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

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

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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

Particle Composites

Short Fibers Composites

Long (Continuous) Fibers Composites

laminateted Composites

Composite Analysis in midas NFX 01

Composite Analysis in midas NFX 01

Big structures Components Meso-scale Micro-scale

Magnification dimensions

Composite Analysis in midas NFX 01

PROs …. • Lightweight • High stiffness • High resistance

CONs … • Cost • Complexity

Composites

Aluminium alloys

Composite Analysis in midas NFX 01

The real strength of composite materials is …

INFINITE POSSIBILITY OF OPTIMISATION & CUSTOMISATION

«TAILOR – ABILITY»

Composite Analysis in midas NFX 01

ISOTROPIC MATERIAL 2 CONSTANTs ANISOTROPIC MATERIAL 21 CONSTANTs Single laminate ? Directional properties are orthogonals 9 CONSTANTs

Composite Analysis in midas NFX 01

Symmetry conditions

Generic expression …

Composite Analysis in midas NFX 01

Assuming Through-the-thickness simplification Plane Strain (s3, t13 , t23 = 0)

Stiffness Matrix

Compliance Matrix

Composite Analysis in midas NFX 01

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

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

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

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

xyxyxy kz 0

Composite Analysis in midas NFX 01

Composite Analysis in midas NFX 01

where

Composite Analysis in midas NFX 01

A B

D

Direct stresses

Coupling terms

Flexural stresses

Composite Analysis in midas NFX 01

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

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

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

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

Composite Analysis in midas NFX 02 midas NFX Composite Material Tutorial

Composite Analysis in midas NFX 01

Midas NFX project applications using composite materials

Matteo Vettori

FEA Consultant

e-FEM, Italy

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

Project Applications using composite Materials with midas NFX 03

Project Applications using composite Materials with midas NFX 03

ZZ: Peeling

ZX: Shear

Project Applications using composite Materials with midas NFX 03

Project Applications using composite Materials with midas NFX 03

Project Applications using composite Materials with midas NFX 03

Project Applications using composite Materials with midas NFX 03

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

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]

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]

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

Project Applications using composite Materials with midas NFX 03 midas NFX Composite Boat Project Application

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