def taper(mesh, taper_ratio, symmetry):
""" Alter the spanwise chord to produce a tapered wing.
Parameters
----------
mesh : array_like
Nodal mesh defining the initial aerodynamic surface.
taper_ratio : float
Taper ratio for the wing; 1 is untapered, 0 goes to a point.
symmetry : boolean
Flag set to true if surface is reflected about y=0 plane.
Returns
-------
mesh : array_like
Nodal mesh defining the tapered aerodynamic surface.
"""
le = mesh[0]
te = mesh[-1]
num_x, num_y, _ = mesh.shape
center_chord = .5 * te + .5 * le
if symmetry:
taper = numpy.linspace(1, taper_ratio, num_y)[::-1]
jac = get_bspline_mtx(num_y, num_y, order=2)
taper = jac.dot(taper)
for i in xrange(num_x):
for ind in xrange(3):
mesh[i, :, ind] = (mesh[i, :, ind] - center_chord[:, ind]) * \
taper + center_chord[:, ind]
else:
ny2 = int((num_y + 1) / 2)
taper = numpy.linspace(1, taper_ratio, ny2)[::-1]
jac = get_bspline_mtx(ny2, ny2, order=2)
taper = jac.dot(taper)
dx = numpy.hstack((taper, taper[::-1][1:]))
for i in xrange(num_x):
for ind in xrange(3):
mesh[i, :, ind] = (mesh[i, :, ind] - center_chord[:, ind]) * \
dx + center_chord[:, ind]
return mesh
def __init__(self, cpname, ptname, n_input, n_output):
super(Bspline, self).__init__()
self.cpname = cpname
self.ptname = ptname
self.jac = get_bspline_mtx(n_input, n_output, order=min(n_input, 4))
self.add_param(cpname, val=np.zeros(n_input))
self.add_output(ptname, val=np.zeros(n_output))
def __init__(self, cpname, ptname, n_input, n_output):
super(Bspline, self).__init__()
self.cpname = cpname
self.ptname = ptname
self.jac = get_bspline_mtx(n_input, n_output, order=min(n_input, 4))
self.add_param(cpname, val=np.zeros(n_input))
self.add_output(ptname, val=np.zeros(n_output))
def solve_nonlinear(self, params, unknowns, resids):
jac = get_bspline_mtx(self.num_twist, self.n, self.mesh)
h_cp = params['twist']
h = jac.dot(h_cp)
self.new_mesh[:] = self.mesh
stretch(self.new_mesh, params['span'])
sweep(self.new_mesh, params['sweep'])
rotate(self.new_mesh, h)
dihedral(self.new_mesh, params['dihedral'])
taper(self.new_mesh, params['taper'])
unknowns['mesh'] = self.new_mesh[:, :self.half + 1, :]
def taper(mesh, taper_ratio):
""" Change the spanwise chord to produce a tapered wing. """
le = mesh[0]
te = mesh[-1]
num_x, num_y, _ = mesh.shape
ny2 = int((num_y + 1) / 2)
center_chord = .5 * te + .5 * le
span = le[-1, 1] - le[0, 1]
taper = numpy.linspace(1, taper_ratio, ny2)[::-1]
jac = get_bspline_mtx(ny2, ny2, mesh, order=2)
taper = jac.dot(taper)
dx = numpy.hstack((taper, taper[::-1][1:]))
for i in xrange(num_x):
for ind in xrange(3):
mesh[i, :, ind] = (mesh[i, :, ind] - center_chord[:, ind]) * \
dx + center_chord[:, ind]
return mesh
def setup(num_inboard=2, num_outboard=3, check=False, out_stream=sys.stdout):
''' Setup the aerostruct mesh using OpenMDAO'''
# Define the aircraft properties
from CRM import span, v, alpha, rho
# Define spatialbeam properties
from aluminum import E, G, stress, mrho
# Create the mesh with 2 inboard points and 3 outboard points.
# This will be mirrored to produce a mesh with 7 spanwise points,
# or 6 spanwise panels
# print(type(num_inboard))
mesh = gen_crm_mesh(int(num_inboard), int(num_outboard), num_x=2)
num_x, num_y = mesh.shape[:2]
num_twist = np.max([int((num_y - 1) / 5), 5])
r = radii(mesh)
# Set the number of thickness control points and the initial thicknesses
num_thickness = num_twist
t = r / 10
mesh = mesh.reshape(-1, mesh.shape[-1])
aero_ind = np.atleast_2d(np.array([num_x, num_y]))
fem_ind = [num_y]
aero_ind, fem_ind = get_inds(aero_ind, fem_ind)
# Set additional mesh parameters
dihedral = 0. # dihedral angle in degrees
sweep = 0. # shearing sweep angle in degrees
taper = 1. # taper ratio
# Initial displacements of zero
tot_n_fem = np.sum(fem_ind[:, 0])
disp = np.zeros((tot_n_fem, 6))
# Define Jacobians for b-spline controls
tot_n_fem = np.sum(fem_ind[:, 0])
num_surf = fem_ind.shape[0]
jac_twist = get_bspline_mtx(num_twist, num_y)
jac_thickness = get_bspline_mtx(num_thickness, tot_n_fem-num_surf)
# Define ...
twist_cp = np.zeros(num_twist)
thickness_cp = np.ones(num_thickness)*np.max(t)
# Define the design variables
des_vars = [
('twist_cp', twist_cp),
('dihedral', dihedral),
('sweep', sweep),
('span', span),
('taper', taper),
('v', v),
('alpha', alpha),
('rho', rho),
('disp', disp),
('aero_ind', aero_ind),
('fem_ind', fem_ind)
]
root = Group()
root.add('des_vars',
IndepVarComp(des_vars),
promotes=['twist_cp','span','v','alpha','rho','disp','dihedral'])
root.add('mesh', # This component is needed, otherwise resulting loads matrix is NaN
GeometryMesh(mesh, aero_ind), # changes mesh given span, sweep, twist, and des_vars
promotes=['span','sweep','dihedral','twist','taper','mesh'])
root.add('def_mesh',
TransferDisplacements(aero_ind, fem_ind),
promotes=['mesh','disp','def_mesh'])
prob = Problem()
prob.root = root
prob.setup(check=check, out_stream=out_stream)
prob.run()
# Output the def_mesh for the aero modules
def_mesh = prob['def_mesh']
# Other variables needed for aero and struct modules
params = {
'mesh': mesh,
'num_x': num_x,
'num_y': num_y,
'span': span,
'twist_cp': twist_cp,
'thickness_cp': thickness_cp,
'v': v,
'alpha': alpha,
'rho': rho,
'r': r,
't': t,
'aero_ind': aero_ind,
'fem_ind': fem_ind,
'num_thickness': num_thickness,
'num_twist': num_twist,
'sweep': sweep,
'taper': taper,
'dihedral': dihedral,
'E': E,
'G': G,
'stress': stress,
'mrho': mrho,
'tot_n_fem': tot_n_fem,
'num_surf': num_surf,
'jac_twist': jac_twist,
'jac_thickness': jac_thickness,
'out_stream': out_stream,
'check': check
}
return (def_mesh, params)
def aero(def_mesh=None, params=None):
if (params is None) or (def_mesh is None):
tmpmesh, params = setup()
if not def_mesh:
def_mesh = tmpmesh
# Unpack variables
mesh = params.get('mesh')
num_x = params.get('num_x')
num_y = params.get('num_y')
span = params.get('span')
twist_cp = params.get('twist_cp')
thickness_cp = params.get('thickness_cp')
v = params.get('v')
alpha = params.get('alpha')
rho = params.get('rho')
r = params.get('r')
t = params.get('t')
aero_ind = params.get('aero_ind')
fem_ind = params.get('fem_ind')
num_thickness = params.get('num_thickness')
num_twist = params.get('num_twist')
sweep = params.get('sweep')
taper = params.get('taper')
disp = params.get('disp')
dihedral = params.get('dihedral')
check = params.get('check')
out_stream = params.get('out_stream')
# Define Jacobians for b-spline controls
tot_n_fem = np.sum(fem_ind[:, 0])
num_surf = fem_ind.shape[0]
jac_twist = get_bspline_mtx(num_twist, num_y)
jac_thickness = get_bspline_mtx(num_thickness, tot_n_fem-num_surf)
disp = np.zeros((num_y, 6)) # for display?
# Define the design variables
des_vars = [
('twist_cp', np.zeros(num_twist)),
('dihedral', dihedral),
('sweep', sweep),
('span', span),
('taper', taper),
('v', v),
('alpha', alpha),
('rho', rho),
('disp', np.zeros((tot_n_fem, 6))),
('def_mesh', def_mesh)
]
root = Group()
root.add('des_vars',
IndepVarComp(des_vars),
promotes=['twist_cp','span','v','alpha','rho','disp','dihedral','def_mesh'])
# root.add('twist_bsp', # What is this doing?
# Bspline('twist_cp', 'twist', jac_twist),
# promotes=['*'])
# root.add('thickness_bsp', # What is this doing?
# Bspline('thickness_cp', 'thickness', jac_thickness),
# promotes=['*'])
# root.add('tube',
# MaterialsTube(fem_ind),
# promotes=['*'])
root.add('VLMstates',
VLMStates(aero_ind),
promotes=[
'def_mesh','b_pts','mid_b','c_pts','widths','normals','S_ref', # VLMGeometry
'alpha','circulations','v', # VLMCirculations
'rho','sec_forces' # VLMForces
])
root.add('loads',
TransferLoads(aero_ind, fem_ind),
promotes=['def_mesh','sec_forces','loads'])
prob = Problem()
prob.root = root
prob.setup(check=check, out_stream=out_stream)
prob.run()
return prob['loads'] # Output the Loads matrix
def setup_aerostruct(self):
"""
Specific method to add the necessary components to the problem for an
aerostructural problem.
"""
# 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()
# Add independent variables that do not belong to a specific component
indep_vars = [
('twist_cp', numpy.zeros(surface['num_twist'])),
('thickness_cp', numpy.ones(surface['num_thickness']) *
numpy.max(surface['t'])), ('r', surface['r']),
('dihedral', surface['dihedral']), ('sweep', surface['sweep']),
('span', surface['span']), ('taper', surface['taper'])
]
# Obtain the Jacobians to interpolate the data from the b-spline
# control points
jac_twist = get_bspline_mtx(surface['num_twist'], surface['num_y'])
jac_thickness = get_bspline_mtx(surface['num_thickness'],
surface['num_y'] - 1)
# Add components to include in the surface's group
tmp_group.add('indep_vars',
IndepVarComp(indep_vars),
promotes=['*'])
tmp_group.add('twist_bsp',
Bspline('twist_cp', 'twist', jac_twist),
promotes=['*'])
tmp_group.add('thickness_bsp',
Bspline('thickness_cp', 'thickness', jac_thickness),
promotes=['*'])
tmp_group.add('tube', MaterialsTube(surface), promotes=['*'])
# Add tmp_group to the problem with the name of the surface.
name_orig = name
name = name[:-1]
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name + ', 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('mesh', GeometryMesh(surface), promotes=['*'])
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()
name = name_orig
exec(name + ' = tmp_group')
exec('coupled.add("' + name[:-1] + '", ' + name + ', promotes=[])')
# Add a loads component to the coupled group
exec('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),
promotes=['*'])
name = name_orig + 'perf'
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name +
', promotes=["rho", "v", "alpha", "Re", "M"])')
# Add a single 'aero_states' component for the whole system within the
# coupled group.
coupled.add('aero_states',
VLMStates(self.surfaces, self.prob_dict),
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']
# 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')
root.connect('coupled.' + name + 'loads.loads',
name + 'perf.loads')
# 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 design variables
root.connect(name[:-1] + '.dihedral',
'coupled.' + name[:-1] + '.dihedral')
root.connect(name[:-1] + '.span', 'coupled.' + name[:-1] + '.span')
root.connect(name[:-1] + '.sweep',
'coupled.' + name[:-1] + '.sweep')
root.connect(name[:-1] + '.taper',
'coupled.' + name[:-1] + '.taper')
root.connect(name[:-1] + '.twist',
'coupled.' + name[:-1] + '.twist')
# Connect structural design variables
root.connect(name[:-1] + '.A', 'coupled.' + name[:-1] + '.A')
root.connect(name[:-1] + '.Iy', 'coupled.' + name[:-1] + '.Iy')
root.connect(name[:-1] + '.Iz', 'coupled.' + name[:-1] + '.Iz')
root.connect(name[:-1] + '.J', 'coupled.' + name[:-1] + '.J')
# Connect performance calculation variables
root.connect(name[:-1] + '.r', name + 'perf.r')
root.connect(name[:-1] + '.A', name + 'perf.A')
# Connection performance functional variables
root.connect(name + 'perf.weight', 'fuelburn.' + name + 'weight')
root.connect(name + 'perf.weight', 'eq_con.' + name + 'weight')
root.connect(name + 'perf.L', 'eq_con.' + name + 'L')
root.connect(name + 'perf.CL', 'fuelburn.' + name + 'CL')
root.connect(name + 'perf.CD', 'fuelburn.' + name + 'CD')
# Connect paramters from the 'coupled' group to the performance
# group.
root.connect('coupled.' + 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')
# Set solver properties for the coupled group
coupled.ln_solver = ScipyGMRES()
coupled.ln_solver.options['iprint'] = 1
coupled.ln_solver.preconditioner = LinearGaussSeidel()
coupled.aero_states.ln_solver = LinearGaussSeidel()
coupled.nl_solver = NLGaussSeidel()
coupled.nl_solver.options['iprint'] = 1
# Ensure that the groups are ordered correctly within the coupled group
# so that a system with multiple surfaces is solved corretly.
order_list = []
for surface in self.surfaces:
order_list.append(surface['name'][:-1])
order_list.append('aero_states')
for surface in self.surfaces:
order_list.append(surface['name'] + 'loads')
coupled.set_order(order_list)
# 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']),
('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('fuelburn',
FunctionalBreguetRange(self.surfaces, self.prob_dict),
promotes=['fuelburn'])
root.add('eq_con',
FunctionalEquilibrium(self.surfaces, self.prob_dict),
promotes=['eq_con', 'fuelburn'])
# Actually set up the system
self.setup_prob()
def setup_aero(self):
"""
Specific method to add the necessary components to the problem for an
aerodynamic problem.
"""
# Set the problem name if the user doesn't
if 'prob_name' not in self.prob_dict.keys():
self.prob_dict['prob_name'] = 'aero'
# 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
name = surface['name']
tmp_group = Group()
# Add independent variables that do not belong to a specific component
indep_vars = [('twist_cp', numpy.zeros(surface['num_twist'])),
('dihedral', surface['dihedral']),
('sweep', surface['sweep']),
('span', surface['span']),
('taper', surface['taper']),
('disp', numpy.zeros((surface['num_y'], 6)))]
# Obtain the Jacobian to interpolate the data from the b-spline
# control points
jac_twist = get_bspline_mtx(surface['num_twist'], surface['num_y'])
# Add aero components to the surface-specific group
tmp_group.add('indep_vars',
IndepVarComp(indep_vars),
promotes=['*'])
tmp_group.add('twist_bsp',
Bspline('twist_cp', 'twist', jac_twist),
promotes=['*'])
tmp_group.add('mesh', GeometryMesh(surface), promotes=['*'])
tmp_group.add('def_mesh',
TransferDisplacements(surface),
promotes=['*'])
tmp_group.add('vlmgeom', VLMGeometry(surface), promotes=['*'])
# Add tmp_group to the problem as the name of the surface.
# Note that is a group and performance group for each
# individual surface.
name_orig = name.strip('_')
name = name_orig
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name + ', promotes=[])')
# Add a performance group for each surface
name = name_orig + '_perf'
exec('root.add("' + name + '", ' + 'VLMFunctionals(surface)' +
', promotes=["v", "alpha", "M", "Re", "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']),
('rho', self.prob_dict['rho'])]
root.add('prob_vars', IndepVarComp(prob_vars), promotes=['*'])
# Add a single 'aero_states' component that solves for the circulations
# and forces from all the surfaces.
# While other components only depends on a single surface,
# this component requires information from all surfaces because
# each surface interacts with the others.
root.add('aero_states',
VLMStates(self.surfaces, self.prob_dict),
promotes=['circulations', 'v', 'alpha', 'rho'])
# Explicitly connect parameters from each surface's group and the common
# 'aero_states' group.
# This is necessary because the VLMStates component requires information
# from each surface, but this information is stored within each
# surface's group.
for surface in self.surfaces:
name = surface['name']
# Perform the connections with the modified names within the
# 'aero_states' group.
root.connect(name[:-1] + '.def_mesh',
'aero_states.' + name + 'def_mesh')
root.connect(name[:-1] + '.b_pts', 'aero_states.' + name + 'b_pts')
root.connect(name[:-1] + '.c_pts', 'aero_states.' + name + 'c_pts')
root.connect(name[:-1] + '.normals',
'aero_states.' + name + 'normals')
# Connect the results from 'aero_states' to the performance groups
root.connect('aero_states.' + name + 'sec_forces',
name + 'perf' + '.sec_forces')
# Connect S_ref for performance calcs
root.connect(name[:-1] + '.S_ref', name + 'perf' + '.S_ref')
# Actually set up the problem
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()
surface['r'] = surface['r'] / 5
surface['t'] = surface['r'] / 20
# 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.
indep_vars = [
('thickness_cp', numpy.ones(surface['num_thickness']) *
numpy.max(surface['t'])), ('r', surface['r']),
('loads', surface['loads'])
]
# Obtain the Jacobians to interpolate the data from the b-spline
# control points
jac_twist = get_bspline_mtx(surface['num_twist'], surface['num_y'])
jac_thickness = get_bspline_mtx(surface['num_thickness'],
surface['num_y'] - 1)
# Add structural components to the surface-specific group
tmp_group.add('indep_vars',
IndepVarComp(indep_vars),
promotes=['*'])
tmp_group.add('twist_bsp',
Bspline('twist_cp', 'twist', jac_twist),
promotes=['*'])
tmp_group.add('thickness_bsp',
Bspline('thickness_cp', 'thickness', jac_thickness),
promotes=['*'])
tmp_group.add('mesh', GeometryMesh(surface), promotes=['*'])
tmp_group.add('tube', MaterialsTube(surface), promotes=['*'])
tmp_group.add('struct_states',
SpatialBeamStates(surface),
promotes=['*'])
tmp_group.add('struct_funcs',
SpatialBeamFunctionals(surface),
promotes=['*'])
# Add tmp_group to the problem with the name of the surface.
# The default is 'wing'.
nm = name
name = name[:-1]
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name + ', promotes=[])')
# Actually set up the problem
self.setup_prob()
def setup(num_inboard=2, num_outboard=3, check=False, out_stream=sys.stdout):
''' Setup the aerostruct mesh using OpenMDAO'''
# Define the aircraft properties
from CRM import span, v, alpha, rho
# Define spatialbeam properties
from aluminum import E, G, stress, mrho
# Create the mesh with 2 inboard points and 3 outboard points.
# This will be mirrored to produce a mesh with 7 spanwise points,
# or 6 spanwise panels
# print(type(num_inboard))
mesh = gen_crm_mesh(int(num_inboard), int(num_outboard), num_x=2)
num_x, num_y = mesh.shape[:2]
num_twist = np.max([int((num_y - 1) / 5), 5])
r = radii(mesh)
# Set the number of thickness control points and the initial thicknesses
num_thickness = num_twist
t = r / 10
mesh = mesh.reshape(-1, mesh.shape[-1])
aero_ind = np.atleast_2d(np.array([num_x, num_y]))
fem_ind = [num_y]
aero_ind, fem_ind = get_inds(aero_ind, fem_ind)
# Set additional mesh parameters
dihedral = 0. # dihedral angle in degrees
sweep = 0. # shearing sweep angle in degrees
taper = 1. # taper ratio
# Initial displacements of zero
tot_n_fem = np.sum(fem_ind[:, 0])
disp = np.zeros((tot_n_fem, 6))
# Define Jacobians for b-spline controls
tot_n_fem = np.sum(fem_ind[:, 0])
num_surf = fem_ind.shape[0]
jac_twist = get_bspline_mtx(num_twist, num_y)
jac_thickness = get_bspline_mtx(num_thickness, tot_n_fem - num_surf)
# Define ...
twist_cp = np.zeros(num_twist)
thickness_cp = np.ones(num_thickness) * np.max(t)
# Define the design variables
des_vars = [('twist_cp', twist_cp), ('dihedral', dihedral),
('sweep', sweep), ('span', span), ('taper', taper), ('v', v),
('alpha', alpha), ('rho', rho), ('disp', disp),
('aero_ind', aero_ind), ('fem_ind', fem_ind)]
root = Group()
root.add(
'des_vars',
IndepVarComp(des_vars),
promotes=['twist_cp', 'span', 'v', 'alpha', 'rho', 'disp', 'dihedral'])
root.add(
'mesh', # This component is needed, otherwise resulting loads matrix is NaN
GeometryMesh(
mesh,
aero_ind), # changes mesh given span, sweep, twist, and des_vars
promotes=['span', 'sweep', 'dihedral', 'twist', 'taper', 'mesh'])
root.add('def_mesh',
TransferDisplacements(aero_ind, fem_ind),
promotes=['mesh', 'disp', 'def_mesh'])
prob = Problem()
prob.root = root
prob.setup(check=check, out_stream=out_stream)
prob.run()
# Output the def_mesh for the aero modules
def_mesh = prob['def_mesh']
# Other variables needed for aero and struct modules
params = {
'mesh': mesh,
'num_x': num_x,
'num_y': num_y,
'span': span,
'twist_cp': twist_cp,
'thickness_cp': thickness_cp,
'v': v,
'alpha': alpha,
'rho': rho,
'r': r,
't': t,
'aero_ind': aero_ind,
'fem_ind': fem_ind,
'num_thickness': num_thickness,
'num_twist': num_twist,
'sweep': sweep,
'taper': taper,
'dihedral': dihedral,
'E': E,
'G': G,
'stress': stress,
'mrho': mrho,
'tot_n_fem': tot_n_fem,
'num_surf': num_surf,
'jac_twist': jac_twist,
'jac_thickness': jac_thickness,
'out_stream': out_stream,
'check': check
}
return (def_mesh, params)
def aero(def_mesh=None, params=None):
if (params is None) or (def_mesh is None):
tmpmesh, params = setup()
if not def_mesh:
def_mesh = tmpmesh
# Unpack variables
mesh = params.get('mesh')
num_x = params.get('num_x')
num_y = params.get('num_y')
span = params.get('span')
twist_cp = params.get('twist_cp')
thickness_cp = params.get('thickness_cp')
v = params.get('v')
alpha = params.get('alpha')
rho = params.get('rho')
r = params.get('r')
t = params.get('t')
aero_ind = params.get('aero_ind')
fem_ind = params.get('fem_ind')
num_thickness = params.get('num_thickness')
num_twist = params.get('num_twist')
sweep = params.get('sweep')
taper = params.get('taper')
disp = params.get('disp')
dihedral = params.get('dihedral')
check = params.get('check')
out_stream = params.get('out_stream')
# Define Jacobians for b-spline controls
tot_n_fem = np.sum(fem_ind[:, 0])
num_surf = fem_ind.shape[0]
jac_twist = get_bspline_mtx(num_twist, num_y)
jac_thickness = get_bspline_mtx(num_thickness, tot_n_fem - num_surf)
disp = np.zeros((num_y, 6)) # for display?
# Define the design variables
des_vars = [('twist_cp', np.zeros(num_twist)), ('dihedral', dihedral),
('sweep', sweep), ('span', span), ('taper', taper), ('v', v),
('alpha', alpha), ('rho', rho),
('disp', np.zeros((tot_n_fem, 6))), ('def_mesh', def_mesh)]
root = Group()
root.add('des_vars',
IndepVarComp(des_vars),
promotes=[
'twist_cp', 'span', 'v', 'alpha', 'rho', 'disp', 'dihedral',
'def_mesh'
])
# root.add('twist_bsp', # What is this doing?
# Bspline('twist_cp', 'twist', jac_twist),
# promotes=['*'])
# root.add('thickness_bsp', # What is this doing?
# Bspline('thickness_cp', 'thickness', jac_thickness),
# promotes=['*'])
# root.add('tube',
# MaterialsTube(fem_ind),
# promotes=['*'])
root.add(
'VLMstates',
VLMStates(aero_ind),
promotes=[
'def_mesh',
'b_pts',
'mid_b',
'c_pts',
'widths',
'normals',
'S_ref', # VLMGeometry
'alpha',
'circulations',
'v', # VLMCirculations
'rho',
'sec_forces' # VLMForces
])
root.add('loads',
TransferLoads(aero_ind, fem_ind),
promotes=['def_mesh', 'sec_forces', 'loads'])
prob = Problem()
prob.root = root
prob.setup(check=check, out_stream=out_stream)
prob.run()
return prob['loads'] # Output the Loads matrix
fem_ind = [num_y]
aero_ind, fem_ind = get_inds(aero_ind, fem_ind)
num_thickness = num_twist
t = r/10
# Define the aircraft properties
execfile('CRM.py')
# Define the material properties
execfile('aluminum.py')
# Create the top-level system
root = Group()
tot_n_fem = numpy.sum(fem_ind[:, 0])
num_surf = fem_ind.shape[0]
jac_twist = get_bspline_mtx(num_twist, num_y)
jac_thickness = get_bspline_mtx(num_thickness, tot_n_fem-num_surf)
# Define the independent variables
indep_vars = [
('span', span),
('twist_cp', numpy.zeros(num_twist)),
('thickness_cp', numpy.ones(num_thickness)*numpy.max(t)),
('v', v),
('alpha', alpha),
('rho', rho),
('r', r),
('t', t),
('aero_ind', aero_ind)
]
def setup_aerostruct(self):
"""
Specific method to add the necessary components to the problem for an
aerostructural problem.
"""
# 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()
# Add independent variables that do not belong to a specific component
indep_vars = [
(name + 'twist_cp', numpy.zeros(surface['num_twist'])),
(name + 'thickness_cp', numpy.ones(surface['num_thickness']) *
numpy.max(surface['t'])), (name + 'r', surface['r']),
(name + 'dihedral', surface['dihedral']),
(name + 'sweep', surface['sweep']),
(name + 'span', surface['span']),
(name + 'taper', surface['taper'])
]
# Obtain the Jacobians to interpolate the data from the b-spline
# control points
jac_twist = get_bspline_mtx(surface['num_twist'], surface['num_y'])
jac_thickness = get_bspline_mtx(surface['num_thickness'],
surface['num_y'] - 1)
# Add components to include in the '_pre_solve' group
tmp_group.add('indep_vars',
IndepVarComp(indep_vars),
promotes=['*'])
tmp_group.add('twist_bsp',
Bspline(name + 'twist_cp', name + 'twist',
jac_twist),
promotes=['*'])
tmp_group.add('thickness_bsp',
Bspline(name + 'thickness_cp', name + 'thickness',
jac_thickness),
promotes=['*'])
tmp_group.add('tube', MaterialsTube(surface), promotes=['*'])
# Add tmp_group to the problem with the name of the surface and
# '_pre_solve' appended.
name_orig = name #.strip('_')
name = name + 'pre_solve'
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name + ', promotes=["*"])')
# Add components to the 'coupled' group for each surface
tmp_group = Group()
tmp_group.add('mesh', GeometryMesh(surface), promotes=['*'])
tmp_group.add('def_mesh',
TransferDisplacements(surface),
promotes=['*'])
tmp_group.add('vlmgeom', VLMGeometry(surface), promotes=['*'])
tmp_group.add('spatialbeamstates',
SpatialBeamStates(surface),
promotes=['*'])
tmp_group.spatialbeamstates.ln_solver = LinearGaussSeidel()
name = name_orig + 'group'
exec(name + ' = tmp_group')
exec('coupled.add("' + name + '", ' + name + ', promotes=["*"])')
# Add a loads component to the coupled group
exec('coupled.add("' + name_orig + 'loads' + '", ' +
'TransferLoads(surface)' + ', promotes=["*"])')
# Add a '_post_solve' group which evaluates the data after solving
# the coupled system
tmp_group = Group()
tmp_group.add('spatialbeamfuncs',
SpatialBeamFunctionals(surface),
promotes=['*'])
tmp_group.add('vlmfuncs', VLMFunctionals(surface), promotes=['*'])
name = name_orig + 'post_solve'
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name + ', promotes=["*"])')
# Add a single 'VLMStates' component for the whole system
coupled.add('vlmstates',
VLMStates(self.surfaces, self.prob_dict),
promotes=['*'])
# Set solver properties for the coupled group
coupled.ln_solver = ScipyGMRES()
coupled.ln_solver.options['iprint'] = 1
coupled.ln_solver.preconditioner = LinearGaussSeidel()
coupled.vlmstates.ln_solver = LinearGaussSeidel()
coupled.nl_solver = NLGaussSeidel()
coupled.nl_solver.options['iprint'] = 1
# Ensure that the groups are ordered correctly within the coupled group
order_list = []
for surface in self.surfaces:
order_list.append(surface['name'] + 'group')
order_list.append('vlmstates')
for surface in self.surfaces:
order_list.append(surface['name'] + 'loads')
coupled.set_order(order_list)
# Add the coupled group to the root problem
root.add('coupled', coupled, promotes=['*'])
# 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']),
('rho', self.prob_dict['rho'])]
root.add('prob_vars', IndepVarComp(prob_vars), promotes=['*'])
# Add functionals to evaluate performance of the system
root.add('fuelburn',
FunctionalBreguetRange(self.surfaces, self.prob_dict),
promotes=['*'])
root.add('eq_con',
FunctionalEquilibrium(self.surfaces, self.prob_dict),
promotes=['*'])
self.setup_prob()
def setup_aero(self):
"""
Specific method to add the necessary components to the problem for an
aerodynamic problem.
"""
# Set the problem name if the user doesn't
if 'prob_name' not in self.prob_dict.keys():
self.prob_dict['prob_name'] = 'aero'
# 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
name = surface['name']
tmp_group = Group()
# Add independent variables that do not belong to a specific component
indep_vars = [(name + 'twist_cp',
numpy.zeros(surface['num_twist'])),
(name + 'dihedral', surface['dihedral']),
(name + 'sweep', surface['sweep']),
(name + 'span', surface['span']),
(name + 'taper', surface['taper']),
(name + 'disp', numpy.zeros((surface['num_y'], 6)))]
# Obtain the Jacobian to interpolate the data from the b-spline
# control points
jac_twist = get_bspline_mtx(surface['num_twist'], surface['num_y'])
# Add aero components to the surface-specific group
tmp_group.add('indep_vars',
IndepVarComp(indep_vars),
promotes=['*'])
tmp_group.add('twist_bsp',
Bspline(name + 'twist_cp', name + 'twist',
jac_twist),
promotes=['*'])
tmp_group.add('mesh', GeometryMesh(surface), promotes=['*'])
tmp_group.add('def_mesh',
TransferDisplacements(surface),
promotes=['*'])
tmp_group.add('vlmgeom', VLMGeometry(surface), promotes=['*'])
# Add tmp_group to the problem with the name of the surface and
# '_pre_solve' appended.
# Note that is a '_pre_solve' and '_post_solve' group for each
# individual surface.
name_orig = name.strip('_')
name = name_orig + '_pre_solve'
exec(name + ' = tmp_group')
exec('root.add("' + name + '", ' + name + ', promotes=["*"])')
# Add a '_post_solve' group
name = name_orig + '_post_solve'
exec('root.add("' + name + '", ' + 'VLMFunctionals(surface)' +
', promotes=["*"])')
# 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']),
('rho', self.prob_dict['rho'])]
root.add('prob_vars', IndepVarComp(prob_vars), promotes=['*'])
# Add a single 'VLMStates' component that solves for the circulations
# and forces from all the surfaces.
# While other components only depends on a single surface,
# this component requires information from all surfaces because
# each surface interacts with the others.
root.add('vlmstates',
VLMStates(self.surfaces, self.prob_dict),
promotes=['*'])
self.setup_prob()
