Ws01_flatplateP

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WORKSHOP 1

COMPOSITE MODEL OF LOADEDFLAT PLATE

WS1-1PAT325, Workshop 1, February 2004Copyright¥ 2004 MSC.Software Corporation



Mar120, Workshop 10, March 2001 WS1-2

PAT325, Workshop 1, February 2004Copyright¥ 2004 MSC.Software Corporation





Problem Description

Model a 1x1 meter plate. Use millimeters as units of length.

The plate is 4 mm thick and is a laminate made up of 16 plies with equal

thickness. The laminate is uniform. The plies have two orientations, 0 and

90 degrees, i.e. parallel to the plate edges.

The material properties of the lamina are

E-modulus: E11 = 181 GPa,

E22

= 10.3 GPa

Shear modulus: G12 = 7.17 GPa,

G23 = 5.00 GPa,

G13 = 7.17 GPa

Poisson Ratio: 0.28

Density: 1.6E-9

The plate is fixed along one edge, and supported laterally at one of the twoopposite corners.

The plate is loaded with a uniform pressure of 0.1 KPa, giving a total force

acting on the plate of 100 Newtons.

We want to investigate the occurring stresses in the layers and the

maximum deflection of the plate.





Suggested Exercise Steps

1. Create a new database2. Create the model surface

3. Mesh the surface to create the model elements

4. Constrain an edge and an opposite point

5. Create pressure loading for the plate

6. Create 2D orthotropic material for lamina

7. Create composite laminate from 2D orthotropic material8. Define 2D shell elements

9. Determine direction of element normals

10. Verify orientation angle of laminate

11. Run analysis using MSC.Nastran

12. Attach .XDB results file to MSC.Patran database

13. Look at stresses and displacements





d

e

f

b c

Open a new database. Name itFlatplate.db.

a. File / New.

b. Enter Flatplate as the file

name.

c. Click OK.

d. Select MSC.Nastran as the Analysis Code.

e. Select Structural as the Analysis Type.

f. Click OK.

a

Step 1. Create a New Database





Create the flatplate geometry.

a. Geometry: Create / Surface /

XYZb. Enter <1000, 1000, 0> as theVector Coordinates List.

c. Enter [0 0 0] as the OriginCoordinates List.

d. Click ±Apply-.

e. Click Iso 3 View.

Step 2. Create the Model Surface

e

b

c

d

a



Mar120, Workshop 10, March 2001 WS1-7PAT325, Workshop 1, February 2004Copyright¥ 2004 MSC.Software Corporation

Step 3. Mesh the Surface to Create the Model Elements

Create a mesh for the model.

a. Elements: Create / Mesh /

Surface.b. Select IsoMesh as theMesher.

c. Select Quad4 as theTopology.

d. Uncheck the AutomaticCalculation.

e. Enter 125 as the GlobalEdge Length Value.

f. Select Surface 1 for theSurface List.

g. Click ±Apply-.

d

e

c

b

a

f

g




Step 4. Constrain an Edge and an Opposite Point

Define constraints.

a. Loads/BCs: Create /

Displacement / Nodal.b. Enter Fixed Edge as theNew Set Name.

c. Click Input Data.

d. Enter <0, 0, 0> as theTranslations.

e. Click OK.

f. Click Select ApplicationRegion.

g. Select Edge Icon.h. Select Surface 1.4 for

Select Geometry Entities.

i. Click Add.

j. Click OK

k. Click ±Apply-.

d

e

g

h

i

j

b

c

a

f

k




Define constraints.


Displacement / Nodal.b. Enter Supported Point asthe New Set Name.


d. Enter < , , 0> as theTranslations.

e. Click OK.


g. Select Point Icon.h. Select Point 2 for Select

Geometry Entities.

i. Click Add.

j. Click OK

k. Click ±Apply-.

b

c

d

e

a

f

g

h

i

j

k

Step 4. Constrain an Edge and an Opposite Point (Cont.)




Define Loading.


Pressure / ElementUniform.

b. Enter Pressure Load asthe New Set Name.


d. Enter 0.0001 as the TopSurf Pressure.

e. Click OK.


g. Select Surface Icon.

h. Select Surface 1 for SelectSurface or Edges.

i. Click Add.

j. Click OK

k. Click ±Apply-.

Step 5. Create Pressure Loading for the Plate

b

c

d

e

a

f

g

h

i

j

k




Note that the pressure0.0001 is in MegaPascals.

Until now this exercise hasbeen quite straight forward,but the next step is to define

the laminate.

The model should looklike this after clicking ±Apply-.

Step 5. Create Pressure Loading for the Plate (Cont.)




Step 6. Create 2D Orthotropic Material for Lamina

Define lamina material properties.

a. Materials: Create / 2D Orthotropic/ Manual Input.

b. Enter ud_t300_n5208 as theMaterial Name.

c. Click Input Properties.d. Select Linear Elastic as the

Constitutive Model.

e. Enter 181000 as the ElasticModulus 11.

f. Enter 10300 as the ElasticModulus 22.

g. Enter 0.28 as the PoissonRatio 12.

h. Enter 7170 as the Shear Modulus 12.

i. Enter 5000 as the Shear Modulus 23.

j. Enter 7170 as the Shear Modulus 13.

k. Enter 1.6E-9 as the Density.

l. Click OK.

m. Click Apply.

b

c

d

ea

f g

h i j

k

lm

These material propertieswill be used later for other workshops. Thus, a sessionfile, material.ses, is providedwith the workshop files. Thiscan be ³played´ into

MSC.Patran creating theproperties quickly and easily.




Step 7. Create Composite Laminate From 2D Orthotropic Material

Define laminate properties.

a. Materials: Create /Composite / Laminate.

b. Enter My first laminateas the Material Name.

c. Select Insert as the TextEntry Mode.

d. Select Material Names.

e. Input16(ud_t300_n5208) asthe Insert MaterialNames.

f. Click Load Text IntoSpreadsheet.

16 rows corresponding toplies are created. Also,need to fill in thickness andorientations.

Now build the laminate out of

the lamina just defined. Takenotice of how the laminate isdefined in the spreadsheet.

bc

de

a

f




a. Select Overwrite as theText Entry Mode.

b. Select Thickness.

c. Enter 16(0.25) as the

Overwrite Thicknesses.d. Click Load Text Into

Spreadsheet.

a

b

c

d

Step 7. Create Composite Laminate (Cont.)




a. Select Overwrite as theText Entry Mode.

b. Select Orientations.

c. Enter 4(90/0) as the

OverwriteOrientations.d. Click Load Text Into

Spreadsheet.

e. Enter 4(0/90) inOverwriteOrientations.

f. Click Load Text Into

Spreadsheet.

g. Click ±Apply-.

(4 pairs of 90 degreesand 0 degrees)

(4 pairs of 0 degree and90 degrees)

a

b

c

d

e

f

g

Step 7. Create Composite Laminate (Cont.)




Step 8. Define 2D Shell Elements

Define 2D element properties.The composite laminatematerial property is to be used.

a. Properties: Create / 2D /Shell.

b. Enter Plate as the

Property Set Name.c. Select Laminate as theOptions.

d. Select StandardFormulation as theOptions.

e. Click Input Properties.

f. Select My FirstLaminate as the

Material Name.g. Select Vector .

h. Enter <1. 0. 0.> as theMaterial Orientations.

i. Click OK.

j. Select Surface1 as theSelect Members.

k. Click Add.

l. Click Apply.

f

gh

i

Now the fiber directions havebeen related to the MSC.Patranglobal X direction. Half of thefibres are rotated 90 degreesrelative to this direction.

b

c

d

e

a

j

k

l




Step 9. Determine Direction of Element Normals

Verify laminate direction.

a. Elements: Verify /Element / Normals.

b. Select Draw NormalVectors as the DisplayControl.

c. Click Apply.

Verify that all vectors are pointing inthe positive z-axis direction

b

c

aIt is best to check amodel before runningan analysis, especiallywhen the materials arelaminates. Remember that layer 1 is at thebottom of the stack of

plies. First, check thedirection of the elementnormals to determinewhat direction is ³up´.




Verify Laminate Direction.

a. Properties: Show.

b. Select OrientationAngle as the ExistingProperties.

c. Select Vector Plotas the DisplayMethod.

d. Click ±Apply-.

The initial reference direction isshown. Note that the individual

fibre directions cannot be seen.They can only be checked in thelaminate spreadsheet. The totallaminate thickness can bechecked, but this is of little interestin this case.

It is necessary to verify that all thelayers are defined correctly, and

there are several tools that can beused to do this task.

Step 10. Verify Orientation Angle of Laminate

b

c

a

d




Step 11. Run Analysis Using MSC.Nastran

Set up and run the analysis.

a. Analysis: Analyze / EntireModel / Full Run

b. Click Subcases.

c. Select Default as an Available Subcases.

d. Click Output Requests.

b

a

c

d




a. Select Advanced as theForm Type.

b. Select STRESS as theOutput Requests.

c. Select Ply Stresses as theComposite Plate Opt.

d. Click OK.

a

bc

d

Step 11. Run Analysis Using MSC.Nastran (Cont.)




a. Click Apply in the SubcaseMenu.

b. Click Cancel.

c. Click Apply in the Analysismenu.

a bc

Step 11. Run Analysis Using MSC.Nastran (Cont.)




Step 12. Attach .XDB Results File to MSC.Patran Database

Create a link to the MSC.Nastrananalysis results file

a. Analysis: Access Results / Attach XDB / Result Entities.

b. Click Select Results Files.

c. Select Flatplate.xdb.

d. Click OK.

e. Click Apply.

c

d

b

e

a




View the results

a. Results: Create / Quick Plot.

b. Select Default, StaticSubcases as the SelectResult Cases.

c. Select Stress Tensor as theSelect Fringe Result.

d. Select Layer 12 as thePosition.

e. Click Close.

f. Select X Component as theQuality.

g. Select Displacements,Translational as the SelectDeformation Result.

h. Click Apply.

Step 13. Look at Stresses and Displacements

d

e

First look at the stresses inone of the layers. Choose layer 12, and plot stresses in the X-direction.

b

c

a

f

g

h

d




Step 13. Look at Stresses and Displacements (Cont.)




Also, investigate the deflection of the plate.

a. Select Displacements,

Translational as theSelect Fringe Result.

b. Click Apply.

b

a

Step 13. Look at Stresses and Displacements (Cont.)




If extra time

Another laminate builder tool can be found in the

Utilities menu: Materials/Laminate Builder Tool.Check it out.

If you have any questions, please do not hesitate to

ask.

Do not delete this database, it will be used later.

Documents

Ws01_flatplateP