def createElement(self, order, quad):
"""
Create an element for the entire mesh
"""
if quad.tag in alum_tags:
stiff = constitutive.PlaneStressConstitutive(alum_props)
elif quad.tag in battery_tags:
stiff = constitutive.PlaneStressConstitutive(battery_props)
else:
print("quad not defined")
# Create the model
model = elements.LinearThermoelasticity2D(stiff)
# Set the basis functions and create the element
if order == 2:
basis = elements.LinearQuadBasis()
elif order == 3:
basis = elements.QuadraticQuadBasis()
elif order == 4:
basis = elements.CubicQuadBasis()
elif order == 5:
basis = elements.QuarticQuadBasis()
elif order == 6:
basis = elements.QuinticQuadBasis()
# Create the element type
element = elements.Element2D(model, basis)
return element
def __init__(self, integrator_options, comm, tacs_comm, model,
n_tacs_procs):
self.tacs_proc = False
if comm.Get_rank() < n_tacs_procs:
self.tacs_proc = True
# Set constitutive properties
T_ref = 300.0
rho = 4540.0 # density, kg/m^3
E = 118e9 # elastic modulus, Pa
nu = 0.325 # poisson's ratio
ys = 1050e6 # yield stress, Pa
kappa = 6.89
specific_heat = 463.0
thickness = 0.015
volume = 25 # need tacs volume for TACSAverageTemperature function
# Create the constitutvie propertes and model
props_plate = constitutive.MaterialProperties(rho=4540.0,
specific_heat=463.0,
kappa=6.89,
E=118e9,
nu=0.325,
ys=1050e6)
#con_plate = constitutive.ShellConstitutive(props_plate,thickness,1,0.01,0.10)
#model_plate = elements.ThermoelasticPlateModel(con_plate)
con_plate = constitutive.PlaneStressConstitutive(props_plate,
t=1.0,
tNum=0)
model_plate = elements.HeatConduction2D(con_plate)
# Create the basis class
quad_basis = elements.LinearQuadBasis()
# Create the element
#element_shield = elements.Element2D(model_shield, quad_basis)
#element_insulation = elements.Element2D(model_insulation, quad_basis)
element_plate = elements.Element2D(model_plate, quad_basis)
varsPerNode = model_plate.getVarsPerNode()
# Load in the mesh
mesh = TACS.MeshLoader(tacs_comm)
mesh.scanBDFFile('tacs_aero.bdf')
# Set the element
mesh.setElement(0, element_plate)
# Create the assembler object
#varsPerNode = heat.getVarsPerNode()
assembler = mesh.createTACS(varsPerNode)
# Create distributed node vector from TACS Assembler object and
# extract the node locations
nbodies = 1
struct_X = []
struct_nnodes = []
for body in range(nbodies):
self.struct_X_vec = assembler.createNodeVec()
assembler.getNodes(self.struct_X_vec)
struct_X.append(self.struct_X_vec.getArray())
struct_nnodes.append(len(struct_X) / 3)
assembler.setNodes(self.struct_X_vec)
# Initialize member variables pertaining to TACS
self.T_ref = T_ref
self.vol = volume
self.assembler = assembler
self.struct_X = struct_X
self.struct_nnodes = struct_nnodes
self.struct_rhs_vec = assembler.createVec()
#self.psi_T_S_vec = assembler.createVec()
#psi_T_S = self.psi_T_S_vec.getArray()
#self.psi_T_S = np.zeros((psi_T_S.size,self.nfunc),dtype=TACS.dtype)
self.ans = self.assembler.createVec()
self.bvec_heat_flux = self.assembler.createVec()
# Things for configuring time marching
self.integrator = {}
for scenario in model.scenarios:
self.integrator[scenario.id] = self.createIntegrator(
self.assembler, integrator_options)
super(wedgeTACS, self).__init__(integrator_options, comm, tacs_comm,
model)
self.initialize(model.scenarios[0], model.bodies)
def __init__(self, comm, tacs_comm, model, n_tacs_procs):
super(wedgeTACS, self).__init__(comm, tacs_comm, model)
self.tacs_proc = False
if comm.Get_rank() < n_tacs_procs:
self.tacs_proc = True
#mesh = TACS.MeshLoader(tacs_comm)
#mesh.scanBDFFile("tacs_aero.bdf")
# Set constitutive properties
T_ref = 300.0
rho = 4540.0 # density, kg/m^3
E = 118e9 # elastic modulus, Pa
nu = 0.325 # poisson's ratio
ys = 1050e6 # yield stress, Pa
kappa = 6.89
specific_heat = 463.0
thickness = 0.015
volume = 25 # need tacs volume for TACSAverageTemperature function
# Create the constitutvie propertes and model
props_plate = constitutive.MaterialProperties(rho=4540.0,
specific_heat=463.0,
kappa=6.89,
E=118e9,
nu=0.325,
ys=1050e6)
#con_plate = constitutive.ShellConstitutive(props_plate,thickness,1,0.01,0.10)
#model_plate = elements.ThermoelasticPlateModel(con_plate)
con_plate = constitutive.PlaneStressConstitutive(props_plate,
t=1.0,
tNum=0)
model_plate = elements.HeatConduction2D(con_plate)
# Create the basis class
quad_basis = elements.LinearQuadBasis()
# Create the element
#element_shield = elements.Element2D(model_shield, quad_basis)
#element_insulation = elements.Element2D(model_insulation, quad_basis)
element_plate = elements.Element2D(model_plate, quad_basis)
varsPerNode = model_plate.getVarsPerNode()
# Load in the mesh
mesh = TACS.MeshLoader(tacs_comm)
mesh.scanBDFFile('tacs_aero.bdf')
# Set the element
mesh.setElement(0, element_plate)
# Create the assembler object
#varsPerNode = heat.getVarsPerNode()
assembler = mesh.createTACS(varsPerNode)
res = assembler.createVec()
ans = assembler.createVec()
mat = assembler.createSchurMat()
# Create distributed node vector from TACS Assembler object and
# extract the node locations
nbodies = 1
struct_X = []
struct_nnodes = []
for body in range(nbodies):
self.struct_X_vec = assembler.createNodeVec()
assembler.getNodes(self.struct_X_vec)
struct_X.append(self.struct_X_vec.getArray())
struct_nnodes.append(len(struct_X) / 3)
assembler.setNodes(self.struct_X_vec)
# Create the preconditioner for the corresponding matrix
pc = TACS.Pc(mat)
alpha = 1.0
beta = 0.0
gamma = 0.0
assembler.assembleJacobian(alpha, beta, gamma, res, mat)
pc.factor()
# Create GMRES object for structural adjoint solves
nrestart = 0 # number of restarts before giving up
m = 30 # size of Krylov subspace (max # of iterations)
gmres = TACS.KSM(mat, pc, m, nrestart)
# Initialize member variables pertaining to TACS
self.T_ref = T_ref
self.vol = volume
self.assembler = assembler
self.res = res
self.ans = ans
self.mat = mat
self.pc = pc
self.struct_X = struct_X
self.struct_nnodes = struct_nnodes
self.gmres = gmres
self.svsens = assembler.createVec()
self.struct_rhs_vec = assembler.createVec()
self.psi_T_S_vec = assembler.createVec()
psi_T_S = self.psi_T_S_vec.getArray()
self.psi_T_S = np.zeros((psi_T_S.size, self.nfunc),
dtype=TACS.dtype)
self.ans_array = []
self.svsenslist = []
self.dvsenslist = []
for func in range(self.nfunc):
self.svsenslist.append(self.assembler.createVec())
self.dvsenslist.append(self.assembler.createDesignVec())
for scenario in range(len(model.scenarios)):
self.ans_array.append(self.ans.getArray().copy())
self.initialize(model.scenarios[0], model.bodies)
if CHTMarkerID != None:
nVertex_CHTMarker = SU2Driver.GetNumberVertices(CHTMarkerID)
# get aero nodes
X = []
for i in range(nVertex_CHTMarker):
X.extend([
SU2Driver.GetVertexCoordX(CHTMarkerID, i),
SU2Driver.GetVertexCoordY(CHTMarkerID, i),
SU2Driver.GetVertexCoordZ(CHTMarkerID, i)
])
# initialize TACS
# Create the constitutvie propertes and model
props = constitutive.MaterialProperties()
con = constitutive.PlaneStressConstitutive(props)
heat = elements.HeatConduction2D(con)
# Create the basis class
quad_basis = elements.LinearQuadBasis()
# Create the element
element = elements.Element2D(heat, quad_basis)
# Load in the mesh
mesh = TACS.MeshLoader(comm)
mesh.scanBDFFile('plate_bump.bdf')
# Set the element
mesh.setElement(0, element)