Multidisciplinary Computation: Application to Fluid-Structure Interaction V. Selmin
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Transcript of Multidisciplinary Computation: Application to Fluid-Structure Interaction V. Selmin
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Multidisciplinary Computation: Application to Fluid-Structure Interaction
V. Selmin
Multidisciplinary Computation and Numerical Simulation
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Multidisciplinary Computation and Numerical Simulation
• Multidisciplinary optimisation process
Integration of different disciplines within the design process,Optimisation, Concurrent Engineering
Development of a new generation of numerical tools
New Trends in Design
Drivers: Reduce product development costs and time to market
• Single discipline optimisation process
From analysis/verification to design/optimisation
• From single to multi-physics
Integration of different disciplines, Interfaces between disciplines,Concurrent Engineering
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Multidisciplinary Computation
Fluid Structure Interaction: Process Overview
Aerodynamics/CFD
Structure/CSM
CFD Grid
Loads transfer
Displacements
Aero-structural Design Process
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Multidisciplinary Computation
Three field approach: basic formulation The coupled transient aeroelastic problem can then be formulated as a three-field problem:1- the fluid2- the structure3- the dynamic meshThe semi-discrete equations governing this tree-way coupled problem can be written as follows
are fictitious mass, damping and stiffness matrices
associated with the fluid moving grid.
is a transfer matrix that describes the action of the structural side of the fluid structure interface on the fluid dynamic mesh.
For example, includes a particular case of the spring based mesh motion scheme
xKxKx
Dx
M
xxfqfq
M
xxRxxxFxx
*t
**2
2*
int2
2
)),,(()(
,),,(,),,(),(),(
tt
tWt
tWtWtWtt
ext
structureonforcesexternalofvector:
forcesstructuralinternalofvector:
matrixstiffness:
matrixdamping:
matrixmass:
vectorntdisplaceme:
fluxesviscousofvector:
fluxesconvectiveofvector:
cellFVtheofvolume:
vectorstatefluid:
velocitypointgrid:
positionpointgrid:
ext
int
f
f
K
D
M
q
R
F
x
x
W
*** ,, KDM
0DM **
*tK
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Multidisciplinary Computation
Three field approach: basic formulation The fluid and mesh equations are directly coupled.The fluid and structure equations are coupled by the interface conditions on
The first transmission condition states that the tractions on the wet surface of the structure are in equilibrium with
those on the fluid side .The second condition expresses the compatibility between the velocity fields of the structure and the fluid at the fluid/structure interface.For inviscid flows, this second equation is replaced by the slip wall boundary condition
The equations governing the structure and fluid mesh motions are coupled by the continuity conditions
tt
-p
FS
FS
nΠnnΠ
SF
SF
S
F
S
F
p
/
/
tovectornormal:
boundaryinterfacestructurefluid:
tensorstressstructure:
tensorstressviscousfluid:
pressure:
ntdisplacemestructure:
fieldntdisplacemefluid:
n
Π
Π
q
q
ttMS
MS
nq
nq
ttFS
SF /
SF /
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Multidisciplinary Computation
Flow Solver for Moving Meshes Conservation law form:
Unknowns & Flux vector (Eulerian approach):
State equation:
Moving meshes (ALE approach):
0),()(
WWWt
WRF
qΠw
ΠRIww
w
Fw
-hw
p
e
W
t
T
t
0
,,
q
Π
ww
w
:fluxheat
:tensorstress
:ratioheats.spec
,2
:energyinternal
:enthalpytotal
:energytotal
:pressure
),,(:velocity
:densitymass
t
tt
t
ee
peh
e
p
wvu
)()1(
),(
gasperfectep
efp
WWWW xFxFF )(),()(x:velocitiesnode
ALE: Arbitrarian Lagrangian Eulerian
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Multidisciplinary Computation
Flow Solver for Moving Meshes Finite Volume DiscretisationDiscretisation of the integral equation:
Discrete equation:
Numerical flux:
Time integration:
0 iiddW
dt
d nR-F
n
n
i
ji
d
d
i
ij
nν
nν
)(),()(),(),,(
..),,,(),,()(
xνRxνxFνxx
νxxxx
ijijijijij
iKjiji
WWW,W
TBWW
0),,( xx WWdt
diii
0),,(11
dtWdtWdt
d n
n
n
n
t
t it
t ii xx
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Multidisciplinary Computation
Flow Solver for Moving Meshes Time IntegrationA second-order accurate time-accurate implicit algorithm that is popular in CFD is the second-order backward difference scheme.A generalisation of this algorithm for dynamic mesh can be written as:
where
and denote some linear combination of the mesh configurations and their velocities, i.e.
The following choice has been made for , denoted by , respectively,
0),,( 1111111 xx ni
nnni
nnni
nnni
n WtWWW
),(),( nnni
ni txxx
1
211 ,
1),1(,
1
21
n
nnnn
t
t
xx ,
1111 ,,,,, nnnnnn xxxxxxxxxx
xx , xx ~~ ,
n
nnnn
t
xx
xxx
x11 ~,
2~
0),,(11
dtWdtWdt
d n
n
n
n
t
t it
t ii xx
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Multidisciplinary Computation
Flow Solver for Moving Meshes GCL conditionA sufficient condition for the previous time integrator to be mathematically consistent is to predict exactly the state of a uniform flow. This condition whic can be formulated as a Geometric Conservation Law states that
This equation is satisfied only for versy special choice of which depends from the particular time integration scheme and type of grid elements adopted. A more versatile technique in order to satisfy the GCL condition consists in the computation of the defect
which is used to correct the coefficient .
Dual Time-Stepping ApproachThe basic idea of the dual time-stepping approach is to treat the unsteady problem as a steady state problem and to solve it as an artificial unsteady equation:
where
since the artificial time is used as a relaxation parameter to find the solution of the previously described steady problem. Special techniques in order to accelerate convergence are allowed.
0)()(
1111
iKjijij
nni
nni
nni
n t xνx
)(
1111 )~(~
iKjijij
nni
nni
nni
ni tGCL xνx
)~,~,(1
)( 11111111 xxR*
ni
nni
nnni
nnni
nn
WWWWt
W
0)(**
Wt
WR
xx ,
1n
*t
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Multidisciplinary Computation
Second Order Structural Solver The governing equation of linear dynamic equilibrium is
that can be rewritten as
where
Time-integration from to using midpoint trapezoidal rule reads
which is second order accurate in time. Note that the previous equations implies that
FqKq
Dq
M
tt 2
2
GQBQ
A t
F
0G
DK
1-0B
M0
01Aq
qQ ,,,
t
nt nnn ttt 1
2111
2/n
nn
n
nn
t
GQQ
BQQ
A
0qqqq
2
11 nn
n
nn
t
forcesexternalofvector:
matrixstiffness:
matrixdamping:
matrixmass:
vectorntdisplaceme:
F
K
D
M
q
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Multidisciplinary Computation
Second Order Time Accurate Staggered Procedure The second-order staggered (SOS) algorithm is built as a leap-frog scheme where the fluid sub-system is
computed at half time stations while the structure sub-system is computed at full
time stations . It can be summarised as follows
1- Predict the structural displacement at time
2- Update the position of the fluid grid in order to match the position that the structure whould have if it were
advanced the predicted displecement .
3- Time integrate the fluid subsystem from to using dual time stepping scheme and a fluid time step . If , sub-cycle the flow solver.
4- Transfer the fluid pressure and viscous stress tensor at time to the structure and compute the
corresponding induced structural loads .
5- Time integrate the structure sub-system from to by using the midpoint rule formula.
),t,t,( 2/1n2/1n
),t,t,( 1nn
2/1nt
t
t nnSnn
qqq
22/1
2/1nq
2/1nx
2/1nt nS
2/1n2/1n Δttt
SF ΔtΔt SF ΔtΔt 2/1nt
2/1nGnt n
Sn1n Δttt
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Multidisciplinary Computation
Transfer of Aerodynamics Loads to the Structure
• Reduced axis approach only valid for wings of high aspect ratios
• Interpolation from CFD solution to CSM grid not accurate for coarse structure representation
• Association to each structural skin elements of a portion of the CFD surface grid
complex but accurate
• Outside wing box contributions
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Multidisciplinary Computation
Transfer of Structure Deformation to the Fluid Mesh
• Reduced axis approach only valid for wings of high aspect ratios
• Interpolation from CSM grid to CFD grid association of each CFD surface node to a CSM
skin element
• Outside wing box nodes treatment
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Multidisciplinary Computation
Fluid Structure Interaction: Simulation Chain
Initial Data
CFD Computation
Loads Computation
CSM Computation
CFD Grid Update
Dt, iter.
End of Process
Displacements Computation
IntermediateSolutions
Steady approach
Unsteady approach
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Multidisciplinary Computation
Fluid Structure Interaction: Workflow
Input DataPreprocessing
Solid ModelGeometry
StructuralModels
MassData
ComputationParameters
StructureCSM
AirflowCharacteristics
Theoretical ModelCFD
AirflowCFD
CFD Grid Update
StructuralResponse
CFD Grid Update
F/S InteractionOutputs
Engine Data Set
Fluid Structure Interaction
DisplacementsUpdate
Task
Principal dependency
Actor
Data TransferInformation
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Multidisciplinary Computation
Fluid Structure Interaction: Dataflow
Airflow Simulation: CFD Simulation
CFDSolver
CFD Simulation
Inputs Outputs
SimulationProcess
Postprocessing
CFD Grid
CFD Computation Parameters
Grid Nodes Velocities
Grid Generation
Outputs
Pressure data
Stress Tensor Data
Inputs
Airflow Characteristics
Outputs
Grid Update
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Multidisciplinary Computation
Fluid Structure Interaction: Dataflow
Airflow Simulation: Grid Generation (CFD)
Surface gridGenerator
Grid Generation
Inputs Outputs
SimulationProcess
Volume GridGenerator
CAD Model
Grid Generation Parameters
Grid SpacingDescription
Element Connectivities
Nodes Co-ordinates
Inputs
CFD Simulation
Outputs
Solid ModelGeometry
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Multidisciplinary Computation
Fluid Structure Interaction: Dataflow
Airflow Simulation: Grid Update (CFD)
Grid Update
Inputs Outputs
SimulationProcess
Initial CFD Grid
Grid Update Parameters
Updated Body Surface Description
Grid Generation
Outputs
Element Connectivities
Nodes Coordinates
Inputs
CFD Simulation
Outputs
Displacements Update
Surface gridUpdate
Volume GridUpdate
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Multidisciplinary Computation
Fluid Structure Interaction: Dataflow
Airflow CharacteristicsAirflow
Characteristics
Inputs Outputs
SimulationProcess
Data Integration
Pressure Data
Stress Tensor
Theoretical/CFD Model
Outputs
Global Aerodynamic Coefficients
Aerodynamic Loadsat monitoring stations
Inputs
Monitoring StationsStructuralModels
Outputs
CFD grid Detailed flowfeatures
Structural Response
CFD to CSM gridsrelationships
OutputsData TransferInformation
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Multidisciplinary Computation
Fluid Structure Interaction: Dataflow
Structural Response
Structural Response
Inputs Outputs
SimulationProcess
CSM Solver
FE Model
Aerodynamic Loads
Material properties
Structure nodedisplacements
Stresses & strains
Inputs
Inertial Loads
StructuralModels
Outputs
DisplacementsUpdate
Additional Loads
Outputs
Airflow Characteristics
Outputs
Mass Data
Engine Data Set
Outputs
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Multidisciplinary Computation
Fluid Structure Integration: Dataflow
Displacements Update
DisplacementsUpdate
Inputs Outputs
SimulationProcess
Postprocessing
CFD grid
Structural nodes Displacements
CFD Surface nodesdisplacement
Inputs
CFD GridUpdate
CSM to CFD gridsrelationships
OutputsData TransferInformation
StructuralResponse
Outputs
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Multidisciplinary Computation
Aerodynamic Solver
• Node-centred based Finite Volume spatial discretisation• Blended second- and fourth order dissipation operators• Operates on structured, unstructured and hybrid grids• Time integration based on Multistage Algorithm (5 stages)• Residual averaging and local timestepping• Preconditioning for low Mach number• Pointwise Baldwin-Barth, K-Rt (EARSM) turbulence models• Chimera strategy implementation
• ALE implementation for moving grid• Time accurate simulation provided by using Dual Timestepping
• Scalar, vector and parallel implementation
RANS Solver
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Multidisciplinary Computation
Structural Analysis and Optimisation
Based essentially on MSC - NASTRAN software
• SOL101 for static analysis
• SOL200 for structural optimisation based on DOT optimiser (SQP)
• In the case of aeroelastic simulations, use of own software both for direct and modal formulations with extraction of the structural matrices from NASTRAN solutions.
FKutu
Dtu
M
2
2
Structural Solver
qu
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Multidisciplinary Computation
Grid Deformation
Spring Analogy
)x(x,0S)(
ijijijiiKjij KFF
Source terms allow to control mesh quality
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Multidisciplinary Computation
Fluid Structure Interaction
Steady Approach
Structural solver
Flow solver
)(wFKu
)()( wFwRt
w
0
Problem Definition
Process Initialisation
CFD Computation
Loads Computation
CSM Computation
CFD Grid Update
Residual Computation
Residual <Resmax ?
End of ProcessNo Yes
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Multidisciplinary Computation
Fluid Structure Interaction
Unsteady Approach
Structural solverFlow solver Coupling
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Multidisciplinary Computation
MSMS uuuu , Continuity Conditions
Mathematical Consistency (GCL)
Steady:
Unsteady
0 Cd
01111
C
mmmmmm dxt 11 mm
Metrics & Nodes Velocities
m
mmmm
t
xxx,
xxx):xR(w,x,
11
2
21nm
21ntn
nnn u
tuu
221
21nx 21nu21nt nnn ttt 2121
21nt 21nGnt nnn ttt 1
SOS Coupling Procedure1- Predict the structural displacement at time
2- Update the position of the fluid grid in order to match
3- Time-integrate the fluid subsystem from to
4- Transfer the fluid stresses at time to the structure and compute
5- Time-integrate the structure sub-system from to using the mid-point rule formula
Fluid Structure Interaction
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Multidisciplinary Computation
Fluid Structure Interaction
SMJ Configuration
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Multidisciplinary Computation
Fluid Structure Interaction
SMJ Test-Case
FE Structural ModelCFD Model
Static cases: Cruise, pull-up manoeuvre & push-down manoeuvreDynamic cases: unstable, marginally stable & stable conditions.
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Multidisciplinary Computation
Static Aeroelasticity
Aeroelastic Simulation: M=0.8, Nz=1, Z=11277 m
M=0.8 , Cl=0.45
Jig Shape Deformed Shape
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Multidisciplinary Computation
Static Aeroelasticity
Aeroelastic Simulation: M=0.8, Nz=1, Z=11277 m
Wing Box Deformation
Von Mises Stresses
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Multidisciplinary Computation
Static Aeroelasticity
Aeroelastic Simulation: M=0.6, Nz=2.5, Z=4500 m
M=0.6 , Cl=0.75
Jig Shape Deformed Shape
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Multidisciplinary Computation
Static Aeroelasticity
Aeroelastic Simulation: M=0.6, Nz=-1, Z=4500 m
M=0.6 , Cl=-0.30
Jig Shape Deformed Shape
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Multidisciplinary Computation
Dynamic Aeroelasticity
SMJ Modal Shapes
Mode 1 (2.01 Hz) Mode 2 (2.82 Hz) Mode 3 (3.70 Hz)
Mode 4 (5.26 Hz) Mode 5 (5.73 Hz) Mode 6 (7.38 Hz)
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Multidisciplinary Computation
Dynamic Aeroelasticity
V-G & V-F Diagrams
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Multidisciplinary Computation
Dynamic AeroelasticityAeroelastic Simulation: M=0.83, z=11300 m
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Multidisciplinary Computation
Dynamic AeroelasticityAeroelastic Simulation: M=0.83, z=11300 m
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Multidisciplinary Computation
Dynamic AeroelasticityAeroelastic Simulation: M=0.83, z=7000 m
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Multidisciplinary Computation
Dynamic Aeroelasticity
Aeroelastic Simulation: M=0.83, z=7000 m
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Multidisciplinary Computation
Flexible Aircraft Motion Equations
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Multidisciplinary Computation
Fluid Structure Interaction
Methods• Linear methods are non conservative for transonic flows (nonlinear effects)• Time dependent methods are too expensive to be used for day to day design work
Validation Need for dedicated and accurate experimental data sets (much more expensive & difficult to obtain than for a single discipline)
• Correction of linear models• Linearised in time/frequency Euler & Navier-Stokes solvers• Reduced order models
Interfaces & CouplingIn the past, God invented the partial differential equations. He was very proud of him. Then, the devil introduced the boundary conditions. Today, the technology can be considered to be mature when referred to single disciplines.For the solution of multidisciplinary problems, the devil is now represented by the interfaces.
Jacques-Louis Lions