def Solve_Py(XBINPUT,XBOPTS):
"""Nonlinear static solver using Python to solve residual
equation. Assembly of matrices is carried out with Fortran subroutines."""
"Check correct solution code"
assert XBOPTS.Solution.value == 112, ('NonlinearStatic requested' +\
' with wrong solution code')
"Initialise beam"
XBINPUT, XBOPTS, NumNodes_tot, XBELEM, PosIni, PsiIni, XBNODE, NumDof \
= BeamInit.Static(XBINPUT,XBOPTS)
"Set initial conditions as undef config"
PosDefor = PosIni.copy(order='F')
PsiDefor = PsiIni.copy(order='F')
if XBOPTS.PrintInfo.value==True:
sys.stdout.write('Solve nonlinear static case in Python ... \n')
"Initialise structural eqn tensors"
KglobalFull = np.zeros((NumDof.value,NumDof.value),\
ct.c_double, 'F'); ks = ct.c_int()
FglobalFull = np.zeros((NumDof.value,NumDof.value),\
ct.c_double, 'F'); fs = ct.c_int()
DeltaS = np.zeros(NumDof.value, ct.c_double, 'F')
Qglobal = np.zeros(NumDof.value, ct.c_double, 'F')
x = np.zeros(NumDof.value, ct.c_double, 'F')
dxdt = np.zeros(NumDof.value, ct.c_double, 'F')
"Load Step tensors"
iForceStep = np.zeros((NumNodes_tot.value,6), ct.c_double, 'F')
iForceStep_Dof = np.zeros(NumDof.value, ct.c_double, 'F')
"Start Load Loop"
for iLoadStep in range(XBOPTS.NumLoadSteps.value):
"Reset convergence parameters"
Iter = 0
ResLog10 = 0.0
iForceStep = XBINPUT.ForceStatic*float( (iLoadStep+1) / \
XBOPTS.NumLoadSteps.value)
if XBOPTS.PrintInfo.value == True:
sys.stdout.write(' iLoad: %-10d\n' %(iLoadStep+1))
sys.stdout.write(' SubIter DeltaF DeltaX ResLog10\n')
"Newton Iteration"
while( (ResLog10 > np.log10(XBOPTS.MinDelta.value)) \
& (Iter < XBOPTS.MaxIterations.value) ):
"Increment iteration counter"
Iter += 1
if XBOPTS.PrintInfo.value == True:
sys.stdout.write(' %-7d ' %(Iter))
"Set structural eqn tensors to zero"
KglobalFull[:,:] = 0.0; ks = ct.c_int()
FglobalFull[:,:] = 0.0; fs = ct.c_int()
Qglobal[:] = 0.0
"Assemble matrices for static problem"
BeamLib.Cbeam3_Asbly_Static(XBINPUT, NumNodes_tot, XBELEM, XBNODE,\
PosIni, PsiIni, PosDefor, PsiDefor,\
iForceStep, NumDof,\
ks, KglobalFull, fs, FglobalFull, Qglobal,\
XBOPTS)
"Get state vector from current deformation"
PosDot = np.zeros((NumNodes_tot.value,3), ct.c_double, 'F') #R
PsiDot = np.zeros((XBINPUT.NumElems,Settings.MaxElNod,3),\
ct.c_double, 'F') #Psi
BeamLib.Cbeam_Solv_Disp2State(NumNodes_tot, NumDof, XBINPUT, XBNODE,\
PosDefor, PsiDefor, PosDot, PsiDot,
x, dxdt)
"Get forces on unconstrained nodes"
BeamLib.f_fem_m2v(ct.byref(NumNodes_tot),\
ct.byref(ct.c_int(6)),\
iForceStep.ctypes.data_as(ct.POINTER(ct.c_double)),\
ct.byref(NumDof),\
iForceStep_Dof.ctypes.data_as(ct.POINTER(ct.c_double)),\
XBNODE.Vdof.ctypes.data_as(ct.POINTER(ct.c_int)) )
"Calculate \Delta RHS"
Qglobal = Qglobal - np.dot(FglobalFull, iForceStep_Dof)
"Calculate \Delta State Vector"
DeltaS = - np.dot(np.linalg.inv(KglobalFull), Qglobal)
if XBOPTS.PrintInfo.value == True:
sys.stdout.write('%-10.4e %-10.4e ' \
% (max(abs(Qglobal)),max(abs(DeltaS))))
"Update Solution"
BeamLib.Cbeam3_Solv_Update_Static(XBINPUT, NumNodes_tot, XBELEM,\
XBNODE, NumDof, DeltaS,\
PosIni, PsiIni, PosDefor,PsiDefor)
"Residual at first iteration"
if(Iter == 1):
Res0_Qglobal = max(abs(Qglobal)) + 1.e-16
Res0_DeltaX = max(abs(DeltaS)) + 1.e-16
"Update residual and compute log10"
Res_Qglobal = max(abs(Qglobal)) + 1.e-16
Res_DeltaX = max(abs(DeltaS)) + 1.e-16
ResLog10 = max([np.log10(Res_Qglobal/Res0_Qglobal), \
np.log10(Res_DeltaX/Res0_DeltaX)])
if XBOPTS.PrintInfo.value == True:
sys.stdout.write('%8.4f\n' %(ResLog10))
"Stop the solution"
if(ResLog10 > 10.):
sys.stderr.write(' STOP\n')
sys.stderr.write(' The max residual is %e\n' %(ResLog10))
exit(1)
"END Newton Loop"
"END Load Loop"
if XBOPTS.PrintInfo.value==True:
sys.stdout.write(' ... done\n')
"Write deformed configuration to file"
ofile = Settings.OutputDir + Settings.OutputFileRoot + '_SOL112_def.dat'
if XBOPTS.PrintInfo.value==True:
sys.stdout.write('Writing file %s ... ' %(ofile))
fp = open(ofile,'w')
fp.write('TITLE="Non-linear static solution: deformed geometry"\n')
fp.write('VARIABLES="iElem" "iNode" "Px" "Py" "Pz" "Rx" "Ry" "Rz"\n')
fp.close()
if XBOPTS.PrintInfo.value==True:
sys.stdout.write('done\n')
WriteMode = 'a'
BeamIO.OutputElems(XBINPUT.NumElems, NumNodes_tot.value, XBELEM, \
PosDefor, PsiDefor, ofile, WriteMode)
"Print deformed configuration"
if XBOPTS.PrintInfo.value==True:
sys.stdout.write('--------------------------------------\n')
sys.stdout.write('NONLINEAR STATIC SOLUTION\n')
sys.stdout.write('%10s %10s %10s\n' %('X','Y','Z'))
for inodi in range(NumNodes_tot.value):
sys.stdout.write(' ')
for inodj in range(3):
sys.stdout.write('%12.5e' %(PosDefor[inodi,inodj]))
sys.stdout.write('\n')
sys.stdout.write('--------------------------------------\n')
"Return solution as optional output argument"
return PosDefor, PsiDefor
def Solve_Py(XBINPUT,XBOPTS,VMOPTS,VMINPUT,AELAOPTS):
"""Nonlinear static solver using Python to solve aeroelastic
equation. Assembly of structural matrices is carried out with
Fortran subroutines. Aerodynamics solved using PyAero.UVLM."""
assert XBOPTS.Solution.value == 112, ('NonlinearStatic requested' +
' with wrong solution code')
# Initialize beam.
XBINPUT, XBOPTS, NumNodes_tot, XBELEM, PosIni, PsiIni, XBNODE, NumDof \
= BeamInit.Static(XBINPUT,XBOPTS)
# Set initial conditions as undef config.
PosDefor = PosIni.copy(order='F')
PsiDefor = PsiIni.copy(order='F')
if XBOPTS.PrintInfo.value==True:
sys.stdout.write('Solve nonlinear static case in Python ... \n')
# Initialise structural eqn tensors.
KglobalFull = np.zeros((NumDof.value,NumDof.value),
ct.c_double, 'F'); ks = ct.c_int()
FglobalFull = np.zeros((NumDof.value,NumDof.value),
ct.c_double, 'F'); fs = ct.c_int()
DeltaS = np.zeros(NumDof.value, ct.c_double, 'F')
Qglobal = np.zeros(NumDof.value, ct.c_double, 'F')
x = np.zeros(NumDof.value, ct.c_double, 'F')
dxdt = np.zeros(NumDof.value, ct.c_double, 'F')
# Beam Load Step tensors
iForceStep = np.zeros((NumNodes_tot.value,6), ct.c_double, 'F')
iForceStep_Dof = np.zeros(NumDof.value, ct.c_double, 'F')
# Initialze Aero.
Section = InitSection(VMOPTS,VMINPUT,AELAOPTS.ElasticAxis)
# Declare memory for Aero grid and velocities.
Zeta = np.zeros((Section.shape[0],PosDefor.shape[0],3),ct.c_double,'C')
ZetaDot = np.zeros((Section.shape[0],PosDefor.shape[0],3),ct.c_double,'C')
# Additional Aero solver variables.
AeroForces = np.zeros((VMOPTS.M.value+1,VMOPTS.N.value+1,3),ct.c_double,'C')
Gamma = np.zeros((VMOPTS.M.value,VMOPTS.N.value),ct.c_double,'C')
# Init external velocities.
Uext = InitSteadyExternalVels(VMOPTS,VMINPUT)
# Create zero triads for motion of reference frame.
VelA_A = np.zeros((3))
OmegaA_A = np.zeros((3))
# Create zero vectors for structural vars not used in static analysis.
PosDotDef = np.zeros_like(PosDefor, ct.c_double, 'F')
PsiDotDef = np.zeros_like(PsiDefor, ct.c_double, 'F')
# Define tecplot stuff.
FileName = Settings.OutputDir + Settings.OutputFileRoot + 'AeroGrid.dat'
Variables = ['X', 'Y', 'Z','Gamma']
FileObject = PostProcess.WriteAeroTecHeader(FileName,
'Default',
Variables)
# Start Load Loop.
for iLoadStep in range(XBOPTS.NumLoadSteps.value):
# Reset convergence parameters and loads.
Iter = 0
ResLog10 = 0.0
XBINPUT.ForceStatic[:,:] = 0.0
AeroForces[:,:,:] = 0.0
# Calculate aero loads.
if hasattr(XBINPUT, 'ForcedVel'):
CoincidentGrid(PosDefor,
PsiDefor,
Section,
XBINPUT.ForcedVel[0,:3],
XBINPUT.ForcedVel[0,3:],
PosDotDef,
PsiDotDef,
XBINPUT,
Zeta,
ZetaDot,
ctrlSurf = VMINPUT.ctrlSurf)
else:
CoincidentGrid(PosDefor, PsiDefor, Section, VelA_A,
OmegaA_A, PosDotDef, PsiDotDef, XBINPUT,
Zeta, ZetaDot,
ctrlSurf = VMINPUT.ctrlSurf)
if hasattr(XBINPUT,'ForcedVel'):
ZetaStar, GammaStar = InitSteadyWake(VMOPTS,VMINPUT,Zeta,XBINPUT.ForcedVel[0,:3])
else:
ZetaStar, GammaStar = InitSteadyWake(VMOPTS,VMINPUT,Zeta)
# Solve for AeroForces.
UVLMLib.Cpp_Solver_VLM(Zeta, ZetaDot, Uext, ZetaStar, VMOPTS,
AeroForces, Gamma, GammaStar)
AeroForces[:,:,:] = AELAOPTS.AirDensity*AeroForces[:,:,:]
# Write solution to tecplot file.
PostProcess.WriteUVLMtoTec(FileObject,
Zeta,
ZetaStar,
Gamma,
GammaStar,
iLoadStep,
XBOPTS.NumLoadSteps.value,
iLoadStep*1.0,
Text = True)
# Map AeroForces to beam.
CoincidentGridForce(XBINPUT, PsiDefor, Section, AeroForces,
XBINPUT.ForceStatic)
# Add gravity loads.
AddGravityLoads(XBINPUT.ForceStatic,XBINPUT,XBELEM,AELAOPTS,
PsiDefor,VMINPUT.c)
# Apply factor corresponding to force step.
iForceStep = XBINPUT.ForceStatic*float( (iLoadStep+1) ) / \
XBOPTS.NumLoadSteps.value
if XBOPTS.PrintInfo.value == True:
sys.stdout.write(' iLoad: %-10d\n' %(iLoadStep+1))
sys.stdout.write(' SubIter DeltaF DeltaX ResLog10\n')
# Start Newton Iteration.
while( (ResLog10 > np.log10(XBOPTS.MinDelta.value))
& (Iter < XBOPTS.MaxIterations.value) ):
Iter += 1
if XBOPTS.PrintInfo.value == True:
sys.stdout.write(' %-7d ' %(Iter))
# Set structural eqn tensors to zero
KglobalFull[:,:] = 0.0; ks = ct.c_int()
FglobalFull[:,:] = 0.0; fs = ct.c_int()
Qglobal[:] = 0.0
# Assemble matrices for static problem
BeamLib.Cbeam3_Asbly_Static(XBINPUT,
NumNodes_tot,
XBELEM,
XBNODE,
PosIni,
PsiIni,
PosDefor,
PsiDefor,
iForceStep,
NumDof,
ks,
KglobalFull,
fs,
FglobalFull,
Qglobal,
XBOPTS)
# Get state vector from current deformation.
PosDot = np.zeros((NumNodes_tot.value,3), ct.c_double, 'F')
PsiDot = np.zeros((XBINPUT.NumElems,Settings.MaxElNod,3),
ct.c_double, 'F')
BeamLib.Cbeam_Solv_Disp2State(NumNodes_tot,
NumDof,
XBINPUT,
XBNODE,
PosDefor,
PsiDefor,
PosDot,
PsiDot,
x,
dxdt)
# Get forces on unconstrained nodes.
BeamLib.f_fem_m2v(ct.byref(NumNodes_tot),
ct.byref(ct.c_int(6)),
iForceStep.ctypes.data_as(ct.POINTER(ct.c_double)),
ct.byref(NumDof),
iForceStep_Dof.ctypes.data_as(ct.POINTER(ct.c_double)),
XBNODE.Vdof.ctypes.data_as(ct.POINTER(ct.c_int)) )
# Calculate \Delta RHS.
Qglobal = Qglobal - np.dot(FglobalFull, iForceStep_Dof)
# Calculate \Delta State Vector.
DeltaS = - np.dot(np.linalg.inv(KglobalFull), Qglobal)
if XBOPTS.PrintInfo.value == True:
sys.stdout.write('%-10.4e %-10.4e '
% (max(abs(Qglobal)),max(abs(DeltaS))))
# Update Solution.
BeamLib.Cbeam3_Solv_Update_Static(XBINPUT,
NumNodes_tot,
XBELEM,
XBNODE,
NumDof,
DeltaS,
PosIni,
PsiIni,
PosDefor,
PsiDefor)
# Record residual at first iteration.
if(Iter == 1):
Res0_Qglobal = max(abs(Qglobal)) + 1.e-16
Res0_DeltaX = max(abs(DeltaS)) + 1.e-16
# Update residual and compute log10
Res_Qglobal = max(abs(Qglobal)) + 1.e-16
Res_DeltaX = max(abs(DeltaS)) + 1.e-16
ResLog10 = max([np.log10(Res_Qglobal/Res0_Qglobal),
np.log10(Res_DeltaX/Res0_DeltaX)] )
if XBOPTS.PrintInfo.value == True:
sys.stdout.write('%8.4f\n' %(ResLog10))
# Stop the solution.
if(ResLog10 > 10.):
sys.stderr.write(' STOP\n')
sys.stderr.write(' The max residual is %e\n' %(ResLog10))
exit(1)
elif Res_DeltaX < 1.e-14:
break
# END Newton iteration
# END Load step loop
if XBOPTS.PrintInfo.value==True:
sys.stdout.write(' ... done\n')
# Write deformed configuration to file.
ofile = Settings.OutputDir + Settings.OutputFileRoot + '_SOL112_def.dat'
if XBOPTS.PrintInfo.value==True:
sys.stdout.write('Writing file %s ... ' %(ofile))
fp = open(ofile,'w')
fp.write('TITLE="Non-linear static solution: deformed geometry"\n')
fp.write('VARIABLES="iElem" "iNode" "Px" "Py" "Pz" "Rx" "Ry" "Rz"\n')
fp.close()
if XBOPTS.PrintInfo.value==True:
sys.stdout.write('done\n')
WriteMode = 'a'
BeamIO.OutputElems(XBINPUT.NumElems, NumNodes_tot.value, XBELEM,
PosDefor, PsiDefor, ofile, WriteMode)
# Print deformed configuration.
if XBOPTS.PrintInfo.value==True:
sys.stdout.write('--------------------------------------\n')
sys.stdout.write('NONLINEAR STATIC SOLUTION\n')
sys.stdout.write('%10s %10s %10s\n' %('X','Y','Z'))
for inodi in range(NumNodes_tot.value):
sys.stdout.write(' ')
for inodj in range(3):
sys.stdout.write('%12.5e' %(PosDefor[inodi,inodj]))
sys.stdout.write('\n')
sys.stdout.write('--------------------------------------\n')
# Close Tecplot ascii FileObject.
PostProcess.CloseAeroTecFile(FileObject)
# Return solution
return PosDefor, PsiDefor, Zeta, ZetaStar, Gamma, GammaStar, iForceStep
