Modeling in the Healthcare Industry: A Collaborative Approach
MULTIFUNCTIONAL COLLABORATIVE MODELING …...MULTIFUNCTIONAL COLLABORATIVE MODELING AND ANALYSIS...
Transcript of MULTIFUNCTIONAL COLLABORATIVE MODELING …...MULTIFUNCTIONAL COLLABORATIVE MODELING AND ANALYSIS...
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MULTIFUNCTIONAL COLLABORATIVEMODELING AND ANALYSIS METHODS IN
ENGINEERING SCIENCE
Jonathan B. RansomNASA Langley Research Center
Mail Stop 240, Hampton, VA [email protected]
FEMCI Workshop 2001Innovative FEM Solutions to Challenging Problems
May 16-17, 2001
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CONVENTIONAL MODELING AND ANALYSISOF COMPLEX SYSTEMS
• Multi-fidelity FE Modeling• Requires months to model• Changes expensive, time consuming and error prone• Model often tied to discipline
Multifunctional Collaborative Methodology
• Multi-fidelity• Multiple Methods• Multiple Disciplines
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OBJECTIVES
• Present general methodology providingcapability for multifunctional modeling,analysis and solution
• Identify computational aspects and relatedalgorithmic issues for this methodology
• Demonstrate the formulation to scalar- andvector-field applications in engineeringscience
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KEY TERMINOLOGY• Multifunctional - Computational methodologies for
rapid, robust solutions featuring multi-fidelity modelingand multiple methods
• Collaborative - Mechanism by which two or morephysical domains or methods are integrated/interfaced
• Engineering science - Broad spectrum of engineering(science, mathematics, numerical analysis)
• Homogeneous modeling - Same spatial modelingapproach among subdomains
• Heterogeneous modeling - Different spatial modelingapproaches among subdomains
Example - Previous interface technology demonstratedcollaborative method for homogeneous FE modelingapplied to solid mechanics
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MULTIFUNCTIONAL METHODOLOGY
Multifunctional Methods Concept and General Formulation
Multiple MethodInterfacing
Non-FEM ModelInterfacing
FEM ModelInterfacing
Multiple DisciplineInterfacing
Homogeneous Modeling Heterogeneous Modeling
Structures
Materials
Electromagnetics
Acoustics
Aerodynamics Flight Systems
? ? ? ?
? ?? ? ? ?
Finite elementmodeling
Finite differencemodeling
? ?
? ?
Boundary elementmodeling
Capability which Enables the Synthesis of Diverse Models
Multi-fidelity
Multiple-domain
Multiple methods
Multiple disciplines
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OUTLINE
• Multifunctional Formulation– Basic assumption– Method of weighted residuals for MFC approach– Collaborative interface treatment– General system of equations
• Selected Applications
• Concluding Remarks
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? ? ? ?
? ?? ? ? ?
Pseudo-nodes
CollaborativeInterface
Finite elementmodeling
Finite differencemodeling
? ?
? ?
Boundary elementmodeling
MULTIFUNCTIONAL FORMULATION-BASIC ASSUMPTION-
Deformation, v, along the interface connecting thesubstructures, ? i, may be expressed as:
where:
• T is an interpolation matrix formed using cubic splines
• qI is a vector of interface degrees of freedom
v = TqI
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MULTIFUNCTIONAL FORMULATION- METHOD OF WEIGHTED RESIDUALS -
Define: ? ? 0I
ps
1cc
1???? ??
??
N
i
N
mm
ii
ssRRRR
3t̂2t̂
? ?
? ?
? ?
? ?? ? ? ?
Vu1
u2
u3
1t̂ ? ?
where the orthogonalized residuals associated with:
0RFR ??? ??
mmmmm
dGoverning equation within the domain
? ? 0uv?R ???? ? ?? ?
I1
c dI
p
i
i
n
jjij
Compatibility constraint for primary variableon interface boundary
Compatibility constraint for secondary variableon interface boundary
0t?R ??? ? ?? ?
I1
c dˆˆI
s
i
i
n
jji
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MULTIFUNCTIONAL FORMULATION- COLLABORATIVE INTERFACE TREATMENT -
substituted into:
0d ??? ??
mmmmm
RFR
? ? 0d I1 I
p ???? ? ?? ?
i
i
n
jjijc uv?R
0dˆˆI
1 I
s ??? ? ?? ?
i
i
n
jjic t?R
Assume for each interface i:
jjijjjijjj S?T?aStTqvqNu ????? and,ˆ ˆ,, I
? ?
? ?
? ?? ?
? ?? ? ? ?
V1q
Iq 3q
2q
3t̂
2t̂
1t̂
mm NF ?FE domains:
FD domains : ? ? ? ?llllm yxyyxx ,, ?? ????F
For weight functions:
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MULTIFUNCTIONAL FORMULATION- GENERAL SYSTEM OF EQUATIONS -
General matrix form for multifunctional collaborative approach
For scalar-fields
??
??
?
??
??
??
??
??
?
??
??
?
???
?
?
???
?
?
00f
aqq
0KKK00K0K
ITIp
I
s
• Sparse
• Non-positive definite
• May be unsymmetric
Matrix characteristics:
? ?
? ?
? ? ? ?
? ?? ? ? ?
V1q
Iq 3q
2q
For vector-fields
where are dependent on fluid mechanics formulation and is discipline-specific
aKKK ,,, TIpsu
??
??
?
??
??
??
??
??
?
??
??
?
???
?
?
???
?
??
??
??
?
??
??
?
???
?
?
???
?
?
00f
aqq
0KKK00K0K
aqq
00000000M
ITIp
I
s
I
..
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• Patch Test Example Problems
• Torsion of Prismatic Bar
• Heat Conduction Problem
• Potential Flow Problem
• Plane Stress Problem
• Plane Flow Problem
• Boeing Crown Panel
• Douglas Stub-Box
APPLICATIONS
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HEAT CONDUCTION PROBLEM
x
y
1.0
T=0
T=00?
??
xT
0???
yT
1.0
Square Plate
x
y Interface
0.00
0.05
0.10
0.15
0.20
0.25
0.30
0.35
0.0 0.2 0.4 0.6 0.8 1.0x
kT(x,0)Q
Analytical SolutionRitz Approx.MD/FE- C/CMD/FE -F/FMD/FE - C/FMD/FE - F/C
Interface
FE/FE Modeling
0.00
0.05
0.10
0.15
0.20
0.25
0.30
0.35
0.0 0.2 0.4 0.6 0.8 1.0x
kT(x,0)Q Analytical Solution
Ritz Approx.MD/FD- F/FMD/FD -C/FMD/FD - F/C
Interface
FD/FD Modeling
0.00
0.05
0.10
0.15
0.20
0.25
0.30
0.35
0.0 0.2 0.4 0.6 0.8 1.0x
kT(x,0)Q
Analytical SolutionRitz Approx.MD/HM- F/FMD/HM -C/FMD/HM - F/C
Interface
FD/FE Modeling
0.0 0.2 0.4 0.6 0.8 1.0x
0.35
0.30
0.25
0.20
0.15
0.10
0.05
0.00
kT(x,0)Q
0.0 0.2 0.4 0.6 0.8 1.0x
0.35
0.30
0.25
0.20
0.15
0.10
0.05
0.00
kT(x,0)Q
0.0 0.2 0.4 0.6 0.8 1.0x
0.35
0.30
0.25
0.20
0.15
0.10
0.05
0.00
kT(x,0)Q
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PLANE STRESS PROBLEM
2a
2b? ?0xN ? ? ? ? hN xx 00 ??
x
yr
?
R0
0
0
?
?
t
n
T
T
a
b
0?? tn TT
0?u
x
y
0?v
? ?0
0
?
??
t
xn
T
T ?
r
A B
D
C
Two Configurations:Infinite plate:2a/R0 = 402b/R0 = 20
Finite-width plate:2a/R0 = 42b/R0 = 2
Plate with Central Cutout
E=10,000 ksi?=0.3h=0.1 in.
Geometric Configuration
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-1.5
-1.0
-0.5
0.0
0.5
1.0
1.5
2.0
2.5
3.0
3.5
0.0 0.5 1.0 1.5 2.0 2.5 3.0 3.5 4.0
r/R 0
N θ
(N x) nom
AnalyticalMultiple-Domain(FD/FE)Multiple-Domain(FE/FE)
Edge ofCutout
Interface
STRESS RESULTANT DISTRIBUTIONFOR FINITE-WIDTH PLATE
? ? ? ? hN nomxnomx ??? ? ???
??? ????
bR
bhhRbAnet0
0 1222 ; ? ?net
nomx AP
?? ;
Interface
Spatial Modeling
Alongline AB
Alongline CD
A B
C
D
A B
C
D
Stress Resultant Contours
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COLLABORATIVE METHODOLOGY DEMONSTRATED ONBOEING CROWN PANEL
Hat StiffenerGapJ-Frame
Mouse Hole Area
Crown Panel Geometry
68 in.
64 in.
Radius = 122 in.
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COLLABORATIVE METHODOLOGY DEMONSTRATED ONBOEING CROWN PANEL
Mouse Hole Area
Gap Combined Finite Element ModelNested Finite Element Models
Deformation Contour Hoop Stress Contour
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Deformed Shape
Nonlinearly Deformed Unstiffened BayAccess Door Cutout
Tipload(kips)
x
Gages C/D
C
D
20000-2000-4000-6000-80000
40
80
120
160
Gage CGage D
Gage CGage D
Axial Strain (microstrains)
Test
Analysis
xx
Gage A
Tipload(kips)
20000-2000-4000-6000-80000
40
80
120
160
Gage AGage B
Gage AGage B
Circumferential Strain (microstrains)
Test
Analysis
Gage BGage A
xx
Gage A
xx
Failureline
Local Modelof NonlinearRegion
APPLICATION OF COLLABORATIVE METHODOLOGY IN NONLINEAR ANALYSIS OF WING STUB BOX
Tip load
Extension structure
Compositewing stub box
Hydraulicjack
Experimental Setup
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SUMMARY
• Results presented for patch test, scalar-field, and vector-field problems
• Results for all problems and multifunctionalapproaches in overall good agreement
• Finite element solutions more accurate thanfinite difference solutions for discretizationsconsidered
• Results with heterogeneous modeling notas accurate as homogeneous modeling
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CONCLUSIONS
• Multifunctional collaborative methodologiesand analysis procedures formulated and placedon solid mathematical foundation– Scalar-field and vector-field problems– Homogeneous and heterogeneous modeling
• Collaborative role of modeling approaches hasbeen illustrated
• Capabilities demonstrated on benchmarkproblems and large scale applications
• Computational challenges overcome
• Application of FD method limits general use