WS1 Composite Wing 021312

7/29/2019 WS1 Composite Wing 021312

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Composites Technology Day, February 2012

Copyright 2012 MSC.Software Corporation

WORKSHOP 1

Composite Wing


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Workshop Objectives

Become familiar with the basic steps in doing a composites analysis

Software Version

Patran 2011

MD Nastran 2011.1

Required File: composite_wing.db


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Problem Description

Assess the strength of a composite wing.

Composite properties have been set up for all the wing components

except the ribs. Your job is to define the ply properties and

composite layup for the ribs, run the analysis, and review the

results.

wing ribs


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a

Step 1. Open an existing Patran Database

Start Patran and open a database

containing a wing model:

a. Click File Open in the Defaults

group.

b. Select composite_wing.db as

the File name.c. Click OK.

c

b


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Step 2. Post the Ribs Group

Post both the inboard and outboard

rib:

a. Select Group/Post

b. Select ribs as the group to post.c. Click Apply.

d. Click Cancel.

a

b

c d


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Step 3. Create a 2D Orthotropic Material

Create a ply material property:

a. Under the Properties tab, click 2D in

the Orthotropicgroup.

b. EnterAS4 forMaterial Name.

c. Click Input Properties.d. Enter the values shown:

Elastic Modulus 11 = 20e6

Elastic Modulus 22 = 1.6e6

Poisson Ratio 12 = 0.34

Shear Modulus 12 = 0.8e6



Density = 0.058

e. Click OK.f. Click Apply.

g. Click Input Properties.

h. Set Constitutive Modelto Failure.

i. Set Composite Failure Theoryto

Tsai-Wu.

j. Enter the values shown:

Tension Stress Limit 11 = 220e3

Tension Stress Limit 22 = 5e3

Compress Stress Limit 11 = 150e3Compress Stress Limit 22 = 30e3

Shear Stress Limit = 18e3

Interaction Term = -2.22e-10

Bonding Shear Stress Limit = 5e3

k. Click OK.

l. Click Apply.

b

d

c

h

i

k

l

j

eg

f

a


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Step 4. Create a Laminate Composite Material

Defined the ply layup sequence:

a. Click Laminate in the Composite

group.

b. Enterrib forMaterial Name.

c. Click material property name AS4

slowly 4 times to make 4 plies

d. Click in the first Thickness cell.

e. Click in the Set Thickness cell andenter0.1 and press the Enter key to

set thickness of all plies to this value.

f. Click in the first Orientation cell.

g. Enter0/45/90/-45 in the Input Data cell

and press Enter.

h. Set the Stacking Sequence Convention

to Symmetric to make this an 8-ply

symmetric layup.

i. Click Apply.

a

c

h

g

i

e

d f

b


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Create a shell property for the ribs:

a.Click Shell in the 2D Properties group.

(You may have to move the Laminated

Composite form out of the way)

b.Enterribs forProperty Set Name.

c.Set option to Laminate.

d.Click Input Properties

e.Click on the Mat Prop Name iconf.Select rib for material

g.Click in the Material Orientation box.

h.Screen pick the basic coordinate

system located at the lower left hand

corner of the screen.

i.Click OK.

Continued on next page.

Step 5. Create Shell Property for Ribs

g

c

b

d

e

f

a

f

i

j

h


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Shell property creation continued:

j.Click Select Application Region

k.Select the Shell Elementpick filter.

l.Rectangular pick all the rib elements.

m.Click Add.

n.Click OK.

o.Click Apply.

Step 5. Create Shell Property for Ribs

k

j

l

l

m

no


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Step 6. Verify the Rib Material Orientation

Verify the Material Orientation:

a.Click Show Property in the

Property Actions group.

b.Click Material Orientation.

c.Click Apply.

d.Review the material orientation,then click Reset Graphics.

b

c

d

a


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Step 7. Review the Model

Plot the loads and constraints

applied to the wing:

a.Group/Post

b.Click Select All

c.Click Apply.

d.Click Cancel.

e.Click the Home tab.

f.Click Plot LBC Markers in theMisc. group.

g.Rotate the model by dragging

the mouse while pressing the

middle mouse button. Observe

the loads and constraints on the

model.

h.After reviewing the model,

click Reset Graphics.

a

b

c d

e

f

h

g


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Step 8. Set Up and Run Analysis

Run a linear static analysis:

a. Under the Analysis tab, click

Entire Model in theAnalyze

group.

b. Entercomposite_wing forJob

Name.

c. Click Solution Type.

d. Make sure Solution Type is

Linear Static.e. Click Solution Parameters.

f. Enter.00259 forWt.-Mass

Conversion.

g. Click Results Output Format.

h. Check OP2.

i. Click OK.

j. Click OK.

k. Click OK.

a

b

c

d

e

g

h

i

j

k

f


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Step 8. Set Up and Run Analysis (Cont.)

l. Click Subcase Select...

m. UnderSubcases Selected

click Default to remove itfrom the collection box

n. UnderSubcases For

Solution Sequence: 101,

click wing up bending to

select it.

o. Click OK.

p. Click Apply.

The job takes less than aminute to run.

l

m

p

n

o


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Step 9. Attach Results File

Attach the op2 results file:

a.Click Output2 in theAccess

Resultsgroup.

b.Click Select Results File.

c.Select composite_wing.op2.

d.Click OK.

e.Click Apply.

a

b

c

d

e


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Step 10. Review Results

Plot deformation:

a. Under the Resultstab, click

Deformation in the Results Plotgroup.

b. Select Displacement, Translational

for Deformation Results.

c. Click Apply.

a

c

b


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Step 10. Review Results (cont.)

Plot ply stresses:

a. Click Fringe in the Results Plot

group.

b. Select Stress Tensorfor Fringe

Result.

c. Set Position to Layer1

d. Set Quantity to X Componente. Click Apply.

On you own, review other layers and

other stress components.

a

c

b

d

e


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Step 10. Review Results (cont.)

Plot max failure indices:

a. Select Failure Indices, Max Indices

for Fringe Result.

b. Click Apply.

a

b


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C i ht 2012 MSC S ft C ti

End of Workshop 1

File/Quit to exit Patran.

WS1 Composite Wing 021312

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