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Total Analysis Solution for Multi-disciplinary Optimum Design
Composite Materials in midas NFX
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Cyprien Rusu
midas NFX international
technical manager
Matteo Vettori
FEA Consultant
e-FEM, Italy
Intro_NFX(왕복선).avi
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1. Introduction to Composite Material in midas NFX – Matteo Vettori, e-FEM srl
2. Analysis Workflow and setup of Composite material Analysis Model – Cyprien Rusu
3. Project Applications using composite Materials with midas NFX – Matteo Vettori, e-FEM srl
4. Summary and Conclusion
2 0 1 3 midas NFX
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Starting from Wikipedia …
Composite materials are materials made from two or more constituent materials with significantly different physical or chemical properties, that when combined, produce a material with better characteristics different from the individual components. The individual components remain separate and distinct within the finished structure. The new material may be preferred for many reasons: common examples include materials which are stronger, lighter or less expensive when compared to traditional materials.
Composite Analysis in midas NFX 01
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Particle Composites
Short Fibers Composites
Long (Continuous) Fibers Composites
laminateted Composites
Composite Analysis in midas NFX 01
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Composite Analysis in midas NFX 01
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Big structures Components Meso-scale Micro-scale
Magnification dimensions
Composite Analysis in midas NFX 01
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PROs …. • Lightweight • High stiffness • High resistance
CONs … • Cost • Complexity
Composites
Aluminium alloys
Composite Analysis in midas NFX 01
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The real strength of composite materials is …
INFINITE POSSIBILITY OF OPTIMISATION & CUSTOMISATION
«TAILOR – ABILITY»
Composite Analysis in midas NFX 01
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ISOTROPIC MATERIAL 2 CONSTANTs ANISOTROPIC MATERIAL 21 CONSTANTs Single laminate ? Directional properties are orthogonals 9 CONSTANTs
Composite Analysis in midas NFX 01
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Symmetry conditions
Generic expression …
Composite Analysis in midas NFX 01
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Assuming Through-the-thickness simplification Plane Strain (s3, t13 , t23 = 0)
Stiffness Matrix
Compliance Matrix
Composite Analysis in midas NFX 01
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laminate properties can be described along specified directions transforming from the Material Reference System to a global Ref.Sys.
Material Ref.Sys. Generic Ref.Sys.
Composite Analysis in midas NFX 01
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In the off-axis reference system, direct stress (s) and tangential deformations (g) are coupled together. A tensile stress results also in a distortion of the laminate
Coupling terms
Composite Analysis in midas NFX 01
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Orientation angle
Q11 , Q22
Q12 , Q13 , Q23 , Q33
45° 30° 60°
@ 45° …….. A longitudinal load generates the maximum transversal load
@ 30/60° .. A longitudinal load generates the maximum distortions
Composite Analysis in midas NFX 01
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1
Y
Z
X q
How to consider a laminatete ?
Classical laminatetion Theory Hipothesis ….
i. laminates are perfectly bonded, shear stresses are rigidly transferred between laminates
ii. A generical through-the-thickness section of the laminatete deforms remaining perpendicular to the laminatete midplane (Kirchoff-Love)
i. Displacements and deformations are continuous through interlaminater interfaces
ii. Shear deformability can be neglected (theory of shells)
Then ….
Composite Analysis in midas NFX 01
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xyxyxy kz 0
Composite Analysis in midas NFX 01
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Composite Analysis in midas NFX 01
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where
Composite Analysis in midas NFX 01
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A B
D
Direct stresses
Coupling terms
Flexural stresses
Composite Analysis in midas NFX 01
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A Orthotropic material
Cross-ply Lay-up Balanced
B Non-symmetrical lay-up
D Orthotropic material
Cross-ply Lay-up Anti-symmetrical lay-up
Composite Analysis in midas NFX 01
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q3 q2 q1 q1 q2 q3
q3 q2 q1 -q1 -q2 -q3
-q3 q3 q2 -q1 -q2 q1
[q3/q2/q1]s
[q3/q2/q1]Q
[-q3/q3/q2 /-q1/-q2/q1]
Homogeneous / Orthotropic Material / symmetrical lay-up
Homogeneous / Orthotropic Material / ANTI - symmetrical lay-up
Homogeneous / Orthotropic Material / BALANCED lay-up / NON-symmetrical
Composite Analysis in midas NFX 01
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0° -45° 45° 90° 90° 45° -45° 0°
0 90 0 90 0° 90 0
q -q q -q q -q q
[0/90/0/ ]s 90
[q/-q/q]s
[0/±45/90]s
CROSS-PLY laminateTE
ANGLE-PLY laminateTE
QUASI ISOTROPIC laminateTE (symmetrical and Balanced)
Composite Analysis in midas NFX 01
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laminatete Shell Elements Only 1 el. through the thickness (>3 integr. Pnts) Orthotropic material/s (E1,E2, G12, ni12) Ply thickness Lay-up definition (etherogeneous) Suitable for plane stress problems
Solid Elements More elements through the thickness (1 elements for each ply / multyply on single element) Orthotropic material/s (E1,E2, G12, ni12) Ply thickness Lay-up definition (etherogeneous) Helps to detail better 3D geometries and local geometries (ex. drop-off ply)
Composite Analysis in midas NFX 01
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Composite Analysis in midas NFX 02 midas NFX Composite Material Tutorial
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Composite Analysis in midas NFX 01
Midas NFX project applications using composite materials
Matteo Vettori
FEA Consultant
e-FEM, Italy
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Project Applications using composite Materials with midas NFX 03
STRUCTURAL ANALYSIS OF FORMULA SAE CAR
PR03 COMPOSITE FRAME
idealization
Graduation Project of Lorenzo Bergonzi @ University of Parma
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Project Applications using composite Materials with midas NFX 03
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Project Applications using composite Materials with midas NFX 03
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ZZ: Peeling
ZX: Shear
Project Applications using composite Materials with midas NFX 03
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Project Applications using composite Materials with midas NFX 03
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Project Applications using composite Materials with midas NFX 03
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Project Applications using composite Materials with midas NFX 03
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Project Applications using composite Materials with midas NFX 03
NAFEMS Composite Benchmark
Project of Lorenzo Bergonzi @ University of Parma
LSMC1 LSMC2 LSMC3
LSMC4 LSMC5 LSMC6
Benchmarks for Membrane and Bending Analysis of laminateted Shells, P. Hopkins - First Published - December 2005
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Project Applications using composite Materials with midas NFX 03
LSMC1 LSMC2 LSMC3
LSMC4 LSMC5 LSMC6
strain & curv. Classical laminatetion Theory load
ε1 1,173710E-08 -3,521130E-09 0,000000E+00 4,711640E-21 -2,553690E-21 0,000000E+00 N1
ε2 -3,521130E-09 3,048780E-07 0,000000E+00 -2,553690E-21 9,949090E-20 0,000000E+00 N2
γ12 0,000000E+00 0,000000E+00 7,812500E-07 0,000000E+00 0,000000E+00 3,252610E-19 N12
κ1 4,711640E-21 -2,553690E-21 0,000000E+00 8,802820E-01 -2,640850E-01 0,000000E+00 M1
κ2 -2,553690E-21 9,949090E-20 0,000000E+00 -2,640850E-01 2,286590E+01 0,000000E+00 M2
κ12 0,000000E+00 0,000000E+00 3,252610E-19 0,000000E+00 0,000000E+00 5,859380E+01 M12
strain & curv. Midas NFX load
ε1 1,173712E-08 -3,521136E-09 0,000000E+00 2,643114E-23 -2,288384E-21 0,000000E+00 N1
ε2 -3,521136E-09 3,048784E-07 0,000000E+00 -2,288547E-21 1,981403E-19 0,000000E+00 N2
γ12 0,000000E+00 0,000000E+00 7,812500E-07 0,000000E+00 0,000000E+00 0,000000E+00 N12
κ1 2,643114E-23 -2,288547E-21 0,000000E+00 8,803204E-01 -2,641061E-01 0,000000E+00 M1
κ2 -2,288384E-21 1,981403E-19 0,000000E+00 -2,641061E-01 2,286606E+01 0,000000E+00 M2
κ12 0,000000E+00 0,000000E+00 0,000000E+00 0,000000E+00 0,000000E+00 5,859261E+01 M12
[0/0/0/0]
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Project Applications using composite Materials with midas NFX 03
LSMC1 LSMC2 LSMC3
LSMC4 LSMC5 LSMC6
strain & curv. Classical laminatetion Theory load
ε1 1,131590E-08 -3,697690E-09 -4,421510E-41 -1,592770E-21 -3,886190E-22 3,273250E-21 N1
ε2 -3,697690E-09 2,010510E-08 1,164550E-40 3,977530E-22 -8,052920E-21 -9,648560E-22 N2
γ12 -4,421510E-41 1,164550E-40 5,593660E-08 1,911530E-21 -3,004650E-21 -1,332640E-20 N12
κ1 -1,592770E-21 3,977530E-22 1,911530E-21 1,807200E-01 -5,859600E-02 -1,428450E-03 M1
κ2 -3,886190E-22 -8,052920E-21 -3,004650E-21 -5,859600E-02 5,179430E-01 -3,317320E-01 M2
κ12 3,273250E-21 -9,648560E-22 -1,332640E-20 -1,428450E-03 -3,317320E-01 1,470740E+00 M12
strain & curv. Midas NFX load
ε1 1,131598E-08 -3,697650E-09 3,286920E-41 -5,613643E-21 4,824670E-22 3,779821E-22 N1
ε2 -3,697650E-09 2,010506E-08 -3,901530E-40 9,570351E-22 1,816786E-20 -1,749701E-20 N2
γ12 3,286920E-41 -3,901530E-40 5,593780E-08 -4,165473E-22 -9,115527E-21 1,708858E-20 N12
κ1 -5,613643E-21 9,570351E-22 -4,165473E-22 1,807200E-01 -5,859543E-02 -1,429153E-03 M1
κ2 4,824670E-22 1,816786E-20 -9,115527E-21 -5,859543E-02 5,179399E-01 -3,317298E-01 M2
κ12 3,779821E-22 -1,749701E-20 1,708858E-20 -1,429153E-03 -3,317298E-01 1,470731E+00 M12
[0/60/-60/0/0/-60/60/0]
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Project Applications using composite Materials with midas NFX 03
Analysis case LSSAM1 laminatete Loa
d
N1 N2 N12 M1 M2 M12 1.5E3 0.0 0.0 0.0 0.0 0.0
Node Constrained degrees of freedom
1 Tx, Ty, Tz, Rx, Ry, Rz
2 Rz
3 Rz
4 Tx, Rz
Ply1 Ply2 Ply3 Ply4
Theory Midas NFX Theory Midas NFX Theory Midas NFX Theory Midas NFX
σl [Pa] -5,1280E+06 -5,1285E+06 1,2590E+07 1,2593E+07 8,5200E+06 8,5204E+06 9,3579E+06 9,3579E+06
σt [Pa] 4,4070E+06 4,4073E+06 1,9830E+06 1,9833E+06 1,2560E+05 1,2564E+05 -1,8600E+06 -1,8596E+06
τlt [Pa] -1,6630E+06 -1,6635E+06 2,5720E+06 2,5719E+06 -2,0510E+06 -2,0514E+06 -5,5580E+05 -5,5577E+05
Tsai-Wu Failure Index
8,8402E-01 8,8131E-01 3,7308E-01 3,7622E-01 1,9901E-02 2,0042E-02 -3,4309E-01 -3,4518E-01
Hill Failure Index
7,7952E-01 7,7944E-01 1,6330E-01 1,6327E-01 4,3510E-03 4,4353E-03 1,3596E-03 1,3900E-01
Hoffmann Failure Index
8,8110E-01 3,7607E-01 3,76E-01 3,7607E-01 2,0039E-02 2,0036E-02 -3,4534E-01 .0,03450769
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Project Applications using composite Materials with midas NFX 03 midas NFX Composite Boat Project Application
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