def test_get_string_vector(): """ Test the function 'get_string_vector'""" tixi = cpsf.open_tixi(CPACS_IN_PATH) xpath = '/cpacs/toolspecific/CEASIOMpy/testVector' # Add a new vector string_vector = ['aaa', 'zzz'] cpsf.add_string_vector(tixi, xpath, string_vector) # Get a string vector string_vector_get = cpsf.get_string_vector(tixi, xpath) assert string_vector_get == string_vector # Raise an error when the XPath is wrong wrong_xpath = '/cpacs/toolspecific/CEASIOMpy/testVectorWrong' with pytest.raises(ValueError): vector = cpsf.get_string_vector(tixi, wrong_xpath) # Raise an error when no value at XPath no_value_xpath = '/cpacs/toolspecific/CEASIOMpy' with pytest.raises(ValueError): vector = cpsf.get_string_vector(tixi, no_value_xpath)
def add_skin_friction(cpacs_path, cpacs_out_path): """ Function to add the skin frinction drag coeffienct to aerodynamic coefficients Function 'add_skin_friction' add the skin friction drag 'cd0' to the SU2 and pyTornado aeroMap, if their UID is not geven, it will add skin friction to all aeroMap. For each aeroMap it creates a new aeroMap where the skin friction drag coeffienct is added with the correct projcetions. Args: cpacs_path (str): Path to CPACS file cpacs_out_path (str): Path to CPACS output file """ tixi = cpsf.open_tixi(cpacs_path) tigl = cpsf.open_tigl(tixi) wing_area_max, wing_span_max = get_largest_wing_dim(tixi, tigl) analyses_xpath = '/cpacs/toolspecific/CEASIOMpy/geometry/analysis' # Requiered input data from CPACS wetted_area = cpsf.get_value(tixi, analyses_xpath + '/wettedArea') # Wing area/span, default values will be calated if no value found in the CPACS file wing_area_xpath = analyses_xpath + '/wingArea' wing_area = cpsf.get_value_or_default(tixi, wing_area_xpath, wing_area_max) wing_span_xpath = analyses_xpath + '/wingSpan' wing_span = cpsf.get_value_or_default(tixi, wing_span_xpath, wing_span_max) aeromap_uid_list = [] # Try to get aeroMapToCalculate aeroMap_to_clculate_xpath = SF_XPATH + '/aeroMapToCalculate' if tixi.checkElement(aeroMap_to_clculate_xpath): aeromap_uid_list = cpsf.get_string_vector(tixi, aeroMap_to_clculate_xpath) else: aeromap_uid_list = [] # If no aeroMap in aeroMapToCalculate, get all existing aeroMap if len(aeromap_uid_list) == 0: try: aeromap_uid_list = apmf.get_aeromap_uid_list(tixi) except: raise ValueError( 'No aeroMap has been found in this CPACS file, skin friction cannot be added!' ) # Get unique aeroMap list aeromap_uid_list = list(set(aeromap_uid_list)) new_aeromap_uid_list = [] # Add skin friction to all listed aeroMap for aeromap_uid in aeromap_uid_list: log.info('adding skin friction coefficients to: ' + aeromap_uid) # Get orignial aeroPerformanceMap AeroCoef = apmf.get_aeromap(tixi, aeromap_uid) AeroCoef.complete_with_zeros() # Create new aeroCoefficient object to store coef with added skin friction AeroCoefSF = apmf.AeroCoefficient() AeroCoefSF.alt = AeroCoef.alt AeroCoefSF.mach = AeroCoef.mach AeroCoefSF.aoa = AeroCoef.aoa AeroCoefSF.aos = AeroCoef.aos # Iterate over all cases case_count = AeroCoef.get_count() for case in range(case_count): # Get parameters for this case alt = AeroCoef.alt[case] mach = AeroCoef.mach[case] aoa = AeroCoef.aoa[case] aos = AeroCoef.aos[case] # Calculate Cd0 for this case cd0 = estimate_skin_friction_coef(wetted_area,wing_area,wing_span, \ mach,alt) # Projection of cd0 on cl, cd and cs axis #TODO: Should Cd0 be projected or not??? aoa_rad = math.radians(aoa) aos_rad = math.radians(aos) cd0_cl = cd0 * math.sin(aoa_rad) cd0_cd = cd0 * math.cos(aoa_rad) * math.cos(aos_rad) cd0_cs = cd0 * math.sin(aos_rad) # Update aerodynamic coefficients cl = AeroCoef.cl[case] + cd0_cl cd = AeroCoef.cd[case] + cd0_cd cs = AeroCoef.cs[case] + cd0_cs # Shoud we change something? e.i. if a force is not apply at aero center...? if len(AeroCoef.cml): cml = AeroCoef.cml[case] else: cml = 0.0 # Shoud be change, just to test pyTornado if len(AeroCoef.cmd): cmd = AeroCoef.cmd[case] else: cmd = 0.0 if len(AeroCoef.cms): cms = AeroCoef.cms[case] else: cms = 0.0 # Add new coefficients into the aeroCoefficient object AeroCoefSF.add_coefficients(cl, cd, cs, cml, cmd, cms) # Create new aeroMap UID aeromap_sf_uid = aeromap_uid + '_SkinFriction' new_aeromap_uid_list.append(aeromap_sf_uid) # Create new description description_xpath = tixi.uIDGetXPath(aeromap_uid) + '/description' sf_description = cpsf.get_value( tixi, description_xpath) + ' Skin friction has been add to this AeroMap.' apmf.create_empty_aeromap(tixi, aeromap_sf_uid, sf_description) # Save aeroCoefficient object Coef in the CPACS file apmf.save_parameters(tixi, aeromap_sf_uid, AeroCoefSF) apmf.save_coefficients(tixi, aeromap_sf_uid, AeroCoefSF) # Get aeroMap list to plot plot_xpath = '/cpacs/toolspecific/CEASIOMpy/aerodynamics/plotAeroCoefficient' aeromap_to_plot_xpath = plot_xpath + '/aeroMapToPlot' if tixi.checkElement(aeromap_to_plot_xpath): aeromap_uid_list = cpsf.get_string_vector(tixi, aeromap_to_plot_xpath) new_aeromap_to_plot = aeromap_uid_list + new_aeromap_uid_list new_aeromap_to_plot = list(set(new_aeromap_to_plot)) cpsf.add_string_vector(tixi, aeromap_to_plot_xpath, new_aeromap_to_plot) else: cpsf.create_branch(tixi, aeromap_to_plot_xpath) cpsf.add_string_vector(tixi, aeromap_to_plot_xpath, new_aeromap_uid_list) log.info('AeroMap "' + aeromap_uid + '" has been added to the CPACS file') cpsf.close_tixi(tixi, cpacs_out_path)
def plot_aero_coef(cpacs_path, cpacs_out_path): """Plot Aero coefficients from the chosen aeroMap in the CPACS file Function 'plot_aero_coef' can plot one or several aeromap from the CPACS file according to some user option, these option will be shown in the the SettingGUI or default values will be used. Args: cpacs_path (str): Path to CPACS file cpacs_out_path (str):Path to CPACS output file """ # Open TIXI handle tixi = cpsf.open_tixi(cpacs_path) aircraft_name = cpsf.aircraft_name(tixi) # Get aeroMap list to plot aeromap_to_plot_xpath = PLOT_XPATH + '/aeroMapToPlot' aeromap_uid_list = [] # Option to select aeromap manualy manual_selct = cpsf.get_value_or_default(tixi, PLOT_XPATH + '/manualSelection', False) if manual_selct: aeromap_uid_list = call_select_aeromap(tixi) cpsf.create_branch(tixi, aeromap_to_plot_xpath) cpsf.add_string_vector(tixi, aeromap_to_plot_xpath, aeromap_uid_list) else: try: aeromap_uid_list = cpsf.get_string_vector(tixi, aeromap_to_plot_xpath) except: # If aeroMapToPlot is not define, select manualy anyway aeromap_uid_list = call_select_aeromap(tixi) cpsf.create_branch(tixi, aeromap_to_plot_xpath) cpsf.add_string_vector(tixi, aeromap_to_plot_xpath, aeromap_uid_list) # Create DataFrame from aeromap(s) aeromap_df_list = [] for aeromap_uid in aeromap_uid_list: aeromap_df = apmf.get_datafram_aeromap(tixi, aeromap_uid) aeromap_df['uid'] = aeromap_uid aeromap_df_list.append(aeromap_df) aeromap = pd.concat(aeromap_df_list, ignore_index=True) if len(aeromap_uid_list) > 1: uid_crit = None else: uid_crit = aeromap_uid_list[0] # Default options title = aircraft_name criterion = pd.Series([True] * len(aeromap.index)) groupby_list = ['uid', 'mach', 'alt', 'aos'] # Get criterion from CPACS crit_xpath = PLOT_XPATH + '/criterion' alt_crit = cpsf.get_value_or_default(tixi, crit_xpath + '/alt', 'None') mach_crit = cpsf.get_value_or_default(tixi, crit_xpath + '/mach', 'None') aos_crit = cpsf.get_value_or_default(tixi, crit_xpath + '/aos', 'None') cpsf.close_tixi(tixi, cpacs_out_path) # Modify criterion and title according to user option if len(aeromap['alt'].unique()) == 1: title += ' - Alt = ' + str(aeromap['alt'].loc[0]) groupby_list.remove('alt') elif alt_crit not in NONE_LIST: criterion = criterion & (aeromap.alt == alt_crit) title += ' - Alt = ' + str(alt_crit) groupby_list.remove('alt') if len(aeromap['mach'].unique()) == 1: title += ' - Mach = ' + str(aeromap['mach'].loc[0]) groupby_list.remove('mach') elif mach_crit not in NONE_LIST: criterion = criterion & (aeromap.mach == mach_crit) title += ' - Mach = ' + str(mach_crit) groupby_list.remove('mach') if len(aeromap['aos'].unique()) == 1: title += ' - AoS = ' + str(aeromap['aos'].loc[0]) groupby_list.remove('aos') elif aos_crit not in NONE_LIST: criterion = criterion & (aeromap.aos == aos_crit) title += ' - AoS = ' + str(aos_crit) groupby_list.remove('aos') if uid_crit is not None and len(groupby_list) > 1: criterion = criterion & (aeromap.uid == uid_crit) title += ' - ' + uid_crit groupby_list.remove('uid') # Plot settings fig, axs = plt.subplots(2, 3) fig.suptitle(title, fontsize=14) fig.set_figheight(8) fig.set_figwidth(15) fig.subplots_adjust(left=0.06) axs[0, 1].axhline(y=0.0, color='k', linestyle='-') # Line at Cm=0 # Plot aerodynamic coerfficients for value, grp in aeromap.loc[criterion].groupby(groupby_list): legend = write_legend(groupby_list, value) axs[0, 0].plot(grp['aoa'], grp['cl'], 'x-', label=legend) axs[1, 0].plot(grp['aoa'], grp['cd'], 'x-') axs[0, 1].plot(grp['aoa'], grp['cms'], 'x-') axs[1, 1].plot(grp['aoa'], grp['cl'] / grp['cd'], 'x-') axs[0, 2].plot(grp['cd'], grp['cl'], 'x-') axs[1, 2].plot(grp['cl'], grp['cl'] / grp['cd'], 'x-') # Set subplot options subplot_options(axs[0, 0], 'CL', 'AoA') subplot_options(axs[1, 0], 'CD', 'AoA') subplot_options(axs[0, 1], 'Cm', 'AoA') subplot_options(axs[1, 1], 'CL/CD', 'AoA') subplot_options(axs[0, 2], 'CL', 'CD') subplot_options(axs[1, 2], 'CL/CD', 'CL') fig.legend(loc='upper right') plt.show()
def __init__(self, tabs, tixi, module_name): """Tab class Note: A tab will only be created if the module actually has any settings which are to be shown Args: tabs (TODO): TODO tixi (handle): Tixi handle module_name (str): String of the module name for which a tab is to be created """ self.var_dict = {} self.group_dict = {} self.module_name = module_name self.tabs = tabs self.tixi = tixi self.tab = tk.Frame(tabs, borderwidth=1) tabs.add(self.tab, text=module_name) # Get GUI dict from specs specs = mif.get_specs_for_module(module_name) self.gui_dict = specs.cpacs_inout.get_gui_dict() #canvas has replaced self.tab in the following lines space_label = tk.Label(self.tab, text=' ') space_label.grid(column=0, row=0) row_pos = 1 for key, (name, def_value, dtype, unit, xpath, description, group) in self.gui_dict.items(): # Create a LabelFrame for new groupe if group: if not group in self.group_dict: self.labelframe = tk.LabelFrame(self.tab, text=group) self.labelframe.grid(column=0, row=row_pos, columnspan=3,sticky= tk.W, padx=5, pady=5) self.group_dict[group] = self.labelframe parent = self.group_dict[group] else: # if not a group, use tab as parent parent = self.tab # Name label for variable if (name is not '__AEROMAP_SELECTION' and name is not '__AEROMAP_CHECHBOX'): self.name_label = tk.Label(parent, text= name) self.name_label.grid(column=0, row=row_pos, sticky= tk.W, padx=5, pady=5) # Type and Value if dtype is bool: self.var_dict[key] = tk.BooleanVar() value = cpsf.get_value_or_default(self.tixi,xpath,def_value) self.var_dict[key].set(value) bool_entry = tk.Checkbutton(parent, text='', variable=self.var_dict[key]) bool_entry.grid(column=1, row=row_pos, padx=5, pady=5) elif dtype is int: value = cpsf.get_value_or_default(self.tixi, xpath, def_value) self.var_dict[key] = tk.IntVar() self.var_dict[key].set(int(value)) value_entry = tk.Entry(parent, bd=2, textvariable=self.var_dict[key]) value_entry.grid(column=1, row=row_pos, padx=5, pady=5) elif dtype is float: value = cpsf.get_value_or_default(self.tixi, xpath, def_value) self.var_dict[key] = tk.DoubleVar() self.var_dict[key].set(value) value_entry = tk.Entry(parent, bd=2, textvariable=self.var_dict[key]) value_entry.grid(column=1, row=row_pos, padx=5, pady=5) elif dtype is 'pathtype': value = cpsf.get_value_or_default(self.tixi,xpath,def_value) self.var_dict[key] = tk.StringVar() self.var_dict[key].set(value) value_entry = tk.Entry(parent, textvariable=self.var_dict[key]) value_entry.grid(column=1, row=row_pos, padx=5, pady=5) self.key = key self.browse_button = tk.Button(parent, text="Browse", command=self._browse_file) self.browse_button.grid(column=2, row=row_pos, padx=5, pady=5) elif dtype is list: if name == '__AEROMAP_SELECTION': # Get the list of all AeroMaps self.aeromap_uid_list = apm.get_aeromap_uid_list(self.tixi) # Try to get the pre-selected AeroMap from the xpath try: selected_aeromap = cpsf.get_value(self.tixi,xpath) selected_aeromap_index = self.aeromap_uid_list.index(selected_aeromap) except: selected_aeromap = '' selected_aeromap_index = 0 self.labelframe = tk.LabelFrame(parent, text='Choose an AeroMap') self.labelframe.grid(column=0, row=row_pos, columnspan=3, sticky=tk.W, padx=5, pady=5) # The Combobox is directly use as the varaible self.var_dict[key] = ttk.Combobox(self.labelframe, values=self.aeromap_uid_list) self.var_dict[key].current(selected_aeromap_index) self.var_dict[key].grid(column=1, row=row_pos, padx=5, pady=5) elif name == '__AEROMAP_CHECHBOX': # Just to find back the name when data are saved self.var_dict[key] = None # __AEROMAP_CHECHBOX is a bit different, data are saved in their own dictionary self.aeromap_var_dict = {} # Get the list of all AeroMaps self.aeromap_uid_list = apm.get_aeromap_uid_list(self.tixi) self.labelframe = tk.LabelFrame(parent, text='Selecte AeroMap(s)') self.labelframe.grid(column=0, row=row_pos, columnspan=3, sticky=tk.W, padx=5, pady=5) # Try to get pre-selected AeroMaps from the xpath try: selected_aeromap = cpsf.get_string_vector(self.tixi,xpath) except: selected_aeromap = '' # Create one checkbox for each AeroMap for aeromap in self.aeromap_uid_list: self.aeromap_var_dict[aeromap] = tk.BooleanVar() #if aeromap in selected_aeromap: # For now, set all to True self.aeromap_var_dict[aeromap].set(True) aeromap_entry = tk.Checkbutton(self.labelframe,text=aeromap,variable=self.aeromap_var_dict[aeromap]) aeromap_entry.pack()#side=tk.TOP, anchor='w') else: # Other kind of list (not aeroMap) # 'def_value' will be the list of possibilies in this case # Try to get the pre-selected AeroMap from the xpath try: # TODO Should be retested... selected_value = cpsf.get_value(self.tixi,xpath) selected_value_index = def_value.index(selected_value) except: selected_value = '' selected_value_index = 0 # The Combobox is directly use as the varaible self.var_dict[key] = ttk.Combobox(parent, values=def_value) self.var_dict[key].current(selected_value_index) self.var_dict[key].grid(column=1, row=row_pos, padx=5, pady=5) else: value = cpsf.get_value_or_default(self.tixi,xpath,def_value) self.var_dict[key] = tk.StringVar() self.var_dict[key].set(value) value_entry = tk.Entry(parent, textvariable=self.var_dict[key]) value_entry.grid(column=1, row=row_pos, padx=5, pady=5) # Units if unit and unit != '1': unit_label = tk.Label(parent, text=pretty_unit(unit)) unit_label.grid(column=2, row=row_pos, padx=5, pady=5) row_pos += 1
def generate_su2_config(cpacs_path, cpacs_out_path, wkdir): """Function to create SU2 confif file. Function 'generate_su2_config' reads data in the CPACS file and generate configuration files for one or multible flight conditions (alt,mach,aoa,aos) Source: * SU2 config template: https://github.com/su2code/SU2/blob/master/config_template.cfg Args: cpacs_path (str): Path to CPACS file cpacs_out_path (str):Path to CPACS output file wkdir (str): Path to the working directory """ # Get value from CPACS tixi = cpsf.open_tixi(cpacs_path) tigl = cpsf.open_tigl(tixi) # Get SU2 mesh path su2_mesh_xpath = '/cpacs/toolspecific/CEASIOMpy/filesPath/su2Mesh' su2_mesh_path = cpsf.get_value(tixi,su2_mesh_xpath) # Get reference values ref_xpath = '/cpacs/vehicles/aircraft/model/reference' ref_len = cpsf.get_value(tixi,ref_xpath + '/length') ref_area = cpsf.get_value(tixi,ref_xpath + '/area') ref_ori_moment_x = cpsf.get_value_or_default(tixi,ref_xpath+'/point/x',0.0) ref_ori_moment_y = cpsf.get_value_or_default(tixi,ref_xpath+'/point/y',0.0) ref_ori_moment_z = cpsf.get_value_or_default(tixi,ref_xpath+'/point/z',0.0) # Get SU2 settings settings_xpath = SU2_XPATH + '/settings' max_iter_xpath = settings_xpath + '/maxIter' max_iter = cpsf.get_value_or_default(tixi, max_iter_xpath,200) cfl_nb_xpath = settings_xpath + '/cflNumber' cfl_nb = cpsf.get_value_or_default(tixi, cfl_nb_xpath,1.0) mg_level_xpath = settings_xpath + '/multigridLevel' mg_level = cpsf.get_value_or_default(tixi, mg_level_xpath,3) # Mesh Marker bc_wall_xpath = SU2_XPATH + '/boundaryConditions/wall' bc_wall_list = su2f.get_mesh_marker(su2_mesh_path) cpsf.create_branch(tixi, bc_wall_xpath) bc_wall_str = ';'.join(bc_wall_list) tixi.updateTextElement(bc_wall_xpath,bc_wall_str) # Fixed CL parameters fixed_cl_xpath = SU2_XPATH + '/fixedCL' fixed_cl = cpsf.get_value_or_default(tixi, fixed_cl_xpath,'NO') target_cl_xpath = SU2_XPATH + '/targetCL' target_cl = cpsf.get_value_or_default(tixi, target_cl_xpath,1.0) if fixed_cl == 'NO': active_aeroMap_xpath = SU2_XPATH + '/aeroMapUID' aeromap_uid = cpsf.get_value(tixi,active_aeroMap_xpath) log.info('Configuration file for ""' + aeromap_uid + '"" calculation will be created.') # Get parameters of the aeroMap (alt,ma,aoa,aos) Param = apmf.get_aeromap(tixi,aeromap_uid) param_count = Param.get_count() if param_count >= 1: alt_list = Param.alt mach_list = Param.mach aoa_list = Param.aoa aos_list = Param.aos else: raise ValueError('No parametre have been found in the aeroMap!') else: # if fixed_cl == 'YES': log.info('Configuration file for fixed CL calculation will be created.') range_xpath = '/cpacs/toolspecific/CEASIOMpy/ranges' # Parameters fixed CL calulation param_count = 1 # These parameters will not be used aoa_list = [0.0] aos_list = [0.0] cruise_mach_xpath= range_xpath + '/cruiseMach' mach = cpsf.get_value_or_default(tixi,cruise_mach_xpath,0.78) mach_list = [mach] cruise_alt_xpath= range_xpath + '/cruiseAltitude' alt = cpsf.get_value_or_default(tixi,cruise_alt_xpath,12000) alt_list = [alt] aeromap_uid = 'aeroMap_fixedCL_SU2' description = 'AeroMap created for SU2 fixed CL value of: ' + str(target_cl) apmf.create_empty_aeromap(tixi, aeromap_uid, description) Parameters = apmf.AeroCoefficient() Parameters.alt = alt_list Parameters.mach = mach_list Parameters.aoa = aoa_list Parameters.aos = aos_list apmf.save_parameters(tixi,aeromap_uid,Parameters) tixi.updateTextElement(SU2_XPATH+ '/aeroMapUID',aeromap_uid) # Get and modify the default configuration file cfg = su2f.read_config(DEFAULT_CONFIG_PATH) # General parmeters cfg['REF_LENGTH'] = ref_len cfg['REF_AREA'] = ref_area cfg['REF_ORIGIN_MOMENT_X'] = ref_ori_moment_x cfg['REF_ORIGIN_MOMENT_Y'] = ref_ori_moment_y cfg['REF_ORIGIN_MOMENT_Z'] = ref_ori_moment_z # Settings cfg['INNER_ITER'] = int(max_iter) cfg['CFL_NUMBER'] = cfl_nb cfg['MGLEVEL'] = int(mg_level) # Fixed CL mode (AOA will not be taken into account) cfg['FIXED_CL_MODE'] = fixed_cl cfg['TARGET_CL'] = target_cl cfg['DCL_DALPHA'] = '0.1' cfg['UPDATE_AOA_ITER_LIMIT'] = '50' cfg['ITER_DCL_DALPHA'] = '80' # TODO: correct value for the 3 previous parameters ?? # Mesh Marker bc_wall_str = '(' + ','.join(bc_wall_list) + ')' cfg['MARKER_EULER'] = bc_wall_str cfg['MARKER_FAR'] = ' (Farfield)' # TODO: maybe make that a variable cfg['MARKER_SYM'] = ' (0)' # TODO: maybe make that a variable? cfg['MARKER_PLOTTING'] = bc_wall_str cfg['MARKER_MONITORING'] = bc_wall_str cfg['MARKER_MOVING'] = '( NONE )' # TODO: when do we need to define MARKER_MOVING? cfg['DV_MARKER'] = bc_wall_str # Parameters which will vary for the different cases (alt,mach,aoa,aos) for case_nb in range(param_count): cfg['MESH_FILENAME'] = su2_mesh_path alt = alt_list[case_nb] mach = mach_list[case_nb] aoa = aoa_list[case_nb] aos = aos_list[case_nb] Atm = get_atmosphere(alt) pressure = Atm.pres temp = Atm.temp cfg['MACH_NUMBER'] = mach cfg['AOA'] = aoa cfg['SIDESLIP_ANGLE'] = aos cfg['FREESTREAM_PRESSURE'] = pressure cfg['FREESTREAM_TEMPERATURE'] = temp cfg['ROTATION_RATE'] = '0.0 0.0 0.0' config_file_name = 'ConfigCFD.cfg' case_dir_name = ''.join(['Case',str(case_nb).zfill(2), '_alt',str(alt), '_mach',str(round(mach,2)), '_aoa',str(round(aoa,1)), '_aos',str(round(aos,1))]) case_dir_path = os.path.join(wkdir,case_dir_name) if not os.path.isdir(case_dir_path): os.mkdir(case_dir_path) config_output_path = os.path.join(wkdir,case_dir_name,config_file_name) su2f.write_config(config_output_path,cfg) # Damping derivatives damping_der_xpath = SU2_XPATH + '/options/clalculateDampingDerivatives' damping_der = cpsf.get_value_or_default(tixi,damping_der_xpath,False) if damping_der: rotation_rate_xpath = SU2_XPATH + '/options/rotationRate' rotation_rate = cpsf.get_value_or_default(tixi,rotation_rate_xpath,1.0) cfg['GRID_MOVEMENT'] = 'ROTATING_FRAME' cfg['ROTATION_RATE'] = str(rotation_rate) + ' 0.0 0.0' os.mkdir(os.path.join(wkdir,case_dir_name+'_dp')) config_output_path = os.path.join(wkdir,case_dir_name+'_dp',config_file_name) su2f.write_config(config_output_path,cfg) cfg['ROTATION_RATE'] = '0.0 ' + str(rotation_rate) + ' 0.0' os.mkdir(os.path.join(wkdir,case_dir_name+'_dq')) config_output_path = os.path.join(wkdir,case_dir_name+'_dq',config_file_name) su2f.write_config(config_output_path,cfg) cfg['ROTATION_RATE'] = '0.0 0.0 ' + str(rotation_rate) os.mkdir(os.path.join(wkdir,case_dir_name+'_dr')) config_output_path = os.path.join(wkdir,case_dir_name+'_dr',config_file_name) su2f.write_config(config_output_path,cfg) log.info('Damping derivatives cases directory has been created.') # Control surfaces deflections control_surf_xpath = SU2_XPATH + '/options/clalculateCotrolSurfacesDeflections' control_surf = cpsf.get_value_or_default(tixi,control_surf_xpath,False) if control_surf: # Get deformed mesh list su2_def_mesh_xpath = SU2_XPATH + '/availableDeformedMesh' if tixi.checkElement(su2_def_mesh_xpath): su2_def_mesh_list = cpsf.get_string_vector(tixi,su2_def_mesh_xpath) else: log.warning('No SU2 deformed mesh has been found!') su2_def_mesh_list = [] for su2_def_mesh in su2_def_mesh_list: mesh_path = os.path.join(wkdir,'MESH',su2_def_mesh) config_dir_path = os.path.join(wkdir,case_dir_name+'_'+su2_def_mesh.split('.')[0]) os.mkdir(config_dir_path) cfg['MESH_FILENAME'] = mesh_path config_file_name = 'ConfigCFD.cfg' config_output_path = os.path.join(wkdir,config_dir_path,config_file_name) su2f.write_config(config_output_path,cfg) # TODO: change that, but if it is save in tooloutput it will be erease by results... cpsf.close_tixi(tixi,cpacs_path)
def test_static_stability_analysis(): """Test function 'staticStabilityAnalysis' """ MODULE_DIR = os.path.dirname(os.path.abspath(__file__)) cpacs_path = os.path.join(MODULE_DIR,'ToolInput','CPACSTestStability.xml') cpacs_out_path = os.path.join(MODULE_DIR,'ToolOutput', 'CPACSTestStability.xml') csv_path = MODULE_DIR + '/ToolInput/csvtest.csv' tixi = cpsf.open_tixi(cpacs_path) # Get Aeromap UID list # uid_list = apmf.get_aeromap_uid_list(tixi) # aeromap_uid = uid_list[0] # # Import aeromap from the CSV to the xml # apmf.aeromap_from_csv(tixi, aeromap_uid, csv_path) # cpsf.close_tixi(tixi, cpacs_out_path) # Make the static stability analysis, on the modified xml file static_stability_analysis(cpacs_path, cpacs_out_path) # Assert that all error messages are present #log_path = os.path.join(LIB_DIR,'StabilityStatic','staticstability.log') # graph_cruising = False # errors = '' # #Open log file # with open(log_path, "r") as f : # # For each line in the log file # for line in f : # # if the info insureing that the graph of cruising aoa VS mach has been generated. # if 'graph : cruising aoa vs mach genrated' in line : # graph_cruising = True # # if 'warning' or 'error ' is in line # if 'ERROR' in line : # # check if error type (altitude) is in line # errors += line # TODO: remove, not good to test with the logfile # Assert that all error type happend only once. #assert graph_cruising == True tixi = cpsf.open_tixi(cpacs_out_path) static_xpath = '/cpacs/toolspecific/CEASIOMpy/stability/static' long_static_stable = cpsf.get_value(tixi, static_xpath+'/results/longitudinalStaticStable') lat_static_stable = cpsf.get_value(tixi, static_xpath+'/results/lateralStaticStable') dir_static_stable = cpsf.get_value(tixi, static_xpath+'/results/directionnalStaticStable') assert long_static_stable assert lat_static_stable assert not dir_static_stable trim_longi_alt = cpsf.get_value(tixi, static_xpath+'/trimConditions/longitudinal/altitude') trim_longi_mach = cpsf.get_value(tixi, static_xpath+'/trimConditions/longitudinal/machNumber') trim_longi_aoa = cpsf.get_value(tixi, static_xpath+'/trimConditions/longitudinal/angleOfAttack') trim_longi_aos = cpsf.get_value(tixi, static_xpath+'/trimConditions/longitudinal/angleOfSideslip') assert trim_longi_alt == 1400 assert trim_longi_mach == 0.6 assert trim_longi_aoa == 3.25803 assert trim_longi_aos == 0 trim_dir_alt = cpsf.get_string_vector(tixi, static_xpath+'/trimConditions/directional/altitude') trim_dir_mach = cpsf.get_string_vector(tixi, static_xpath+'/trimConditions/directional/machNumber') trim_dir_aoa = cpsf.get_string_vector(tixi, static_xpath+'/trimConditions/directional/angleOfAttack') trim_dir_aos = cpsf.get_string_vector(tixi, static_xpath+'/trimConditions/directional/angleOfSideslip') assert trim_dir_alt == ['2400','2500','2600','2700'] assert trim_dir_mach == ['0.6','0.5','0.5','0.5'] assert trim_dir_aoa == ['1','2','4','2.5'] assert trim_dir_aos == ['0','0','0','0'] cpsf.close_tixi(tixi, cpacs_out_path)
def plot_aero_coef(cpacs_path, cpacs_out_path): """Function to plot available aerodynamic coefficients from aeroMap. Function 'plot_aero_coef' plot aerodynamic coefficients (CL,CD,Cm) of the aeroMap selected in the CPACS file or if not define, ask the user to select them. Args: cpacs_path (str): Path to CPACS file cpacs_out_path (str):Path to CPACS output file """ # Open TIXI handle tixi = cpsf.open_tixi(cpacs_path) # Prepare subplots figure_1 = plt.figure(figsize=(9, 9)) subplot1 = figure_1.add_subplot(221) subplot2 = figure_1.add_subplot(222) subplot3 = figure_1.add_subplot(223) subplot4 = figure_1.add_subplot(224) LINE_STYLE = ['bo-', 'ro-', 'go-', 'co-', 'mo-', 'ko-', 'yo-'] # Get aeroMap list to plot aeromap_to_plot_xpath = PLOT_XPATH + '/aeroMapToPlot' aeromap_uid_list = [] try: aeromap_uid_list = cpsf.get_string_vector(tixi, aeromap_to_plot_xpath) except: # If aeroMapToPlot is not define, open GUI to select which ones shoud be aeromap_uid_list = call_select_aeromap(tixi) cpsf.create_branch(tixi, aeromap_to_plot_xpath) cpsf.add_string_vector(tixi, aeromap_to_plot_xpath, aeromap_uid_list) for i, aeromap_uid in enumerate(aeromap_uid_list): log.info('"' + aeromap_uid + '" will be added to the plot.') # Get aeroMap to plot and replace missing results with zeros AeroCoef = apmf.get_aeromap(tixi, aeromap_uid) AeroCoef.complete_with_zeros() AeroCoef.print_coef_list() # Subplot1 x1 = AeroCoef.aoa y1 = AeroCoef.cl subplot1.plot(x1, y1, LINE_STYLE[i]) # Subplot2 x2 = AeroCoef.aoa y2 = AeroCoef.cms subplot2.plot(x2, y2, LINE_STYLE[i]) # Subplot3 x3 = AeroCoef.aoa y3 = AeroCoef.cd subplot3.plot(x3, y3, LINE_STYLE[i]) # Subplot4 x4 = AeroCoef.aoa if any(AeroCoef.cd) == 0.0: cl_cd = [0] * len(AeroCoef.aoa) else: cl_cd = res = [cl / cd for cl, cd in zip(AeroCoef.cl, AeroCoef.cd)] y4 = cl_cd subplot4.plot(x4, y4, LINE_STYLE[i]) # Labels subplot1.set_xlabel('Angle of attack') subplot1.set_ylabel('Lift coefficient') subplot2.set_xlabel('Angle of attack') subplot2.set_ylabel('Moment coefficient') subplot3.set_xlabel('Angle of attack') subplot3.set_ylabel('Drag coefficient') subplot4.set_xlabel('Angle of attack') subplot4.set_ylabel('Efficiency CL/CD') # Legend figure_1.legend(aeromap_uid_list) # Grid subplot1.grid() subplot2.grid() subplot3.grid() subplot4.grid() cpsf.close_tixi(tixi, cpacs_out_path) plt.show()
def dynamic_stability_analysis(cpacs_path, cpacs_out_path): """Function to analyse a full Aeromap Function 'dynamic_stability_analysis' analyses longitudinal dynamic stability and directionnal dynamic. Args: cpacs_path (str): Path to CPACS file cpacs_out_path (str):Path to CPACS output file plot (boolean): Choise to plot graph or not Returns: (#TODO put that in the documentation) * Adrvertisements certifying if the aircraft is stable or Not * In case of longitudinal dynamic UNstability or unvalid test on data: - Plot cms VS aoa for constant Alt, Mach and different aos - Plot cms VS aoa for const alt and aos and different mach - plot cms VS aoa for constant mach, AOS and different altitudes * In case of directionnal dynamic UNstability or unvalid test on data: - Pcot cml VS aos for constant Alt, Mach and different aoa - Plot cml VS aos for const alt and aoa and different mach - plot cml VS aos for constant mach, AOA and different altitudes * Plot one graph of cruising angles of attack for different mach and altitudes Make the following tests: * Check the CPACS path * For longitudinal dynamic stability analysis: - If there is more than one angle of attack for a given altitude, mach, aos - If cml values are only zeros for a given altitude, mach, aos - If there one aoa value which is repeated for a given altitude, mach, aos * For directionnal dynamic stability analysis: - If there is more than one angle of sideslip for a given altitude, mach, aoa - If cms values are only zeros for a given altitude, mach, aoa - If there one aos value which is repeated for a given altitude, mach, aoa """ # XPATH definition aeromap_uid_xpath = DYNAMIC_ANALYSIS_XPATH + '/aeroMapUid' aircraft_class_xpath = DYNAMIC_ANALYSIS_XPATH + '/class' # Classes 1 2 3 4 small, heavy ... aircraft_cathegory_xpath = DYNAMIC_ANALYSIS_XPATH + '/category' # flight phase A B C selected_mass_config_xpath = DYNAMIC_ANALYSIS_XPATH + '/massConfiguration' longi_analysis_xpath = DYNAMIC_ANALYSIS_XPATH + '/instabilityModes/longitudinal' direc_analysis_xpath = DYNAMIC_ANALYSIS_XPATH + '/instabilityModes/lateralDirectional' show_plot_xpath = DYNAMIC_ANALYSIS_XPATH + '/showPlots' save_plot_xpath = DYNAMIC_ANALYSIS_XPATH + '/savePlots' model_xpath = '/cpacs/vehicles/aircraft/model' ref_area_xpath = model_xpath + '/reference/area' ref_length_xpath = model_xpath + '/reference/length' flight_qualities_case_xpath = model_xpath + '/analyses/flyingQualities/fqCase' masses_location_xpath = model_xpath + '/analyses/massBreakdown/designMasses' # aircraft_class_xpath = flight_qualities_case_xpath + '/class' # Classes 1 2 3 4 small, heavy ... # aircraft_cathegory_xpath = flight_qualities_case_xpath + '/cathegory' # flight phase A B C # Ask user flight path angles : gamma_e thrust_available = None # Thrust data are not available flight_path_angle_deg = [ 0 ] # [-15,-10,-5,0,5,10,15] # The user should have the choice to select them !!!!!!!!!!!!!!!!!!!! flight_path_angle = [ angle * (np.pi / 180) for angle in flight_path_angle_deg ] # flight_path_angle in [rad] tixi = cpsf.open_tixi(cpacs_path) # Get aeromap uid aeromap_uid = cpsf.get_value(tixi, aeromap_uid_xpath) log.info('The following aeroMap will be analysed: ' + aeromap_uid) # Mass configuration: (Maximum landing mass, Maximum ramp mass (the maximum weight authorised for the ground handling), Take off mass, Zero Fuel mass) mass_config = cpsf.get_value(tixi, selected_mass_config_xpath) log.info('The aircraft mass configuration used for analysis is: ' + mass_config) # Analyses to do : longitudinal / Lateral-Directional longitudinal_analysis = cpsf.get_value(tixi, longi_analysis_xpath) lateral_directional_analysis = False # lateral_directional_analysis = cpsf.get_value(tixi, direc_analysis_xpath ) # Plots configuration with Setting GUI show_plots = cpsf.get_value_or_default(tixi, show_plot_xpath, False) save_plots = cpsf.get_value_or_default(tixi, save_plot_xpath, False) mass_config_xpath = masses_location_xpath + '/' + mass_config if tixi.checkElement(mass_config_xpath): mass_xpath = mass_config_xpath + '/mass' I_xx_xpath = mass_config_xpath + '/massInertia/Jxx' I_yy_xpath = mass_config_xpath + '/massInertia/Jyy' I_zz_xpath = mass_config_xpath + '/massInertia/Jzz' I_xz_xpath = mass_config_xpath + '/massInertia/Jxz' else: raise ValueError( 'The mass configuration : {} is not defined in the CPACS file !!!'. format(mass_config)) s = cpsf.get_value( tixi, ref_area_xpath ) # Wing area : s for non-dimonsionalisation of aero data. mac = cpsf.get_value( tixi, ref_length_xpath ) # ref length for non dimensionalisation, Mean aerodynamic chord: mac, # TODO: check that b = s / mac # TODO: find a way to get that xh = 10 # distance Aircaft cg-ac_horizontal-tail-plane. m = cpsf.get_value(tixi, mass_xpath) # aircraft mass dimensional I_xx = cpsf.get_value(tixi, I_xx_xpath) # X inertia dimensional I_yy = cpsf.get_value(tixi, I_yy_xpath) # Y inertia dimensional I_zz = cpsf.get_value(tixi, I_zz_xpath) # Z inertia dimensional I_xz = cpsf.get_value(tixi, I_xz_xpath) # XZ inertia dimensional aircraft_class = cpsf.get_value( tixi, aircraft_class_xpath) # aircraft class 1 2 3 4 flight_phase = cpsf.get_string_vector( tixi, aircraft_cathegory_xpath)[0] # Flight phase A B C Coeffs = apmf.get_aeromap( tixi, aeromap_uid ) # Warning: Empty uID found! This might lead to unknown errors! alt_list = Coeffs.alt mach_list = Coeffs.mach aoa_list = Coeffs.aoa aos_list = Coeffs.aos cl_list = Coeffs.cl cd_list = Coeffs.cd cs_list = Coeffs.cs cml_list = Coeffs.cml cms_list = Coeffs.cms cmd_list = Coeffs.cmd dcsdrstar_list = Coeffs.dcsdrstar dcsdpstar_list = Coeffs.dcsdpstar dcldqstar_list = Coeffs.dcldqstar dcmsdqstar_list = Coeffs.dcmsdqstar dcddqstar_list = Coeffs.dcddqstar dcmldqstar_list = Coeffs.dcmldqstar dcmddpstar_list = Coeffs.dcmddpstar dcmldpstar_list = Coeffs.dcmldpstar dcmldrstar_list = Coeffs.dcmldrstar dcmddrstar_list = Coeffs.dcmddrstar # All different vallues with only one occurence alt_unic = get_unic(alt_list) mach_unic = get_unic(mach_list) aos_unic = get_unic(aos_list) aoa_unic = get_unic(aoa_list) # TODO get from CPACS incrementalMap = False for alt in alt_unic: idx_alt = [i for i in range(len(alt_list)) if alt_list[i] == alt] Atm = get_atmosphere(alt) g = Atm.grav a = Atm.sos rho = Atm.dens for mach in mach_unic: print('Mach : ', mach) idx_mach = [ i for i in range(len(mach_list)) if mach_list[i] == mach ] u0, m_adim, i_xx, i_yy, i_zz, i_xz = adimensionalise( a, mach, rho, s, b, mac, m, I_xx, I_yy, I_zz, I_xz) # u0 is V0 in Cook # Hyp: trim condition when: ( beta = 0 and dCm/dalpha = 0) OR ( aos=0 and dcms/daoa = 0 ) if 0 not in aos_unic: log.warning( 'The aircraft can not be trimmed (requiring symetric flight condition) as beta never equal to 0 for Alt = {}, mach = {}' .format(alt, mach)) else: idx_aos = [i for i in range(len(aos_list)) if aos_list[i] == 0] find_index = get_index(idx_alt, idx_mach, idx_aos) # If there is only one data at (alt, mach, aos) then dont make stability anlysis if len(find_index) <= 1: log.warning( 'Not enough data at : Alt = {} , mach = {}, aos = 0, can not perform stability analysis' .format(alt, mach)) # If there is at leat 2 data at (alt, mach, aos) then, make stability anlysis else: # Calculate trim conditions cms = [] aoa = [] cl = [] for index in find_index: cms.append(cms_list[index]) aoa.append(aoa_list[index] * np.pi / 180) cl.append(cl_list[index]) cl_required = (m * g) / (0.5 * rho * u0**2 * s) (trim_aoa, idx_trim_before, idx_trim_after, ratio) = trim_condition( alt, mach, cl_required, cl, aoa, ) if trim_aoa: trim_aoa_deg = trim_aoa * 180 / np.pi trim_cms = interpolation(cms, idx_trim_before, idx_trim_after, ratio) pitch_moment_derivative_rad = ( cms[idx_trim_after] - cms[idx_trim_before]) / ( aoa[idx_trim_after] - aoa[idx_trim_before]) pitch_moment_derivative_deg = pitch_moment_derivative_rad / ( 180 / np.pi) # Find incremental cms if incrementalMap: for index, mach_number in enumerate(mach_unic, 0): if mach_number == mach: mach_index = index dcms_before = dcms_list[mach_index * len(aoa_unic) + idx_trim_before] dcms_after = dcms_list[mach_index * len(aoa_unic) + idx_trim_after] dcms = dcms_before + ratio * (dcms_after - dcms_before) trim_elevator = -trim_cms / dcms # Trim elevator deflection in [°] else: dcms = None trim_elevator = None else: trim_aoa_deg = None trim_cms = None pitch_moment_derivative_deg = None dcms = None trim_elevator = None # Longitudinal dynamic stability, # Stability analysis if longitudinal_analysis and trim_cms: cl = [] cd = [] dcldqstar = [] dcddqstar = [] dcmsdqstar = [] for index in find_index: cl.append(cl_list[index]) cd.append(cd_list[index]) dcldqstar.append(dcldqstar_list[index]) dcddqstar.append(dcddqstar_list[index]) dcmsdqstar.append(dcmsdqstar_list[index]) # Trimm variables cd0 = interpolation(cd, idx_trim_before, idx_trim_after, ratio) # Dragg coeff at trim cl0 = interpolation(cl, idx_trim_before, idx_trim_after, ratio) # Lift coeff at trim cl_dividedby_cd_trim = cl0 / cd0 # cl/cd ratio at trim, at trim aoa # Lift & drag coefficient derivative with respect to AOA at trimm cl_alpha0 = (cl[idx_trim_after] - cl[idx_trim_before] ) / (aoa[idx_trim_after] - aoa[idx_trim_before]) cd_alpha0 = (cd[idx_trim_after] - cd[idx_trim_before] ) / (aoa[idx_trim_after] - aoa[idx_trim_before]) print(idx_trim_before, idx_trim_after, ratio) dcddqstar0 = interpolation(dcddqstar, idx_trim_before, idx_trim_after, ratio) # x_q dcldqstar0 = interpolation(dcldqstar, idx_trim_before, idx_trim_after, ratio) # z_q dcmsdqstar0 = interpolation(dcmsdqstar, idx_trim_before, idx_trim_after, ratio) # m_q cm_alpha0 = trim_cms # Speed derivatives if there is at least 2 distinct mach values if len(mach_unic) >= 2: dcddm0 = speed_derivative_at_trim( cd_list, mach, mach_list, mach_unic, idx_alt, aoa_list, aos_list, idx_trim_before, idx_trim_after, ratio) if dcddm0 == None: dcddm0 = 0 log.warning( 'Not enough data to determine dcddm or (Cd_mach) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: dcddm = 0' .format(alt, mach, round(trim_aoa_deg, 2))) dcldm0 = speed_derivative_at_trim( cl_list, mach, mach_list, mach_unic, idx_alt, aoa_list, aos_list, idx_trim_before, idx_trim_after, ratio) if dcldm0 == None: dcldm0 = 0 log.warning( 'Not enough data to determine dcldm (Cl_mach) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: dcldm = 0' .format(alt, mach, round(trim_aoa_deg, 2))) else: dcddm0 = 0 dcldm0 = 0 log.warning( 'Not enough data to determine dcddm (Cd_mach) and dcldm (Cl_mach) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: dcddm = dcldm = 0' .format(alt, mach, round(trim_aoa_deg, 2))) # Controls Derivatives to be found in the CPACS (To be calculated) dcddeta0 = 0 dcldeta0 = 0 dcmsdeta0 = 0 dcddtau0 = 0 dcldtau0 = 0 dcmsdtau0 = 0 # Traduction Ceasiom -> Theory Ue = u0 * np.cos( trim_aoa ) # *np.cos(aos) as aos = 0 at trim, cos(aos)=1 We = u0 * np.sin( trim_aoa ) # *np.cos(aos) as aos = 0 at trim, cos(aos)=1 # Dimentionless State Space variables, # In generalised body axes coordinates , # simplifications: Ue=V0, We=0, sin(Theta_e)=0 cos(Theta_e)=0 if thrust_available: # If power data X_u = -(2 * cd0 + mach * dcddm0) + 1 / ( 0.5 * rho * s * a ^ 2 ) * dtaudm0 # dtaudm dimensional Thrust derivative at trim conditions, P340 Michael V. Cook else: # Glider Mode X_u = -(2 * cd0 + mach * dcddm0) Z_u = -(2 * cl0 + mach * dcldm0) M_u = 0 # Negligible for subsonic conditions or better with P289 Yechout (cm_u+2cm0) X_w = (cl0 - cd_alpha0) Z_w = -(cl_alpha0 + cd0) M_w = cm_alpha0 X_q = dcddqstar0 # Normally almost = 0 Z_q = dcldqstar0 M_q = -dcmsdqstar0 X_dotw = 0 # Negligible Z_dotw = 1 / 3 * M_q / u0 / ( xh / mac ) # Thumb rule : M_alpha_dot = 1/3 Mq , ( not true for 747 :caughey P83,M_alpha_dot = 1/6Mq ) M_dotw = 1 / 3 * M_q / u0 # Thumb rule : M_alpha_dot = 1/3 Mq # Controls: X_eta = dcddeta0 # To be found from the cpacs file, and defined by the user! Z_eta = dcldeta0 # To be found from the cpacs file, and defined by the user! M_eta = dcmsdeta0 # To be found from the cpacs file, and defined by the user! X_tau = dcddtau0 # To be found from the cpacs file, and defined by the user! Z_tau = dcldtau0 # To be found from the cpacs file, and defined by the user! M_tau = dcmsdtau0 # To be found from the cpacs file, and defined by the user! # ----------------- Traduction Ceasiom -> Theory END ----------------------------------- # Sign check (Ref: Thomas Yechout Book, P304) check_sign_longi(cd_alpha0, M_w, cl_alpha0, M_dotw, Z_dotw, M_q, Z_q, M_eta, Z_eta) # Laterl-Directional if lateral_directional_analysis: cml = [] # N cmd = [] # L aos = [] aoa = [] # For Ue We cs = [] # For y_v dcsdpstar = [] # y_p dcmddpstar = [] # l_p dcmldpstar = [] # n_p dcsdrstar = [] # y_r dcmldrstar = [] # n_r dcmddrstar = [] # l_r for index in find_index: cml.append(cml_list[index]) # N , N_v cmd.append(cmd_list[index]) # L , L_v aos.append(aos_list[index] * np.pi / 180) aoa.append(aoa_list[index]) # For Ue We cs.append(cs_list[index]) dcsdpstar.append(dcsdpstar_list[index]) # y_p dcmddpstar.append(dcmddpstar_list[index]) # l_p dcmldpstar.append(dcmldpstar_list[index]) # n_p dcsdrstar.append(dcsdrstar_list[index]) # y_r dcmldrstar.append(dcmldrstar_list[index]) # n_r dcmddrstar.append(dcmddrstar_list[index]) # l_r #Trimm condition calculation # speed derivatives : y_v / l_v / n_v / Must be devided by speed given that the hyp v=Beta*U if len(aos_unic) >= 2: print('Mach : ', mach, ' and idx_mach : ', idx_mach) cs_beta0 = speed_derivative_at_trim_lat( cs_list, aos_list, aos_unic, idx_alt, idx_mach, aoa_list, idx_trim_before, idx_trim_after, ratio) # y_v if cs_beta0 == None: cs_beta0 = 0 log.warning( 'Not enough data to determine cs_beta (Y_v) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: cs_beta = 0' .format(alt, mach, round(trim_aoa_deg, 2))) cmd_beta0 = speed_derivative_at_trim_lat( cmd_list, aos_list, aos_unic, idx_alt, idx_mach, aoa_list, idx_trim_before, idx_trim_after, ratio) # l_v if cmd_beta0 == None: cmd_beta0 = 0 log.warning( 'Not enough data to determine cmd_beta (L_v) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: cmd_beta = 0' .format(alt, mach, round(trim_aoa_deg, 2))) cml_beta0 = speed_derivative_at_trim_lat( cml_list, aos_list, aos_unic, idx_alt, idx_mach, aoa_list, idx_trim_before, idx_trim_after, ratio) # n_v if cml_beta0 == None: cml_beta0 = 0 log.warning( 'Not enough data to determine cml_beta (N_v) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: cml_beta = 0' .format(alt, mach, round(trim_aoa_deg, 2))) else: cs_beta0 = 0 cmd_beta0 = 0 cml_beta0 = 0 log.warning( 'Not enough data to determine cs_beta (Y_v), cmd_beta (L_v) and cml_beta (N_v) at trim condition at Alt = {}, mach = {}, aoa = {}, aos = 0. Assumption: cs_beta = cmd_beta = cml_beta = 0' .format(alt, mach, round(trim_aoa_deg, 2))) dcsdpstar0 = interpolation(dcsdpstar, idx_trim_before, idx_trim_after, ratio) # y_p dcmddpstar0 = interpolation(dcmddpstar, idx_trim_before, idx_trim_after, ratio) # l_p dcmldpstar0 = interpolation(dcmldpstar, idx_trim_before, idx_trim_after, ratio) # n_p dcsdrstar0 = interpolation(dcsdrstar, idx_trim_before, idx_trim_after, ratio) # y_r dcmldrstar0 = interpolation(dcmldrstar, idx_trim_before, idx_trim_after, ratio) # n_r dcmddrstar0 = interpolation(dcmddrstar, idx_trim_before, idx_trim_after, ratio) # l_r # TODO: calculate that and find in the cpacs dcsdxi0 = 0 dcmddxi0 = 0 dcmldxi0 = 0 dcsdzeta0 = 0 dcmddzeta0 = 0 dcmldzeta0 = 0 # Traduction Ceasiom -> Theory Y_v = cs_beta0 L_v = cmd_beta0 N_v = cml_beta0 Y_p = -dcsdpstar0 * mac / b L_p = -dcmddpstar0 * mac / b N_p = dcmldpstar0 * mac / b Y_r = dcsdrstar0 * mac / b N_r = -dcmldrstar0 * mac / b # mac/b :Because coefficients in ceasiom are nondimensionalised by the mac instead of the span L_r = dcmddrstar0 * mac / b # Controls: # Ailerons Y_xi = dcsdxi0 # To be found from the cpacs file, and defined by the user! L_xi = dcmddxi0 # To be found from the cpacs file, and defined by the user! N_xi = dcmldxi0 # To be found from the cpacs file, and defined by the user! # Rudder Y_zeta = dcsdzeta0 # To be found from the cpacs file, and defined by the user! L_zeta = dcmddzeta0 # To be found from the cpacs file, and defined by the user! N_zeta = dcmldzeta0 # To be found from the cpacs file, and defined by the user! Ue = u0 * np.cos( trim_aoa ) # *np.cos(aos) as aos = 0 at trim, cos(aos)=1 We = u0 * np.sin( trim_aoa ) # *np.cos(aos) as aos = 0 at trim, cos(aos)=1 # Sign check (Ref: Thomas Yechout Book, P304) check_sign_lat(Y_v, L_v, N_v, Y_p, L_p, Y_r, L_r, N_r, L_xi, Y_zeta, L_zeta, N_zeta) if trim_aoa: for angles in flight_path_angle: theta_e = angles + trim_aoa if longitudinal_analysis: (A_longi, B_longi, x_u,z_u,m_u,x_w,z_w,m_w, x_q,z_q,m_q,x_theta,z_theta,m_theta,x_eta,z_eta,m_eta, x_tau,z_tau,m_tau)\ = concise_derivative_longi(X_u,Z_u,M_u,X_w,Z_w,M_w,\ X_q,Z_q,M_q,X_dotw,Z_dotw,M_dotw,X_eta,Z_eta,M_eta,\ X_tau,Z_tau,M_tau, g, theta_e, u0,We,Ue,mac,m_adim,i_yy) C_longi = np.identity(4) D_longi = np.zeros((4, 2)) # Identify longitudinal roots if longi_root_identification( A_longi )[0] == None: # If longitudinal root not complex conjugate raise warning and plot roots eg_value_longi = longi_root_identification( A_longi)[1] log.warning( 'Longi : charcateristic equation roots are not complex conjugate : {}' .format(eg_value_longi)) legend = [ 'Root1', 'Root2', 'Root3', 'Root4' ] plot_title = 'S-plane longitudinal characteristic equation roots at (Alt = {}, Mach= {}, trimed at aoa = {}°)'.format( alt, mach, trim_aoa) plot_splane(eg_value_longi, plot_title, legend, show_plots, save_plots) else: # Longitudinal roots are complex conjugate (sp1, sp2, ph1, ph2, eg_value_longi , eg_vector_longi, eg_vector_longi_magnitude)\ = longi_root_identification(A_longi) legend = ['sp1', 'sp2', 'ph1', 'ph2'] plot_title = 'S-plane longitudinal characteristic equation roots at (Alt = {}, Mach= {}, trimed at aoa = {}°)'.format( alt, mach, trim_aoa) plot_splane(eg_value_longi, plot_title, legend, show_plots, save_plots) # Modes parameters : damping ratio, frequence, CAP, time tou double amplitude Z_w_dimensional = Z_w * ( 0.5 * rho * s * u0**2 ) # Z_w* (0.5*rho*s*u0**2) is the dimensional form of Z_w, Z_w = -(cl_alpha0 + cd0) P312 Yechout z_alpha = Z_w_dimensional * u0 / m # alpha = w/u0 hence, z_alpha = Z_w_dimensional * u0 [Newton/rad/Kg : m/s^2 /rad] load_factor = -z_alpha / g # number of g's/rad (1g/rad 2g/rad 3g/rad) (sp_freq, sp_damp, sp_cap, ph_freq, ph_damp, ph_t2)\ = longi_mode_characteristic(sp1,sp2,ph1,ph2,load_factor) # Rating sp_damp_rate = short_period_damping_rating( aircraft_class, sp_damp) sp_freq_rate = short_period_frequency_rating( flight_phase, aircraft_class, sp_freq, load_factor) # Plot SP freq vs Load factor legend = 'Alt = {}, Mach= {}, trim aoa = {}°'.format( alt, mach, trim_aoa) if flight_phase == 'A': plot_sp_level_a([load_factor], [sp_freq], legend, show_plots, save_plots) elif flight_phase == 'B': plot_sp_level_b( x_axis, y_axis, legend, show_plots, save_plots) else: plot_sp_level_c( x_axis, y_axis, legend, show_plots, save_plots) sp_cap_rate = cap_rating( flight_phase, sp_cap, sp_damp) ph_rate = phugoid_rating(ph_damp, ph_t2) # Raise warning if unstable mode in the log file if sp_damp_rate == None: log.warning( 'ShortPeriod UNstable at Alt = {}, Mach = {} , due to DampRatio = {} ' .format(alt, mach, round(sp_damp, 4))) if sp_freq_rate == None: log.warning( 'ShortPeriod UNstable at Alt = {}, Mach = {} , due to UnDampedFreq = {} rad/s ' .format(alt, mach, round(sp_freq, 4))) if sp_cap_rate == None: log.warning( 'ShortPeriod UNstable at Alt = {}, Mach = {} , with CAP evaluation, DampRatio = {} , CAP = {} ' .format(alt, mach, round(sp_damp, 4), round(sp_cap, 4))) if ph_rate == None: log.warning( 'Phugoid UNstable at Alt = {}, Mach = {} , DampRatio = {} , UnDampedFreq = {} rad/s' .format(alt, mach, round(ph_damp, 4), round(ph_freq, 4))) # TODO # Compute numerator TF for (Alt, mach, flight_path_angle, aoa_trim, aos=0 if lateral_directional_analysis: (A_direc, B_direc,y_v,l_v,n_v,y_p,y_phi,y_psi,l_p,l_phi,l_psi,n_p,y_r,l_r,n_r,n_phi,n_psi, y_xi,l_xi,n_xi, y_zeta,l_zeta,n_zeta)\ = concise_derivative_lat(Y_v,L_v,N_v,Y_p,L_p,N_p,Y_r,L_r,N_r,\ Y_xi,L_xi,N_xi, Y_zeta,L_zeta,N_zeta,\ g, b, theta_e, u0,We,Ue,m_adim,i_xx,i_zz,i_xz ) C_direc = np.identity(5) D_direc = np.zeros((5, 2)) if direc_root_identification( A_direc )[0] == None: # Lateral-directional roots are correctly identified eg_value_direc = direc_root_identification( A_direc)[1] print( 'Lat-Dir : charcateristic equation roots are not complex conjugate : {}' .format(eg_value_direc)) legend = [ 'Root1', 'Root2', 'Root3', 'Root4' ] plot_title = 'S-plane lateral characteristic equation roots at (Alt = {}, Mach= {}, trimed at aoa = {}°)'.format( alt, mach, trim_aoa) plot_splane(eg_value_direc, plot_title, legend, show_plots, save_plots) else: # Lateral-directional roots are correctly identified (roll, spiral, dr1, dr2, eg_value_direc, eg_vector_direc, eg_vector_direc_magnitude)\ = direc_root_identification(A_direc) legend = ['roll', 'spiral', 'dr1', 'dr2'] plot_title = 'S-plane lateralcharacteristic equation roots at (Alt = {}, Mach= {}, trimed at aoa = {}°)'.format( alt, mach, trim_aoa) plot_splane(eg_value_direc, plot_title, legend, show_plots, save_plots) (roll_timecst, spiral_timecst, spiral_t2, dr_freq, dr_damp, dr_damp_freq) = direc_mode_characteristic( roll, spiral, dr1, dr2) # Rating roll_rate = roll_rating( flight_phase, aircraft_class, roll_timecst) spiral_rate = spiral_rating( flight_phase, spiral_timecst, spiral_t2) dr_rate = dutch_roll_rating( flight_phase, aircraft_class, dr_damp, dr_freq, dr_damp_freq) # Raise warning in the log file if unstable mode if roll_rate == None: log.warning( 'Roll mode UNstable at Alt = {}, Mach = {} , due to roll root = {}, roll time contatant = {} s' .format(alt, mach, round(roll_root, 4), round(roll_timecst, 4))) if spiral_rate == None: log.warning( 'Spiral mode UNstable at Alt = {}, Mach = {} , spiral root = {}, time_double_ampl = {}' .format(alt, mach, round(spiral_root, 4), round(spiral_t2, 4))) if dr_rate == None: log.warning( 'Dutch Roll UNstable at Alt = {}, Mach = {} , Damping Ratio = {} , frequency = {} rad/s ' .format(alt, mach, round(dr_damp, 4), round(dr_freq, 4)))