def setup_aerostruct(self):
"""
Specific method to add the necessary components to the problem for an
aerostructural problem.
Because this code has been extended to work for multiple aerostructural
surfaces, a good portion of it is spent doing the bookkeeping for parameter
passing and ensuring that each component modifies the correct data.
"""
# Set the problem name if the user doesn't
if 'prob_name' not in self.prob_dict.keys():
self.prob_dict['prob_name'] = 'aerostruct'
# Create the base root-level group
root = Group()
coupled = Group()
# Create the problem and assign the root group
self.prob = Problem()
self.prob.root = root
# Loop over each surface in the surfaces list
for surface in self.surfaces:
# Get the surface name and create a group to contain components
# only for this surface
name = surface['name']
tmp_group = Group()
# Strip the surface names from the desvars list and save this
# modified list as self.desvars
desvar_names = []
for desvar in self.desvars.keys():
# Check to make sure that the surface's name is in the design
# variable and only add the desvar to the list if it corresponds
# to this surface.
if name[:-1] in desvar:
desvar_names.append(''.join(desvar.split('.')[1:]))
# Add independent variables that do not belong to a specific component
indep_vars = []
for var in surface['geo_vars']:
if var in desvar_names or var in surface['initial_geo'] or 'thickness' in var:
indep_vars.append((var, surface[var]))
# Add components to include in the surface's group
tmp_group.add('indep_vars',
IndepVarComp(indep_vars),
promotes=['*'])
tmp_group.add('tube',
MaterialsTube(surface),
promotes=['*'])
tmp_group.add('mesh',
GeometryMesh(surface, self.desvars),
promotes=['*'])
tmp_group.add('struct_setup',
SpatialBeamSetup(surface),
promotes=['*'])
# Add bspline components for active bspline geometric variables.
# We only add the component if the corresponding variable is a desvar,
# a special parameter (radius), or if the user or geometry provided
# an initial distribution.
for var in surface['bsp_vars']:
if var in desvar_names or var in surface['initial_geo'] or 'thickness' in var:
n_pts = surface['num_y']
if var in ['thickness_cp', 'radius_cp']:
n_pts -= 1
trunc_var = var.split('_')[0]
tmp_group.add(trunc_var + '_bsp',
Bspline(var, trunc_var, surface['num_'+var], n_pts),
promotes=['*'])
# Add monotonic constraints for selected variables
if surface['monotonic_con'] is not None:
if type(surface['monotonic_con']) is not list:
surface['monotonic_con'] = [surface['monotonic_con']]
for var in surface['monotonic_con']:
tmp_group.add('monotonic_' + var,
MonotonicConstraint(var, surface), promotes=['*'])
# Add tmp_group to the problem with the name of the surface.
name_orig = name
name = name[:-1]
root.add(name, tmp_group, promotes=[])
# Add components to the 'coupled' group for each surface.
# The 'coupled' group must contain all components and parameters
# needed to converge the aerostructural system.
tmp_group = Group()
tmp_group.add('def_mesh',
TransferDisplacements(surface),
promotes=['*'])
tmp_group.add('aero_geom',
VLMGeometry(surface),
promotes=['*'])
tmp_group.add('struct_states',
SpatialBeamStates(surface),
promotes=['*'])
tmp_group.struct_states.ln_solver = LinearGaussSeidel()
tmp_group.struct_states.ln_solver.options['atol'] = 1e-20
name = name_orig
coupled.add(name[:-1], tmp_group, promotes=[])
# Add a loads component to the coupled group
coupled.add(name_orig + 'loads', TransferLoads(surface), promotes=[])
# Add a performance group which evaluates the data after solving
# the coupled system
tmp_group = Group()
tmp_group.add('struct_funcs',
SpatialBeamFunctionals(surface),
promotes=['*'])
tmp_group.add('aero_funcs',
VLMFunctionals(surface, self.prob_dict),
promotes=['*'])
root.add(name_orig + 'perf', tmp_group, promotes=["rho", "v", "alpha", "re", "M"])
root.add_metadata(surface['name'] + 'yield_stress', surface['yield'])
root.add_metadata(surface['name'] + 'fem_origin', surface['fem_origin'])
# Add a single 'aero_states' component for the whole system within the
# coupled group.
coupled.add('aero_states',
VLMStates(self.surfaces),
promotes=['v', 'alpha', 'rho'])
# Explicitly connect parameters from each surface's group and the common
# 'aero_states' group.
for surface in self.surfaces:
name = surface['name']
root.connect(name[:-1] + '.K', 'coupled.' + name[:-1] + '.K')
# Perform the connections with the modified names within the
# 'aero_states' group.
root.connect('coupled.' + name[:-1] + '.def_mesh', 'coupled.aero_states.' + name + 'def_mesh')
root.connect('coupled.' + name[:-1] + '.b_pts', 'coupled.aero_states.' + name + 'b_pts')
root.connect('coupled.' + name[:-1] + '.c_pts', 'coupled.aero_states.' + name + 'c_pts')
root.connect('coupled.' + name[:-1] + '.normals', 'coupled.aero_states.' + name + 'normals')
# Connect the results from 'aero_states' to the performance groups
root.connect('coupled.aero_states.' + name + 'sec_forces', name + 'perf' + '.sec_forces')
# Connect the results from 'coupled' to the performance groups
root.connect('coupled.' + name[:-1] + '.def_mesh', 'coupled.' + name + 'loads.def_mesh')
root.connect('coupled.aero_states.' + name + 'sec_forces', 'coupled.' + name + 'loads.sec_forces')
# 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.
root.connect('coupled.' + name + 'loads.loads', 'coupled.' + name[:-1] + '.loads')
# Connect aerodyamic mesh to coupled group mesh
root.connect(name[:-1] + '.mesh', 'coupled.' + name[:-1] + '.mesh')
# Connect performance calculation variables
root.connect(name[:-1] + '.radius', name + 'perf.radius')
root.connect(name[:-1] + '.A', name + 'perf.A')
root.connect(name[:-1] + '.thickness', name + 'perf.thickness')
# Connection performance functional variables
root.connect(name + 'perf.structural_weight', 'total_perf.' + name + 'structural_weight')
root.connect(name + 'perf.L', 'total_perf.' + name + 'L')
root.connect(name + 'perf.CL', 'total_perf.' + name + 'CL')
root.connect(name + 'perf.CD', 'total_perf.' + name + 'CD')
root.connect('coupled.aero_states.' + name + 'sec_forces', 'total_perf.' + name + 'sec_forces')
# Connect parameters from the 'coupled' group to the performance
# groups for the individual surfaces.
root.connect(name[:-1] + '.nodes', name + 'perf.nodes')
root.connect('coupled.' + name[:-1] + '.disp', name + 'perf.disp')
root.connect('coupled.' + name[:-1] + '.S_ref', name + 'perf.S_ref')
root.connect('coupled.' + name[:-1] + '.widths', name + 'perf.widths')
root.connect('coupled.' + name[:-1] + '.lengths', name + 'perf.lengths')
root.connect('coupled.' + name[:-1] + '.cos_sweep', name + 'perf.cos_sweep')
# Connect parameters from the 'coupled' group to the total performance group.
root.connect('coupled.' + name[:-1] + '.S_ref', 'total_perf.' + name + 'S_ref')
root.connect('coupled.' + name[:-1] + '.widths', 'total_perf.' + name + 'widths')
root.connect('coupled.' + name[:-1] + '.chords', 'total_perf.' + name + 'chords')
root.connect('coupled.' + name[:-1] + '.b_pts', 'total_perf.' + name + 'b_pts')
root.connect(name + 'perf.cg_location', 'total_perf.' + name + 'cg_location')
# Set solver properties for the coupled group
coupled.ln_solver = ScipyGMRES()
coupled.ln_solver.preconditioner = LinearGaussSeidel()
coupled.aero_states.ln_solver = LinearGaussSeidel()
coupled.nl_solver = NLGaussSeidel()
# This is only available in the most recent version of OpenMDAO.
# It may help converge tightly coupled systems when using NLGS.
try:
coupled.nl_solver.options['use_aitken'] = True
coupled.nl_solver.options['aitken_alpha_min'] = 0.01
# coupled.nl_solver.options['aitken_alpha_max'] = 0.5
except:
pass
if self.prob_dict['print_level'] == 2:
coupled.ln_solver.options['iprint'] = 1
if self.prob_dict['print_level']:
coupled.nl_solver.options['iprint'] = 1
# Add the coupled group to the root problem
root.add('coupled', coupled, promotes=['v', 'alpha', 'rho'])
# Add problem information as an independent variables component
prob_vars = [('v', self.prob_dict['v']),
('alpha', self.prob_dict['alpha']),
('M', self.prob_dict['M']),
('re', self.prob_dict['Re']/self.prob_dict['reynolds_length']),
('rho', self.prob_dict['rho'])]
root.add('prob_vars',
IndepVarComp(prob_vars),
promotes=['*'])
# Add functionals to evaluate performance of the system.
# Note that only the interesting results are promoted here; not all
# of the parameters.
root.add('total_perf',
TotalPerformance(self.surfaces, self.prob_dict),
promotes=['L_equals_W', 'fuelburn', 'CM', 'CL', 'CD', 'v', 'rho', 'cg', 'weighted_obj', 'total_weight'])
# Actually set up the system
self.setup_prob()
def setup_struct(self):
"""
Specific method to add the necessary components to the problem for a
structural problem.
"""
# Set the problem name if the user doesn't
if 'prob_name' not in self.prob_dict.keys():
self.prob_dict['prob_name'] = 'struct'
# Create the base root-level group
root = Group()
# Create the problem and assign the root group
self.prob = Problem()
self.prob.root = root
# Loop over each surface in the surfaces list
for surface in self.surfaces:
# Get the surface name and create a group to contain components
# only for this surface.
# This group's name is whatever the surface's name is.
# The default is 'wing'.
name = surface['name']
tmp_group = Group()
# Strip the surface names from the desvars list and save this
# modified list as self.desvars
desvar_names = []
for desvar in self.desvars.keys():
# Check to make sure that the surface's name is in the design
# variable and only add the desvar to the list if it corresponds
# to this surface.
if name[:-1] in desvar:
desvar_names.append(''.join(desvar.split('.')[1:]))
# Add independent variables that do not belong to a specific component.
# Note that these are the only ones necessary for structual-only
# analysis and optimization.
# Here we check and only add the variables that are desvars or a
# special var, radius, which is necessary to compute weight.
indep_vars = [('loads', surface['loads'])]
for var in surface['geo_vars']:
if var in desvar_names or 'thickness' in var or var in surface['initial_geo']:
indep_vars.append((var, surface[var]))
# Add structural components to the surface-specific group
tmp_group.add('indep_vars',
IndepVarComp(indep_vars),
promotes=['*'])
tmp_group.add('mesh',
GeometryMesh(surface, self.desvars),
promotes=['*'])
tmp_group.add('tube',
MaterialsTube(surface),
promotes=['*'])
tmp_group.add('struct_setup',
SpatialBeamSetup(surface),
promotes=['*'])
tmp_group.add('struct_states',
SpatialBeamStates(surface),
promotes=['*'])
tmp_group.add('struct_funcs',
SpatialBeamFunctionals(surface),
promotes=['*'])
# Add bspline components for active bspline geometric variables.
# We only add the component if the corresponding variable is a desvar
# or special (radius).
for var in surface['bsp_vars']:
if var in desvar_names or var in surface['initial_geo'] or 'thickness' in var:
n_pts = surface['num_y']
if var in ['thickness_cp', 'radius_cp']:
n_pts -= 1
trunc_var = var.split('_')[0]
tmp_group.add(trunc_var + '_bsp',
Bspline(var, trunc_var, surface['num_'+var], n_pts),
promotes=['*'])
# Add tmp_group to the problem with the name of the surface.
# The default is 'wing'.
root.add(name[:-1], tmp_group, promotes=[])
root.add_metadata(surface['name'] + 'yield_stress', surface['yield'])
root.add_metadata(surface['name'] + 'fem_origin', surface['fem_origin'])
# Actually set up the problem
self.setup_prob()
