Abaqus Tutorial 11b PlyFailure (1)
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Transcript of Abaqus Tutorial 11b PlyFailure (1)
Strategic
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Tutorial Modelling
First matrix crack
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Tutorial 11b: Composites
Modelling ply failure
Stephanie Miot
Fibre failure
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: Composites ,
Fibre failure initiation
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1. Introduction
In this tutorial, you will modify a structural model of
material properties including
static analysis of a bending
propagation with Abaqus/Viewer
When you complete this tutorial, y
- Define the material properties of a composite ply
of the Hashin’s failure criteria
- Define a damage propagation model
- Use the visualization module to create
different plies
Preliminaries
The stiffened panel is composed of:
- a skin
• Dimensions: 16
• Lay-up: (-452,
• Material: UD carbon / epoxy
- 2 stiffeners
• Dimensions: 20
• Lay-up: (02, -45
• Material: UD carbon / epoxy
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modify a structural model of a stiffened panel
material properties including the ply failure parameters. You will then
bending test and visualize the simulation of the damage
Abaqus/Viewer.
When you complete this tutorial, you will be able to:
Define the material properties of a composite ply including the
ashin’s failure criteria
Define a damage propagation model
Use the visualization module to create ply stack plots and contour plots
The stiffened panel is composed of:
Dimensions: 1600 mm x 1000 m, 6 mm thick
, 452, 02, 902, 02, 902)S
Material: UD carbon / epoxy T300/M18
Dimensions: 200 mm x 140 mm, 1600 mm long, 4 mm thick
452, 902, 452)S
Material: UD carbon / epoxy T800/M18
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a stiffened panel to define the
You will then perform a
simulation of the damage
including the coefficients
and contour plots on
m long, 4 mm thick
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2. Setting up the model
Open the model Tutorial11b
This file contains the assembly as presented in Figure 1.
MPa.
In this tutorial, you will define
- the properties for each
and the progressive damage models
- the lay-up of the components
- the mesh
- the static analysis
- the boundary conditions and the loading.
Finally, you will run a static analysis and use the visualization module to post
process the results of the simulation.
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Figure 1: Stiffened panel
Setting up the model
Tutorial11b .cae.
the assembly as presented in Figure 1. The units are: mm and
define:
for each material and include the Hashin’s failure criteria
nd the progressive damage models
components
boundary conditions and the loading.
run a static analysis and use the visualization module to post
process the results of the simulation.
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The units are: mm and
Hashin’s failure criteria
run a static analysis and use the visualization module to post-
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3. Material and section
1. Define the mechanical
properties:
E1
E2
ν12
G12
G13
G23
Hashin’s failure criteria coefficients
XT
XC
YT
YC
SL
ST
Long. tensile fracture energy: Gftc
Long. compressive fracture energy: Gfcc
Trans. tensile fracture energy: Gmtc
Trans. compressive fracture energy: Gmcc
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and section properties
behaviour of the UD plies with the following
T300/M18 T800/M18
Elasticity coefficients
170 GPa 192
9 GPa 15
0.34 0.3
4.8 GPa 5.6
4.8 GPa 5.6
4.5 GPa 4.9
Hashin’s failure criteria coefficients
2050 MPa 2240 MPa
1200 MPa 1230 MPa
62 MPa 71
190 MPa 210 MPa
81 MPa 90
81 MPa 90
Fracture toughnesses
95 kJ/m² 105 kJ/m
103 kJ/m² 108
0.2 kJ/m² 0.2 kJ/m²
0.2 kJ/m² 0.2 kJ/m²
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following material
T800/M18
92 GPa
GPa
0.34
5.6 GPa
5.6 GPa
4.9 GPa
0 MPa
0 MPa
MPa
0 MPa
MPa
MPa
5 kJ/m²
108 kJ/m²
0.2 kJ/m²
0.2 kJ/m²
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a. Go into the Property Module
b. In the Edit Material dialog box, name the material
c. From the material editor’s menu bar, select
Elastic. Select Type: Lamina
d. Select Mechanical → Damage for Fiber
Damage and enter the material
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Property Module and click the Create Material icon
dialog box, name the material T300/M18.
From the material editor’s menu bar, select Mechanical →
Type: Lamina and enter the material data as defined above.
Damage for Fiber -Reinforced Composites
nter the material data as defined above.
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icon
Elasticity →
and enter the material data as defined above.
Reinforced Composites → Hashin
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e. Click Suboptions and select
dialog box, enter the parameters as defined above.
f. Click Suboptions and select
viscosity coefficient for each failure mode: 1e
g. Follow the instructions a
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and select Damage Evolution . In the Suboption Editor
he parameters as defined above.
and select Damage Stabilization . Specify the value of the
for each failure mode: 1e-4.
a to f to create the material T800/M18.
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Suboption Editor
Specify the value of the
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2. Define the lay-up of each component
stacking sequence is defined as:
made of 16 plies. The stacking sequence is defined as:
a. Click the Create Composite Layup
definition: Skin lay-up. Set the
Type: Continuum Shell
b. In the Edit Composite Layup
Definition: Coordinate system
Datum csys-1 . Click OK
c. Accept the default selection for the
Stacking Direction: Element direction 3
d. In the Plies tab, toggle on
the plies then double-click the
e. Double-click the Material
f. Double-click the Element Relative Thickness
thickness of each ply at 0.
Note: The sum of the relative thicknesses does not need to be equal to 1. The
result will be automatically normalised by Abaqus.
g. In the column Rotation Angle
h. Finally, set the number of
i. Use the options available in the
lay-up. Then click OK to create the new
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each component . The skin is made of 24 plies. The
stacking sequence is defined as: (-452, 452, 02, 902, 02, 902)S. The stiffener is
made of 16 plies. The stacking sequence is defined as: (02, -452, 90
Composite Layup icon . Name the new lay
. Set the Initial ply count at 6 and select the
Continuum Shell . Click Continue...
Edit Composite Layup dialog box, define the Layup orientation. Select
Definition: Coordinate system . Click the Select CSYS icon to select
OK to go back to the composite lay-up editor.
Accept the default selection for the Normal direction: Axis 3
Stacking Direction: Element direction 3 .
tab, toggle on Make calculated sections symmetric
click the Region button and select the entire part
Material button and select the material: T300/M18
Element Relative Thickness button and set the relative
at 0.25.
Note: The sum of the relative thicknesses does not need to be equal to 1. The
result will be automatically normalised by Abaqus.
Rotation Angle , define the orientation for each ply.
of Integration Points at 1.
the options available in the Display tab to check the orientation of the
to create the new lay-up.
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The skin is made of 24 plies. The
The stiffener is
902, 452)S.
. Name the new lay-up
and select the Element
dialog box, define the Layup orientation. Select
icon to select
up editor.
Normal direction: Axis 3 and the
Make calculated sections symmetric . Rename
button and select the entire part.
T300/M18.
button and set the relative
Note: The sum of the relative thicknesses does not need to be equal to 1. The
ne the orientation for each ply.
tab to check the orientation of the
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j. Follow the instructions a
Note: The stiffener is made of
- seat, 16-ply region, (0
- web, 32-ply region, (0
See Tutorial 10 for more detailed instructions if needed.
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a to i to define the lay-up of the stiffener.
Note: The stiffener is made of two regions:
(02, -452, 902, 452)S
(02, -452, 902, 452, 452, 902, -452, 02)S
See Tutorial 10 for more detailed instructions if needed.
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4. Mesh
1. Create the FE mesh for the
a. Go into the Mesh Module
b. Click the Assign Element Type
Element Type dialog box, select
other default selections.
c. Click the Seed Part icon . Set the
d. Click the Assign Mesh Controls
Algorithm : Medial axis.
e. Click the Mesh Part icon
f. Check that the stacking direction is correct. Click the
icon and select the top face of the skin to define the reference
orientation.
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1. Create the FE mesh for the skin .
Module and select the Part: Skin in the menu bar.
Assign Element Type icon . Select the entire part. In the
dialog box, select Family: Continuum Shell and accept the
other default selections.
icon . Set the approximate global size
Assign Mesh Controls icon . Select Technique
: Medial axis.
icon and click Yes.
Check that the stacking direction is correct. Click the Assign Stack Direction
and select the top face of the skin to define the reference
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in the menu bar.
. Select the entire part. In the
and accept the
approximate global size at 30 mm.
Technique : Sweep and
Assign Stack Direction
and select the top face of the skin to define the reference
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2. Create the FE mesh for the
a. Select the Part: Stiffener
tree and select Make Current
b. Assign the element type:
size of the elements at 2
c. Mesh the part and assign the stacking direction.
d. In the menu bar, select
different instances.
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. Create the FE mesh for the stiffener .
Part: Stiffener in the menu bar or right click Stiffener
Make Current .
ype: Continuum Shell and set the approximate global
of the elements at 20 mm.
Mesh the part and assign the stacking direction.
In the menu bar, select Object: Assembly to visualise the mesh
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Stiffener in the model
approximate global
to visualise the mesh of the
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5. Static analysis
1. Create a new analysis step
a. Go into the Step Module
b. Select the type of procedure:
c. In the Edit Step dialog box, toggle on
define the Maximum number of increments:
size: Initial: 0.01, Minimum:
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Static analysis
new analysis step and define the parameters of the analysis
Module . Click the Create Step icon
Select the type of procedure: Static, General and click Continue...
dialog box, toggle on Nlgeom . In the Incrementation
aximum number of increments: 100 000 and the
Minimum: 1e-9, Maximum: 0.1. Click OK.
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and define the parameters of the analysis.
Continue...
Incrementation tab,
100 000 and the Increment
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2. Create new output requests.
the damage variables and the default selection of the layered section points
includes only the top and bottom points
damage evolution in each ply
field output to the output database file
a. Click the Create Field Output
b. In the Edit Field Output Request
Then select Frequency: Evenly spaced time intervals
c. In the Output Variables
variable S, then expand
DAMAGEFT , DAMAGEF
HSNFCCRT, HSNMTCRT
State/Field/User/Time
d. Specify the output at layered section points: 1, 2, 3, 4, 5, 6
e. Click the Field Output Manager
requests F-Output-2 created in
f. Rename the new field output request:
Output Requests Manager
g. Modify the selection of the
specification of the layered section points: 1, 2, 3, 4. Click
h. Follow the instructions e
for the second stiffener:
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Create new output requests. The preselected default output does not include
and the default selection of the layered section points
includes only the top and bottom points. To visualize the stresses and the
damage evolution in each ply in the Visualization module, you will write additional
field output to the output database file.
Create Field Output icon
Edit Field Output Request dialog box, select Domain: Set:
Frequency: Evenly spaced time intervals and set
Output Variables list, expand the Stresses list and toggle on the
, then expand the Failure/Fracture list and toggle on the variables
DAMAGEFC, DAMAGEMT , DAMAGEMC ,
HSNMTCRT, and HSNMCCRT. Finally,
list and toggle on the variable STATUS.
the output at layered section points: 1, 2, 3, 4, 5, 6 and c
Field Output Manager icon . Select the second field output
created in Step-1 and click Copy...
Rename the new field output request: F-Output-3 and click OK
Output Requests Manager , F-Output-3 is selected. Click Edit...
Modify the selection of the Domain: Set: Stiffener-1.All . Then modify the
specification of the layered section points: 1, 2, 3, 4. Click OK.
e to g to create a new field output request:
for the second stiffener: Domain: Set: Stiffener-2.All .
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does not include
and the default selection of the layered section points
stresses and the
write additional
Domain: Set: Skin-1.All .
and set Interval: 10 .
list and toggle on the
list and toggle on the variables
, HSNFTCRT,
expand the
click OK.
. Select the second field output
OK. In the Field
Edit...
. Then modify the
to create a new field output request: F-Output-4
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6. Boundary conditions
1. Preliminary work: create a reference point and define a coupling constraint
between the point and the face of the skin where the loading is applied. This is to
simplify the post-processing. The displacement and the total reaction force can
then be extracted at a single point.
a. Go into the Interaction
b. Specify the coordinates
c. Click the Create Constraint
Coupling . Click Continue...
d. Select the constraint control points: RP
Surface and the surface: BC
e. In the Edit Constraint
Coupling type: Kinematic
Click OK.
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conditions
create a reference point and define a coupling constraint
between the point and the face of the skin where the loading is applied. This is to
processing. The displacement and the total reaction force can
en be extracted at a single point.
Interaction Module . Click the Create Reference Point
Specify the coordinates X, Y, Z: 0., 900., 3.
Create Constraint icon . Accept the default name and select
Continue...
constraint control points: RP -1, the constraint region type:
surface: BC -2.
Edit Constraint dialog box, accept the default selections for the
Coupling type: Kinematic and the Constrained degrees of freedom: A
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create a reference point and define a coupling constraint
between the point and the face of the skin where the loading is applied. This is to
processing. The displacement and the total reaction force can
Create Reference Point icon
. Accept the default name and select
constraint region type:
dialog box, accept the default selections for the
Constrained degrees of freedom: A ll .
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2. Create new boundary conditions
a. Go into the Load Module
b. Select Step: Initial
Displacement/Rotation
c. Select the region from the list of eligible
U3. Click OK.
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Create new boundary conditions
Module . Click the Create Boundary Condition
Step: Initial , Category: Mechanical and
Displacement/Rotation . Click Continue...
Select the region from the list of eligible Sets: BC-1 . Toggle on
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Create Boundary Condition icon
and Type:
. Toggle on U1, U2 and
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d. Create a new Boundary Condition. Select
Mechanical and Type: Displacement/Rotation
e. Select the reference point
U2 = 14 mm and U3 = -
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Create a new Boundary Condition. Select Step: Step- 1
Type: Displacement/Rotation . Click Continue...
Select the reference point RP-1 then specify the applied displacements:
-70 mm. Click OK.
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1, Category:
Continue...
then specify the applied displacements:
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7. Analysis and post
1. Run the job.
a. Go into the Job Module
b. Name the new job: Panel01
c. In the Edit Job dialog box, open the tab:
multiple processors and set the number of processors at
default selections and click
d. Click Monitor... to monitor the job while it is running.
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nalysis and post -processing
Module . Click the Create Job icon.
Panel01. Click Continue...
dialog box, open the tab: Parallelization . Toggle On
and set the number of processors at 4. Accept the other
default selections and click OK. Then submit the job: Panel01.
to monitor the job while it is running.
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. Toggle On Use
. Accept the other
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2. Analyse the results of the simulation.
a. When the job submission has been completed, in the
box, click Results or open
b. Click the Create Display
Create...
c. In the Create Display Group
Click the Replace icon
d. Click the Plot Contours on Deformed Shape icon
e. Click the Field Output Dialog
f. In the Field Output dialog box,
Output Variable: HSNFTCRT
g. In the Section Points dialog box, click
the ply Skin - ply 0 - 1 . Click
You can then visualise the fibre failure prediction
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the results of the simulation.
When the job submission has been completed, in the Job Manager
open Panel01.odb in the Visualization Module
Create Display Group icon or click Tools → Displa
Create Display Group dialog box, select Part instances:
icon then click Dismiss .
Plot Contours on Deformed Shape icon
Output Dialog icon or click Result → Field Output
dialog box, in the Primary Variable tab, select the
HSNFTCRT. Click Apply then click Section Points..
dialog box, click Selection method: Plies
. Click Apply .
You can then visualise the fibre failure prediction in the 0° ply.
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Job Manager dialog
Visualization Module .
Displa y Group →
Part instances: SKIN-1.
Field Output .
tab, select the
Section Points..
Plies and select
1
2
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h. In the Field Output dialog box, select the
visualise the fibre failure
dialog box, click Selection method: Plies
Click Apply .
i. In the Field Output dialog box, select the
visualise the matrix failure
select the ply Skin - ply
the propagation of the matrix damage in the different plies
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dialog box, select the Output Variable: DAMAGEFT
fibre failure propagation. Click Apply . In the Section Points
Selection method: Plies and select the ply Skin
dialog box, select the Output Variable: DAMAGE
failure propagation. In the Section Points
ply 90-1. Then select Skin - ply -45 . You can observe
propagation of the matrix damage in the different plies.
1
2
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Output Variable: DAMAGEFT to
Section Points
Skin - ply 0 - 1 .
Output Variable: DAMAGE MT to
Section Points dialog box,
. You can observe
1
2
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j. Click the Replace All icon
k. Click the Common Options
edges . Click OK.
l. In the Field Output dialog box, select the
the Section Points dialog box, select the ply
Select various variables and
for the damage initiation and propagation in different plies.
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icon .
Common Options icon and select Visible Edges:
dialog box, select the Output Variable: DAMAGE
dialog box, select the ply SRO - ply 0 . Click
Select various variables and section points to plot the numerical predictions
for the damage initiation and propagation in different plies.
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Visible Edges: Feature
Output Variable: DAMAGE FT. In
Click Apply .
to plot the numerical predictions
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m. Click Tools → XY Data
ODB field output . Click
n. In the XY Data from ODB Field Output
select Position: Unique Nodal
force and toggle on Magnitude
toggle on Magnitude . In the
sets: ASSEMBLY_CONSTRAINT
warning message is displayed. Click
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XY Data → Create . In the Create XY Data dialog box, select
. Click Continue...
XY Data from ODB Field Output dialog box, in the Variables
Position: Unique Nodal . In the variables list, expand RF: Reaction
Magnitude , then expand U: Spatial displacement
. In the Elements/Nodes tab, select Method: Node
ASSEMBLY_CONSTRAINT -2_REFERENCE_POINT. Click
warning message is displayed. Click OK. Then click Dismiss .
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dialog box, select
Variables tab,
RF: Reaction
Spatial displacement and
Method: Node
. Click Save. A
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o. Click Tools → XY Data
Operate on XY data . Click
p. In the Operate on XY
combine(X,X) . Double click
double click RF:Magnitude
q. In the model tree, expand
r. Double-click the chart. In the
click Dismiss . Double-click the
Title tab, click the Font
click the Font icon and set the size at 18.
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XY Data → Create . In the Create XY Data dialog box, select
. Click Continue...
Operate on XY Data dialog box, in the Operators
. Double click U:Magnitude PI: ASSEMBLY... , add “
Magnitude PI: ASSEMBLY... . Click Plot Expression
In the model tree, expand XYData and rename _temp_1: LoadDisp
click the chart. In the Chart Options dialog box, toggle off
click the X axis. In the Axis Options dialog box, in the
icon. Set the size at 24 and click OK. In the
on and set the size at 18.
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dialog box, select
column, click
, add “,” then
Plot Expression .
_temp_1: LoadDisp .
dialog box, toggle off Fill then
dialog box, in the
. In the Axes tab,
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s. Follow instruction r to modify the font sizes for the Y axis.
t. Click Options → XY Options
increase the thickness of the curve then click
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to modify the font sizes for the Y axis.
XY Options → Curve... In the Curve Options
increase the thickness of the curve then click Dismiss .
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Curve Options dialog box,