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.
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
class AVL(Aero_Analysis):
""" SUAVE.Analyses.Aerodynamics.AVL
aerodynamic model that performs a vortex lattice analysis using AVL
(Athena Vortex Lattice, by Mark Drela of MIT).
this class is callable, see self.__call__
"""
def __defaults__(self):
self.tag = 'avl'
self.keep_files = True
self.settings = Settings()
self.current_status = Data()
self.current_status.batch_index = 0
self.current_status.batch_file = None
self.current_status.deck_file = None
self.current_status.cases = None
self.features = None
def finalize(self):
features = self.features
self.tag = 'avl_analysis_of_{}'.format(features.tag)
run_folder = self.settings.filenames.run_folder
if os.path.exists(run_folder):
if self.keep_files:
warn('deleting old avl run files',Warning)
rmtree(run_folder)
os.mkdir(run_folder)
return
def evaluate(self,state,**args):
# unpack
conditions = state.conditions
results = self.evaluate_conditions(conditions)
# pack conditions
state.conditions.aerodynamics.lift_coefficient = results.conditions.aerodynamics.lift_coefficient
state.conditions.aerodynamics.drag_coefficient = results.conditions.aerodynamics.drag_coefficient
state.conditions.aerodynamics.pitch_moment_coefficient = results.conditions.aerodynamics.pitch_moment_coefficient
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)
# 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
# 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
case.aero_result_filename_1 = aero_results_template_1.format(
case.tag) # 'stability_axis_derivatives_{}.dat'
case.aero_result_filename_2 = aero_results_template_2.format(
case.tag) # 'surface_forces_{}.dat'
case.aero_result_filename_3 = aero_results_template_3.format(
case.tag) # 'strip_forces_{}.dat'
case.aero_result_filename_4 = aero_results_template_4.format(
case.tag) # 'body_axis_derivatives_{}.dat'
case.eigen_result_filename_1 = dynamic_results_template_1.format(
case.tag) # 'eigen_mode_{}.dat'
case.eigen_result_filename_2 = dynamic_results_template_2.format(
case.tag) # '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