def evaluate_conditions(self,run_conditions): """ process vehicle to setup geometry, condititon and configuration Inputs: run_conditions - DataDict() of aerodynamic conditions; until input method is finalized, will just assume mass_properties are always as defined in self.features Outputs: results - a DataDict() of type SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics(), augmented with case data on moment coefficients and control derivatives Assumptions: """ # unpack run_folder = os.path.abspath(self.settings.filenames.run_folder) output_template = self.settings.filenames.output_template batch_template = self.settings.filenames.batch_template deck_template = self.settings.filenames.deck_template # update current status self.current_status.batch_index += 1 batch_index = self.current_status.batch_index self.current_status.batch_file = batch_template.format(batch_index) self.current_status.deck_file = deck_template.format(batch_index) # translate conditions cases = translate_conditions_to_cases(self,run_conditions) self.current_status.cases = cases # case filenames for case in cases: case.result_filename = output_template.format(case.tag) # write the input files with redirect.folder(run_folder,force=False): write_geometry(self) write_run_cases(self) write_input_deck(self) # RUN AVL! results_avl = run_analysis(self) # translate results results = translate_results_to_conditions(cases,results_avl) if not self.keep_files: rmtree( run_folder ) return results
def evaluate_conditions(self,run_conditions): """ process vehicle to setup geometry, condititon and configuration Inputs: run_conditions - DataDict() of aerodynamic conditions; until input method is finalized, will just assume mass_properties are always as defined in self.features Outputs: results - a DataDict() of type SUAVE.Analyses.Mission.Segments.Conditions.Aerodynamics(), augmented with case data on moment coefficients and control derivatives Assumptions: """ # unpack run_folder = os.path.abspath(self.settings.filenames.run_folder) output_template = self.settings.filenames.output_template batch_template = self.settings.filenames.batch_template deck_template = self.settings.filenames.deck_template # update current status self.current_status.batch_index += 1 batch_index = self.current_status.batch_index self.current_status.batch_file = batch_template.format(batch_index) self.current_status.deck_file = deck_template.format(batch_index) # translate conditions cases = translate_conditions_to_cases(self,run_conditions) self.current_status.cases = cases # case filenames for case in cases: case.result_filename = output_template.format(case.tag)
def evaluate_conditions(self,run_conditions): """Process vehicle to setup geometry, condititon, and configuration. Assumptions: None Source: N/A Inputs: run_conditions <SUAVE data type> aerodynamic conditions; until input method is finalized, will assume mass_properties are always as defined in self.features Outputs: results <SUAVE data type> Properties Used: self.settings.filenames. run_folder output_template batch_template deck_template self.current_status. batch_index batch_file deck_file cases """ # unpack run_folder = os.path.abspath(self.settings.filenames.run_folder) output_template = self.settings.filenames.output_template batch_template = self.settings.filenames.batch_template deck_template = self.settings.filenames.deck_template spanwise_vortices_per_meter = self.settings.spanwise_vortex_density # update current status self.current_status.batch_index += 1 batch_index = self.current_status.batch_index self.current_status.batch_file = batch_template.format(batch_index) self.current_status.deck_file = deck_template.format(batch_index) # control surfaces num_cs = 0 for wing in self.geometry.wings: for segment in wing.Segments: wing_segment = wing.Segments[segment] section_cs = len(wing_segment.control_surfaces) if section_cs != 0: cs_shift = True num_cs = num_cs + section_cs # translate conditions cases = translate_conditions_to_cases(self,run_conditions) for case in cases: cases[case].stability_and_control.number_control_surfaces = num_cs self.current_status.cases = cases # case filenames for case in cases: cases[case].result_filename = output_template.format(case) #case.eigen_result_filename = stability_output_template.format(batch_index) # SUAVE-AVL dynamic stability under development # write the input files with redirect.folder(run_folder,force=False): write_geometry(self,spanwise_vortices_per_meter) write_run_cases(self) write_input_deck(self) # RUN AVL! results_avl = run_analysis(self) # translate results results = translate_results_to_conditions(cases,results_avl) if not self.keep_files: rmtree( run_folder ) return results
def evaluate_conditions(self, run_conditions, trim_aircraft): """Process vehicle to setup geometry, condititon, and configuration. Assumptions: None Source: N/A Inputs: run_conditions <SUAVE data type> aerodynamic conditions; until input method is finalized, will assume mass_properties are always as defined in self.features Outputs: results <SUAVE data type> Properties Used: self.settings.filenames. run_folder output_template batch_template deck_template self.current_status. batch_index batch_file deck_file cases """ # unpack run_folder = os.path.abspath(self.settings.filenames.run_folder) run_script_path = run_folder.rstrip('avl_files').rstrip('/') aero_results_template_1 = self.settings.filenames.aero_output_template_1 # 'stability_axis_derivatives_{}.dat' aero_results_template_2 = self.settings.filenames.aero_output_template_2 # 'surface_forces_{}.dat' aero_results_template_3 = self.settings.filenames.aero_output_template_3 # 'strip_forces_{}.dat' aero_results_template_4 = self.settings.filenames.aero_output_template_4 # 'body_axis_derivatives_{}.dat' dynamic_results_template_1 = self.settings.filenames.dynamic_output_template_1 # 'eigen_mode_{}.dat' dynamic_results_template_2 = self.settings.filenames.dynamic_output_template_2 # 'system_matrix_{}.dat' batch_template = self.settings.filenames.batch_template deck_template = self.settings.filenames.deck_template # rename defaul avl aircraft tag self.tag = 'avl_analysis_of_{}'.format(self.geometry.tag) self.settings.filenames.features = self.geometry._base.tag + '.avl' self.settings.filenames.mass_file = self.geometry._base.tag + '.mass' # update current status self.current_status.batch_index += 1 batch_index = self.current_status.batch_index self.current_status.batch_file = batch_template.format(batch_index) self.current_status.deck_file = deck_template.format(batch_index) # control surfaces num_cs = 0 cs_names = [] cs_functions = [] for wing in self.geometry.wings: # this parses through the wings to determine how many control surfaces does the vehicle have if wing.control_surfaces: wing = populate_control_sections(wing) num_cs_on_wing = len(wing.control_surfaces) num_cs += num_cs_on_wing for cs in wing.control_surfaces: ctrl_surf = wing.control_surfaces[cs] cs_names.append(ctrl_surf.tag) if (type(ctrl_surf) == Slat): ctrl_surf_function = 'slat' elif (type(ctrl_surf) == Flap): ctrl_surf_function = 'flap' elif (type(ctrl_surf) == Aileron): ctrl_surf_function = 'aileron' elif (type(ctrl_surf) == Elevator): ctrl_surf_function = 'elevator' elif (type(ctrl_surf) == Rudder): ctrl_surf_function = 'rudder' cs_functions.append(ctrl_surf_function) # translate conditions cases = translate_conditions_to_cases(self, run_conditions) for case in cases: cases[case].stability_and_control.number_control_surfaces = num_cs cases[case].stability_and_control.control_surface_names = cs_names self.current_status.cases = cases # write case filenames using the templates defined in MACE/Analyses/AVL/AVL_Data_Classes/Settings.py for case in cases: cases[ case].aero_result_filename_1 = aero_results_template_1.format( case) # 'stability_axis_derivatives_{}.dat' cases[ case].aero_result_filename_2 = aero_results_template_2.format( case) # 'surface_forces_{}.dat' cases[ case].aero_result_filename_3 = aero_results_template_3.format( case) # 'strip_forces_{}.dat' cases[ case].aero_result_filename_4 = aero_results_template_4.format( case) # 'body_axis_derivatives_{}.dat' cases[ case].eigen_result_filename_1 = dynamic_results_template_1.format( case) # 'eigen_mode_{}.dat' cases[ case].eigen_result_filename_2 = dynamic_results_template_2.format( case) # 'system_matrix_{}.dat' # write the input files with redirect.folder(run_folder, force=False): write_geometry(self, run_script_path) write_mass_file(self, run_conditions) write_run_cases(self, trim_aircraft) write_input_deck(self, trim_aircraft) # RUN AVL! results_avl = run_analysis(self) # translate results results = translate_results_to_conditions(cases, results_avl) if not self.keep_files: rmtree(run_folder) return results
def evaluate_conditions(self, run_conditions): """Process vehicle to setup geometry, condititon, and configuration. Assumptions: None Source: N/A Inputs: run_conditions <SUAVE data type> aerodynamic conditions; until input method is finalized, will assume mass_properties are always as defined in self.features Outputs: results <SUAVE data type> Properties Used: self.settings.filenames. run_folder output_template batch_template deck_template self.current_status. batch_index batch_file deck_file cases """ # unpack run_folder = os.path.abspath(self.settings.filenames.run_folder) output_template = self.settings.filenames.output_template batch_template = self.settings.filenames.batch_template deck_template = self.settings.filenames.deck_template # rename defaul avl aircraft tag self.settings.filenames.features = self.geometry._base.tag + '.avl' # update current status self.current_status.batch_index += 1 batch_index = self.current_status.batch_index self.current_status.batch_file = batch_template.format(batch_index) self.current_status.deck_file = deck_template.format(batch_index) # control surfaces num_cs = 0 for wing in self.geometry.wings: for segment in wing.Segments: wing_segment = wing.Segments[segment] section_cs = len(wing_segment.control_surfaces) if section_cs != 0: cs_shift = True num_cs = num_cs + section_cs # translate conditions cases = translate_conditions_to_cases(self, run_conditions) for case in cases: cases[case].stability_and_control.number_control_surfaces = num_cs self.current_status.cases = cases # case filenames for case in cases: cases[case].result_filename = output_template.format(case) # write the input files with redirect.folder(run_folder, force=False): write_geometry(self) write_run_cases(self) write_input_deck(self) # RUN AVL! results_avl = run_analysis(self) # translate results results = translate_results_to_conditions(cases, results_avl) if not self.keep_files: rmtree(run_folder) return results
def evaluate_conditions(self, run_conditions): """Process vehicle to setup geometry, condititon, and configuration. Assumptions: None Source: N/A Inputs: run_conditions <SUAVE data type> aerodynamic conditions; until input method is finalized, will assume mass_properties are always as defined in self.features Outputs: results <SUAVE data type> Properties Used: self.settings.filenames. run_folder output_template batch_template deck_template self.current_status. batch_index batch_file deck_file cases """ # unpack run_folder = os.path.abspath(self.settings.filenames.run_folder) output_template = self.settings.filenames.output_template batch_template = self.settings.filenames.batch_template deck_template = self.settings.filenames.deck_template # stability_output_template = self.settings.filenames.stability_output_template # SUAVE-AVL dynamic stability under development # update current status self.current_status.batch_index += 1 batch_index = self.current_status.batch_index self.current_status.batch_file = batch_template.format(batch_index) self.current_status.deck_file = deck_template.format(batch_index) # translate conditions cases = translate_conditions_to_cases(self, run_conditions) self.current_status.cases = cases # case filenames for case in cases: cases[case].result_filename = output_template.format(case) #case.eigen_result_filename = stability_output_template.format(batch_index) # SUAVE-AVL dynamic stability under development # write the input files with redirect.folder(run_folder, force=False): write_geometry(self) write_run_cases(self) write_input_deck(self) # RUN AVL! results_avl = run_analysis(self) # translate results results = translate_results_to_conditions(cases, results_avl) if not self.keep_files: rmtree(run_folder) return results