Laminate Design

ABD Matrix TutorialABD Matrix TutorialBasic Composite Part Design

CATIA v5: Composite Engineering Design ProductLevel: BeginnerLevel: Beginner

Creating Virtual Composite Parts

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Tutorial Backgroundg

• What you will learn:– How to create a simple composite Laminate using the CATIA v5 Composite

Engineering Design module.– How to gather important engineering information from the model using the

Numerical Analysis functionNumerical Analysis function• User Background:

– User should have at least 500 hours of Catia experience before attempting tutorial.

• Time for Completion: ≈ 1 hour• Tutorial written by Norm Lamar, founder of ABD Matrix.

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Section 1: Create the Reference Surface

• Create a 10 in. square surface (See Figure 1)• Make sure the surface lies in the X Y plane• Make sure the surface lies in the X-Y plane• Create 4 curves; one on each edge of the surface• Now, enter the Composite Design module• Command Sequence: select,

– Start Z– Mechanical Design – Composite Design

• You can also use the following macro to gain access: : X

Y

Figure 1. Surface Model of the Square Plate g q

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Section 2: Defining Composite Parameters

• Now you will define the composite parameters • Command Sequence: select• Command Sequence: select,

– Insert – Parameters – Composite Parameters

• You can also use the following macro toigain access :

• Figure 2 appears, and now you have the option of adding, removing or redefining ply angles.Figure 2. Composite Parameters Dialog Box

• In this exercise the default angles are used. • Note: After you have defined the angles, you will

notice that all the composite-based icons in the menu bars are no longer grayed out

g p g

Optional: Ply angle colors are already defined by CATIA’s default color selection; however, if you want to change a color of a ply angle, simply highlight the angle value, then select the menu (shown by red circle in Figure 2) and select a color of your choiceModel Tree Maturity

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circle in Figure 2) and select a color of your choice

Section 3: Zone Group Definition

• You will need to define a Zone Group first• Command Sequence: select• Command Sequence: select,

– Insert – Preliminary Design – Zones Group

• You can also use the following macro to gain access :

• Leave the default name• Select the plate’s surface to define the geometry

that will be used to build the laminate

Figure 3. Zone Group Definition Dialog Box

• Rosette Definition: select the default coordinate system in the model tree

• The Rosette Transfer type remains Cartesian• Your done, select OK

Next, you will defining zones within the zone group youjust created. Please take note of your Model Tree.

Model Tree Maturity

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Section 4: Zone Geometry and Laminate Definition

• Zones Geometry Definition• Command Sequence: select,

– Insert – Preliminary Design – Create Zone

• You can also use the following macro to gain access :

S l h i l d fi C 1• Select the curves create previously to define Contour.1. The name Sketch.1 should appear

– Important: select the curves in a sequential order• Now, select the laminate tab (Located in red circle)• Select the material menu and select Glass• A row will appear showing the Glass material• A row will appear showing the Glass material• Now you will define the number of plies per angle. For

this example, enter 2 plies per angle by placing your cursor under the corresponding column, then double click. A box should appear allowing you to enter the total number of plies.

Figure 5. Zone Geometry Definition

• Click Ok. Evaluate the Model Tree to see changes

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Example of curve selection: note sequence Z 1

Important: Make sure the name Zone 1 appears in the Catia model; if not, thenyou have not defined the zone correctly. Go back and check to make sure that

34

p q Zone.1

Copyright 2008. ABD Matrix, All Rights Reserved. 6Figure 6. Zone Laminate Definition

you have not defined the zone correctly. Go back and check to make sure thatyou selected the curves in the correct order.

Section 4b: Model Tree Maturity Checky

Your model tree should appear similar to the one shown

You can, at any time, modify these parameters by simplyright-clicking on an item that you wish to modify

Your laminate definition will appear when youhave correctly defined the zoney

Results from input shown in Figure 6, on page 6

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Section 5: Creating Plies from a Zoneg

• You have developed enough information to create your first Laminate. In this case, 8 plies of glass, oriented using the definition found in section 4using the definition found in section 4.

• Next, you will create plies from the zone• Command Sequence: select,

– Insert– Plies– Plies Creation from Zones

• You can also use the following macro to gain access : • Create plies in new group should be pre-selected; if not,

depress the button• If it isn’t already, Deselect Create plies without stagger; it y p gg

will not be used for this exercise• Your done with dialog box manipulation, select OK

Note: Stacking information will appear in the model tree. Lookfor 8 sequences and a newly created geometrical setfor 8 sequences and a newly created geometrical set.

See next page for model tree details

Figure 7. Plies Creation Dialog Box

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Section 5b: Stacking Information

Using Sequence.1 as an example, we can see how Catiaconstructs the composite part.

In this case Ply 1 is made from glass has a zero degreeIn this case, Ply.1 is made from glass, has a zero-degreeorientation and is defined geometrically by Contour.7; whichis a derivative of the previously defined Contour.6

The subsequent Sequences shown are built the same way

The newly created Geometrical Set.2 holds the 8 curves needed to build each ply in the sequences. They are created

automatically during the ply creation stage

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Section 6: Applying the Ply Explodery g y

• Showing the plies• Make sure your sequences were created; otherwise,

this ply exploder will fail.• The ply exploder will automatically build 2-D surfaces

for each ply in the z-direction. This will enhance the visual perspective of the Laminate, allowing the engineer to check the integrity of the composite build.

• Command Sequence: select,– Insert– Plies – Ply Exploder

• You can also use the following macro to gain access :• You will use all the default settings except for scale.Shell Constant Offset You will use all the default settings except for scale.

Also, make sure the Shell Constant Offset ply representation is selected-it should be by default.

• Modify the scale to read 20.• Your done, select OK

Shell Constant Offset

Copyright 2008. ABD Matrix, All Rights Reserved. 10Figure 8. Ply Exploder Dialog Box

Section 7: The Finished Composite Part

The final composite part build is shown in Figure 9.

The ply schematic shows the laminate stack in 3 D The colors clearlyThe ply schematic shows the laminate stack in 3-D. The colors clearlyshow the varying angles of each ply in the Laminate.

Question: Is there any other information that can be gleaned fromthis model that we do not already have? The answer is yes.

Figure 9. Final Composite Part Build

Using the Numerical Analysis tool, the engineer can extractinformation such as: ply surface areas, ply or laminate weightsvolumetric mass and much more.

The next section will show just how this is done.

Detail A

P1 → 0°

P2 → 45°

P3 45°

Ply Schematic

P3 → 45°

P7 → 90°

P4 → -45°

P5 → -45°

P6 → 90°

Copyright 2008. ABD Matrix, All Rights Reserved. 11Detail A

P7 90

P8 → 0°

Section 8: Numerical Analysis of the Ply

• Want to know more than just ply angles and thickness? • Use the Numerical Analysis tool • Command Sequence: select,

– Insert– Analysisy– Numerical Analysis

• You can also use the following macro to gain access :

• What is the Aerial mass of the ply? Let’s find out by selecting Ply 1 from the model treeselecting Ply.1 from the model tree.

• Once selected the Numerical Analysis dialog box will update the analysis parameters. See Figure 10.

• Aerial ply mass: 0.043 lb

Figure 10. Numerical Analysis of Ply.1

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Section 8b: Numerical Analysis of the Composite Laminate

• What is the Aerial mass of the Laminate? Let’s find out by selecting the Plies Group.1 from the model tree.

• Once selected the Numerical Analysis dialog box will update the analysis parameters See Figure 10update the analysis parameters. See Figure 10.

• Aerial Laminate mass: 0.341 lb

• You can export your data into Excel by using the Export y y gbutton.

Figure 10. Numerical Analysis of Ply.1

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Congratulations! g

• You are now able to create a simple composite laminate with CATIA’s Composite Engineering Design productproduct.

• Use the composite module for preliminary design tasks to quickly create a realistic laminate.

• To learn more, try my intermediate and advanced tutorials.

• If you have questions or comments; or, you found a mistake in the tutorial, send a email to [email protected]

Copyright 2008. ABD Matrix, All Rights Reserved. 14