags", "detectwinglet")
# Positionings
if tixi.checkElement(wing_xpath + "/positionings"):
pos_cnt = tixi.getNamedChildrenCount(wing_xpath + "/positionings",
"positioning")
log.info(str(wing_cnt) + ' "positionning" has been found : ')
pos_x_list = []
pos_y_list = []
pos_z_list = []
from_sec_list = []
to_sec_list = []
for i_pos in range(pos_cnt):
pos_xpath = wing_xpath + "/positionings/positioning[" + str(
i_pos + 1) + "]"
length = tixi.getDoubleElement(pos_xpath + "/length")
sweep_deg = tixi.getDoubleElement(pos_xpath + "/sweepAngle")
sweep = math.radians(sweep_deg)
dihedral_deg = tixi.getDoubleElement(pos_xpath +
"/dihedralAngle")
dihedral = math.radians(dihedral_deg)
# Get the corresponding translation of each positionning
pos_x_list.append(length * math.sin(sweep))
pos_y_list.append(length * math.cos(dihedral) *
math.cos(sweep))
pos_z_list.append(length * math.sin(dihedral) *
math.cos(sweep))
# Get which section are connected by the positionning
if tixi.checkElement(pos_xpath + "/fromSectionUID"):
from_sec = tixi.getTextElement(pos_xpath +
"/fromSectionUID")
else:
from_sec = ""
from_sec_list.append(from_sec)
if tixi.checkElement(pos_xpath + "/toSectionUID"):
to_sec = tixi.getTextElement(pos_xpath + "/toSectionUID")
else:
to_sec = ""
to_sec_list.append(to_sec)
# Re-loop though the positionning to re-order them
for j_pos in range(pos_cnt):
if from_sec_list[j_pos] == "":
prev_pos_x = 0
prev_pos_y = 0
prev_pos_z = 0
elif from_sec_list[j_pos] == to_sec_list[j_pos - 1]:
prev_pos_x = pos_x_list[j_pos - 1]
prev_pos_y = pos_y_list[j_pos - 1]
prev_pos_z = pos_z_list[j_pos - 1]
else:
index_prev = to_sec_list.index(from_sec_list[j_pos])
prev_pos_x = pos_x_list[index_prev]
prev_pos_y = pos_y_list[index_prev]
prev_pos_z = pos_z_list[index_prev]
pos_x_list[j_pos] += prev_pos_x
pos_y_list[j_pos] += prev_pos_y
pos_z_list[j_pos] += prev_pos_z
else:
log.warning('No "positionings" have been found!')
pos_cnt = 0
# Sections
sec_cnt = tixi.getNamedChildrenCount(wing_xpath + "/sections",
"section")
log.info(" -" + str(sec_cnt) + " wing sections have been found")
wing_sec_index = 1
if pos_cnt == 0:
pos_x_list = [0.0] * sec_cnt
pos_y_list = [0.0] * sec_cnt
pos_z_list = [0.0] * sec_cnt
for i_sec in reversed(range(sec_cnt)):
sec_xpath = wing_xpath + "/sections/section[" + str(i_sec +
1) + "]"
sec_uid = tixi.getTextAttribute(sec_xpath, "uID")
sec_transf = Transformation()
sec_transf.get_cpacs_transf(tixi, sec_xpath)
# Elements
elem_cnt = tixi.getNamedChildrenCount(sec_xpath + "/elements",
"element")
if elem_cnt > 1:
log.warning("Sections " + sec_uid + " contains multiple \
element, it could be an issue for the conversion \
to SUMO!")
for i_elem in range(elem_cnt):
elem_xpath = sec_xpath + "/elements/element[" + str(i_elem +
1) + "]"
elem_uid = tixi.getTextAttribute(elem_xpath, "uID")
elem_transf = Transformation()
elem_transf.get_cpacs_transf(tixi, elem_xpath)
# Get wing profile (airfoil)
prof_uid = tixi.getTextElement(elem_xpath + "/airfoilUID")
prof_vect_x, prof_vect_y, prof_vect_z = get_profile_coord(
tixi, prof_uid)
# Apply scaling
for i, item in enumerate(prof_vect_x):
prof_vect_x[i] = (item * elem_transf.scaling.x *
sec_transf.scaling.x *
wing_transf.scaling.x)
for i, item in enumerate(prof_vect_y):
prof_vect_y[i] = (item * elem_transf.scaling.y *
sec_transf.scaling.y *
wing_transf.scaling.y)
for i, item in enumerate(prof_vect_z):
prof_vect_z[i] = (item * elem_transf.scaling.z *
sec_transf.scaling.z *
wing_transf.scaling.z)
# Plot setions (for tests)
# if (i_sec>8 and i_sec<=10):
# plt.plot(prof_vect_x, prof_vect_z,'x')
# plt.xlabel('x')
# plt.ylabel('z')
# plt.grid(True)
# plt.show()
prof_size_x = max(prof_vect_x) - min(prof_vect_x)
prof_size_y = max(prof_vect_y) - min(prof_vect_y)
prof_size_z = max(prof_vect_z) - min(prof_vect_z)
if prof_size_y == 0:
prof_vect_x[:] = [x / prof_size_x for x in prof_vect_x]
prof_vect_z[:] = [z / prof_size_x for z in prof_vect_z]
# Is it correct to divide by prof_size_x ????
wg_sec_chord = prof_size_x
else:
log.error("An airfoil profile is not define correctly")
# SUMO variable for WingSection
wg_sec_center_x = (elem_transf.translation.x +
sec_transf.translation.x +
pos_x_list[i_sec]) * wing_transf.scaling.x
wg_sec_center_y = (
elem_transf.translation.y * sec_transf.scaling.y +
sec_transf.translation.y +
pos_y_list[i_sec]) * wing_transf.scaling.y
wg_sec_center_z = (
elem_transf.translation.z * sec_transf.scaling.z +
sec_transf.translation.z +
pos_z_list[i_sec]) * wing_transf.scaling.z
# Add roation from element and sections
# Adding the two angles: Maybe not work in every case!!!
add_rotation = SimpleNamespace()
add_rotation.x = elem_transf.rotation.x + sec_transf.rotation.x
add_rotation.y = elem_transf.rotation.y + sec_transf.rotation.y
add_rotation.z = elem_transf.rotation.z + sec_transf.rotation.z
# Get Section rotation for SUMO
wg_sec_rot = euler2fix(add_rotation)
wg_sec_dihed = math.radians(wg_sec_rot.x)
wg_sec_twist = math.radians(wg_sec_rot.y)
wg_sec_yaw = math.radians(wg_sec_rot.z)
# Convert point list into string
prof_str = ""
# Airfoil points order : shoud be from TE (1 0) to LE (0 0)
# then TE(1 0), but not reverse way.
# to avoid double zero, not accepted by SUMO
for i, item in enumerate(prof_vect_x):
# if not (prof_vect_x[i] == prof_vect_x[i-1] or \
# round(prof_vect_z[i],4) == round(prof_vect_z[i-1],4)):
if round(prof_vect_z[i], 4) != round(
prof_vect_z[i - 1], 4):
prof_str += (str(round(prof_vect_x[i], 4)) + " " +
str(round(prof_vect_z[i], 4)) + " ")
sumo.addTextElementAtIndex(wg_sk_xpath, "WingSection",
prof_str, wing_sec_index)
wg_sec_xpath = wg_sk_xpath + "/WingSection[" + str(
wing_sec_index) + "]"
sumo.addTextAttribute(wg_sec_xpath, "airfoil", prof_uid)
sumo.addTextAttribute(wg_sec_xpath, "name", sec_uid)
wg_sec_center_str = (str(wg_sec_center_x) + " " +
str(wg_sec_center_y) + " " +
str(wg_sec_center_z))
sumo.addTextAttribute(wg_sec_xpath, "center",
wg_sec_center_str)
sumo.addTextAttribute(wg_sec_xpath, "chord", str(wg_sec_chord))
sumo.addTextAttribute(wg_sec_xpath, "dihedral",
str(wg_sec_dihed))
sumo.addTextAttribute(wg_sec_xpath, "twist", str(wg_sec_twist))
sumo.addTextAttribute(wg_sec_xpath, "yaw", str(wg_sec_yaw))
sumo.addTextAttribute(wg_sec_xpath, "napprox", "-1")
sumo.addTextAttribute(wg_sec_xpath, "reversed", "false")
sumo.addTextAttribute(wg_sec_xpath, "vbreak", "false")
wing_sec_index += 1
# Add Wing caps
add_wing_cap(sumo, wg_sk_xpath)
# Engyine pylon(s) ---------------------------------------------------------
inc_pylon_xpath = "/cpacs/toolspecific/CEASIOMpy/engine/includePylon"
include_pylon = get_value_or_default(tixi, inc_pylon_xpath, False)
if tixi.checkElement(PYLONS_XPATH) and include_pylon:
pylon_cnt = tixi.getNamedChildrenCount(PYLONS_XPATH, "enginePylon")
log.info(str(pylon_cnt) + " pylons has been found.")
else:
pylon_cnt = 0
log.warning("No pylon has been found in this CPACS file!")
for i_pylon in range(pylon_cnt):
pylon_xpath = PYLONS_XPATH + "/enginePylon[" + str(i_pylon + 1) + "]"
pylon_uid = tixi.getTextAttribute(pylon_xpath, "uID")
pylon_transf = Transformation()
pylon_transf.get_cpacs_transf(tixi, pylon_xpath)
# Create new wing (SUMO) Pylons will be modeled as a wings
sumo.createElementAtIndex("/Assembly", "WingSkeleton", i_pylon + 1)
wg_sk_xpath = "/Assembly/WingSkeleton[" + str(i_pylon + 1) + "]"
sumo.addTextAttribute(wg_sk_xpath, "akimatg", "false")
sumo.addTextAttribute(wg_sk_xpath, "name", pylon_uid)
# Create a class for the transformation of the WingSkeleton
wg_sk_tansf = Transformation()
# Convert WingSkeleton rotation and add it to SUMO
wg_sk_tansf.rotation = euler2fix(pylon_transf.rotation)
wg_sk_rot_str = sumo_str_format(
math.radians(wg_sk_tansf.rotation.x),
math.radians(wg_sk_tansf.rotation.y),
math.radians(wg_sk_tansf.rotation.z),
)
sumo.addTextAttribute(wg_sk_xpath, "rotation", wg_sk_rot_str)
# Add WingSkeleton origin
wg_sk_tansf.translation = pylon_transf.translation
sumo.addTextAttribute(
wg_sk_xpath,
"origin",
sumo_str_format(wg_sk_tansf.translation.x,
wg_sk_tansf.translation.y,
wg_sk_tansf.translation.z),
)
sumo.addTextAttribute(wg_sk_xpath, "flags", "detectwinglet")
# Positionings
if tixi.checkElement(pylon_xpath + "/positionings"):
pos_cnt = tixi.getNamedChildrenCount(pylon_xpath + "/positionings",
"positioning")
log.info(str(pylon_cnt) + ' "positionning" has been found : ')
pos_x_list = []
pos_y_list = []
pos_z_list = []
from_sec_list = []
to_sec_list = []
for i_pos in range(pos_cnt):
pos_xpath = pylon_xpath + "/positionings/positioning[" + str(
i_pos + 1) + "]"
length = tixi.getDoubleElement(pos_xpath + "/length")
sweep_deg = tixi.getDoubleElement(pos_xpath + "/sweepAngle")
sweep = math.radians(sweep_deg)
dihedral_deg = tixi.getDoubleElement(pos_xpath +
"/dihedralAngle")
dihedral = math.radians(dihedral_deg)
# Get the corresponding translation of each positionning
pos_x_list.append(length * math.sin(sweep))
pos_y_list.append(length * math.cos(dihedral) *
math.cos(sweep))
pos_z_list.append(length * math.sin(dihedral) *
math.cos(sweep))
# Get which section are connected by the positionning
if tixi.checkElement(pos_xpath + "/fromSectionUID"):
from_sec = tixi.getTextElement(pos_xpath +
"/fromSectionUID")
else:
from_sec = ""
from_sec_list.append(from_sec)
if tixi.checkElement(pos_xpath + "/toSectionUID"):
to_sec = tixi.getTextElement(pos_xpath + "/toSectionUID")
else:
to_sec = ""
to_sec_list.append(to_sec)
# Re-loop though the positionning to re-order them
for j_pos in range(pos_cnt):
if from_sec_list[j_pos] == "":
prev_pos_x = 0
prev_pos_y = 0
prev_pos_z = 0
elif from_sec_list[j_pos] == to_sec_list[j_pos - 1]:
prev_pos_x = pos_x_list[j_pos - 1]
prev_pos_y = pos_y_list[j_pos - 1]
prev_pos_z = pos_z_list[j_pos - 1]
else:
index_prev = to_sec_list.index(from_sec_list[j_pos])
prev_pos_x = pos_x_list[index_prev]
prev_pos_y = pos_y_list[index_prev]
prev_pos_z = pos_z_list[index_prev]
pos_x_list[j_pos] += prev_pos_x
pos_y_list[j_pos] += prev_pos_y
pos_z_list[j_pos] += prev_pos_z
else:
log.warning('No "positionings" have been found!')
pos_cnt = 0
# Sections
sec_cnt = tixi.getNamedChildrenCount(pylon_xpath + "/sections",
"section")
log.info(" -" + str(sec_cnt) + " wing sections have been found")
wing_sec_index = 1
if pos_cnt == 0:
pos_x_list = [0.0] * sec_cnt
pos_y_list = [0.0] * sec_cnt
pos_z_list = [0.0] * sec_cnt
check_reversed_wing = []
for i_sec in range(sec_cnt):
# for i_sec in reversed(range(sec_cnt)):
sec_xpath = pylon_xpath + "/sections/section[" + str(i_sec +
1) + "]"
sec_uid = tixi.getTextAttribute(sec_xpath, "uID")
sec_transf = Transformation()
sec_transf.get_cpacs_transf(tixi, sec_xpath)
# Elements
elem_cnt = tixi.getNamedChildrenCount(sec_xpath + "/elements",
"element")
if elem_cnt > 1:
log.warning("Sections " + sec_uid + " contains multiple \
element, it could be an issue for the conversion \
to SUMO!")
for i_elem in range(elem_cnt):
elem_xpath = sec_xpath + "/elements/element[" + str(i_elem +
1) + "]"
elem_uid = tixi.getTextAttribute(elem_xpath, "uID")
elem_transf = Transformation()
elem_transf.get_cpacs_transf(tixi, elem_xpath)
# Get pylon profile (airfoil)
prof_uid = tixi.getTextElement(elem_xpath + "/airfoilUID")
prof_vect_x, prof_vect_y, prof_vect_z = get_profile_coord(
tixi, prof_uid)
# Apply scaling
for i, item in enumerate(prof_vect_x):
prof_vect_x[i] = (item * elem_transf.scaling.x *
sec_transf.scaling.x *
pylon_transf.scaling.x)
for i, item in enumerate(prof_vect_y):
prof_vect_y[i] = (item * elem_transf.scaling.y *
sec_transf.scaling.y *
pylon_transf.scaling.y)
for i, item in enumerate(prof_vect_z):
prof_vect_z[i] = (item * elem_transf.scaling.z *
sec_transf.scaling.z *
pylon_transf.scaling.z)
prof_size_x = max(prof_vect_x) - min(prof_vect_x)
prof_size_y = max(prof_vect_y) - min(prof_vect_y)
prof_size_z = max(prof_vect_z) - min(prof_vect_z)
if prof_size_y == 0:
prof_vect_x[:] = [x / prof_size_x for x in prof_vect_x]
prof_vect_z[:] = [z / prof_size_x for z in prof_vect_z]
# Is it correct to divide by prof_size_x ????
wg_sec_chord = prof_size_x
else:
log.error("An airfoil profile is not define correctly")
# SUMO variable for WingSection
wg_sec_center_x = (elem_transf.translation.x +
sec_transf.translation.x +
pos_x_list[i_sec]) * pylon_transf.scaling.x
wg_sec_center_y = (
elem_transf.translation.y * sec_transf.scaling.y +
sec_transf.translation.y +
pos_y_list[i_sec]) * pylon_transf.scaling.y
wg_sec_center_z = (
elem_transf.translation.z * sec_transf.scaling.z +
sec_transf.translation.z +
pos_z_list[i_sec]) * pylon_transf.scaling.z
check_reversed_wing.append(wg_sec_center_y)
# Add roation from element and sections
# Adding the two angles: Maybe not work in every case!!!
add_rotation = SimpleNamespace()
add_rotation.x = elem_transf.rotation.x + sec_transf.rotation.x
add_rotation.y = elem_transf.rotation.y + sec_transf.rotation.y
add_rotation.z = elem_transf.rotation.z + sec_transf.rotation.z
# Get Section rotation for SUMO
wg_sec_rot = euler2fix(add_rotation)
wg_sec_dihed = math.radians(wg_sec_rot.x)
wg_sec_twist = math.radians(wg_sec_rot.y)
wg_sec_yaw = math.radians(wg_sec_rot.z)
# Convert point list into string
prof_str = ""
# Airfoil points order : should be from TE (1 0) to LE (0 0)
# then TE(1 0), but not reverse way.
# to avoid double zero, not accepted by SUMO
for i, item in enumerate(prof_vect_x):
# if not (prof_vect_x[i] == prof_vect_x[i-1] or \
# round(prof_vect_z[i],4) == round(prof_vect_z[i-1],4)):
if round(prof_vect_z[i], 4) != round(
prof_vect_z[i - 1], 4):
prof_str += (str(round(prof_vect_x[i], 4)) + " " +
str(round(prof_vect_z[i], 4)) + " ")
sumo.addTextElementAtIndex(wg_sk_xpath, "WingSection",
prof_str, wing_sec_index)
wg_sec_xpath = wg_sk_xpath + "/WingSection[" + str(
wing_sec_index) + "]"
sumo.addTextAttribute(wg_sec_xpath, "airfoil", prof_uid)
sumo.addTextAttribute(wg_sec_xpath, "name", sec_uid)
sumo.addTextAttribute(
wg_sec_xpath,
"center",
sumo_str_format(wg_sec_center_x, wg_sec_center_y,
wg_sec_center_z),
)
sumo.addTextAttribute(wg_sec_xpath, "chord", str(wg_sec_chord))
sumo.addTextAttribute(wg_sec_xpath, "dihedral",
str(wg_sec_dihed))
sumo.addTextAttribute(wg_sec_xpath, "twist", str(wg_sec_twist))
sumo.addTextAttribute(wg_sec_xpath, "yaw", str(wg_sec_yaw))
sumo.addTextAttribute(wg_sec_xpath, "napprox", "-1")
sumo.addTextAttribute(wg_sec_xpath, "reversed", "false")
sumo.addTextAttribute(wg_sec_xpath, "vbreak", "false")
wing_sec_index += 1
# Check if the wing section order must be inverted with reversed attribute
if check_reversed_wing[0] < check_reversed_wing[1]:
log.info("Wing section order will be reversed.")
for i_sec in range(sec_cnt):
wg_sec_xpath = wg_sk_xpath + "/WingSection[" + str(i_sec +
1) + "]"
sumo.removeAttribute(wg_sec_xpath, "reversed")
sumo.addTextAttribute(wg_sec_xpath, "reversed", "true")
# If symmetry, create a mirror copy of the Pylon
if tixi.checkAttribute(pylon_xpath, "symmetry"):
if tixi.getTextAttribute(pylon_xpath, "symmetry") == "x-z-plane":
sumo_mirror_copy(sumo, wg_sk_xpath, pylon_uid, True)
add_wing_cap(sumo, wg_sk_xpath)
# Engine(s) ----------------------------------------------------------------
inc_engine_xpath = "/cpacs/toolspecific/CEASIOMpy/engine/includeEngine"
include_engine = get_value_or_default(tixi, inc_engine_xpath, False)
if tixi.checkElement(ENGINES_XPATH) and include_engine:
engine_cnt = tixi.getNamedChildrenCount(ENGINES_XPATH, "engine")
log.info(str(engine_cnt) + " engines has been found.")
else:
engine_cnt = 0
log.warning("No engine has been found in this CPACS file!")
for i_engine in range(engine_cnt):
engine_xpath = ENGINES_XPATH + "/engine[" + str(i_engine + 1) + "]"
engine = Engine(tixi, engine_xpath)
# Nacelle (sumo)
xengtransl = engine.transf.translation.x
yengtransl = engine.transf.translation.y
zengtransl = engine.transf.translation.z
engineparts = [
engine.nacelle.fancowl, engine.nacelle.corecowl,
engine.nacelle.centercowl
]
for engpart in engineparts:
if not engpart.isengpart:
log.info("This engine part is not define.")
continue
if engpart.iscone:
xcontours = engpart.pointlist.xlist
ycontours = engpart.pointlist.ylist
xengtransl += engpart.xoffset
ysectransl = 0
zsectransl = 0
else:
xlist = engpart.section.pointlist.xlist
ylist = engpart.section.pointlist.ylist
xscaling = engpart.section.transf.scaling.x
zscaling = engpart.section.transf.scaling.z
# Why scaling z for point in y??? CPACS mystery...
xlist = [i * xscaling for i in xlist]
ylist = [i * zscaling for i in ylist]
# Nacelle parts contour points
# In CPACS nacelles are define as the revolution of section, in SUMO they have to
# be define as a body composed of section + a lip at the inlet
# Find upper part of the profile
xminidx = xlist.index(min(xlist))
yavg1 = sum(ylist[0:xminidx]) / (xminidx)
yavg2 = sum(ylist[xminidx:-1]) / (len(ylist) - xminidx)
if yavg1 > yavg2:
xcontours = xlist[0:xminidx]
ycontours = ylist[0:xminidx]
else:
xcontours = xlist[xminidx:-1]
ycontours = ylist[xminidx:-1]
ysectransl = engpart.section.transf.translation.y
zsectransl = engpart.section.transf.translation.z
# # Plot
# fig, ax = plt.subplots()
# ax.plot(xlist, ylist,'x')
# ax.plot(xcontours, ycontours,'or')
# ax.set(xlabel='x', ylabel='y',title='Engine profile')
# ax.grid()
# plt.show()
sumo.createElementAtIndex("/Assembly", "BodySkeleton", i_fus + 1)
body_xpath = "/Assembly/BodySkeleton[" + str(i_fus + 1) + "]"
sumo.addTextAttribute(body_xpath, "akimatg", "false")
sumo.addTextAttribute(body_xpath, "name", engpart.uid)
# Add body rotation and origin
sumo.addTextAttribute(body_xpath, "rotation",
sumo_str_format(0, 0, 0))
sumo.addTextAttribute(
body_xpath,
"origin",
sumo_str_format(xengtransl + ysectransl, yengtransl,
zengtransl),
)
# Add section
for i_sec in range(len(xcontours)):
namesec = "section_" + str(i_sec + 1)
# Only circle profiles
prof_str = " 0 -1 0.7071 -0.7071 1 0 0.7071 0.7071 0 1"
sumo.addTextElementAtIndex(body_xpath, "BodyFrame", prof_str,
i_sec + 1)
frame_xpath = body_xpath + "/BodyFrame[" + str(i_sec + 1) + "]"
diam = (ycontours[i_sec] + zsectransl) * 2
if diam < 0.01:
diam = 0.01
sumo.addTextAttribute(frame_xpath, "center",
sumo_str_format(xcontours[i_sec], 0, 0))
sumo.addTextAttribute(frame_xpath, "height", str(diam))
sumo.addTextAttribute(frame_xpath, "width", str(diam))
sumo.addTextAttribute(frame_xpath, "name", namesec)
# Nacelle/engine options
sumo_add_nacelle_lip(sumo, body_xpath)
if not engpart.iscone:
sumo_add_engine_bc(sumo, "Engine", engpart.uid)
if engine.sym:
sumo.createElementAtIndex("/Assembly", "BodySkeleton",
i_fus + 1)
body_xpath = "/Assembly/BodySkeleton[" + str(i_fus + 1) + "]"
sumo.addTextAttribute(body_xpath, "akimatg", "false")
sumo.addTextAttribute(body_xpath, "name", engpart.uid + "_sym")
# Add body rotation and origin
sumo.addTextAttribute(body_xpath, "rotation",
sumo_str_format(0, 0, 0))
sumo.addTextAttribute(
body_xpath,
"origin",
sumo_str_format(xengtransl + ysectransl, -yengtransl,
zengtransl),
)
# Add section
for i_sec in range(len(xcontours)):
namesec = "section_" + str(i_sec + 1)
# Only circle profiles
prof_str = " 0 -1 0.7071 -0.7071 1 0 0.7071 0.7071 0 1"
sumo.addTextElementAtIndex(body_xpath, "BodyFrame",
prof_str, i_sec + 1)
frame_xpath = body_xpath + "/BodyFrame[" + str(i_sec +
1) + "]"
diam = (ycontours[i_sec] + zsectransl) * 2
if diam < 0.01:
diam = 0.01
sumo.addTextAttribute(
frame_xpath, "center",
sumo_str_format(xcontours[i_sec], 0, 0))
sumo.addTextAttribute(frame_xpath, "height", str(diam))
sumo.addTextAttribute(frame_xpath, "width", str(diam))
sumo.addTextAttribute(frame_xpath, "name", namesec)
# Nacelle/Enine options
sumo_add_nacelle_lip(sumo, body_xpath)
if not engpart.iscone:
sumo_add_engine_bc(sumo, "Engine_sym",
engpart.uid + "_sym")
# Get results directory
results_dir = get_results_directory("CPACS2SUMO")
sumo_file_path = Path(results_dir, "ToolOutput.smx")
create_branch(tixi, SUMOFILE_XPATH)
tixi.updateTextElement(SUMOFILE_XPATH, str(sumo_file_path))
# Save CPACS and SMX file
tixi.save(cpacs_out_path)
sumo.save(str(sumo_file_path))
def get_cl(cpacs_path, cpacs_out_path):
"""Function to calculate CL required as a function of the parameter found
in the CPACS file.
Function 'get_cl' find input value in the CPACS file, calculate the
required CL (with function calculate_cl) and save the CL value in the
CPACS file.
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str): Path to CPACS output file
"""
cpacs = CPACS(cpacs_path)
tixi = cpacs.tixi
# XPath definition
model_xpath = "/cpacs/vehicles/aircraft/model"
ref_area_xpath = model_xpath + "/reference/area"
mass_type_xpath = "/cpacs/toolspecific/CEASIOMpy/aerodynamics/clCalculation/massType"
custom_mass_xpath = "/cpacs/toolspecific/CEASIOMpy/aerodynamics/clCalculation/customMass"
percent_fuel_mass_xpath = (
"/cpacs/toolspecific/CEASIOMpy/aerodynamics/clCalculation/percentFuelMass"
)
cruise_alt_xpath = CLCALC_XPATH + "/cruiseAltitude"
cruise_mach_xpath = CLCALC_XPATH + "/cruiseMach"
load_fact_xpath = CLCALC_XPATH + "/loadFactor"
# Required input data from CPACS
ref_area = get_value(tixi, ref_area_xpath)
log.info(f"Aircraft reference area is {ref_area} [m^2]")
# Mass
mass = None
mass_type = get_value_or_default(tixi, mass_type_xpath, "mTOM")
if mass_type == "Custom":
mass = get_value(tixi, custom_mass_xpath)
elif mass_type == "% fuel mass":
percent_fuel_mass = get_value(tixi, percent_fuel_mass_xpath)
mtom = get_value(
tixi,
model_xpath + "/analyses/massBreakdown/designMasses/mTOM/mass")
mzfm = get_value(
tixi,
model_xpath + "/analyses/massBreakdown/designMasses/mZFM/mass")
if mzfm > mtom:
raise ValueError("mZFM is bigger than mTOM!")
mass = (mtom - mzfm) * percent_fuel_mass / 100 + mzfm
else:
mass_xpath = model_xpath + f"/analyses/massBreakdown/designMasses/{mass_type}/mass"
mass = get_value(tixi, mass_xpath)
# mtom = get_value(tixi,mtom_xpath)
if mass:
log.info(f"Aircraft mass use for this analysis is {mass} [kg]")
else:
raise ValueError("The chosen aircraft mass has not been found!")
# Required 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)
# CL calculation
target_cl = calculate_cl(ref_area, cruise_alt, cruise_mach, mass,
load_fact)
# Save TargetCL and fixedCL option
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")
cpacs.save_cpacs(cpacs_out_path, overwrite=True)
def cpacs_update(mw, out, cpacs_path, cpacs_out_path):
""" The function updates the cpacs file after the Weight analysis.
Args:
mw (class) : MassesWeights class
out (class) : WeightOutput class
cpacs_path (str) : Path to the CPACS file
cpacs_out_path (str) : Path to the output CPACS file
"""
tixi = open_tixi(
cpacs_out_path
) # (because it has been modifed somewre else, TODO: change that)
# Path update
if not tixi.checkElement(CREW_XPATH + "/cabinCrewMembers/cabinCrewMemberNb"):
create_branch(tixi, CREW_XPATH + "/cabinCrewMembers/cabinCrewMemberNb")
tixi.updateDoubleElement(
CREW_XPATH + "/cabinCrewMembers/cabinCrewMemberNb", out.cabin_crew_nb, "%g"
)
if not tixi.checkElement(PASS_XPATH + "/passNb"):
tixi.createElement(PASS_XPATH, "passNb")
tixi.updateIntegerElement(PASS_XPATH + "/passNb", out.pass_nb, "%i")
if not tixi.checkElement(PASS_XPATH + "/rowNb"):
tixi.createElement(PASS_XPATH, "rowNb")
tixi.updateIntegerElement(PASS_XPATH + "/rowNb", out.row_nb, "%i")
if not tixi.checkElement(PASS_XPATH + "/aisleNb"):
tixi.createElement(PASS_XPATH, "aisleNb")
tixi.updateIntegerElement(PASS_XPATH + "/aisleNb", out.aisle_nb, "%i")
if not tixi.checkElement(PASS_XPATH + "/toiletNb"):
tixi.createElement(PASS_XPATH, "toiletNb")
tixi.updateIntegerElement(PASS_XPATH + "/toiletNb", out.toilet_nb, "%i")
if not tixi.checkElement(PASS_XPATH + "/abreastNb"):
tixi.createElement(PASS_XPATH, "abreastNb")
tixi.updateIntegerElement(PASS_XPATH + "/abreastNb", out.abreast_nb, "%i")
if not tixi.checkElement(PASS_XPATH + "/fuelMassMaxpass"):
tixi.createElement(PASS_XPATH, "fuelMassMaxpass")
FMP_XPATH = PASS_XPATH + "/fuelMassMaxpass"
if not tixi.checkElement(FMP_XPATH + "/description"):
tixi.createElement(FMP_XPATH, "description")
tixi.updateTextElement(
FMP_XPATH + "/description", "Maximum amount of " + "fuel with maximum payload [kg]"
)
if not tixi.checkElement(FMP_XPATH + "/mass"):
tixi.createElement(FMP_XPATH, "mass")
tixi.updateDoubleElement(FMP_XPATH + "/mass", mw.mass_fuel_maxpass, "%g")
# CPACS MASS BREAKDOWN UPDATE
# Path creation
if tixi.checkElement(MASSBREAKDOWN_XPATH):
tixi.removeElement(MASSBREAKDOWN_XPATH)
MD_XPATH = MASSBREAKDOWN_XPATH + "/designMasses"
MTOM_XPATH = MD_XPATH + "/mTOM"
MZFM_XPATH = MD_XPATH + "/mZFM"
MF_XPATH = MASSBREAKDOWN_XPATH + "/fuel/massDescription"
OEM_XPATH = MASSBREAKDOWN_XPATH + "/mOEM/massDescription"
PAY_XPATH = MASSBREAKDOWN_XPATH + "/payload/massDescription"
MC_XPATH = MASSBREAKDOWN_XPATH + "/payload/mCargo"
OIM_XPATH = MASSBREAKDOWN_XPATH + "/mOEM/mOperatorItems/mCrewMembers/massDescription"
create_branch(tixi, MTOM_XPATH + "/mass", False)
create_branch(tixi, MZFM_XPATH + "/mass", False)
create_branch(tixi, MF_XPATH + "/mass", False)
create_branch(tixi, OEM_XPATH + "/mass", False)
create_branch(tixi, PAY_XPATH + "/mass", False)
create_branch(tixi, MC_XPATH, False)
create_branch(tixi, OIM_XPATH + "/mass", False)
# DESIGN MASSES
add_uid(tixi, MTOM_XPATH, "MTOM")
tixi.createElement(MTOM_XPATH, "name")
tixi.updateTextElement(MTOM_XPATH + "/name", "Maximum take-off mass")
tixi.createElement(MTOM_XPATH, "description")
tixi.updateTextElement(
MTOM_XPATH + "/description",
"Maximum " + "take off mass [kg], CoG coordinate [m] and " + "moment of inertia.",
)
tixi.updateDoubleElement(MTOM_XPATH + "/mass", mw.maximum_take_off_mass, "%g")
# MZFM
add_uid(tixi, MZFM_XPATH, "MZFM")
tixi.createElement(MZFM_XPATH, "name")
tixi.updateTextElement(MZFM_XPATH + "/name", "Maximum zero fuel mass")
tixi.createElement(MZFM_XPATH, "description")
tixi.updateTextElement(
MZFM_XPATH + "/description",
"Maximum "
+ "zero fuel mass [kg] and corresponding CoG "
+ "coordinate [m], moment of inertia.",
)
tixi.updateDoubleElement(MZFM_XPATH + "/mass", mw.zero_fuel_mass, "%g")
# FUEL MASS
add_uid(tixi, MF_XPATH, "MFM")
tixi.createElement(MF_XPATH, "name")
tixi.updateTextElement(MF_XPATH + "/name", "Max fuel mass")
tixi.createElement(MF_XPATH, "description")
tixi.updateTextElement(MF_XPATH + "/description", "Maximum fuel mass [kg]")
tixi.updateDoubleElement(MF_XPATH + "/mass", mw.mass_fuel_max, "%g")
# OEM
add_uid(tixi, OEM_XPATH, "OEM")
tixi.createElement(OEM_XPATH, "name")
tixi.updateTextElement(OEM_XPATH + "/name", "Operating empty mass")
tixi.createElement(OEM_XPATH, "description")
tixi.updateTextElement(
OEM_XPATH + "/description", "Operating empty" + " mass [kg] and related inertia [kgm^2]."
)
tixi.updateDoubleElement(OEM_XPATH + "/mass", mw.operating_empty_mass, "%g")
tixi.updateDoubleElement(OIM_XPATH + "/mass", mw.mass_crew, "%g")
add_uid(tixi, OIM_XPATH, "massCrew")
# PAYLOAD MASS AND FUEL WITH MAX PAYLOAD
add_uid(tixi, PAY_XPATH, "MPM")
tixi.createElement(PAY_XPATH, "name")
tixi.updateTextElement(PAY_XPATH + "/name", "Max payload mass")
tixi.createElement(PAY_XPATH, "description")
tixi.updateTextElement(PAY_XPATH + "/description", "Maximum " + "payload mass [kg].")
tixi.updateDoubleElement(PAY_XPATH + "/mass", mw.mass_payload, "%g")
if mw.mass_cargo:
tixi.createElement(MC_XPATH, "massCargo")
tixi.updateDoubleElement(MC_XPATH + "/massCargo", mw.mass_cargo, "%g")
tixi.save(cpacs_out_path)
def add_skin_friction(cpacs_path, cpacs_out_path):
"""Function to add the skin frictions drag coefficient to aerodynamic coefficients
Function 'add_skin_friction' add the skin friction drag 'cd0' to the
SU2 and pyTornado aeroMap, if their UID is not given, it will add skin
friction to all aeroMap. For each aeroMap it creates a new aeroMap where
the skin friction drag coefficient is added with the correct projections.
Args:
cpacs_path (str): Path to CPACS file
cpacs_out_path (str): Path to CPACS output file
"""
# Load a CPACS file
cpacs = CPACS(cpacs_path)
analyses_xpath = "/cpacs/toolspecific/CEASIOMpy/geometry/analysis"
# Required input data from CPACS
wetted_area = get_value(cpacs.tixi, analyses_xpath + "/wettedArea")
# Wing area/span, default values will be calculated if no value found in the CPACS file
wing_area_xpath = analyses_xpath + "/wingArea"
wing_area = get_value_or_default(cpacs.tixi, wing_area_xpath,
cpacs.aircraft.wing_area)
wing_span_xpath = analyses_xpath + "/wingSpan"
wing_span = get_value_or_default(cpacs.tixi, wing_span_xpath,
cpacs.aircraft.wing_span)
# Get aeroMapToCalculate
aeroMap_to_calculate_xpath = SF_XPATH + "/aeroMapToCalculate"
if cpacs.tixi.checkElement(aeroMap_to_calculate_xpath):
aeromap_uid_list = get_string_vector(cpacs.tixi,
aeroMap_to_calculate_xpath)
else:
aeromap_uid_list = []
# If no aeroMap in aeroMapToCalculate, get all existing aeroMap
if len(aeromap_uid_list) == 0:
aeromap_uid_list = cpacs.get_aeromap_uid_list()
if not aeromap_uid_list:
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)
aeromap = cpacs.get_aeromap_by_uid(aeromap_uid)
# Create new aeromap object to store coef with added skin friction
aeromap_sf = cpacs.duplicate_aeromap(aeromap_uid,
aeromap_uid + "_SkinFriction")
aeromap_sf.description = (
aeromap_sf.description +
" Skin friction has been add to this AeroMap.")
# Add skin friction to all force coefficient (with projections)
aeromap_sf.df["cd"] = aeromap.df.apply(
lambda row: row["cd"] + estimate_skin_friction_coef(
wetted_area, wing_area, wing_span, row["machNumber"], row[
"altitude"]) * math.cos(math.radians(row["angleOfAttack"]))
* math.cos(math.radians(row["angleOfSideslip"])),
axis=1,
)
aeromap_sf.df["cl"] = aeromap.df.apply(
lambda row: row["cl"] + estimate_skin_friction_coef(
wetted_area, wing_area, wing_span, row[
"machNumber"], row["altitude"]) * math.sin(
math.radians(row["angleOfAttack"])),
axis=1,
)
aeromap_sf.df["cs"] = aeromap.df.apply(
lambda row: row["cs"] + estimate_skin_friction_coef(
wetted_area, wing_area, wing_span, row["machNumber"], row[
"altitude"]) * math.sin(
math.radians(row["angleOfSideslip"])),
axis=1,
)
# TODO: Should we change something in moment coef?
# e.i. if a force is not apply at aero center...?
aeromap_sf.save()
# Get aeroMap list to plot
plot_xpath = "/cpacs/toolspecific/CEASIOMpy/aerodynamics/plotAeroCoefficient"
aeromap_to_plot_xpath = plot_xpath + "/aeroMapToPlot"
if cpacs.tixi.checkElement(aeromap_to_plot_xpath):
aeromap_uid_list = get_string_vector(cpacs.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))
add_string_vector(cpacs.tixi, aeromap_to_plot_xpath,
new_aeromap_to_plot)
else:
create_branch(cpacs.tixi, aeromap_to_plot_xpath)
add_string_vector(cpacs.tixi, aeromap_to_plot_xpath,
new_aeromap_uid_list)
log.info('AeroMap "' + aeromap_uid + '" has been added to the CPACS file')
cpacs.save_cpacs(cpacs_out_path, overwrite=True)
def cpacs_mbd_update(out, mw, bi, ms_zpm, out_xml):
""" The function updates the cpacs file after the Weight_and_Balance
program.
INPUT
(float) mass_pass --Arg.: Passenger mass, countig also the
extra mass.
(class) out --Arg.: BalanceOutput class.
(class) mw --Arg.: MassesWeights class.
(class) bi --Arg.: BalanceInput class.
##======= Classes are defined in the InputClasses folder =======##
(cahr) out_xml --Arg.: Path of the output file.
OUTPUT
(file) cpacs.xml --Out.: Updated cpacs file.
"""
tixi = open_tixi(out_xml)
# CREATING PATH ==========================================================
MB_PATH = "/cpacs/vehicles/aircraft/" + "model/analyses/massBreakdown"
MD_PATH = MB_PATH + "/designMasses"
MTOM_PATH = MD_PATH + "/mTOM"
MZFM_PATH = MD_PATH + "/mZFM"
OEM_PATH = MB_PATH + "/mOEM/massDescription"
J_PATH = OEM_PATH + "/massInertia/J"
CG_PATH = OEM_PATH + "/location/"
create_branch(tixi, MTOM_PATH + "/location/x", False)
create_branch(tixi, MTOM_PATH + "/location/y", False)
create_branch(tixi, MTOM_PATH + "/location/z", False)
create_branch(tixi, MTOM_PATH + "/massInertia/Jxx", False)
create_branch(tixi, MTOM_PATH + "/massInertia/Jyy", False)
create_branch(tixi, MTOM_PATH + "/massInertia/Jzz", False)
create_branch(tixi, MTOM_PATH + "/massInertia/Jxy", False)
create_branch(tixi, MTOM_PATH + "/massInertia/Jyz", False)
create_branch(tixi, MTOM_PATH + "/massInertia/Jxz", False)
create_branch(tixi, MZFM_PATH + "/location/x", False)
create_branch(tixi, MZFM_PATH + "/location/y", False)
create_branch(tixi, MZFM_PATH + "/location/z", False)
create_branch(tixi, MZFM_PATH + "/massInertia/Jxx", False)
create_branch(tixi, MZFM_PATH + "/massInertia/Jyy", False)
create_branch(tixi, MZFM_PATH + "/massInertia/Jzz", False)
create_branch(tixi, MZFM_PATH + "/massInertia/Jxy", False)
create_branch(tixi, MZFM_PATH + "/massInertia/Jyz", False)
create_branch(tixi, MZFM_PATH + "/massInertia/Jxz", False)
create_branch(tixi, OEM_PATH + "/location/x", False)
create_branch(tixi, OEM_PATH + "/location/y", False)
create_branch(tixi, OEM_PATH + "/location/z", False)
create_branch(tixi, OEM_PATH + "/massInertia/Jxx", False)
create_branch(tixi, OEM_PATH + "/massInertia/Jyy", False)
create_branch(tixi, OEM_PATH + "/massInertia/Jzz", False)
create_branch(tixi, OEM_PATH + "/massInertia/Jxy", False)
create_branch(tixi, OEM_PATH + "/massInertia/Jyz", False)
create_branch(tixi, OEM_PATH + "/massInertia/Jxz", False)
# DESIGN MASSES ==========================================================
# MTOM -------------------------------------------------------------------
tixi.uIDSetToXPath(MTOM_PATH + "/location", "MTOMloc")
tixi.updateDoubleElement(MTOM_PATH + "/location" + "/x",
out.center_of_gravity[0], "%g")
tixi.updateDoubleElement(MTOM_PATH + "/location" + "/y",
out.center_of_gravity[1], "%g")
tixi.updateDoubleElement(MTOM_PATH + "/location" + "/z",
out.center_of_gravity[2], "%g")
tixi.updateDoubleElement(MTOM_PATH + "/massInertia" + "/Jxx", out.Ixx_lump,
"%g")
tixi.updateDoubleElement(MTOM_PATH + "/massInertia" + "/Jyy", out.Iyy_lump,
"%g")
tixi.updateDoubleElement(MTOM_PATH + "/massInertia" + "/Jzz", out.Izz_lump,
"%g")
tixi.updateDoubleElement(MTOM_PATH + "/massInertia" + "/Jxy", out.Ixy_lump,
"%g")
tixi.updateDoubleElement(MTOM_PATH + "/massInertia" + "/Jyz", out.Iyz_lump,
"%g")
tixi.updateDoubleElement(MTOM_PATH + "/massInertia" + "/Jxz", out.Ixz_lump,
"%g")
# MZFM -------------------------------------------------------------------
add_uid(tixi, MZFM_PATH + "/location", "MZFMloc")
# updating path
tixi.updateDoubleElement(MZFM_PATH + "/location" + "/x", out.cg_zpm[0],
"%g")
tixi.updateDoubleElement(MZFM_PATH + "/location" + "/y", out.cg_zpm[1],
"%g")
tixi.updateDoubleElement(MZFM_PATH + "/location" + "/z", out.cg_zpm[2],
"%g")
tixi.updateDoubleElement(MZFM_PATH + "/massInertia" + "/Jxx",
out.Ixx_lump_zfm, "%g")
tixi.updateDoubleElement(MZFM_PATH + "/massInertia" + "/Jyy",
out.Iyy_lump_zfm, "%g")
tixi.updateDoubleElement(MZFM_PATH + "/massInertia" + "/Jzz",
out.Izz_lump_zfm, "%g")
tixi.updateDoubleElement(MZFM_PATH + "/massInertia" + "/Jxy",
out.Ixy_lump_zfm, "%g")
tixi.updateDoubleElement(MZFM_PATH + "/massInertia" + "/Jyz",
out.Iyz_lump_zfm, "%g")
tixi.updateDoubleElement(MZFM_PATH + "/massInertia" + "/Jxz",
out.Ixz_lump_zfm, "%g")
# OEM ====================================================================
add_uid(tixi, OEM_PATH + "/location", "OEMloc")
tixi.updateDoubleElement((CG_PATH + "x"), out.cg_oem[0], "%g")
tixi.updateDoubleElement((CG_PATH + "y"), out.cg_oem[1], "%g")
tixi.updateDoubleElement((CG_PATH + "z"), out.cg_oem[2], "%g")
tixi.updateDoubleElement((J_PATH + "xx"), out.Ixx_lump_oem, "%g")
tixi.updateDoubleElement((J_PATH + "yy"), out.Iyy_lump_oem, "%g")
tixi.updateDoubleElement((J_PATH + "zz"), out.Izz_lump_oem, "%g")
tixi.updateDoubleElement((J_PATH + "xy"), out.Ixy_lump_oem, "%g")
tixi.updateDoubleElement((J_PATH + "yz"), out.Iyz_lump_oem, "%g")
tixi.updateDoubleElement((J_PATH + "xz"), out.Ixz_lump_oem, "%g")
# ZPM INERTIA ============================================================
B_PATH = "/cpacs/toolspecific/CEASIOMpy/balance"
ZPM_PATH = B_PATH + "/mZPM"
create_branch(tixi, ZPM_PATH + "/name", False)
tixi.updateTextElement(ZPM_PATH + "/name", "Maximum no payload mass")
create_branch(tixi, ZPM_PATH + "/description", False)
tixi.updateTextElement(
ZPM_PATH + "/description",
"Maximum " + "no payload mass [kg], CoG coordinate [m] and " +
"moment of inertia.",
)
create_branch(tixi, ZPM_PATH + "/mass", False)
tixi.updateDoubleElement(ZPM_PATH + "/mass", ms_zpm, "%g")
create_branch(tixi, ZPM_PATH + "/location/x", False)
create_branch(tixi, ZPM_PATH + "/location/y", False)
create_branch(tixi, ZPM_PATH + "/location/z", False)
create_branch(tixi, ZPM_PATH + "/massInertia/Jxx", False)
create_branch(tixi, ZPM_PATH + "/massInertia/Jyy", False)
create_branch(tixi, ZPM_PATH + "/massInertia/Jzz", False)
create_branch(tixi, ZPM_PATH + "/massInertia/Jxy", False)
create_branch(tixi, ZPM_PATH + "/massInertia/Jyz", False)
create_branch(tixi, ZPM_PATH + "/massInertia/Jxz", False)
LOC_PATH = ZPM_PATH + "/location"
MOI_PATH = ZPM_PATH + "/massInertia"
add_uid(tixi, ZPM_PATH, "MZPM")
add_uid(tixi, LOC_PATH, "MZPMloc")
tixi.updateDoubleElement((LOC_PATH + "/x"), out.cg_zpm[0], "%g")
tixi.updateDoubleElement((LOC_PATH + "/y"), out.cg_zpm[1], "%g")
tixi.updateDoubleElement((LOC_PATH + "/z"), out.cg_zpm[2], "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jxx"), out.Ixx_lump_zpm, "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jyy"), out.Iyy_lump_zpm, "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jzz"), out.Izz_lump_zpm, "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jxy"), out.Ixy_lump_zpm, "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jyz"), out.Iyz_lump_zpm, "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jxz"), out.Ixz_lump_zpm, "%g")
# USER CASE ==============================================================
if bi.USER_CASE:
UC_PATH = "/cpacs/toolspecific/CEASIOMpy/balance/userBalance"
LOC_PATH = UC_PATH + "/location"
MOI_PATH = UC_PATH + "/massInertia"
create_branch(tixi, LOC_PATH + "/x", False)
create_branch(tixi, LOC_PATH + "/y", False)
create_branch(tixi, LOC_PATH + "/z", False)
create_branch(tixi, MOI_PATH + "/Jxx", False)
create_branch(tixi, MOI_PATH + "/Jyy", False)
create_branch(tixi, MOI_PATH + "/Jzz", False)
create_branch(tixi, MOI_PATH + "/Jxy", False)
create_branch(tixi, MOI_PATH + "/Jyz", False)
create_branch(tixi, MOI_PATH + "/Jxz", False)
add_uid(tixi, LOC_PATH, "USERCase")
tixi.updateDoubleElement((LOC_PATH + "/x"), out.cg_user[0], "%g")
tixi.updateDoubleElement((LOC_PATH + "/y"), out.cg_user[1], "%g")
tixi.updateDoubleElement((LOC_PATH + "/z"), out.cg_user[2], "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jxx"), out.Ixx_lump_user, "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jyy"), out.Iyy_lump_user, "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jzz"), out.Izz_lump_user, "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jxy"), out.Ixy_lump_user, "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jyz"), out.Iyz_lump_user, "%g")
tixi.updateDoubleElement((MOI_PATH + "/Jxz"), out.Ixz_lump_user, "%g")
# Saving and closing the new cpacs file inside the ToolOutput folder -----
tixi.save(out_xml)
return ()
def get_data(mw, bi, cpacs_in):
""" The function extracts from the XML file the required input data,
the code will use the default value when they are missing.
INPUT
(class) mw --Arg.: MassesWeight class.
(class) bi --Arg.: BalanceInput class.
##======= Classes are defined in the InputClasses folder =======##
(char) cpacs_in --Arg.: Relative location of the xml file in the
ToolInput folder (cpacs option) or
relative location of the temp. xml file in
the ToolOutput folder (input option).
OUTPUT
(class) mw --Out.: MassesWeight class updated.
(class) bi --Out.: RangeInput class updated.
(file) cpacs_in --Out.: Updated cpasc file.
"""
log.info("CPACS file path check")
# path definition ========================================================
# Opening CPACS file
tixi = open_tixi(cpacs_in)
TSPEC_PATH = "/cpacs/toolspecific/CEASIOMpy"
FMP_PATH = TSPEC_PATH + "/weight/passengers/fuelMassMaxpass/mass"
PROP_PATH = TSPEC_PATH + "/propulsion"
BC_PATH = TSPEC_PATH + "/balance/userBalance"
create_branch(tixi, BC_PATH, False)
MASS_PATH = "/cpacs/vehicles/aircraft/model/analyses/massBreakdown"
MTOM_PATH = MASS_PATH + "/designMasses/mTOM/mass"
F_PATH = MASS_PATH + "/fuel/massDescription/mass"
OEM_PATH = MASS_PATH + "/mOEM/massDescription/mass"
PAY_PATH = MASS_PATH + "/payload/massDescription/mass"
# Compulsory path checks =================================================
if not tixi.checkElement(TSPEC_PATH):
raise Exception("Missing required toolspecific path. Run " +
"Weight_main.py, in the 1Weight_module folder.")
elif not tixi.checkElement(MASS_PATH):
raise Exception("Missing required massBreakdown path. Run " +
"Weight_main.py, in the 1Weight_module folder.")
elif not tixi.checkElement(MTOM_PATH):
raise Exception("Missing required mTOM/mass path. Run " +
"Weight_main.py, in the 1Weight_module folder.")
elif not tixi.checkElement(FMP_PATH):
raise Exception("Missing required fuelMassMaxpass/mass path. Run " +
"Weight_main.py, in the 1Weight_module folder.")
elif not tixi.checkElement(OEM_PATH):
raise Exception("Missing required mOEM/massDescription/mass " +
"path. Run " +
"Weight_main.py, in the 1Weight_module folder.")
elif not tixi.checkElement(PAY_PATH):
raise Exception("Missing required payload/massDescription/mass " +
"path. Run " +
"Weight_main.py, in the 1Weight_module folder.")
elif not tixi.checkElement(F_PATH):
raise Exception("Missing required /fuel/massDescription/mass " +
"path. Run " +
"Weight_main.py, in the 1Weight_module folder.")
else:
log.info("All path correctly defined in the toolinput.xml file, " +
"beginning data extracction.")
# Gathering data =========================================================
# TOOLSPECIFIC ----------------------------------------------------------
if not tixi.checkElement(PROP_PATH + "/wingMountedEngine"):
create_branch(tixi, PROP_PATH, False)
tixi.createElement(PROP_PATH, "wingMountedEngine")
if bi.WING_MOUNTED:
tixi.updateTextElement(PROP_PATH + "/wingMountedEngine", "True")
else:
tixi.updateTextElement(PROP_PATH + "/wingMountedEngine", "False")
else:
temp = tixi.getTextElement(PROP_PATH + "/wingMountedEngine")
if temp == "False":
bi.WING_MOUNTED = False
else:
bi.WING_MOUNTED = True
# User Case Balance
if not tixi.checkElement(BC_PATH + "/userCase"):
tixi.createElement(BC_PATH, "userCase")
if bi.USER_CASE:
tixi.updateTextElement(BC_PATH + "/userCase", "True")
print("1")
else:
tixi.updateTextElement(BC_PATH + "/userCase", "False")
print("2")
else:
temp = tixi.getTextElement(BC_PATH + "/userCase")
if temp == "False":
bi.USER_CASE = False
else:
bi.USER_CASE = True
if bi.USER_CASE:
if tixi.checkElement(BC_PATH + "/fuelPercentage"):
bi.F_PERC = tixi.getDoubleElement(BC_PATH + "/fuelPercentage")
elif bi.F_PERC:
tixi.createElement(BC_PATH, "fuelPercentage")
tixi.updateDoubleElement(BC_PATH + "/fuelPercentage", bi.F_PERC,
"%g")
else:
raise Exception("User balance option defined" +
" True but no fuel percentage data in the" +
" CPACS file or in th BalanceInput class.")
if tixi.checkElement(BC_PATH + "/payloadPercentage"):
bi.P_PERC = tixi.getDoubleElement(BC_PATH + "/payloadPercentage")
elif bi.P_PERC:
tixi.createElement(BC_PATH, "payloadPercentage")
tixi.updateDoubleElement(BC_PATH + "/payloadPercentage", bi.P_PERC,
"%g")
else:
raise Exception("User balance option defined" +
" True but no payload percentage data in" +
" the CPACS file or in th BalanceInput class.")
# REQUIRED TOOLSPECIFIC DATA ============================================
# Fuel
mw.mass_fuel_maxpass = tixi.getDoubleElement(FMP_PATH)
# REQUIRED MASSBREAKDOWN DATA ===========================================
mw.maximum_take_off_mass = tixi.getDoubleElement(MTOM_PATH)
mw.operating_empty_mass = tixi.getDoubleElement(OEM_PATH)
mw.mass_payload = tixi.getDoubleElement(PAY_PATH)
mw.mass_fuel_max = tixi.getDoubleElement(F_PATH)
log.info("Data from CPACS file succesfully extracted")
# Saving and closing the cpacs file ======================================
tixi.save(cpacs_in)
return (mw, bi)
def cpacs_weight_update(out, mw, ui, cpacs_out_path):
""" The function that update the cpacs file after the Weight_unc_main
program.
Args:
out (class): Output class.
mw (class): Mass and weight class.
ui (class): UserInputs class.
cpacs_out_path (str): Path of the output file.
"""
tixi = open_tixi(cpacs_out_path)
# Path definition
MB_PATH = "/cpacs/vehicles/aircraft/model/analyses/massBreakdown"
if tixi.checkElement(MB_PATH):
tixi.removeElement(MB_PATH)
MD_PATH = MB_PATH + "/designMasses"
MTOM_PATH = MD_PATH + "/mTOM"
MZFM_PATH = MD_PATH + "/mZFM"
MF_PATH = MB_PATH + "/fuel/massDescription"
OEM_PATH = MB_PATH + "/mOEM/massDescription"
PAY_PATH = MB_PATH + "/payload/massDescription"
MC_PATH = MB_PATH + "/payload/mCargo"
EM_PATH = MB_PATH + "/mOEM/mEM"
OIM_PATH = MB_PATH + "/mOEM/mOperatorItems/mCrewMembers/massDescription"
MSYS_PATH = EM_PATH + "/mSystems/massDescription/mass"
MSTR_PATH = EM_PATH + "/mStructure/massDescription/mass"
MEN_PATH = EM_PATH + "/mPowerUnits/massDescription/mass"
create_branch(tixi, MTOM_PATH + "/mass", False)
create_branch(tixi, MZFM_PATH + "/mass", False)
create_branch(tixi, MF_PATH + "/mass", False)
create_branch(tixi, OEM_PATH + "/mass", False)
create_branch(tixi, PAY_PATH + "/mass", False)
create_branch(tixi, MC_PATH, False)
create_branch(tixi, OIM_PATH + "/mass", False)
create_branch(tixi, EM_PATH, False)
create_branch(tixi, MSYS_PATH, False)
create_branch(tixi, MSTR_PATH, False)
create_branch(tixi, MEN_PATH, False)
# DESIGN MASSES
add_uid(tixi, MTOM_PATH, "MTOM")
tixi.createElement(MTOM_PATH, "name")
tixi.updateTextElement(MTOM_PATH + "/name", "Maximum take-off mass")
tixi.createElement(MTOM_PATH, "description")
tixi.updateTextElement(
MTOM_PATH + "/description",
"Maximum " + "take off mass [kg], CoG coordinate [m] and " +
"moment of inertia.",
)
tixi.updateDoubleElement(MTOM_PATH + "/mass", mw.maximum_take_off_mass,
"%g")
# MZFM
add_uid(tixi, MZFM_PATH, "MZFM")
tixi.createElement(MZFM_PATH, "name")
tixi.updateTextElement(MZFM_PATH + "/name", "Maximum zero fuel mass")
tixi.createElement(MZFM_PATH, "description")
tixi.updateTextElement(
MZFM_PATH + "/description",
"Maximum " + "zero fuel mass [kg] and corresponding CoG " +
"coordinate [m], moment of inertia.",
)
tixi.updateDoubleElement(MZFM_PATH + "/mass", mw.zero_fuel_mass, "%g")
# FUEL MASS
add_uid(tixi, MF_PATH, "MFM")
tixi.createElement(MF_PATH, "name")
tixi.updateTextElement(MF_PATH + "/name", "Max fuel mass")
tixi.createElement(MF_PATH, "description")
tixi.updateTextElement(MF_PATH + "/description", "Maximum fuel mass [kg].")
tixi.updateDoubleElement(MF_PATH + "/mass", mw.mass_fuel_max, "%g")
# OEM
add_uid(tixi, OEM_PATH, "OEM")
tixi.createElement(OEM_PATH, "name")
tixi.updateTextElement(OEM_PATH + "/name", "Operating empty mass")
tixi.createElement(OEM_PATH, "description")
tixi.updateTextElement(
OEM_PATH + "/description",
"Operating empty" + " mass [kg] and related inertia [kgm^2].")
tixi.updateDoubleElement(OEM_PATH + "/mass", mw.operating_empty_mass, "%g")
tixi.updateDoubleElement(OIM_PATH + "/mass", mw.mass_crew, "%g")
add_uid(tixi, OIM_PATH, "massCrew")
tixi.updateDoubleElement(MSYS_PATH, mw.mass_systems, "%g")
add_uid(tixi, EM_PATH + "/mSystems/massDescription", "mSys")
tixi.updateDoubleElement(MSTR_PATH, mw.mass_structure, "%g")
add_uid(tixi, EM_PATH + "/mStructure/massDescription", "mStrt")
tixi.updateDoubleElement(MEN_PATH, mw.mass_engines, "%g")
add_uid(tixi, EM_PATH + "/mPowerUnits/massDescription", "mEng")
# PAYLOAD MASS AND FUEL CARGO MASS =======================================
add_uid(tixi, PAY_PATH, "MPM")
tixi.createElement(PAY_PATH, "name")
tixi.updateTextElement(PAY_PATH + "/name", "Max payload mass")
tixi.createElement(PAY_PATH, "description")
tixi.updateTextElement(PAY_PATH + "/description",
"Maximum payload mass [kg].")
tixi.updateDoubleElement(PAY_PATH + "/mass", mw.mass_payload, "%g")
tixi.createElement(MC_PATH, "massCargo")
tixi.updateDoubleElement(MC_PATH + "/massCargo", ui.MASS_CARGO, "%g")
tixi.save(cpacs_out_path)
return ()
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
cpacs = CPACS(cpacs_path)
# Get aeroMap list to plot
aeromap_to_plot_xpath = PLOT_XPATH + "/aeroMapToPlot"
aeromap_uid_list = []
# Option to select aeromap manualy
manual_selct = get_value_or_default(cpacs.tixi, PLOT_XPATH + "/manualSelection", False)
if manual_selct:
aeromap_uid_list = open_select_aeromap_gui(cpacs)
create_branch(cpacs.tixi, aeromap_to_plot_xpath)
add_string_vector(cpacs.tixi, aeromap_to_plot_xpath, aeromap_uid_list)
else:
try:
aeromap_uid_list = get_string_vector(cpacs.tixi, aeromap_to_plot_xpath)
except ValueError:
# If aeroMapToPlot is not define, select manualy anyway
aeromap_uid_list = open_select_aeromap_gui(cpacs)
create_branch(cpacs.tixi, aeromap_to_plot_xpath)
add_string_vector(cpacs.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 = cpacs.get_aeromap_by_uid(aeromap_uid).df
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 = cpacs.ac_name
criterion = pd.Series([True] * len(aeromap.index))
groupby_list = ["uid", "machNumber", "altitude", "angleOfSideslip"]
# Get criterion from CPACS
crit_xpath = PLOT_XPATH + "/criterion"
alt_crit = get_value_or_default(cpacs.tixi, crit_xpath + "/alt", "None")
mach_crit = get_value_or_default(cpacs.tixi, crit_xpath + "/mach", "None")
aos_crit = get_value_or_default(cpacs.tixi, crit_xpath + "/aos", "None")
cpacs.save_cpacs(cpacs_out_path, overwrite=True)
# Modify criterion and title according to user option
if len(aeromap["altitude"].unique()) == 1:
title += " - Alt = " + str(aeromap["altitude"].loc[0])
groupby_list.remove("altitude")
elif alt_crit not in NONE_LIST:
criterion = criterion & (aeromap.altitude == alt_crit)
title += " - Alt = " + str(alt_crit)
groupby_list.remove("altitude")
if len(aeromap["machNumber"].unique()) == 1:
title += " - Mach = " + str(aeromap["machNumber"].loc[0])
groupby_list.remove("machNumber")
elif mach_crit not in NONE_LIST:
criterion = criterion & (aeromap.machNumber == mach_crit)
title += " - Mach = " + str(mach_crit)
groupby_list.remove("machNumber")
if len(aeromap["angleOfSideslip"].unique()) == 1:
title += " - AoS = " + str(aeromap["angleOfSideslip"].loc[0])
groupby_list.remove("angleOfSideslip")
elif aos_crit not in NONE_LIST:
criterion = criterion & (aeromap.angleOfSideslip == aos_crit)
title += " - AoS = " + str(aos_crit)
groupby_list.remove("angleOfSideslip")
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["angleOfAttack"], grp["cl"], "x-", label=legend)
axs[1, 0].plot(grp["angleOfAttack"], grp["cd"], "x-")
axs[0, 1].plot(grp["angleOfAttack"], grp["cms"], "x-")
axs[1, 1].plot(grp["angleOfAttack"], 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 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
"""
cpacs = CPACS(cpacs_path)
if not os.path.exists(wkdir):
raise OSError("The working directory : " + wkdir + "does not exit!")
dir_list = os.listdir(wkdir)
# Get and save Wetted area
wetted_area = get_wetted_area(wkdir)
create_branch(cpacs.tixi, WETTED_AREA_XPATH)
cpacs.tixi.updateDoubleElement(WETTED_AREA_XPATH, wetted_area, "%g")
# Check if loads shoud be extracted
check_extract_loads_xpath = SU2_XPATH + "/results/extractLoads"
check_extract_loads = get_value_or_default(cpacs.tixi,
check_extract_loads_xpath,
False)
# Get fixed_cl option
fixed_cl_xpath = SU2_XPATH + "/fixedCL"
fixed_cl = get_value_or_default(cpacs.tixi, fixed_cl_xpath, "NO")
# Get aeroMap uid
if fixed_cl == "YES":
aeromap_uid = "aeroMap_fixedCL_SU2"
elif fixed_cl == "NO":
su2_aeromap_xpath = SU2_XPATH + "/aeroMapUID"
aeromap_uid = get_value(cpacs.tixi, su2_aeromap_xpath)
else:
raise ValueError(
"The value for fixed_cl is not valid! Should be YES or NO")
aeromap = cpacs.get_aeromap_by_uid(aeromap_uid)
alt_list = aeromap.get("altitude").tolist()
mach_list = aeromap.get("machNumber").tolist()
aoa_list = aeromap.get("angleOfAttack").tolist()
aos_list = aeromap.get("angleOfSideslip").tolist()
case_dir_list = [dir for dir in dir_list if "Case" in dir]
for config_dir in sorted(case_dir_list):
case_nb = int(config_dir.split("_")[0].split("Case")[1])
aoa = aoa_list[case_nb]
aos = aos_list[case_nb]
mach = mach_list[case_nb]
alt = alt_list[case_nb]
config_dir_path = os.path.join(wkdir, config_dir)
if os.path.isdir(config_dir_path):
force_file_path = os.path.join(config_dir_path,
"forces_breakdown.dat")
if not os.path.isfile(force_file_path):
raise OSError("No result force file have been found!")
if fixed_cl == "YES":
cl_cd, aoa = get_efficiency_and_aoa(force_file_path)
# Replace aoa with the with the value from fixed cl calculation
aeromap.df.loc[0, ["angleOfAttack"]] = aoa
# Save cl/cd found during the fixed CL calculation
# TODO: maybe save cl/cd somewhere else
lDRatio_xpath = "/cpacs/toolspecific/CEASIOMpy/ranges/lDRatio"
create_branch(cpacs.tixi, lDRatio_xpath)
cpacs.tixi.updateDoubleElement(lDRatio_xpath, cl_cd, "%g")
# Read result file
with open(force_file_path) 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 = get_value_or_default(cpacs.tixi,
rotation_rate_xpath, -1.0)
ref_len = cpacs.aircraft.ref_lenght
adim_rot_rate = rotation_rate * ref_len / velocity
coefs = {
"cl": cl,
"cd": cd,
"cs": cs,
"cmd": cmd,
"cms": cms,
"cml": cml
}
if "_dp" in config_dir:
for coef in COEFS:
coef_baseline = aeromap.get(coef,
alt=alt,
mach=mach,
aoa=aoa,
aos=aos)
dcoef = (coefs[coef] - coef_baseline) / adim_rot_rate
aeromap.add_damping_derivatives(
alt=alt,
mach=mach,
aos=aos,
aoa=aoa,
coef=coef,
axis="dp",
value=dcoef,
rate=rotation_rate,
)
elif "_dq" in config_dir:
for coef in COEFS:
coef_baseline = aeromap.get(coef,
alt=alt,
mach=mach,
aoa=aoa,
aos=aos)
dcoef = (coefs[coef] - coef_baseline) / adim_rot_rate
aeromap.add_damping_derivatives(
alt=alt,
mach=mach,
aos=aos,
aoa=aoa,
coef=coef,
axis="dq",
value=dcoef,
rate=rotation_rate,
)
elif "_dr" in config_dir:
for coef in COEFS:
coef_baseline = aeromap.get(coef,
alt=alt,
mach=mach,
aoa=aoa,
aos=aos)
dcoef = (coefs[coef] - coef_baseline) / adim_rot_rate
aeromap.add_damping_derivatives(
alt=alt,
mach=mach,
aos=aos,
aoa=aoa,
coef=coef,
axis="dr",
value=dcoef,
rate=rotation_rate,
)
elif "_TED_" in config_dir:
# TODO: convert when it is possible to save TED in cpacspy
raise NotImplementedError("TED not implemented yet")
# 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 = a.p.m.f.IncrementMap(ted_uid)
# 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: # Baseline coefficients, (no damping derivative or control surfaces case)
aeromap.add_coefficients(
alt=alt,
mach=mach,
aos=aos,
aoa=aoa,
cd=cd,
cl=cl,
cs=cs,
cml=cml,
cmd=cmd,
cms=cms,
)
if check_extract_loads:
results_files_dir = os.path.join(wkdir, config_dir)
extract_loads(results_files_dir)
# Save object Coef in the CPACS file
aeromap.save()
# Save the CPACS file
cpacs.save_cpacs(cpacs_out_path, overwrite=True)
