def setup(self):
surfaces = self.options['surfaces']
coupled = Group()
for surface in surfaces:
name = surface['name']
# Connect the output of the loads component with the FEM
# displacement parameter. This links the coupling within the coupled
# group that necessitates the subgroup solver.
coupled.connect(name + '_loads.loads', name + '.loads')
# Perform the connections with the modified names within the
# 'aero_states' group.
coupled.connect(name + '.normals', 'aero_states.' + name + '_normals')
coupled.connect(name + '.def_mesh', 'aero_states.' + name + '_def_mesh')
# Connect the results from 'coupled' to the performance groups
coupled.connect(name + '.def_mesh', name + '_loads.def_mesh')
coupled.connect('aero_states.' + name + '_sec_forces', name + '_loads.sec_forces')
# Connect the results from 'aero_states' to the performance groups
self.connect('coupled.aero_states.' + name + '_sec_forces', name + '_perf' + '.sec_forces')
# Connection performance functional variables
self.connect(name + '_perf.CL', 'total_perf.' + name + '_CL')
self.connect(name + '_perf.CD', 'total_perf.' + name + '_CD')
self.connect('coupled.aero_states.' + name + '_sec_forces', 'total_perf.' + name + '_sec_forces')
self.connect('coupled.' + name + '.chords', name + '_perf.aero_funcs.chords')
# Connect parameters from the 'coupled' group to the performance
# groups for the individual surfaces.
self.connect('coupled.' + name + '.disp', name + '_perf.disp')
self.connect('coupled.' + name + '.S_ref', name + '_perf.S_ref')
self.connect('coupled.' + name + '.widths', name + '_perf.widths')
# self.connect('coupled.' + name + '.chords', name + '_perf.chords')
self.connect('coupled.' + name + '.lengths', name + '_perf.lengths')
self.connect('coupled.' + name + '.cos_sweep', name + '_perf.cos_sweep')
# Connect parameters from the 'coupled' group to the total performance group.
self.connect('coupled.' + name + '.S_ref', 'total_perf.' + name + '_S_ref')
self.connect('coupled.' + name + '.widths', 'total_perf.' + name + '_widths')
self.connect('coupled.' + name + '.chords', 'total_perf.' + name + '_chords')
self.connect('coupled.' + name + '.b_pts', 'total_perf.' + name + '_b_pts')
# Add components to the 'coupled' group for each surface.
# The 'coupled' group must contain all components and parameters
# needed to converge the aerostructural system.
coupled_AS_group = CoupledAS(surface=surface)
if surface['distributed_fuel_weight']:
promotes = ['load_factor']
else:
promotes = []
coupled.add_subsystem(name, coupled_AS_group, promotes_inputs=promotes)
# Add a single 'aero_states' component for the whole system within the
# coupled group.
coupled.add_subsystem('aero_states',
VLMStates(surfaces=surfaces),
promotes_inputs=['v', 'alpha', 'rho'])
# Explicitly connect parameters from each surface's group and the common
# 'aero_states' group.
for surface in surfaces:
name = surface['name']
# Add a loads component to the coupled group
coupled.add_subsystem(name + '_loads', LoadTransfer(surface=surface))
"""
### Change the solver settings here ###
"""
# Set solver properties for the coupled group
# coupled.linear_solver = ScipyIterativeSolver()
# coupled.linear_solver.precon = LinearRunOnce()
coupled.nonlinear_solver = NonlinearBlockGS(use_aitken=True)
coupled.nonlinear_solver.options['maxiter'] = 100
coupled.nonlinear_solver.options['atol'] = 1e-7
coupled.nonlinear_solver.options['rtol'] = 1e-30
# coupled.linear_solver = DirectSolver()
coupled.linear_solver = DirectSolver(assemble_jac=True)
coupled.options['assembled_jac_type'] = 'csc'
# coupled.nonlinear_solver = NewtonSolver(solve_subsystems=True)
# coupled.nonlinear_solver.options['maxiter'] = 50
coupled.nonlinear_solver.options['iprint'] = 2
"""
### End change of solver settings ###
"""
# Add the coupled group to the model problem
self.add_subsystem('coupled', coupled, promotes_inputs=['v', 'alpha', 'rho'])
for surface in surfaces:
name = surface['name']
# Add a performance group which evaluates the data after solving
# the coupled system
perf_group = CoupledPerformance(surface=surface)
self.add_subsystem(name + '_perf', perf_group, promotes_inputs=['rho', 'v', 'alpha', 're', 'Mach_number'])
# Add functionals to evaluate performance of the system.
# Note that only the interesting results are promoted here; not all
# of the parameters.
self.add_subsystem('total_perf',
TotalPerformance(surfaces=surfaces,
user_specified_Sref=self.options['user_specified_Sref'],
internally_connect_fuelburn=self.options['internally_connect_fuelburn']),
promotes_inputs=['v', 'rho', 'empty_cg', 'total_weight', 'CT', 'speed_of_sound', 'R', 'Mach_number', 'W0', 'load_factor', 'S_ref_total'],
promotes_outputs=['L_equals_W', 'fuelburn', 'CL', 'CD', 'CM', 'cg'])
def setup(self):
surfaces = self.options['surfaces']
rotational = self.options['rotational']
rollOnly = self.options['rollOnly']
coupled = om.Group()
for surface in surfaces:
name = surface['name']
# Connect the output of the loads component with the FEM
# displacement parameter. This links the coupling within the coupled
# group that necessitates the subgroup solver.
coupled.connect(name + '_loads.loads', name + '.loads')
# Perform the connections with the modified names within the
# 'aero_states' group.
coupled.connect(name + '.def_mesh',
'aero_states.' + name + '_def_mesh')
# Connect the results from 'coupled' to the performance groups
coupled.connect(name + '.def_mesh', name + '_loads.def_mesh')
coupled.connect('aero_states.' + name + '_sec_forces',
name + '_loads.sec_forces')
# Connect the results from 'aero_states' to the performance groups
self.connect('coupled.aero_states.' + name + '_sec_forces',
name + '_perf' + '.sec_forces')
# Connection performance functional variables
self.connect(name + '_perf.CL', 'total_perf.' + name + '_CL')
self.connect(name + '_perf.CD', 'total_perf.' + name + '_CD')
self.connect('coupled.aero_states.' + name + '_sec_forces',
'total_perf.' + name + '_sec_forces')
self.connect('coupled.' + name + '.chords',
name + '_perf.aero_funcs.chords')
# Connect parameters from the 'coupled' group to the performance
# groups for the individual surfaces.
self.connect('coupled.' + name + '.disp', name + '_perf.disp')
self.connect('coupled.' + name + '.S_ref', name + '_perf.S_ref')
self.connect('coupled.' + name + '.widths', name + '_perf.widths')
# self.connect('coupled.' + name + '.chords', name + '_perf.chords')
self.connect('coupled.' + name + '.lengths',
name + '_perf.lengths')
self.connect('coupled.' + name + '.cos_sweep',
name + '_perf.cos_sweep')
# Connect parameters from the 'coupled' group to the total performance group.
self.connect('coupled.' + name + '.S_ref',
'total_perf.' + name + '_S_ref')
self.connect('coupled.' + name + '.widths',
'total_perf.' + name + '_widths')
self.connect('coupled.' + name + '.chords',
'total_perf.' + name + '_chords')
self.connect('coupled.' + name + '.b_pts',
'total_perf.' + name + '_b_pts')
# Add components to the 'coupled' group for each surface.
# The 'coupled' group must contain all components and parameters
# needed to converge the aerostructural system.
coupled_AS_group = _CoupledAS(surface=surface)
if surface[
'distributed_fuel_weight'] or 'n_point_masses' in surface.keys(
) or surface['struct_weight_relief']:
prom_in = ['load_factor']
else:
prom_in = []
coupled.add_subsystem(name,
coupled_AS_group,
promotes_inputs=prom_in)
if self.options['compressible'] == True:
aero_states = CompressibleVLMStates(surfaces=surfaces,
rotational=rotational)
prom_in = ['v', 'alpha', 'beta', 'rho', 'Mach_number']
else:
aero_states = VLMStates(surfaces=surfaces, rotational=rotational)
prom_in = ['v', 'alpha', 'beta', 'rho']
# If rotational, add in roll rate and cg
if rotational:
prom_in.extend(['omega', 'cg'])
# Add a single 'aero_states' component for the whole system within the
# coupled group.
coupled.add_subsystem('aero_states',
aero_states,
promotes_inputs=prom_in)
# Explicitly connect parameters from each surface's group and the common
# 'aero_states' group.
for surface in surfaces:
name = surface['name']
# Connect normals
if 'control_surfaces' in surface:
first = surface['control_surfaces'][0]['name']
last = surface['control_surfaces'][-1]['name']
coupled.connect(
f'{name}.aero_geom.normals',
f'{name}.control_surfaces.undeflected_normals')
coupled.connect(f'{name}.control_surfaces.deflected_normals',
f'aero_states.{name}_normals')
else:
coupled.connect(f'{name}.aero_geom.normals',
f'aero_states.{name}_normals')
# Add a loads component to the coupled group
for surface in surfaces:
name = surface['name']
coupled.add_subsystem(name + '_loads',
LoadTransfer(surface=surface))
"""
### Change the solver settings here ###
"""
# Set solver properties for the coupled group
# coupled.linear_solver = ScipyKrylov()
# coupled.linear_solver.precon = om.LinearRunOnce()
coupled.nonlinear_solver = om.NonlinearBlockGS(use_aitken=True)
coupled.nonlinear_solver.options['maxiter'] = 100
coupled.nonlinear_solver.options['atol'] = 1e-7
coupled.nonlinear_solver.options['rtol'] = 1e-30
coupled.nonlinear_solver.options['iprint'] = 2
coupled.nonlinear_solver.options['err_on_non_converge'] = True
# coupled.linear_solver = om.DirectSolver()
coupled.linear_solver = om.DirectSolver(assemble_jac=True)
coupled.options['assembled_jac_type'] = 'csc'
# coupled.nonlinear_solver = om.NewtonSolver(solve_subsystems=True)
# coupled.nonlinear_solver.options['maxiter'] = 50
"""
### End change of solver settings ###
"""
prom_in = ['v', 'alpha', 'rho']
if self.options['compressible'] == True:
prom_in.append('Mach_number')
# If rotational, add in roll rate and cg
if rotational:
prom_in.extend(['omega', 'cg'])
# Add the coupled group to the model problem
self.add_subsystem('coupled', coupled, promotes_inputs=prom_in)
for surface in surfaces:
name = surface['name']
# Add a performance group which evaluates the data after solving
# the coupled system
perf_group = CoupledPerformance(surface=surface)
self.add_subsystem(
name + '_perf',
perf_group,
promotes_inputs=['rho', 'v', 'alpha', 're', 'Mach_number'])
# Add functionals to evaluate performance of the system.
# Note that only the interesting results are promoted here; not all
# of the parameters.
if not rotational:
self.add_subsystem(
'total_perf',
TotalPerformance(
surfaces=surfaces,
user_specified_Sref=self.options['user_specified_Sref'],
internally_connect_fuelburn=self.
options['internally_connect_fuelburn']),
promotes_inputs=[
'v', 'rho', 'empty_cg', 'total_weight', 'CT',
'speed_of_sound', 'R', 'Mach_number', 'W0', 'load_factor',
'S_ref_total'
],
promotes_outputs=[
'L_equals_W', 'fuelburn', 'CL', 'CD', 'CM', 'cg'
])
elif rotational:
# In rotational case cannot take in empty_cg and calculate cg.
# Leads to a cycle between three groups (rotational aero needs
# cg well before cg calculation)
if rollOnly:
self.add_subsystem(
'total_perf',
TotalRollPerformance(
surfaces=surfaces,
user_specified_Sref=self.
options['user_specified_Sref'],
internally_connect_fuelburn=self.
options['internally_connect_fuelburn'],
rotational=self.options['rotational']),
promotes_inputs=['v', 'rho', 'cg', 'S_ref_total'],
promotes_outputs=['CL', 'CD', 'CM'])
else:
self.add_subsystem(
'total_perf',
TotalPerformance(surfaces=surfaces,
user_specified_Sref=self.
options['user_specified_Sref'],
internally_connect_fuelburn=self.
options['internally_connect_fuelburn'],
rotational=self.options['rotational']),
promotes_inputs=[
'v', 'rho', 'cg', 'CT', 'speed_of_sound', 'R',
'Mach_number', 'W0', 'load_factor', 'S_ref_total'
],
promotes_outputs=[
'L_equals_W', 'fuelburn', 'CL', 'CD', 'CM'
])