MSC.Software Corporation 2 MacArthur Place Santa Ana, CA 92707, USA Tel: (714) 540-8900 Fax: (714) 784-4056 Web: http://www.mscsoftware.com Linear Static, Normal Modes, and Buckling Analysis Using MSC.Nastran and MSC.Patran January 2003 NAS120 Workbook Part Number: NA*V2003*Z*Z*Z*SM-NAS120-WBK United States MSC.Patran Support Tel: 1-800-732-7284 Fax: (714) 979-2990 Tokyo, Japan Tel: 81-3-3505-0266 Fax: 81-3-3505-0914 Munich, Germany Tel: (+49)-89-43 19 87 0 Fax: (+49)-89-43 61 716
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Linear Static Normal Modes and Buckling Analysis Using MSC.nastran and MSC.patran
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MSC.Software Corporation2 MacArthur Place
Santa Ana, CA 92707, USATel: (714) 540-8900Fax: (714) 784-4056
Web: http://www.mscsoftware.com
Linear Static, Normal Modes, and Buckling Analysis Using MSC.Nastran and MSC.Patran
January 2003
NAS120 Workbook
Part Number: NA*V2003*Z*Z*Z*SM-NAS120-WBK
United StatesMSC.Patran SupportTel: 1-800-732-7284Fax: (714) 979-2990
Tokyo, JapanTel: 81-3-3505-0266Fax: 81-3-3505-0914
MSC.Software Corporation reserves the right to make changes in specifications and other information contained in this document without prior notice.The concepts, methods, and examples presented in this text are for illustrative and educational purposes only, and are not intended to be exhaustive or to apply to any particular engineering problem or design. MSC.Software Corporation assumes no liability or responsibility to any person or company for direct or indirect damages resulting from the use of any information contained herein.User Documentation: Copyright 2003 MSC.Software Corporation. Printed in U.S.A. All Rights Reserved.This notice shall be marked on any reproduction of this documentation, in whole or in part. Any reproduction or distribution of this document, in whole or in part, without the prior written consent of MSC.Software Corporation is prohibited.MSC and MSC. are registered trademarks and service marks of MSC.Software Corporation. NASTRAN is a registered trademark of the National Aeronautics and Space Administration. MSC.Nastran is an enhanced proprietary version developed and maintained by MSC.Software Corporation. MSC.Patran is a trademark of MSC.Software Corporation. All other trademarks are the property of their respective owners.
TABLE OF CONTENTS
Workshop 1 Landing Gear Strut
Workshop 2 Simply Supported Beam
Workshop 3 Editing a Nastran Input File
Workshop 4 Stadium Truss
Workshop 5 Coordinate Systems
Workshop 6 Bridge Truss
Workshop 7 Fully-Stressed Beam
Workshop 8 Tapered Plate
Workshop 9 Tension Coupon
Workshop 10 2 1/2 D Clamp
Workshop 11 Support Bracket
Workshop 12 Spacecraft Fairing
Workshop 13 RBE2 vs. RBE3
Workshop 14 Normal Modes of a Rectangular Plate
Workshop 15 Buckling of a Submarine Pressure Hull
Workshop 16 Parasolid Modeling
Workshop 17 Stiffened Plate
Workshop 18 Annular Plate
WS1-1
WORKSHOP 1
LANDING GEAR STRUT ANALYSIS
NAS120, Workshop 1, January 2003
WS1-2NAS120, Workshop 1, January 2003
WS1-3NAS120, Workshop 1, January 2003
Problem Description A landing gear strut has been designed for a new fighter jet. Determine
if the landing gear strut has been designed properly to withstand the landing load.
E = 30 x 106 psi ν =0.3 Landing Load = 7,080 lb
WS1-4NAS120, Workshop 1, January 2003
Workshop Objectives Learn the typical workflow of a finite element analysis using MSC.Patran
and MSC.Nastran.
WS1-5NAS120, Workshop 1, January 2003
Suggested Exercise Steps1. Create a new database and name it strut.db. 2. Import the strut geometry.3. Mesh the strut to create solid elements. 4. Apply Loads and Boundary Conditions.5. Create material properties. 6. Create physical properties.7. Run analysis with MSC.Nastran.8. Read the results into MSC.Patran.9. Plot the Von Mises stress and displacement.
WS1-6NAS120, Workshop 1, January 2003
a
b c
d
f
g
Step 1. Create New Database
Create a new database called strut.db
a. File / New.b. Enter strut as the file name.c. Click OK.d. Choose Tolerance Based on
Model.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
e
WS1-7NAS120, Workshop 1, January 2003
Step 2. Import Geometry
Import the parasolid filea. File : Import.b. Select the file
strut.xmt.c. Click Apply.
b
c
a
WS1-8NAS120, Workshop 1, January 2003
Step 3. Mesh the Object
Create a solid mesha. Elements: Create / Mesh
/ Solid.b. Select the entire solid.c. Deselect Automatic
Calculation under Global Edge Length.
d. Enter 0.5 for the Global Edge Length.
e. Click Apply.f. Click on the Iso2 View
Icon.
a
b
cd
e
f
WS1-9NAS120, Workshop 1, January 2003
Step 4. Apply Loads and Boundary Conditions
Create a boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter hub cylinder as the
New Set Name.c. Click Input Data.d. Enter <0 0 0> for
Translations. e. Click OK.
b
c
d
e
a
WS1-10NAS120, Workshop 1, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Set the Selection Filter to Surface or Face and select the cylinder at the bottom of the strut, as shown.
d. Click Add.e. Click OK. f. Click Apply.
ae
f
d
b
Step 4. Apply Loads and Boundary Conditions
c
WS1-11NAS120, Workshop 1, January 2003
Step 4. Apply Loads and Boundary Conditions
Create a loada. Loads/BCs: Create / Total
Load / Element Uniform.b. Enter landing load as the
New Set Name.c. Click Input Data.d. Enter <0 –7080 0> for
Load. e. Click OK.
b
c
d
e
a
WS1-12NAS120, Workshop 1, January 2003
Apply the loada. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Select the upper circular surface at the top of the strut, as shown.
d. Click Add.e. Click OK. f. Click Apply.
ae
f
d
b
Step 4. Apply Loads and Boundary Conditions
c
WS1-13NAS120, Workshop 1, January 2003
Step 5. Create Material Properties
a
c
b
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter steel for the Material
Name.c. Click Input Properties.d. Enter 30e6 for the Elastic
Modulus.e. Enter 0.3 for the Poisson
Ratio.f. Click OK. g. Click Apply.
d
gf
e
WS1-14NAS120, Workshop 1, January 2003
Step 6. Create Physical Properties
Create physical propertiesa. Properties: Create / 3D /
Solid.b. Enter strut as the Property
Set Name.c. Click Input Properties.d. Select steel as the
material.e. Click OK.
a
b
c
e
d
WS1-15NAS120, Workshop 1, January 2003
Apply the physical propertiesa. Properties: Create / 3D
/ Solid.b. Click in the Select
Members box.c. Rectangular pick the
entire solid as shown.d. Click Add.e. Click Apply.
a
bd
e
Step 6. Create Physical Properties
c
WS1-16NAS120, Workshop 1, January 2003
Step 7. Run Linear Static Analysis
Analyze the modela. Analysis: Analyze /
Entire Model / Full Run.
b. Click Solution Type.c. Choose Linear Static
as the Solution Type.d. Click OK.e. Click Apply.
a
b
c
d
e
WS1-17NAS120, Workshop 1, January 2003
Step 8. Read Results into MSC.Patran
Attach the results filea. Analysis: Access Results /
Attach XDB / Result Entities.
b. Click Select Results File.c. Choose the results file
strut.xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS1-18NAS120, Workshop 1, January 2003
Step 9. Plot Stress and Displacement
Create a quick plota. Results: Create / Quick
Plot.b. Select Stress Tensor as
the Fringe Result.c. Select Displacements,
Translational as the Deformation Result.
d. Click Apply.e. Click on the Iso1 View
Icon.
a
d
c
b
e
WORKSHOP 2
Simply Supported Beam
NAS120, Workshop 2, January 2003 WS2-1
WS2-2NAS120, Workshop 2, January 2003
Problem Description Analyze a simply-supported beam with a concentrated load Beam dimension 1” x 1” x 12” E = 30 x 106 psi ν =0.3 Load = 200 lb
PP
WS2-3NAS120, Workshop 2, January 2003
Workshop Objectives A finite element model must be properly constrained to prevent rigid
body motion. This workshop demonstrates how to properly constrain a model in 3-D space.
WS2-4NAS120, Workshop 2, January 2003
Suggested Exercise Steps1. Create a new database and name it inadequate_constraint.db. 2. Create a solid to represent the beam.3. Mesh the solid to create 3D elements. 4. Create in-plane boundary conditions.5. Apply loads.6. Create material properties. 7. Create physical properties.8. Run analysis with MSC.Nastran.9. View fatal errors in the .f06 file.10. Add new boundary condition to properly constrain model.11. Re-run the analysis. View the .f06 file.12. Access the results file.13. Plot results.
WS2-5NAS120, Workshop 2, January 2003
a
b c
d
f
g
Step 1. Create New Database
Create a new database called inadequate_constraint.db
a. File / New.b. Enter inadequate_constraint
as the file name.c. Click OK.d. Choose Tolerance Based on
Model.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
e
WS2-6NAS120, Workshop 2, January 2003
Step 2. Create Geometry
Create a solida. Geometry : Create /
Solid / Primitiveb. Enter 12 for the X
Lengthc. Click Apply.d. Change to iso 1 view
a
b
c
d
WS2-7NAS120, Workshop 2, January 2003
Step 3. Mesh the Solid
Create a solid mesha. Elements: Create / Mesh
/ Solidb. Screen pick the solidc. Click Apply.
d
a
b
c
WS2-8NAS120, Workshop 2, January 2003
Step 4. Create Boundary Conditions
Create a boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter left_end as the New
Set Name.c. Click Input Data.d. Enter <0,0, > for
Translations. e. Click OK.
b
c
d
e
a
WS2-9NAS120, Workshop 2, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Select the curve filterd. Screen pick the left
edge as showne. Click Add.f. Click OK. g. Click Apply.
a
e
g
d
b
Step 4. Create Boundary Conditions
c
Screen pick this lower edge
f
WS2-10NAS120, Workshop 2, January 2003
Step 4. Create Boundary Conditions
Create another boundary condition
a. Loads/BCs: Create / Displacement / Nodal.
b. Enter right_end as the New Set Name.
c. Click Input Data.d. Enter < ,0, > for
Translations. e. Click OK.
b
c
d
e
a
WS2-11NAS120, Workshop 2, January 2003
Apply the boundary conditiona. Click Select Application
Region.b. For the Geometry Filter
select Geometry.c. Select the curve filterd. Screen pick the right edge
as showne. Click Add.f. Click OK. g. Click Apply.
a
e
g
d
b
Step 4. Create Boundary Conditions
c
Screen pick this edge
f
WS2-12NAS120, Workshop 2, January 2003
Step 5. Apply Load
Create a loada. Loads/BCs: Create / Force
/ Nodal.b. Enter load as the New Set
Name.c. Click Input Data.d. Enter <0 -100 0> for Force. e. Click OK.
b
c
d
e
a
WS2-13NAS120, Workshop 2, January 2003
Apply the loada. Click Select
Application Region.b. For the Geometry
Filter select FEM.c. Shift/pick the two
nodes as shownd. Click Add.e. Click OK. f. Click Apply.
a
e
f
d
b
Step 5. Apply Load
cScreen pick these nodes
WS2-14NAS120, Workshop 2, January 2003
Step 6. Create Material Properties
a
c
b
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter steel for the Material
Name.c. Click Input Properties.d. Enter 30e6 for the Elastic
Modulus.e. Enter 0.3 for the Poisson
Ratio.f. Click OK. g. Click Apply.
d
gf
e
WS2-15NAS120, Workshop 2, January 2003
Step 7. Create Physical Properties
Create physical propertiesa. Properties: Create / 3D /
Solidb. Enter solid_beam as the
Property Set Name.c. Click Input Properties.d. Click on steel to select ite. Click OK.
a
b
c
d
e
WS2-16NAS120, Workshop 2, January 2003
Apply the physical propertiesa. Click in the Select
Members box.b. Screen pick the solidc. Click Add.d. Click Apply.
ac
d
Step 7. Create Physical Properties
b
WS2-17NAS120, Workshop 2, January 2003
Step 8. Run Linear Static Analysis
Analyze the modela. Analysis: Analyze /
Entire Model / Full Run.
b. Click Solution Type.c. Choose Linear Static
as the Solution Type.d. Click OK.e. Click Apply.
a
b
c
d
e
WS2-18NAS120, Workshop 2, January 2003
Step 9. View F06 File
Examine the .f06 filea. Open the file titled
inadequate_constraint.f06 with any text editor.
b. Examine the warning and fatal messages.
Why has the job failed?a. The warning message in the .f06 file lists T3 as the
problem degree of freedom.b. With constraints in the x-y plane only, the beam has a
rigid body motion in the z direction. Need to add a constraint in the z direction.
WS2-19NAS120, Workshop 2, January 2003
Step 10. Add New Boundary Condition
Add a boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter z_constraint as the
New Set Name.c. Click Input Data.d. Enter < , ,0 > for
Translations. e. Click OK.
b
c
d
e
a
WS2-20NAS120, Workshop 2, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Select the point filterd. Screen pick the left
corner as showne. Click Add.f. Click OK. g. Click Apply.
a
e
g
d
b
Step 10. Add New Boundary Condition
c
Screen pick this point f
WS2-21NAS120, Workshop 2, January 2003
Step 11. Re-run Linear Static Analysis
Analyze the modela. Analysis: Analyze /
Entire Model / Full Run.
b. Click Solution Type.c. Choose Linear Static
as the Solution Type.d. Click OK.e. Click Apply.
After the analysis is completed, view the .f06 file to make sure there is no warning or fatal error message.
a
b
c
d
e
WS2-22NAS120, Workshop 2, January 2003
Step 12. Access the Results File
Access the results filea. Analysis: Access Results /
Attach XDB / Result Entities.b. Click Select Results File.c. Select the file
Plot the resultsa. Results: Create / Quick Plotb. Select Stress Tensor for
fringe resultc. Select Displacement,
Translational for deformation result
d. Click Apply.
-- End of workshop --
a
b
c
d
WS2-24NAS120, Workshop 2, January 2003
WORKSHOP 3
Editing a Nastran Input File
NAS120, Workshop 3, January 2003 WS3-1
WS3-2NAS120, Workshop 3, January 2003
Problem Description The given Nastran input file contains several errors. Find the errors and correct them.
WS3-3NAS120, Workshop 3, January 2003
Workshop Objectives Become familiar with several of the most common errors in a Nastran
input file.
Learn to edit the Nastran file and submit the analysis job.
WS3-4NAS120, Workshop 3, January 2003
Exercise Steps1. Using a text editor, open the Nastran file truss_assembly_rev1.bdf and review it. 2. Submit the file to Nastran Solver.3. Review the .f06 file and find out why the job failed. 4. Edit the Nastran input file to correct the errors.5. Re-submit the file to Nastran Solver.6. Repeat the steps until the job completes successfully.
WS4-1
WORKSHOP 4
Stadium Truss
NAS120, Workshop 4, January 2003
WS4-2NAS120, Workshop 4, January 2003
WS4-3NAS120, Workshop 4, January 2003
Problem Description Three truss designs are presented on the following pages. Select
one design and analyze it. The truss is made from steel with E = 30 x 106 psi and ν = 0.3. The cross-sectional area is A = 4.516 in2. A 500-lb point load is applied at (60,168,0). The truss is bolted down at the Y=0 boundary. Model the truss with rod elements.
WS4-4NAS120, Workshop 4, January 2003
Workshop Objectives Build the truss model and analyze it. Determine the maximum
displacement and stresses. Is your design better than the arched-roof truss design presented in the Case Study?
Visualize the load path in the truss by plotting the rod element axial stresses. Follow the load from the load application point to the fixed base. Do the stresses make sense to you?
Become familiar with the .f06 file
WS4-5NAS120, Workshop 4, January 2003
Configuration #1
Problem Information
WS4-6NAS120, Workshop 4, January 2003
Configuration #2
WS4-7NAS120, Workshop 4, January 2003
Configuration #3
WS4-8NAS120, Workshop 4, January 2003
Suggested Exercise Steps1. Select a truss configuration to model2. Create a new database3. Create nodes and elements4. Create Material Properties 5. Create Physical Properties6. Apply Loads and Boundary Conditions7. Run the finite element analysis using MSC.Nastran8. Read the results into MSC.Patran9. Plot displacements and stresses10. Examine the .f06 file
WS4-9NAS120, Workshop 4, January 2003
Step 1. Choose a Truss Configuration
Configuration #1
WS4-10NAS120, Workshop 4, January 2003
Step 2. Create New Database
Create a new database called stadium_truss.db.
a. File / New.b. Enter stadium_truss as the
file name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.
g. Click OK.
a
d
e
f
gb c
WS4-11NAS120, Workshop 4, January 2003
Step 3. Create Nodes and Elements
Create the first node.a. Elements: Create / Node
/ Edit.b. Enter [420 0 0] for the
Node Location List.c. Click Apply.d. Click the Node size icon.
d d
a
b
c
WS4-12NAS120, Workshop 4, January 2003
Step 3. Create Nodes and Elements
Finish creating all 11 nodes.
WS4-13NAS120, Workshop 4, January 2003
Step 3. Create Nodes and Elements
Create an element between the first two nodes.
a. Elements: Create / Element / Edit.
b. Set the Shape to Bar, Topology to Bar 2, and Pattern to Standard.
c. Screen click on Node 1 and Node 2. An element is automatically created because Auto Execute is checked.
b
c
a
Node 1 Node 2
WS4-14NAS120, Workshop 4, January 2003
Finish creating all19 elements.
Step 3. Create Nodes and Elements
WS4-15NAS120, Workshop 4, January 2003
Step 4. Create Material Properties
Create an isotropic materiala. Materials: Create /
Isotropic / Manual Input.b. Under Material Name
input Steel.c. Click Input Properties,
then enter 30e6 for the elastic modulus and 0.3for the Poisson Ratio.
d. Click OK.e. Click Apply.
a
e
b
d
c
d
WS4-16NAS120, Workshop 4, January 2003
Step 5. Create Physical Properties
Create physical properties for the rod elements
a. Properties: Create / 1 D / Rod.
b. Under Property Set Name input Circular_Rod.
c. Click Input Properties. d. Select steel for the material. e. Enter 4.516 for the Area.f. Click OK.
a
b
c
d
e
f
WS4-17NAS120, Workshop 4, January 2003
Step 5. Create Physical Properties
Select application regiona. Click in the Select
Members Box.b. Select the Beam
element filter.c. Use the cursor to
drag across all elements
d. Click Add.e. Click Apply.
a
b
c
d
e
WS4-18NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Create the boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. For the set name, input
Fixed.c. Click Input Data.d. Enter <0 0 0> for
Translations and <0 0 0> for Rotations.
e. Click OK.
a
b
c
d
e
WS4-19NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter, select FEM.c. For the application
region, select the base of the truss.
d. Click Add.e. Click OK.
a
b
c
d
e
WS4-20NAS120, Workshop 4, January 2003
Finish creating the boundary condition
a. Click Apply.
Step 6. Apply Loads and Boundary Conditions
a
WS4-21NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Create another boundary condition to constrain DOFs not connected to any element
a. Loads/BCs: Create / Displacement / Nodal.
b. For the set name, input Unused_DOF.
c. Click Input Data.d. Enter < , ,0>for
Translations and <0 0 0> for Rotations.
e. Click OK.
a
b
c
d
e
WS4-22NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Apply the displacementsa. Click Select
Application Region.b. For the Geometry
Filter, select FEM.c. For the application
region, select the rest of the truss.
d. Click Add.e. Click OK.f. Click Apply.
a
c
d
e
f
b
WS4-23NAS120, Workshop 4, January 2003
Create a load named forcea. Loads/BCs: Create / Force /
Nodal.b. For the New Set Name,
enter Force.c. Click Input Data.d. Enter a force of <0 –500 0>.e. Click OK.
Step 6. Apply Loads and Boundary Conditions
a
b
c
d
e
WS4-24NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Apply the load forcea. Click Select
Application Region.b. For the Geometry
Filter, select FEM.c. For the application
region, select the node at the tip of the truss as shown.
d. Click Add.e. Click OK.
a
b
c
d
e
WS4-25NAS120, Workshop 4, January 2003
Finish creating the loada. Click Apply.
Step 6. Apply Loads and Boundary Conditions
a
WS4-26NAS120, Workshop 4, January 2003
Step 7. Nastran Analysis
Analyze the modela. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Typec. Choose Linear Static.d. Click OK.e. Click Apply.
b
a
e
c
d
WS4-27NAS120, Workshop 4, January 2003
Step 8. Read Results File into Patran
Attach the results filea. Analysis: Access Results
/ Attach XDB / Result Entities.
b. Click Select Results File.
c. Choose the results file stadium_truss.xdb.
d. Click OK.e. Click Apply.
e
a
b
c
d
WS4-28NAS120, Workshop 4, January 2003
Step 9. Plot Displacements and Stresses
Create a quick plota. Results: Create / Quick
Plot.b. Select Stress Tensor
and X Component as the Fringe Result.
c. Select Displacements, Translational as the deformation result.
d. Click Apply. e. Record the maximum
displacement and maximum and minimum stress.
Max displacement = ______
Max X Stress = ______
Min X Stress = ______
a
b
c
d
WS4-29NAS120, Workshop 4, January 2003
Step 9. Plot Displacements and Stresses
a
b
d
e
f
Create a fringe plota. Results: Create / Fringe.b. Select Stress Tensor as
the Fringe Result.c. Select X Component as
the Fringe Result Quantity.
d. Click on the Plot Options Icon.
e. Set the Averaging Definition Domain to None.
f. Click Apply.
c
WS4-30NAS120, Workshop 4, January 2003
Step 9. Plot Displacements and Stresses
View the un-averaged resultsa. Note the change in
maximum stress.
Un-averaged Max Stress =
____________________
Un-averaged Min Stress =
____________________
WS4-31NAS120, Workshop 4, January 2003
Step 10. Examine the .f06 File
Examine the .f06 filea. Open the directory in
which your database is saved.
b. Find the file titled stadium_truss.f06 .
c. Open this file with any text editor.
d. Verify that the displacement and stress results agree with the graphical results shown in Patran.
WS4-32NAS120, Workshop 4, January 2003
Step 1. Choose a Truss Configuration
Configuration #2
WS4-33NAS120, Workshop 4, January 2003
Step 2. Create New Database
Create a new database called stadium_truss.db.
a. File / New.b. Enter stadium_truss as the
file name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.
g. Click OK.
a
d
e
f
gb c
WS4-34NAS120, Workshop 4, January 2003
Step 3. Create Nodes and Elements
Create the first node.a. Elements: Create / Node
/ Edit.b. Enter [420 0 0] for the
Node Location List.c. Click Apply.d. Click the Node Size icon.
d d
a
b
c
WS4-35NAS120, Workshop 4, January 2003
Step 3. Create Nodes and Elements
Finish creating all 9 nodes.
WS4-36NAS120, Workshop 4, January 2003
Step 3. Create Nodes and Elements
Create an element between the first two nodes.
a. Elements: Create / Element / Edit.
b. Set the Shape to Bar, Topology to Bar 2, and Pattern to Standard.
c. Screen click on Node 1 and Node 2. An element is automatically created because Auto Execute is checked.
b
c
a
Node 1 Node 2
WS4-37NAS120, Workshop 4, January 2003
Finish creating all15 elements.
Step 3. Create Nodes and Elements
WS4-38NAS120, Workshop 4, January 2003
Step 4. Create Material Properties
Create an isotropic materiala. Materials: Create /
Isotropic / Manual Input.b. Under Material Name
input Steel.c. Click Input Properties,
then enter 30e6 for the elastic modulus and 0.3for the Poisson Ratio.
d. Click OK.e. Click Apply.
a
e
b
d
c
d
WS4-39NAS120, Workshop 4, January 2003
Step 5. Create Physical Properties
Create physical properties for the rod elements
a. Properties: Create / 1 D / Rod.
b. Under Property Set Name input Circular_Rod.
c. Click Input Properties. d. Select steel for the material. e. Enter 4.516 for the Area.f. Click OK.
a
b
c
d
e
f
WS4-40NAS120, Workshop 4, January 2003
Step 5. Create Physical Properties
Select application regiona. Click in the Select
Members Box.b. Select the Beam
element filter.c. Use the cursor to
drag across all elements
d. Click Add.e. Click Apply.
a
b
c
d
e
WS4-41NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Create the boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. For the set name, input
Fixed.c. Click Input Data.d. Enter <0 0 0> for
Translations and <0 0 0> for Rotations.
e. Click OK.
a
b
c
d
e
WS4-42NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter, select FEM.c. For the application
region, select the base of the truss.
d. Click Add.e. Click OK.
a
b
c
d
e
WS4-43NAS120, Workshop 4, January 2003
Finish creating the boundary condition
a. Click Apply.
Step 6. Apply Loads and Boundary Conditions
a
WS4-44NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Create another boundary condition to constrain DOFs not connected to any element
a. Loads/BCs: Create / Displacement / Nodal.
b. For the set name, input Unused_DOF.
c. Click Input Data.d. Enter < , ,0>for
Translations and <0 0 0> for Rotations.
e. Click OK.
a
b
c
d
e
WS4-45NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Apply the displacementsa. Click Select
Application Region.b. For the Geometry
Filter, select FEM.c. For the application
region, select the rest of the truss.
d. Click Add.e. Click OK.f. Click Apply.
a
c
d
ef
b
WS4-46NAS120, Workshop 4, January 2003
Create a load named forcea. Loads/BCs: Create / Force /
Nodal.b. For the New Set Name,
enter Force.c. Click Input Data.d. Enter a force of <0 –500 0>.e. Click OK.
Step 6. Apply Loads and Boundary Conditions
a
b
c
d
e
WS4-47NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Apply the load forcea. Click Select
Application Region.b. For the Geometry
Filter, select FEM.c. For the application
region, select the node below the tip of the truss as shown.
d. Click Add.e. Click OK.
a
b
c
d
e
WS4-48NAS120, Workshop 4, January 2003
Finish creating the loada. Click Apply.
Step 6. Apply Loads and Boundary Conditions
a
WS4-49NAS120, Workshop 4, January 2003
Step 7. Nastran Analysis
Analyze the modela. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Typec. Choose Linear Static.d. Click OK.e. Click Apply.
b
a
e
c
d
WS4-50NAS120, Workshop 4, January 2003
Step 8. Read Results File into Patran
Attach the results filea. Analysis: Access Results
/ Attach XDB / Result Entities.
b. Click Select Results File.
c. Choose the results file stadium_truss.xdb.
d. Click OK.e. Click Apply.
e
a
b
c
d
WS4-51NAS120, Workshop 4, January 2003
Step 9. Plot Displacements and Stresses
Create a quick plota. Results: Create / Quick
Plot.b. Select Stress Tensor
and X Component as the Fringe Result.
c. Select Displacements, Translational as the deformation result.
d. Click Apply. e. Record the maximum
displacement and maximum and minimum stress.
Max displacement = ______
Max X Stress = ______
Min X Stress = ______
a
b
c
d
WS4-52NAS120, Workshop 4, January 2003
Step 9. Plot Displacements and Stresses
a
b
d
e
f
Create a fringe plota. Results: Create / Fringe.b. Select Stress Tensor as
the Fringe Result.c. Select X Component as
the Fringe Result Quantity.
d. Click on the Plot Options Icon.
e. Set the Averaging Definition Domain to None.
f. Click Apply.
c
WS4-53NAS120, Workshop 4, January 2003
Step 9. Plot Displacements and Stresses
View the un-averaged resultsa. Note the change in
maximum stress.
Un-averaged Max Stress =
____________________
Un-averaged Min Stress =
____________________
WS4-54NAS120, Workshop 4, January 2003
Step 10. Examine the .f06 File
Examine the .f06 filea. Open the directory in
which your database is saved.
b. Find the file titled stadium_truss.f06 .
c. Open this file with any text editor.
d. Verify that the displacement and stress results agree with the graphical results shown in Patran.
WS4-55NAS120, Workshop 4, January 2003
Step 1. Choose a Truss Configuration
Configuration #3
WS4-56NAS120, Workshop 4, January 2003
Step 2. Create New Database
Create a new database called stadium_truss.db.
a. File / New.b. Enter stadium_truss as the
file name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.
g. Click OK.
a
d
e
f
gb c
WS4-57NAS120, Workshop 4, January 2003
Step 3. Create Nodes and Elements
Create the first node.a. Elements: Create / Node
/ Edit.b. Enter [420 0 0] for the
Node Location List.c. Click Apply.d. Click the Node Size icon.
d d
a
b
c
WS4-58NAS120, Workshop 4, January 2003
Step 3. Create Nodes and Elements
Finish creating all 18 nodes.
WS4-59NAS120, Workshop 4, January 2003
Step 3. Create Nodes and Elements
Create an element between the first two nodes.
a. Elements: Create / Element / Edit.
b. Set the Shape to Bar, Topology to Bar 2, and Pattern to Standard.
c. Screen click on Node 1 and Node 2. An element is automatically created because Auto Execute is checked.
b
c
a
Node 1 Node 2
WS4-60NAS120, Workshop 4, January 2003
Finish creating all 34 elements.
Step 3. Create Nodes and Elements
WS4-61NAS120, Workshop 4, January 2003
Step 4. Create Material Properties
Create an isotropic materiala. Materials: Create /
Isotropic / Manual Input.b. Under Material Name
input Steel.c. Click Input Properties,
then enter 30e6 for the Elastic Modulus and 0.3for the Poisson Ratio.
d. Click OK.e. Click Apply.
a
e
b
d
c
d
WS4-62NAS120, Workshop 4, January 2003
Step 5. Create Physical Properties
Create physical properties for the rod elements
a. Properties: Create / 1 D / Rod.
b. Under Property Set Name input Circular_Rod.
c. Click Input Properties. d. Select steel for the material. e. Enter 4.516 for the Area.f. Click OK.
a
b
c
d
e
f
WS4-63NAS120, Workshop 4, January 2003
Step 5. Create Physical Properties
Select application regiona. Click in the Select
Members Box.b. Select the Beam
element filter.c. Use the cursor to
drag across all elements
d. Click Add.e. Click Apply.
a
b
c
d
e
WS4-64NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Create the boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. For the set name, input
Fixed.c. Click Input Data.d. Enter <0 0 0> for
Translations and <0 0 0> for Rotations.
e. Click OK.
a
b
c
d
e
WS4-65NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter, select FEM.c. For the application
region, select the base of the truss.
d. Click Add.e. Click OK.
a
b
c
d
e
WS4-66NAS120, Workshop 4, January 2003
Finish creating the boundary condition
a. Click Apply.
Step 6. Apply Loads and Boundary Conditions
a
WS4-67NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Create another boundary condition to constrain DOFs not connected to any element
a. Loads/BCs: Create / Displacement / Nodal.
b. For the set name, input Unused_DOF.
c. Click Input Data.d. Enter < , ,0>for
Translations and <0 0 0> for Rotations.
e. Click OK.
a
b
c
d
e
WS4-68NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Apply the displacementsa. Click Select
Application Region.b. For the Geometry
Filter, select FEM.c. For the application
region, select the rest of the truss.
d. Click Add.e. Click OK.f. Click Apply.
a
c
d
e
f
b
WS4-69NAS120, Workshop 4, January 2003
Create a load named forcea. Loads/BCs: Create / Force /
Nodal.b. For the New Set Name,
enter Force.c. Click Input Data.d. Enter a force of <0 –500 0>.e. Click OK.
Step 6. Apply Loads and Boundary Conditions
a
b
c
d
e
WS4-70NAS120, Workshop 4, January 2003
Step 6. Apply Loads and Boundary Conditions
Apply the load forcea. Click Select
Application Region.b. For the Geometry
Filter, select FEM.c. For the application
region, select the node at the tip of the truss as shown.
d. Click Add.e. Click OK.
a
b
c
d
e
WS4-71NAS120, Workshop 4, January 2003
Finish creating the loada. Click Apply.
Step 6. Apply Loads and Boundary Conditions
a
WS4-72NAS120, Workshop 4, January 2003
Step 7. Nastran Analysis
Analyze the modela. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Typec. Choose Linear Static.d. Click OK.e. Click Apply.
b
a
e
c
d
WS4-73NAS120, Workshop 4, January 2003
Step 8. Read Results File into Patran
Attach the results filea. Analysis: Access Results
/ Attach XDB / Result Entities.
b. Click Select Results File.
c. Choose the results file stadium_truss.xdb.
d. Click OK.e. Click Apply.
e
a
b
c
d
WS4-74NAS120, Workshop 4, January 2003
Step 9. Plot Displacements and Stresses
Create a quick plota. Results: Create / Quick
Plot.b. Select Stress Tensor
and X Component as the Fringe Result.
c. Select Displacements, Translational as the deformation result.
d. Click Apply. e. Record the maximum
displacement and maximum and minimum stress.
Max displacement = ______
Max X Stress = ______
Min X Stress = ______
a
b
c
d
WS4-75NAS120, Workshop 4, January 2003
Step 9. Plot Displacements and Stresses
Create a fringe plota. Results: Create / Fringe.b. Select Stress Tensor as
the Fringe Result.c. Select X Component as
the Fringe Result Quantity.
d. Click on the Plot Options Icon.
e. Set the Averaging Definition Domain to None.
f. Click Apply.
a
b
d
e
f
c
WS4-76NAS120, Workshop 4, January 2003
Step 9. Plot Displacements and Stresses
View the un-averaged resultsa. Note the change in
maximum stress.
Un-averaged Max Stress =
____________________
Un-averaged Min Stress =
____________________
WS4-77NAS120, Workshop 4, January 2003
Step 10. Examine the .f06 File
Examine the .f06 filea. Open the directory in
which your database is saved.
b. Find the file titled stadium_truss.f06 .
c. Open this file with any text editor.
d. Verify that the displacement and stress results agree with the graphical results shown in Patran.
WS4-78NAS120, Workshop 4, January 2003
WORKSHOP 5
Coordinate Systems
WS5-1NAS120, Workshop 5, January 2003
WS5-2NAS120, Workshop 5, January 2003
Problem Description Create two coordinate systems Use one coordinate system to define the model Use the second coordinate system to define the displacement
coordinate system
WS5-3NAS120, Workshop 5, January 2003
Workshop Objectives Understand the difference between Reference Coordinate System and
Displacement Coordinate System
WS5-4NAS120, Workshop 5, January 2003
Suggested Exercise Steps1. Create a new database 2. Create a square surface3. Mesh the surface to create 2D elements. 4. Create material properties. 5. Create physical properties.6. Create a Nastran input file7. Review the Nastran input file8. Create two coordinate systems9. Modify the nodal coordinate systems10. Create a new Nastran input file11. Review the new Nastran input file
WS5-5NAS120, Workshop 5, January 2003
a
b c
d
f
g
Step 1. Create New Database
Create a new database called coord_system.db
a. File / New.b. Enter coord_system as the
file name.c. Click OK.d. Choose Tolerance Based on
Model.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
e
WS5-6NAS120, Workshop 5, January 2003
Step 2. Create Geometry
Create a 1 x 1 surfacea. Geometry : Create /
Surface / XYZb. Click Apply.
a
b
WS5-7NAS120, Workshop 5, January 2003
Step 3. Mesh the Surface
Mesh the surfacea. Elements: Create / Mesh
/ Surfaceb. Screen pick the surfacec. Enter 0.3 as the Global
Edge Lengthd. Click Apply.
d
a
b
c
d
WS5-8NAS120, Workshop 5, January 2003
Step 4. Create Material Properties
a
c
b
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter steel for the Material
Name.c. Click Input Properties.d. Enter 30e6 for the Elastic
Set Name.c. Click Input Properties.d. Click on steel to select ite. Enter 0.1 as the thicknessf. Click OK.
a
b
c
d
e
f
WS5-10NAS120, Workshop 5, January 2003
Apply the physical propertiesa. Click in the Select
Members box.b. Screen pick the surfacec. Click Add.d. Click Apply.
ac
d
Step 5. Create Physical Properties
b
WS5-11NAS120, Workshop 5, January 2003
Step 6. Create a Nastran Input File
Create a Nastran input filea. Analysis: Analyze / Entire
Model / Analysis Deckb. Click Apply.
a
b
WS5-12NAS120, Workshop 5, January 2003
Step 7. Review the Nastran Input File
Examine the Nastran input filea. Open the directory in which your
database is saved.b. Find the file titled
coord_system.bdfc. Open this file with any text editor
and review it.d. Notice that field 3 and field 7 of the
GRID entries are blank which means the basic coordinate system (coordinate system 0) is used here.
Field 3 Field 7
WS5-13NAS120, Workshop 5, January 2003
Step 8. Create a new coordinate system
Create a new coordinate system
a. Geometry : Create / Coord / Euler
b. Enter 100 as the Coord ID
c. Screen pick point 3 as the origin
a
bc
WS5-14NAS120, Workshop 5, January 2003
Step 8. Create a second coordinate system
Create another coordinate systema. Geometry : Create / Coord
/ Eulerb. Enter 200 as the Coord IDc. Click Rotation Parametersd. Enter 45 as the angle of
rotation about the z axise. Click OKf. Click in the Origin boxg. Screen pick point 4 as the
origin
a
b
c
d
ef
g
WS5-15NAS120, Workshop 5, January 2003
Step 9. Modify the nodal coordinate frames
Modify the Reference Coordinate Frame
a. Elements: Modify / Node / Edit
b. Check the Refer. Coordinate Frame box
c. Rectangular select all nodes
d. Click in the Refer. Coordinate Frame box
e. Screen pick coord frame 100
f. Click Apply.
d
a
bc
d
e
WS5-16NAS120, Workshop 5, January 2003
Step 9. Modify the nodal coordinate frames
Modify the Analysis Coordinate Frame
a. Elements: Modify / Node / Edit
b. Uncheck the Refer. Coordinate Frame box and check the Analysis Coordinate Frame box
c. Rectangular select the lower row of nodes
d. Click in the Analysis Coordinate Frame box
e. Screen pick coord frame 200
f. Click Apply.
d
a
b
c
d
e
WS5-17NAS120, Workshop 5, January 2003
Step 10. Create a new Nastran Input File
Create a Nastran input filea. Analysis: Analyze / Entire
Model / Analysis Deckb. Enter coord_system_rev1
as the Job Namec. Click Apply.
a
b
c
WS5-18NAS120, Workshop 5, January 2003
Step 11. Review the new Nastran Input File
Examine the Nastran input filea. Open the directory in which your
database is saved.b. Find the file titled
coord_system_rev1.bdfc. Open this file with any text editor
and review it.d. Notice that field 3 and field 7 of the
GRID entries have been changed.Field 3 Field 7
WS6-1
WORKSHOP 6
BRIDGE TRUSS
NAS120, Workshop 6, January 2003
WS6-2NAS120, Workshop 6, January 2003
WS6-3NAS120, Workshop 6, January 2003
Problem Description The preliminary design of a steel truss bridge has just been finished.
You are asked to evaluate the structural integrity of this bridge. The truss is made from steel with E = 30 x 106 psi and ν = 0.3 The truss members are I-beams with H = 18 in, W = 12 in, Tf = 0.5 in,
and Tw = 0.5 in The bridge needs to be able to support a 23,000 lb truck traveling over
it. The truck weight is supported by two planar trusses. Model one planar truss with half the truck weight applied to it.
One end of the truss is pinned while the other end is free to slide horizontally.
WS6-4NAS120, Workshop 6, January 2003
11,500 lb
(Subcase 1)
x
y
11,500 lb
(Subcase 2)
WS6-5NAS120, Workshop 6, January 2003
Workshop Objectives Learn to mesh line geometry to generate CBAR elements
Become familiar with setting up the CBAR orientation vector and section properties
Learn to set up multiple load cases
Learn to view the different CBAR stress components in Patran
WS6-6NAS120, Workshop 6, January 2003
Suggested Exercise Steps1. Create a new database. 2. Create a geometry model of the truss using the table on the previous page. 3. Use Mesh Seeds to define the mesh density.4. Create a finite element mesh. 5. Define material properties. 6. Create Physical Properties using the beam library. 7. Create boundary conditions.8. Create loads.9. Set up load cases.10. Run the finite element analysis using MSC.Nastran.11. Plot displacements and stresses.
WS6-7NAS120, Workshop 6, January 2003
a
b c
d
e
f
g
Step 1. Create New Database
Create a new database called bridge_truss.db
a. File / New.b. Enter bridge_truss as the
file name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
WS6-8NAS120, Workshop 6, January 2003
Step 2. Create Geometry
Create the first pointa. Geometry: Create / Point /
XYZ.b. Enter [0 0 0] for the Point
Coordinate List.c. Click Apply.d. Turn Point size on.
a
b
c
d
WS6-9NAS120, Workshop 6, January 2003
Step 2. Create Geometry
Finish creating all 12 points.
WS6-10NAS120, Workshop 6, January 2003
Step 2. Create Geometry
Create curves to represent the truss members
a. Geometry: Create / Curve / Point.
b. Screen pick the bottom left point as shown.
c. Screen pick the top left point. A curve is automatically created because Auto Execute is checked.
a
b
c
WS6-11NAS120, Workshop 6, January 2003
Step 2. Create Geometry
Finish creating all 21 curves.
WS6-12NAS120, Workshop 6, January 2003
Step 3. Create Mesh Seeds
Create a uniform mesh seeda. Elements: Create / Mesh
Seed / Uniform.b. Enter 6 for the Number of
Elements.c. Click in the Curve List box.d. Rectangular pick the
bottom of the truss.
a
b
c
d
WS6-13NAS120, Workshop 6, January 2003
Step 3. Create Mesh Seeds
Create another mesh seeda. Elements: Create / Mesh
Seed / Uniform.b. Enter 2 for the Number of
Elements.c. Click in the Curve List
box. d. Rectangular pick the rest
of the truss, as shown.
a
b
c
d
WS6-14NAS120, Workshop 6, January 2003
Step 4. Create Mesh
Create a finite element mesha. Elements: Create / Mesh /
Curve.b. Set Topology to Bar2.c. Click in the Curve List box.d. Rectangular pick all of the
curves as shown.e. Click Apply.
a
b
c
d
e
WS6-15NAS120, Workshop 6, January 2003
Step 4. Create Mesh
Equivalence the modela. Elements: Equivalence / All
/ Tolerance Cube.b. Click Apply.
a
b
WS6-16NAS120, Workshop 6, January 2003
Step 5. Create Material Properties
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter steel as the Material
Name.c. Click Input Properties.d. Enter 30e6 for the elastic
modulus and 0.3 for the Poisson Ratio.
e. Click OK. f. Click Apply.
a
b
c
d
fe
WS6-17NAS120, Workshop 6, January 2003
Step 6. Create Physical Properties
Create element propertiesa. Properties: Create / 1D /
Beam.b. Enter i_beam as the
Property Set Name.c. Click Input Properties.d. Select steel as the
material.e. Click on the Beam Library
button.
a
b
ed
c
WS6-18NAS120, Workshop 6, January 2003
Step 6. Create Physical Properties
Define the beam section a. Enter i_section for the
New Section Name.b. Enter the appropriate
values to define the beam’s dimensions .
c. Click Calculate/Displayto view the beam section and its section properties.
d. After verifying that the section is correct, Click OK.
a
b
c
d
WS6-19NAS120, Workshop 6, January 2003
Step 6. Create Physical Properties
Define the bar orientation a. Enter <1 2 0> for the
Bar Orientation.b. Click OK. Note:
Any vector in the XY plane that is not parallel to any truss member would work as well.
a
b
WS6-20NAS120, Workshop 6, January 2003
Step 6. Create Physical Properties
Select application regiona. Click in the Select
Members box.b. Rectangular pick the
entire truss as shown.c. Click Add.d. Click Apply.
b
ac
d
WS6-21NAS120, Workshop 6, January 2003
Step 6. Create Physical Properties
Verify the beam sectiona. Display-
Load/BC/Element Props.
b. Set Beam Display to 3D:Full-Span.
c. Shade the model.d. Rotate the model
and zoom in to verify that the I-beams are oriented correctly.
e. Return to the front view.
f. Set Beam Display back to 1D:Line.
a
b
c
d
e
f
WS6-22NAS120, Workshop 6, January 2003
Step 7. Create Boundary Conditions
Create a boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter left_side as the New
Set Name.c. Click Input Data.d. Enter <0 0 0> for
Translations and <0,0, > for Rotations.
e. Click OK.
a
b
d
e
c
WS6-23NAS120, Workshop 6, January 2003
Step 7. Create Boundary Conditions
Apply the boundary conditiona. Reset graphics.b. Click Select
Application Region.c. Select the bottom left
point as the application region.
d. Click Add.e. Click OK. f. Click Apply.
be
f
c d
a
WS6-24NAS120, Workshop 6, January 2003
Step 7. Create Boundary Conditions
Create another boundary condition
a. Loads/BCs: Create / Displacement / Nodal.
b. Enter right_side as the New Set Name.
c. Click Input Data.d. Enter < ,0,0> for
Translations and <0,0, > for Rotations.
e. Click OK.
a
b
c
d
e
WS6-25NAS120, Workshop 6, January 2003
Step 7. Create Boundary Conditions
Apply the boundary conditiona. Click Select
Application Region.b. Select the bottom
right point as the application region.
c. Click Add.d. Click OK. e. Click Apply.
a
bc
d
e
WS6-26NAS120, Workshop 6, January 2003
Step 8. Create Loads
Create the mid span loada. Loads/BCs: Create / Force /
Nodal.b. Enter mid_span_load as
the New Set Name.c. Click Input Data.d. Enter <0 –11500 0> for the
Force.e. Click OK.
c
b
a
d
e
WS6-27NAS120, Workshop 6, January 2003
Apply the mid span loada. Click Select Application
Region.b. Set the geometry filter to
FEM.c. For the application region
select the node in the middle of the span to the right of the center, as shown.
d. Click Add.e. Click OK.f. Click Apply.
Step 8. Create Loads
a
cd
e
f
b
WS6-28NAS120, Workshop 6, January 2003
Step 8. Create Loads
Create the truss joint loada. Loads/BCs: Create / Force /
Nodal.b. Enter truss_joint_load as
the New Set Name.c. Click Input Data.d. Enter <0 –11500 0> for the
Force.e. Click OK.
a
b
c
d
e
WS6-29NAS120, Workshop 6, January 2003
Step 8. Create Loads
Apply the loada. Click Select Application
Region.b. Set the geometry filter to
Geometry.c. For the application
region select the point at the center of the bridge, as shown.
d. Click Add.e. Click OK.f. Click Apply.
a
b
cd
e
f
WS6-30NAS120, Workshop 6, January 2003
Step 9. Set Up Load Cases
Create a load casea. Load Cases: Create.b. Enter mid_span as the
Load Case Name.c. Click Assign/Prioritize
Loads/BCs.d. Click on Displ_left_side,
Displ_right_side, andForce_mid_span_load to add them to the Load Case.
e. Click OK.f. Click Apply.
a
b
c
d
e
f
WS6-31NAS120, Workshop 6, January 2003
Step 9. Set Up Load Cases
Create another load casea. Load Cases: Create.b. Enter truss_joint as the
Load Case Name.c. Click Assign/Prioritize
Loads/BCs.d. Click on Displ_left_side,
Displ_right_side, andForce_truss_joint_load to add them to the Load Case.
e. Click OK.f. Click Apply.
a
b
c
d
e
f
WS6-32NAS120, Workshop 6, January 2003
Step 10. Run Linear Static Analysis
Choose the analysis typea. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Type.c. Choose Linear Static.d. Click OK.
a
b
d
c
WS6-33NAS120, Workshop 6, January 2003
Step 10. Run Linear Static Analysis
Analyze the modela. Analysis: Analyze / Entire
Model / Full Run.b. Click Subcase Select.c. Click Unselect All.d. Click on mid_span and
truss_joint to add them to the Subcases Selected list.
e. Click OK.f. Click Apply.
a
b
c
d
e f
WS6-34NAS120, Workshop 6, January 2003
Step 11. Plot Displacements and Stresses
Attach the results filea. Analysis: Access Results /
Attach XDB / Result Entities.
b. Click Select Results File.c. Choose the results file
bridge_truss.xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS6-35NAS120, Workshop 6, January 2003
Step 11. Plot Displacements and Stresses
Create a deformation plot for the mid span result case
a. Results: Create / Deformation.
b. Select the Mid Span Result Case.
c. Select Displacements, Translational as the Deformation Result.
d. Check Animate.e. Click Apply.f. Record the maximum
deformation.g. Click Stop Animation.
Max Deformation =
____________
a
c
d
e
b
WS6-36NAS120, Workshop 6, January 2003
Step 11. Plot Displacements and Stresses
Create a Fringe Plot of X Component Axial Stress
a. Results: Create / Fringe.
b. Select the Mid Span Result Case.
c. Select Stress Tensor, Axial as the Fringe Result.
d. Select X Componentas the Fringe Result Quantity.
e. Click on the Plot Options icon.
f. Set the Averaging Definition Domain to None.
g. Click Apply.
b
c
d
a
e
f
g
WS6-37NAS120, Workshop 6, January 2003
Step 11. Plot Displacements and Stresses
View the resultsa. Record the maximum
and minimum X component axial stress.
Max X Axial Stress =
_________________
Min X Axial Stress =
__________________
WS6-38NAS120, Workshop 6, January 2003
Step 11. Plot Displacements and Stresses
Create Fringe Plots of X Component Bending Stress
a. Results: Create / Fringe.b. Click Select Results.c. Select the Mid Span
Result Case.d. Select Stress Tensor,
Bending as the Fringe Result.
e. Select X Component as the Fringe Result Quantity.
f. Click Apply.g. Repeat the procedure for
positions D,E, and F, by clicking Position and selecting them from the position list.
h. Record the overall maximum and minimum stresses.
Min Stress = _________
Max Stress = _________
a
b
c
d
e
f
g
WS6-39NAS120, Workshop 6, January 2003
Step 11. Plot Displacements and Stresses
Create Fringe Plots of maximum and minimum combined bar stresses
a. Results: Create / Fringe.
b. Select the Mid Span Result Case.
c. Select Bar Stresses, Maximum Combined as the Fringe Result.
d. Click Apply.e. Record the Maximum
combined stress. Max Stress= _______
f. Repeat the procedure with Bar Stresses, Minimum Combined as the Fringe Result and record the Minimum Stress. Min Stress = _______
a
b
c
d
WS6-40NAS120, Workshop 6, January 2003
Step 11. Plot Displacements and Stresses
Create a deformation plot for the truss joint result case
a. Results: Create / Deformation.
b. Select the Truss Joint Result Case.
c. Select Displacements, Translational as the Deformation Result.
d. Check Animate.e. Reset Graphics.f. Click Apply.g. Record the maximum
deformation.h. Click Stop Animation.
Max Deformation =
____________
a
c
d
e
b
f
WS6-41NAS120, Workshop 6, January 2003
Step 11. Plot Displacements and Stresses
Create a Fringe Plot of X Component Axial Stress
a. Results: Create / Fringe.
b. Select the Truss Joint Result Case.
c. Select Stress Tensor, Axial as the Fringe Result.
d. Select X Componentas the Fringe Result Quantity.
e. Click on the Plot Options icon.
f. Set the Averaging Definition Domain to None.
g. Click Apply.
b
c
d
a
e
f
g
WS6-42NAS120, Workshop 6, January 2003
Step 11. Plot Displacements and Stresses
View the resultsa. Record the maximum
and minimum X component axial stress.
Max X Axial Stress =
_________________
Min X Axial Stress =
__________________
WS6-43NAS120, Workshop 6, January 2003
Step 11. Plot Displacements and Stresses
Create Fringe Plots of X Component Bending Stress
a. Results: Create / Fringe.b. Click Select Results.c. Select the Truss Joint
Result Case.d. Select Stress Tensor,
Bending as the Fringe Result.
e. Select X Component as the Fringe Result Quantity.
f. Click Apply.g. Repeat the procedure for
positions D,E, and F, by clicking Position and selecting them from the position list.
h. Record the overall maximum and minimum stresses.
Min Stress = _________
Max Stress = _________
a
b
c
d
e
f
g
WS6-44NAS120, Workshop 6, January 2003
Step 11. Plot Displacements and Stresses
Create Fringe Plots of maximum and minimum combined bar stresses
a. Results: Create / Fringe.
b. Select the Truss Joint Result Case.
c. Select Bar Stresses, Maximum Combined as the Fringe Result.
d. Click Apply.e. Record the Maximum
combined stress. Max Stress= _______
f. Repeat the procedure with Bar Stresses, Minimum Combined as the Fringe Result and record the Minimum Stress.Min Stress = _______
a
b
c
d
WS7-1
WORKSHOP 7
FULLY STRESSED BEAM
NAS120, Workshop 7, January 2003
P
WS7-2NAS120, Workshop 7, January 2003
WS7-3NAS120, Workshop 7, January 2003
Problem Description To minimize the the amount of material in a beam, one may
vary the dimension of the cross sections in order to maintain a constant bending stress along the beam. A beam in this condition is called a fully stressed beam.
Analyze the following machine component which has been designed to a fully stressed condition.
P
x
h
WS7-4NAS120, Workshop 7, January 2003
Problem Description (cont.) The length of the beam is 12 in. The width of the beam is 0.5 in.
The height of the beam is defined as:
The beam is made from titanium alloy Ti-6Al-4V with E = 16 x 106
psi and ν = 0.31.
The tip load is 500 lb.
Model the cantilever beam with CBEAM elements.
x=h
x=h
.5.0w in=
WS7-5NAS120, Workshop 7, January 2003
Workshop Objectives Build the beam model and analyze it. Determine the maximum
displacement.
Verify that the bending stress is constant throughout the beam.
Compare analysis results to theoretical results.
Examine the .f06 file.
WS7-6NAS120, Workshop 7, January 2003
Suggested Exercise Steps
1. Create a new database and name it beam.db. 2. Create a curve to represent the geometry.3. Mesh the curve to generate elements. Create at least 20 elements to
capture the variation in beam cross section.4. Create material properties.5. Create a field which represents the height of the beam.
Hint: use the expression 0.001 + to avoid singularity at the tip of the beam.
6. Plot the field to visually verify it.7. Create physical properties using the beam library.8. Change the display to 3D Full Span to inspect the cross sections.
Return the display to 1D line when you are done.9. Apply Loads and Boundary Conditions. 10. Run the finite element analysis using MSC.Nastran. 11. Read the results into MSC.Patran.12. Plot displacements and stresses.13. Examine the .f06 file.
x
WS7-7NAS120, Workshop 7, January 2003
a
b c
d
f
g
Step 1. Create New Database
Create a new database called beam.db
a. File / New.b. Enter beam as the file name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
e
WS7-8NAS120, Workshop 7, January 2003
Step 2. Create a Curve
Create a curvea. Geometry: Create /
Curve / XYZ.b. Enter <12 0 0> for the
Vector Coordinates list.c. Click Apply.
b
c
a
WS7-9NAS120, Workshop 7, January 2003
Step 3. Mesh the Curve
Create a mesh seeda. Elements: Create / Mesh
Seed / Uniform.b. Enter 20 for the number
of elements.c. Select the curve.
a
b
c
WS7-10NAS120, Workshop 7, January 2003
Step 3. Mesh the Curve
Create a mesha. Elements: Create /
Mesh / Curve.b. Select the curve.c. Click Apply.
a
b
c
WS7-11NAS120, Workshop 7, January 2003
Step 4. Create Material Properties
a
c
b
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter Ti-6Al-4V for the
Material Name.c. Click Input Properties.d. Enter 16e6 for the Elastic
Modulus.e. Enter 0.31 for the Poisson
Ratio.f. Click OK. g. Click Apply.
d
gf
e
WS7-12NAS120, Workshop 7, January 2003
Step 5. Create a Field
Create a field for the beam height.a. Fields: Create / Spatial /
PCL Function.b. Enter height for the Field
Name.c. Enter 0.001+SQRT(‘X) for
the Scalar Function.d. Click Apply.
a
b
c
d
WS7-13NAS120, Workshop 7, January 2003
Step 6. Plot the Field
Plot the field for the beam height.
a. Fields: Show.b. Select height as the
Field To Show.c. Click Specify Range.d. Enter 12 for the
c. Click on the right arrow and then select the solid rectangular section.
d. Enter 0.5 for the width.e. Select height as the field
for the height.f. Click OK.g. Click OK in the Input
Properties form.
a
b
c
d
e
f
g
WS7-16NAS120, Workshop 7, January 2003
Apply the physical propertiesa. Properties: Create / 1D
/ Beam.b. Click in the Select
Members box.c. Screen pick to select
the curve.d. Click Add.e. Click Apply.
a
b
c
d
e
Step 7. Create Physical Properties
WS7-17NAS120, Workshop 7, January 2003
Step 8. Display Beam Properties
Display the beam propertiesa. Display:
Load/BC/Elem. Props.b. Set the Beam Display
to 3D: Full Span + Offsets
c. Click Apply.d. Click on the Iso 1 View
Icon.e. After verifying the
beam section, reset the Beam Display to 1D:Line and click Apply and Cancel.
f. Click on the Front View icon.
a
b
c
df
e
WS7-18NAS120, Workshop 7, January 2003
Step 9. Apply Loads and Boundary Conditions
Create a boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter right_end as the
New Set Name.c. Click Input Data.d. Enter <0 0 0> for
Translations and Rotations. e. Click OK.
b
c
d
e
a
WS7-19NAS120, Workshop 7, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Select the point at the right end of the beam, as shown.
d. Click Add.e. Click OK. f. Click Apply.
ae
f
d
b
Step 9. Apply Loads and Boundary Conditions
c
WS7-20NAS120, Workshop 7, January 2003
Step 9. Apply Loads and Boundary Conditions
Create the loada. Loads/BCs: Create / Force
/ Nodal.b. Enter tip_load as the New
Set Name.c. Click Input Data.d. Enter <0 –500 0> for Force. e. Click OK.
b
c
d
e
a
WS7-21NAS120, Workshop 7, January 2003
Step 9. Apply Loads and Boundary Conditions
Apply the loada. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Select the point at the left end of the beam, as shown.
d. Click Add.e. Click OK. f. Click Apply.
ae
f
d
b
c
WS7-22NAS120, Workshop 7, January 2003
Step 10. Run Finite Element Analysis
Analyze the modela. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Type.c. Choose Linear Static.d. Click OK. e. Click Apply.
a
e
b
d
c
WS7-23NAS120, Workshop 7, January 2003
Step 11. Read Results into MSC.Patran
Attach the results filea. Analysis: Access Results
/ Attach XDB / Result Entities.
b. Click Select Results File.
c. Choose the results file beam.xdb.
d. Click OK. e. Click Apply.
a
b
c
e
d
WS7-24NAS120, Workshop 7, January 2003
Step 12. Plot Displacements and Stresses
Create a quick plota. Results: Create / Quick
Plot.b. Select Bar Stresses,
Maximum Combined as the Fringe Result.
c. Select Displacements, Translational as the Deformation Result.
d. Click Apply.
a
d
c
b
Notice that the stress in the beam is constant along its length.
WS7-25NAS120, Workshop 7, January 2003
Step 13. Examine the .f06 File
Examine the .f06 filea. Open the directory in
which your database is saved.
b. Find the file titled beam.f06 .
c. Open this file with any text editor.
d. Verify that the stress results agree with the graphical results shown in Patran.
WS7-26NAS120, Workshop 7, January 2003
WORKSHOP 8
TAPERED PLATE
WS8-1NAS120, Workshop 8, January 2003
WS8-2NAS120, Workshop 8, January 2003
WS8-3NAS120, Workshop 8, January 2003
Problem DescriptionModel a tapered annular plate with a variable pressure loading. Due to symmetry, only a 45° slice of the plate will be modeled.
The plate is constructed from two different materials as shown below:
Inner RegionSteel
Outer Region Aluminum
WS8-4NAS120, Workshop 8, January 2003
Problem Description (cont.)The thickness variation in the plate is shown below:
0
0.05
0.1
0.15
0.2
0.25
0 0.5 1 1.5 2 2.5 3 3.5 4 4.5
Radial Distance, r, inches
Thic
knes
s, in
ches
WS8-5NAS120, Workshop 8, January 2003
Analysis Code: MSC.Nastran
Element Type: Quad4
Element Global Edge Length: 0.5
Problem Description (Cont.)
Table 8.1 Mesh Definition
Table 8.2 Material Properties:
Material: Steel Aluminum
Modulus of Elasticity: 30E+06 10E+06
Poisson Ratio: 0.30 0.33
Density: 7.324E-04 2.588E-04
WS8-6NAS120, Workshop 8, January 2003
Workshop Objectives:
1. Learn to use fields to define element thickness
2. Learn to use fields to create variable pressure loading
WS8-7NAS120, Workshop 8, January 2003
Suggested Exercise Steps:
1. Create geometry representing a 45° slice of the annular plate.
2. Create the finite element mesh using the information listed in Table 12.1.
3. Create a cylindrical coordinate system.
4. Using the cylindrical coordinate system, define a spatially varying field which represents the plate thickness. Verify the field by creating an XY-plot.
5. Define material properties using the material constants shown in Table 12.2.
WS8-8NAS120, Workshop 8, January 2003
Suggested Exercise Steps:
6. Define element properties by assigning the material type and element thickness to the correct region of the model.
7. Verify that the spatial variation of the element thickness has been assigned correctly to the model by creating a scalar plot.
8. Define a spatially varying field that represents the pressure load.
9. Apply the pressure load.
10. Verify that the pressure has been assigned correctly by modifying plot markers.
WS8-9NAS120, Workshop 8, January 2003
Create a New Database
Create a new database called annular_plate.db
a. File / New.
b. Enter tapered_plate as the file name.
c. Click OK.
d. Choose Default Tolerance.
e. Select MSC.Nastran as the Analysis Code.
f. Select Structural as the Analysis Type.
g. Click OK.
WS8-10NAS120, Workshop 8, January 2003
Create a curve
a. Geometry: Create / Curve / 2D ArcAngles.
b. Enter 1.0 for the Radius.
c. Enter 0.0 for Start Angle and 45 for End Angle.
Create a field which defines the variation in pressure.
a. Fields: Create / Spatial / PCL Function.
b. Type in pressure_variation for the Field Name.
c. Select Coord 1 for Coordinate System.
d. Enter the function: 100*’R.e. Click Apply.
a
b
c
d
e
WS8-24NAS120, Workshop 8, January 2003
Step 9. Loads/BCs: Create /Pressure/ Element Uniform
Create a pressure load.a. Loads/BCs: Create / Pressure /
Element Variable.b. Type in press for the New Set
Name.c. Set the Target Element Type to
2D.d. Click Input Data.e. Click on the Bottom Surf
Pressure list box and select the field pressure_variation.
f. Click OK.
a
b
d
e
f
c
WS8-25NAS120, Workshop 8, January 2003
Step 9. Loads/BCs: Create /Pressure/ Element Uniform
a
Select an application region.a. Click on the Iso 3 View
Icon.b. Click Select Application
Region.c. For the Geometry Filter
select Geometry.d. Select the Surface or
Face filter.e. Click in the application
region list box and select both surfaces.
f. Click Add.g. Click OK.h. Click Apply.
b
e
c
f
g
h
d
WS8-26NAS120, Workshop 8, January 2003
Step 10. Modify Plot Markers
Modify the pressure plot markers.a. Display:
Load/BC/Elem.Props.b. Click on Vectors/Filters.c. Change the length to
Scaled- Screen Relative.d. Click Apply.e. Click Cancel.f. Click on Label Style.g. Set the Label Format to
Integer.h. Click OK.i. Click Apply.
a
b
c
d e
f
g
h
i
WS8-27NAS120, Workshop 8, January 2003
Step 10. Modify Plot Markers
View the model with the modified plot markers.
WS8-28NAS120, Workshop 8, January 2003
WS9A-1
WORKSHOP 9A
TENSION COUPON
NAS120, Workshop 9A, January 2003
WS9A-2NAS120, Workshop 9A, January 2003
WS9A-3NAS120, Workshop 9A, January 2003
Problem Description A tension coupon is constructed from aluminum with E = 10 x 106 psi and ν =
0.3
The coupon thickness is 0.125 in
An edge load of 50 lb is applied to the tension coupon
WS9A-4NAS120, Workshop 9A, January 2003
50 lb
10 in
4 in
2.0 DIA Hole
WS9A-5NAS120, Workshop 9A, January 2003
Workshop Objectives Build the tension coupon geometry
Control the mesh by using techniques discussed in class
Compare FEA stress results to theoretical results
From “Stress Concentration Factors” by R. E. Peterson, Figure 86:
σmax = 432 psi
WS9A-6NAS120, Workshop 9A, January 2003
Suggested Exercise Steps1. Create a new database. 2. Create a geometry model of the tension coupon. 3. Use Mesh Seeds to define the mesh density.4. Create a finite element mesh.5. Verify the finite element mesh. 6. Define material properties. 7. Define element properties and apply them to the model. 8. Apply boundary conditions to the model.9. Apply loads to the model.10. Submit the model to MSC.Nastran for analysis.11. Post Process results using MSC.Patran.
WS9A-7NAS120, Workshop 9A, January 2003
a
b c
d
e
f
g
Step 1. Create New Database
Create a new database called tension_coupon.db.
a. File / New.b. Enter tension_coupon_a as
the file name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
WS9A-8NAS120, Workshop 9A, January 2003
Step 2. Create Geometry
Create the first curve.a. Geometry: Create / Curve
/ XYZ.b. Enter <0 4 0> for the
Vector Coordinate List.c. Enter [0 0 0] for the Origin
Coordinate List.d. Click Apply.
a
b
c
d
WS9A-9NAS120, Workshop 9A, January 2003
Step 2. Create Geometry
Create the second curve by translating the first curve.
a. Geometry: Transform / Curve / Translate.
b. Enter <10 0 0> for the Translation Vector.
c. Click in the Curve List box and screen pick the first curve.
a
b
c
WS9A-10NAS120, Workshop 9A, January 2003
Step 2. Create Geometry
Create two more curvesa. Geometry: Create / Curve /
Point.b. Screen pick the point at the
bottom of the left curve.c. Screen pick the point at the
bottom of the right curve. A curve is automatically created because Auto Execute is checked.
d. Screen pick the top of the left curve.
e. Finish creating the top curve by screen picking the point at the top of the right curve as shown.
a
b c
ed
WS9A-11NAS120, Workshop 9A, January 2003
Step 2. Create Geometry
Create a chain curvea. Geometry: Create / Curve /
Chain.b. Rectangular pick all four
curves.c. Click Apply.d. When the message box
appears, choose Yes to delete the original curves.
a
b
c
d
WS9A-12NAS120, Workshop 9A, January 2003
Step 2. Create Geometry
Create a circlea. Geometry: Create / Curve /
2D Circle.b. For the circle radius, enter
1.0.c. For the Center Point List,
enter [5 2 0].d. Click Apply.
a
c
b
d
WS9A-13NAS120, Workshop 9A, January 2003
Step 2. Create Geometry
Create a trimmed surfacea. Geometry: Create / Surface
/ Trimmed / Option: Planar.b. Click in the Outer Loop List
box.c. Screen pick the outer
curve.d. Click in the Inner Loop List
box.e. Screen pick the inner circle.f. Click Apply.g. When the message boxes
appear, choose Yes to delete the original curves.
h. Click the Refresh Graphics icon
a
b
d
c
e
f
g
h
WS9A-14NAS120, Workshop 9A, January 2003
Step 2. Create Geometry
Create two more circlesa. Geometry: Create / Curve /
2D Circle.b. For the circle radius, enter
1.1.c. For the Center Point List,
enter [5 2 0].d. Click Apply.e. Repeat this procedure for a
circle with a radius of 1.2.
a
b
d
c
WS9A-15NAS120, Workshop 9A, January 2003
Step 2. Create Geometry
Associate the two curves to the surface
a. Geometry: Associate / Curve / Surface.
b. Select the Curve filter.c. Rectangular pick both
circles.d. Screen pick the trimmed
surface.
ab
c
d
WS9A-16NAS120, Workshop 9A, January 2003
Step 3. Create Mesh Seeds
Create a uniform mesh seeda. Elements: Create / Mesh
Seed / Uniform.b. Enter 48 for the Number of
Elements.c. Click in the Curve List box.d. Select the Curve or Edge
element filter. e. Rectangular pick the two
circles and the edge of the hole.
a
b
c
d
e
WS9A-17NAS120, Workshop 9A, January 2003
Step 3. Create Mesh Seeds
Create a biased mesh seeda. Elements: Create / Mesh
Seed / Two Way Bias.b. Enter 20 for the Number of
Elements.c. Enter 0.25 for L2/L1.d. Click on the Curve List box. e. Screen pick the top edge of
the surface, as shown. f. Screen pick the bottom
edge of the surface to apply the mesh seed there as well.
a
bc
d
f
e
WS9A-18NAS120, Workshop 9A, January 2003
Step 4. Create Mesh
Create a finite element mesha. Elements: Create / Mesh /
Surface.b. Set the Element Shape to
Quad, Mesher to Paver, and Topology to Quad4.
c. Click in the Surface List box.
d. Screen pick the surface as shown.
e. Enter 1.0 as the value for Global Edge Length.
f. Click Apply.
a
b
cd
f
e
WS9A-19NAS120, Workshop 9A, January 2003
Step 5. Verify Mesh
Verify the quality of the finite elements
a. Elements: Verify / Quad / All.
b. Click Apply.c. Review the summary table.
a
b
c
WS9A-20NAS120, Workshop 9A, January 2003
Step 5. Verify Mesh
Perform specific quality tests on the elements.
a. Elements: Verify / Quad / Aspect.
b. Click Apply.c. Review the fringe plot.d. Repeat for Warp, Skew,
and Taper tests.
a
b
c
d
WS9A-21NAS120, Workshop 9A, January 2003
Step 6. Create Material Properties
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter aluminum as the
Material Name.c. Click Input Properties.d. Enter 10e6 for the elastic
modulus and 0.3 for the Poisson Ratio.
e. Click OK. f. Click Apply.
a
b
c
d
fe
WS9A-22NAS120, Workshop 9A, January 2003
Step 7. Create Element Properties
Create element propertiesa. Properties: Create / 2D /
Shell.b. Enter plate as the Property
Set Name.c. Click Input Properties.d. Select aluminum as the
material.e. Enter 0.125 for the
thickness.f. Click OK.
a
b
c
d
e
f
WS9A-23NAS120, Workshop 9A, January 2003
Step 7. Create Element Properties
Select application regiona. Click in the Select
Members box.b. Screen pick the
surface as shown.c. Click Add.d. Click Apply.
b
ac
d
WS9A-24NAS120, Workshop 9A, January 2003
Step 8. Apply Boundary Conditions
Create the boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter fixed as the New Set
Name.c. Click Input Data.d. Enter <0 0 0> for
Translations and <0 0 0>for Rotations.
e. Click OK.
a
b
d
e
c
WS9A-25NAS120, Workshop 9A, January 2003
Step 8. Apply Boundary Conditions
Apply the boundary conditiona. Click Select Application
Region.b. Select the Curve or Edge
filter.c. Select the left edge of the
surface as the application region.
d. Click Add.e. Click OK. f. Click Apply.
a
d
e
f
b
c
WS9A-26NAS120, Workshop 9A, January 2003
Step 8. Apply Boundary Conditions
The boundary condition should agree with what’s shown on the right
WS9A-27NAS120, Workshop 9A, January 2003
Step 9. Apply Loads
Create the loada. Loads/BCs: Create / Total
Load / Element Uniform.b. Enter force as the New Set
Name.c. Set the Target Element
Type to 2D.d. Click Input Data.e. Enter <50 0 0> for the Edge
Load.f. Click OK.
d
b
c
a
e
f
WS9A-28NAS120, Workshop 9A, January 2003
Apply the loada. Click Select Application
Region.b. For the application region
select the right edge of the surface as shown.
c. Click Add.d. Click OK.e. Click Apply.
Step 9. Apply Loads
a
b
c
d
e
WS9A-29NAS120, Workshop 9A, January 2003
Step 9. Apply Loads
The loads and boundary condition should agree with what’s shown on the right.
WS9A-30NAS120, Workshop 9A, January 2003
Step 10. Run Linear Static Analysis
Analyze the modela. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Type.c. Choose Linear Static.d. Click OK. e. Click Apply.
a
e
b
d
c
WS9A-31NAS120, Workshop 9A, January 2003
Step 11. Post Process with MSC.Patran
Attach the results filea. Analysis: Access Results /
Attach XDB / Result Entities.
b. Click Select Results File.c. Choose the results file
tension_coupon_a.xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS9A-32NAS120, Workshop 9A, January 2003
Step 11. Post Process with MSC.Patran
Erase geometrya. Display: Plot/Erase.b. Under Geometry click
Erase.c. Click OK.
a
b
c
WS9A-33NAS120, Workshop 9A, January 2003
Step 11. Post Process with MSC.Patran
Create a general Quick Plota. Results: Create / Quick
Plot.b. Select Stress Tensor
as the Fringe Result.c. Select Von Mises as
the Fringe Result Quantity.
d. Click Apply.
a
b
c
d
WS9A-34NAS120, Workshop 9A, January 2003
Step 11. Post Process with MSC.Patran
Create a Quick Plot of X Component Stress
a. Results: Create / Quick Plot.
b. Select Stress Tensor as the Fringe Result.
c. Select X Componentas the Fringe Result Quantity.
d. Click Apply.e. Record the maximum X
component stress.
Max X Stress = ________
b
c
d
a
WS9A-35NAS120, Workshop 9A, January 2003
Step 11. Post Process with MSC.Patran
Create a fringe plot of X Component Stress
a. Results: Create / Fringe.
b. Select Stress Tensor as the Fringe Result.
c. Select X Componentas the Fringe Result Quantity.
d. Click Apply.e. Record the maximum X
component stress.
Max X Stress = ________
d
a
b
c
WS9A-36NAS120, Workshop 9A, January 2003
Step 11. Post Process with MSC.Patran
By default, MSC.Nastran presents element stress results in the element coordinate system.
For the Fringe Plot option, MSC.Patran takes the MSC.Nastran results and plot them as is.
For the Quick Plot option, MSC.Patran automatically transforms the stress results into the basic coordinate system first before plotting them.
WS9A-37NAS120, Workshop 9A, January 2003
Step 11. Post Process with MSC.Patran
Show the element coordinate systems
a. Elements: Show / Element / Coord.Sys
b. Rectangular pick the entire surface.
c. Note the various orientations of the X direction.
d. Click reset graphics.
a
b
d
WS9A-38NAS120, Workshop 9A, January 2003
Step 11. Post Process with MSC.Patran
Create another fringe Plota. Results: Create /
Fringe.b. Select Stress Tensor
as the Fringe Result.c. Select X Component
as the Fringe Result Quantity.
d. Click on the Plot Options Icon.
e. Set the coordinate transformation to CID.
f. Screen pick coordinate frame 0.
g. Click Apply.
a
b
c
de
f
g
WS9A-39NAS120, Workshop 9A, January 2003
Step 11. Post Process with MSC.Patran
View the revised resultsa. Note the change in
maximum stress.
Max X Stress = _________
WS9A-40NAS120, Workshop 9A, January 2003
WS9B-1
WORKSHOP 9B
TENSION COUPON
NAS120, Workshop 9B, January 2003
WS9B-2NAS120, Workshop 9B, January 2003
WS9B-3NAS120, Workshop 9B, January 2003
Problem Description A tension coupon is constructed from aluminum with E = 10 x 106 psi and ν =
0.3
The coupon thickness is 0.125 in
An edge load of 50 lb is applied to the tension coupon
WS9B-4NAS120, Workshop 9B, January 2003
50 lb
10 in
4 in
2.0 DIA Hole
WS9B-5NAS120, Workshop 9B, January 2003
Workshop Objectives Build the tension coupon geometry
Control the mesh by using techniques discussed in class
Compare FEA stress results to theoretical results
From “Stress Concentration Factors” by R. E. Peterson, Figure 86:
σmax = 432 psi
WS9B-6NAS120, Workshop 9B, January 2003
Suggested Exercise Steps1. Create a new database. 2. Create a geometry model of the tension coupon. 3. Use Mesh Seeds to define the mesh density.4. Create a finite element mesh.5. Verify the finite element mesh. 6. Define material properties. 7. Define element properties and apply them to the model. 8. Apply boundary conditions to the model.9. Apply loads to the model.10. Submit the model to MSC.Nastran for analysis.11. Post Process results using MSC.Patran.
WS9B-7NAS120, Workshop 9B, January 2003
a
b c
d
e
f
g
Step 1. Create New Database
Create a new database called tension_coupon.db
a. File / New.b. Enter tension_coupon_b as
the file name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
WS9B-8NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Create the first curvea. Geometry: Create / Curve
/ XYZ.b. Enter <0 4 0> for the
Vector Coordinate List.c. Enter [0 0 0] for the Origin
Coordinate List.d. Click Apply.
a
b
c
d
WS9B-9NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Create the second curve by translating the first curve
a. Geometry: Transform / Curve / Translate.
b. Enter <10 0 0> for the Translation Vector.
c. Click in the Curve List box and screen pick the first curve.
a
b
c
WS9B-10NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Create two more curvesa. Geometry: Create / Curve /
Point.b. Screen pick the point at the
bottom of the left curve.c. Screen pick the point at the
bottom of the right curve. A curve is automatically created because Auto Execute is checked.
d. Screen pick the top of the left curve.
e. Finish creating the top curve by screen picking the point at the top of the right curve as shown.
a
b c
ed
WS9B-11NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Create a chain curvea. Geometry: Create / Curve /
Chain.b. Rectangular pick all four
curves.c. Click Apply.d. When the message box
appears, choose Yes to delete the original curves.
a
b
c
d
WS9B-12NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Create a circlea. Geometry: Create / Curve /
2D Circle.b. For the circle radius, enter
1.0.c. For the Center Point List
enter [5 2 0].d. Click Apply.
a
c
b
d
WS9B-13NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Create a trimmed surfacea. Geometry: Create / Surface
/ Trimmed / Option: Planar.b. Click in the Outer Loop List
box.c. Screen pick the outer
curve.d. Click in the Inner Loop List
box.e. Screen pick the inner circle.f. Click Apply.g. When the message boxes
appear, choose Yes to delete the original curves.
h. Click the Refresh Graphics icon
a
b
d
c
e
f
g
h
WS9B-14NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Create two more curvesa. Geometry: Create /
Curve / XYZ.b. Enter <0 4 0> for the
Vector Coordinate List.c. Enter [3 0 0] for the
Origin Coordinate List.d. Click Apply.e. Repeat this procedure
with [7 0 0] as the Origin Coordinate List.
a
b
d
c
WS9B-15NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Break the surface into 3 surfacesa. Geometry: Edit / Surface /
Break.b. Set the Option to Curve.c. Screen pick the trimmed
surface. d. Screen pick the left curve
as shown.e. When the message box
appears, choose Yes to delete the original surfaces.
f. Screen pick the new trimmed surface, and pick the right curve to break it.
a
b
cd
e
f
WS9B-16NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Create additional pointsa. Turn Point size on.b. Geometry: Create / Point /
Interpolate.c. Set the Option to Curve.d. Screen pick the top of the
surface above the circle as shown.
e. Repeat the procedure by screen picking each of the other three edges surrounding the circle.
a
b
cd
WS9B-17NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Create four curvesa. Geometry: Create / Curve /
Point.b. Screen pick the point
above the center of the circle as shown.
c. Screen pick the point below the center of the circle to create a curve.
d. Repeat the procedure by screen picking opposite points surrounding the circle to create four curves as shown.
ab
c
WS9B-18NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Break the magenta surfacea. Geometry: Edit / Surface /
Break.b. Screen pick the magenta
surface.c. Screen pick a diagonal
curve. d. When the message box
appears, choose Yes to delete the original surfaces.
e. Repeat the procedure to break two surfaces with the second diagonal.
f. Repeat the procedure to break two surfaces with the vertical curve.
g. Repeat the procedure to break two surfaces with the horizontal curve.
a
bc
d
e f
g
The original magenta surface has been broken into 8 green surfaces.
WS9B-19NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Break the rectangular surfacesa. Geometry: Edit / Surface /
Break.b. Set the option to Point.c. Screen pick the left
rectangular surface as shown.
d. Screen pick the point on the edge of the rectangular surface as shown.
e. When the message box appears, choose Yes to delete the original surfaces.
f. Repeat the procedure by screen picking the other rectangular surface and the point on the edge of the surface.
e
a
bc
d f
WS9B-20NAS120, Workshop 9B, January 2003
Step 2. Create Geometry
Delete excess curvesa. Turn Point size offb. Geometry: Delete / Curve. c. Rectangular pick all of the
curves as shown.d. Click Apply.e. Click Refresh graphics.
b
a
c
d
e
WS9B-21NAS120, Workshop 9B, January 2003
Step 3. Create Mesh Seeds
Create a uniform mesh seeda. Elements: Create / Mesh
Seed / Uniform.b. Enter 3 for the Number of
Elements.c. Click in the Curve List box.d. Screen pick each of the
four edges on the left and right sides of the circle as shown.
a
b
c
d
WS9B-22NAS120, Workshop 9B, January 2003
Step 3. Create Mesh Seeds
a
bc
d
Create a biased mesh seeda. Elements: Create / Mesh
Seed / One Way Bias.b. Enter 6 for the Number of
Elements.c. Enter 4 for L2/L1.
Depending on the direction of the arrow, you may have to enter 0.25 (or-4) to get the correct biasing.
d. Click on the Curve List box. e. Screen pick the four
remaining edges on the circle.
f. Screen pick the horizontal edge to the right of the circle.
e f
WS9B-23NAS120, Workshop 9B, January 2003
The mesh seeds should agree with the picture on the right.
Step 3. Create Mesh Seeds
WS9B-24NAS120, Workshop 9B, January 2003
Step 4. Create Mesh
Create a finite element mesha. Elements: Create / Mesh /
Surface.b. Set the Element Shape to
Quad, Mesher to IsoMesh, and Topology to Quad4.
c. Click in the Surface List box.
d. Rectangular pick the surfaces as shown.
e. Enter 0.5 as the value for Global Edge Length.
f. Click Apply.
a
b
c
f
e
d
WS9B-25NAS120, Workshop 9B, January 2003
Step 4. Create Mesh
Equivalence the modela. Elements: Equivalence /
All / Tolerance Cube. b. Click Apply.
a
b
WS9B-26NAS120, Workshop 9B, January 2003
Step 5. Verify Mesh
Verify the quality of the finite elements
a. Elements: Verify / Quad / All.
b. Click Apply.c. Review the summary table.
a
b
c
WS9B-27NAS120, Workshop 9B, January 2003
Step 5. Verify Mesh
Perform specific quality tests on the elements.
a. Elements: Verify / Quad / Aspect.
b. Click Apply.c. Review the fringe plot.d. Repeat for Warp, Skew,
and Taper tests.
a
b
c
d
WS9B-28NAS120, Workshop 9B, January 2003
Step 6. Create Material Properties
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter aluminum as the
Material Name.c. Click Input Properties.d. Enter 10e6 for the elastic
modulus and 0.3 for the Poisson Ratio.
e. Click OK. f. Click Apply.
a
b
c
d
fe
WS9B-29NAS120, Workshop 9B, January 2003
Step 7. Create Element Properties
Create element propertiesa. Properties: Create / 2D /
Shell.b. Enter plate as the Property
Set Name.c. Click Input Properties.d. Select aluminum as the
material.e. Enter 0.125 for the
thickness.f. Click OK.
a
b
c
d
e
f
WS9B-30NAS120, Workshop 9B, January 2003
Step 7. Create Element Properties
Select application regiona. Click in the Select
Members box.b. Rectangular pick
the surfaces as shown.
c. Click Add.d. Click Apply.
ac
d
b
WS9B-31NAS120, Workshop 9B, January 2003
Step 8. Apply Boundary Conditions
Create the boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter fixed as the New Set
Name.c. Click Input Data.d. Enter <0 0 0> for
Translations and <0 0 0>for Rotations.
e. Click OK.
a
b
d
e
c
WS9B-32NAS120, Workshop 9B, January 2003
Step 8. Apply Boundary Conditions
Apply the boundary conditiona. Click Select
Application Region.b. Select the Curve or
Edge filter.c. Select the bottom left
edge of the surface.d. Click Add.e. Select the top left edge
of the surface.f. Click Add.g. Click OK. h. Click Apply.
ag
h
b
c
e
d f
WS9B-33NAS120, Workshop 9B, January 2003
Step 8. Apply Boundary Conditions
The boundary condition should agree with what’s shown on the right
WS9B-34NAS120, Workshop 9B, January 2003
Step 9. Apply Loads
Create the loada. Loads/BCs: Create / Total
Load / Element Uniform.b. Enter force as the New Set
Name.c. Set the Target Element
Type to 2D.d. Click Input Data.e. Enter <50 0 0> for the Edge
Load.f. Click OK.
d
b
c
a
e
f
WS9B-35NAS120, Workshop 9B, January 2003
Apply the loada. Click Select
Application Region.b. For the application
region select the right edge of the top right surface as shown.
c. Click Add.d. Select the right edge of
the bottom right surface.
e. Click Add.f. Click OK.g. Click Apply.
Step 9. Apply Loads
a
b
c
f
g
ed
WS9B-36NAS120, Workshop 9B, January 2003
Step 9. Apply Loads
The loads and boundary condition should agree with what’s shown on the right.
WS9B-37NAS120, Workshop 9B, January 2003
Step 10. Run Linear Static Analysis
Analyze the modela. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Type.c. Choose Linear Static.d. Click OK. e. Click Apply.
a
e
b
d
c
WS9B-38NAS120, Workshop 9B, January 2003
Step 11. Post Process with MSC.Patran
Attach the results filea. Analysis: Access Results /
Attach XDB / Result Entities.
b. Click Select Results File.c. Choose the results file
tension_coupon_b.xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS9B-39NAS120, Workshop 9B, January 2003
Step 11. Post Process with MSC.Patran
Erase geometrya. Display: Plot/Erase.b. Under Geometry click
Erase.c. Click OK.
a
b
c
WS9B-40NAS120, Workshop 9B, January 2003
Step 11. Post Process with MSC.Patran
Create a Quick Plot of X Component Stress
a. Results: Create / Quick Plot.
b. Select Stress Tensor as the Fringe Result.
c. Select X Componentas the Fringe Result Quantity.
d. Click Apply.e. Record the maximum X
component stress.
Max X Stress = ________
a
b
c
d
WS9C-1
WORKSHOP 9C
TENSION COUPON
NAS120, Workshop 9C, January 2003
WS9C-2NAS120, Workshop 9C, January 2003
WS9C-3NAS120, Workshop 9C, January 2003
Problem Description A tension coupon is constructed from aluminum with E = 10 x 106 psi and ν =
0.3
The coupon thickness is 0.125 in
An edge load of 50 lb is applied to the tension coupon
WS9C-4NAS120, Workshop 9C, January 2003
50 lb
10 in
4 in
2.0 DIA Hole
WS9C-5NAS120, Workshop 9C, January 2003
Workshop Objectives Build the tension coupon geometry
Control the mesh by using techniques discussed in class
Compare FEA stress results to theoretical results
From “Stress Concentration Factors” by R. E. Peterson, Figure 86:
σmax = 432 psi
WS9C-6NAS120, Workshop 9C, January 2003
Suggested Exercise Steps1. Create a new database. 2. Create a geometry model of the tension coupon. 3. Use Mesh Seeds to define the mesh density.4. Create a finite element mesh.5. Verify the finite element mesh. 6. Define material properties. 7. Define element properties and apply them to the model. 8. Apply boundary conditions to the model.9. Apply loads to the model.10. Submit the model to MSC.Nastran for analysis.11. Post Process results using MSC.Patran.
WS9C-7NAS120, Workshop 9C, January 2003
a
b c
d
e
f
g
Step 1. Create New Database
Create a new database called tension_coupon.db
a. File / New.b. Enter tension_coupon_c as
the file name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
WS9C-8NAS120, Workshop 9C, January 2003
Step 2. Create Geometry
Create two arcsa. Geometry: Create / Curve
/ 2D ArcAngles.b. Enter 0 for the Start Angle.c. Enter 45 for the End
Angle.d. Enter [5 2 0] for the Center
Point List.e. Click Apply.f. Repeat the procedure with
45 as the Start Angle and 90 as the End Angle.
a
b
c
d
e
WS9C-9NAS120, Workshop 9C, January 2003
Step 2. Create Geometry
Create two more curves.a. Geometry: Create / Curve /
XYZ.b. Enter <0 2 0> for the Vector
Coordinates List.c. Enter [7 2 0] for the Origin
Coordinates List. d. Click Apply.e. Repeat the procedure using
<2 0 0> as the vector and [5 4 0] as the origin.
a
b
c
d
WS9C-10NAS120, Workshop 9C, January 2003
Step 2. Create Geometry
Create two surfacesa. Geometry: Create / Surface
/ Curve.b. Screen pick the top curve
as shown.c. Screen pick the upper arc.d. Screen pick the right curve
as shown.e. Screen pick the lower arc.f. Turn on display lines.
ab
c
e
d
f
WS9C-11NAS120, Workshop 9C, January 2003
Step 2. Create Geometry
Create an extruded surfacea. Geometry: Create / Surface
/ Extrude.b. Enter <3 0 0> as the
Translation Vector.c. Click in the Curve List box,
then screen pick the right curve as shown.
a
c b
WS9C-12NAS120, Workshop 9C, January 2003
Step 2. Create Geometry
Mirror the surfacesa. Geometry: Transform /
Surface / Mirror.b. Set the Mirror Plane
Normal to Coord 0.2.c. For the Offset enter 2.d. Click in the Surface
List box.e. Rectangular select all
the surfaces as shown.
a
c
b
e
d
WS9C-13NAS120, Workshop 9C, January 2003
Step 2. Create Geometry
Mirror the surfaces againa. Geometry: Transform /
Surface / Mirror.b. Set the Mirror Plane
Normal to Coord 0.1.c. For the Offset enter 5.d. Click in the Surface
List box.e. Rectangular select all
the surfaces as shown.
a
b
ce
d
WS9C-14NAS120, Workshop 9C, January 2003
Step 2. Create Geometry
The mirrored surfaces should look like the picture on the right.
a. Turn off display lines
a
WS9C-15NAS120, Workshop 9C, January 2003
Step 3. Create Mesh Seeds
Create a uniform mesh seeda. Elements: Create / Mesh
Seed / Uniform.b. Enter 3 for the Number of
Elements.c. Click in the Curve List box.d. Screen pick each of the
four edges on the left and right sides of the circle as shown.
a
b
c
d
WS9C-16NAS120, Workshop 9C, January 2003
Step 3. Create Mesh Seeds
a
bc
d
Create a biased mesh seeda. Elements: Create / Mesh
Seed / One Way Bias.b. Enter 6 for the Number of
Elements.c. Enter 4 for L2/L1. d. Click on the Curve List box. e. Screen pick three of the
remaining edges on the circle as shown. e
WS9C-17NAS120, Workshop 9C, January 2003
Step 3. Create Mesh Seeds
Create a biased mesh seeda. Elements: Create / Mesh
Seed / One Way Bias.b. Enter 6 for the Number of
Elements.c. Enter 0.25 (or -4) for L2/L1. d. Click on the Curve List box.e. Screen pick the 1 remaining
edge on the circle. f. Screen pick the horizontal
edge to the right of the circle.
a
bc
d
e
f
WS9C-18NAS120, Workshop 9C, January 2003
The mesh seeds should agree with the picture on the right.
Step 3. Create Mesh Seeds
WS9C-19NAS120, Workshop 9C, January 2003
Step 4. Create Mesh
Create a finite element mesha. Elements: Create / Mesh /
Surface.b. Set the Element Shape to
Quad, Mesher to IsoMesh, and Topology to Quad4.
c. Click in the Surface List box.
d. Rectangular pick the surfaces as shown.
e. Enter 0.5 as the value for Global Edge Length.
f. Click Apply.
a
b
c
f
e
d
WS9C-20NAS120, Workshop 9C, January 2003
Step 4. Create Mesh
Equivalence the modela. Elements: Equivalence /
All / Tolerance Cube. b. Click Apply.
a
b
WS9C-21NAS120, Workshop 9C, January 2003
Step 5. Verify Mesh
Verify the quality of the finite elements
a. Elements: Verify / Quad / All.
b. Click Apply.c. Review the summary table.
a
b
c
WS9C-22NAS120, Workshop 9C, January 2003
Step 5. Verify Mesh
Perform specific quality tests on the elements.
a. Elements: Verify / Quad / Aspect.
b. Click Apply.c. Review the fringe plot.d. Repeat for Warp, Skew,
and Taper tests.
a
b
c
d
WS9C-23NAS120, Workshop 9C, January 2003
Step 5. Create Material Properties
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter aluminum as the
Material Name.c. Click Input Properties.d. Enter 10e6 for the elastic
modulus and 0.3 for the Poisson Ratio.
e. Click OK. f. Click Apply.
a
b
c
d
fe
WS9C-24NAS120, Workshop 9C, January 2003
Step 6. Create Element Properties
Create element propertiesa. Properties: Create / 2D /
Shell.b. Enter plate as the Property
Set Name.c. Click Input Properties.d. Select aluminum as the
material.e. Enter 0.125 for the
thickness.f. Click OK.
a
b
c
d
e
f
WS9C-25NAS120, Workshop 9C, January 2003
Step 6. Create Element Properties
Select application regiona. Click in the Select
Members box.b. Rectangular pick
the surfaces as shown.
c. Click Add.d. Click Apply.
ac
d
b
WS9C-26NAS120, Workshop 9C, January 2003
Step 7. Apply Boundary Conditions
Create the boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter fixed as the New Set
Name.c. Click Input Data.d. Enter <0 0 0> for
Translations and <0 0 0>for Rotations.
e. Click OK.
a
b
d
e
c
WS9C-27NAS120, Workshop 9C, January 2003
Step 7. Apply Boundary Conditions
Apply the boundary conditiona. Click Select
Application Region.b. Select the Curve or
Edge filter.c. Select the bottom left
edge of the surface.d. Click Add.e. Select the top left edge
of the surface.f. Click Add.g. Click OK. h. Click Apply.
ag
h
b
c
e
d f
WS9C-28NAS120, Workshop 9C, January 2003
Step 7. Apply Boundary Conditions
The boundary condition should agree with what’s shown on the right
WS9C-29NAS120, Workshop 9C, January 2003
Step 8. Apply Loads
Create the loada. Loads/BCs: Create / Total
Load / Element Uniform.b. Enter force as the New Set
Name.c. Set the Target Element
Type to 2D.d. Click Input Data.e. Enter <50 0 0> for the Edge
Load.f. Click OK.
d
b
c
a
e
f
WS9C-30NAS120, Workshop 9C, January 2003
Apply the loada. Click Select
Application Region.b. For the application
region select the right edge of the top right surface as shown.
c. Click Add.d. Select the right edge of
the bottom right surface.
e. Click Add.f. Click OK.g. Click Apply.
Step 8. Apply Loads
a
b
c
f
g
ed
WS9C-31NAS120, Workshop 9C, January 2003
Step 8. Apply Loads
The loads and boundary condition should agree with what’s shown on the right.
WS9C-32NAS120, Workshop 9C, January 2003
Step 9. Run Linear Static Analysis
Analyze the modela. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Type.c. Choose Linear Static.d. Click OK. e. Click Apply.
a
e
b
d
c
WS9C-33NAS120, Workshop 9C, January 2003
Step 10. Post Process with MSC.Patran
Attach the results filea. Analysis: Access Results /
Attach XDB / Result Entities.
b. Click Select Results File.c. Choose the results file
tension_coupon_c.xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS9C-34NAS120, Workshop 9C, January 2003
Step 10. Post Process with MSC.Patran
Erase geometrya. Display: Plot/Erase.b. Under Geometry click
Erase.c. Click OK.
a
b
c
WS9C-35NAS120, Workshop 9C, January 2003
Step 10. Post Process with MSC.Patran
Create a Quick Plot of X Component Stress
a. Results: Create / Quick Plot.
b. Select Stress Tensor as the Fringe Result.
c. Select X Componentas the Fringe Result Quantity.
d. Click Apply.e. Record the maximum X
component stress.
Max X Stress = ________
a
b
c
d
WS9C-36NAS120, Workshop 9C, January 2003
WS10A-1
WORKSHOP 10A
2½ D CLAMP – SWEEP MESHER
NAS120, Workshop 10A, January 2003
WS10A-2NAS120, Workshop 10A, January 2003
WS10A-3NAS120, Workshop 10A, January 2003
Problem Description Analyze the clamp shown below:
60 mm
100 mm150 mm
200 mm
30 mm
30 mm
50 mmR = 10 mm
WS10A-4NAS120, Workshop 10A, January 2003
Problem Description (cont.) A pressure loading of 1 N/mm2 is applied to the top face. Constrain the bolt hole in all three translations. Material Properties:
E = 109 x 103 N/mm2
ν =0.3
WS10A-5NAS120, Workshop 10A, January 2003
Workshop Objectives Practice the construction of a 2 ½ D solid model by sweeping 2D
elements.
WS10A-6NAS120, Workshop 10A, January 2003
Suggested Exercise Steps1. Create a new database. 2. Create surface geometry. 3. Mesh the surface to create CQUAD4 plate elements.4. Sweep the plate elements into solid elements. 5. Create a boundary condition.6. Create a pressure load.7. Define material properties.8. Create Physical Properties.9. Run the finite element analysis using MSC.Nastran.10. Plot displacements and stresses.
WS10A-7NAS120, Workshop 10A, January 2003
a
b c
d
f
g
h
Step 1. Create New Database
Create a new database called clamp.db
a. File / New.b. Enter clamp as the file name.c. Click OK.d. Choose Tolerance Based on
Model.e. Enter 200 for the Approximate
Maximum Model Dimension.f. Select MSC.Nastran as the
Analysis Code.g. Select Structural as the
Analysis Type.h. Click OK.
a
e
WS10A-8NAS120, Workshop 10A, January 2003
Step 2. Create Surface Geometry
Create the first surfacea. Geometry: Create /
Surface / XYZ.b. Enter <150 100 0> for the
Vector Coordinate List.c. Click Apply.
a
b
c
WS10A-9NAS120, Workshop 10A, January 2003
Step 2. Create Surface Geometry
Add a hole to the surfacea. Geometry: Edit /
Surface / Add Hole.b. Enter 10 for the Hole
Radius.c. Enter [50 100 0] for the
Center Point List.d. Click in the Surface
box.e. Screen Pick Surface 1.f. Click Apply.
a
b
c
e
d
f
WS10A-10NAS120, Workshop 10A, January 2003
Step 2. Create Geometry
a
c
Create another surfacea. Geometry: Create /
Surface / XYZ.b. Enter <50 100 0> for the
Vector Coordinate List.c. Click in the Origin
Coordinates List box.d. Screen Pick the origin as
shown.b
d
WS10A-11NAS120, Workshop 10A, January 2003
Step 3. Create Mesh
Create a surface mesha. Elements: Create /
Mesh / Surface.b. Set the Mesher to
Paver.c. Click on Paver
Parameters.d. Set the Max h/L value
to 0.05.e. Click OK.f. Click in the Surface
List box.g. Rectangular pick both
surfaces. h. Set the Global Edge
Length to 10.i. Click Apply.
a
b
c d
f
g
h
i
e
WS10A-12NAS120, Workshop 10A, January 2003
Step 3. Create Mesh
View the meshed surfacea. Click on the Iso 3 View
Icon.
a
WS10A-13NAS120, Workshop 10A, January 2003
Step 4. Create Solid Elements
Sweep the plate elements into solid elements.
a. Elements: Sweep / Element / Extrude.
b. Click Mesh Control.c. Set the Number of
Elements to 6.d. Click OK.e. Set the Direction Vector
to <0 0 1>.f. Set the Extrude
Distance to 30.g. Click in the Base Entity
List box.h. Polygon pick the 2D
elements as shown.i. Click Apply.
a
bc
e d
f
h
g
i
WS10A-14NAS120, Workshop 10A, January 2003
Step 4. Create Solid Elements
Sweep the plate elements into solid elements.
a. Elements: Sweep / Element / Extrude.
b. Click Mesh Control.c. Set the number of
elements to 12.d. Click OK.e. Set the Direction Vector
to <0 0 1>.f. Set the Extrude
Distance to 60.g. Click in the Base Entity
List box.h. Polygon pick the rest of
the 2D elements as shown.
i. Click Apply.
a
bc
e d
f
h
g
i
WS10A-15NAS120, Workshop 10A, January 2003
Delete the plate elementsa. Elements: Delete /
Element.b. Pick the Quad Element
Filter.c. Rectangular pick all
elements.d. Click Apply.
Step 4. Create Solid Elements
a
b
c
d
WS10A-16NAS120, Workshop 10A, January 2003
Step 4. Create Solid Elements
Verify element boundariesa. Elements: Verify /
Element / Boundaries.b. Click Apply. a
b
WS10A-17NAS120, Workshop 10A, January 2003
Step 4. Create Solid Elements
Equivalence the modela. Elements: Equivalence
/ All / Tolerance Cube.b. Click Apply. a
b
WS10A-18NAS120, Workshop 10A, January 2003
Step 4. Create Solid Elements
Verify element boundaries again
a. Elements: Verify / Element / Boundaries.
b. Click Apply.aa
b
WS10A-19NAS120, Workshop 10A, January 2003
Step 5. Create Boundary Condition
Set Picking Preferencesa. Select Preferences /
Picking b. Choose Enclose
Centroid for Rectangle/Polygon Picking.
c. Click Close.
a
b
c
WS10A-20NAS120, Workshop 10A, January 2003
Step 5. Create Boundary Condition
Create the boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter bolt_hole as the
New Set Name.c. Click Input Data.d. Enter <0 0 0> for
Translations e. Click OK.
a
b
c
d
e
WS10A-21NAS120, Workshop 10A, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select FEM.c. Click on Front View
Icon.d. Zoom in using View
Corners.e. Polygon pick nodes
on the bolt hole.f. Click Add.g. Click OK. h. Click Apply.
Step 5. Create Boundary Condition
ag
h
c
f
b
cd
WS10A-22NAS120, Workshop 10A, January 2003
a
Step 6. Create Load
Create the pressure loada. Loads/BCs: Create /
Pressure / Element Uniform.b. Enter clamp_pressure as
the New Set Name.c. Click Input Data.d. Enter 1 for the Pressure.e. Click OK.
b
e
d
c
WS10A-23NAS120, Workshop 10A, January 2003
Apply the pressure loada. Click Select
Application Region.b. For the Geometry
Filter select FEM.c. Click on Bottom View
Icon.d. Click on Fit View Icon.e. Rectangular pick the
top surface of solid elements as shown.
f. Click Add.g. Click OK. h. Click Apply.
Step 6. Create Load
a
b
cd
e
f
g
h
WS10A-24NAS120, Workshop 10A, January 2003
Step 7. Define Material Properties
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter titanium as the
Material Name.c. Click Input Properties.d. Enter 109e3 for the elastic
modulus and 0.3 for the Poisson Ratio.
e. Click OK. f. Click Apply.
a
b
c
d
fe
WS10A-25NAS120, Workshop 10A, January 2003
Step 8. Create Physical Properties
Create element propertiesa. Properties: Create / 3D /
Solid.b. Enter solid as the Property
Set Name.c. Click Input Properties.d. Select titanium as the
material.e. Click OK.
a
b
e
d
c
WS10A-26NAS120, Workshop 10A, January 2003
Step 8. Create Physical Properties
Apply the element propertiesa. Properties: Create / 3D /
Solid.b. Click in the Select
Members box.c. Select the Solid Element
filter.d. Rectangular pick all
elements as shown.e. Click Add.f. Click Apply.
a
b
c
d
e
f
WS10A-27NAS120, Workshop 10A, January 2003
Step 9. Run Linear Static Analysis
Choose the analysis typea. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Type.c. Choose Linear Static.d. Click OK. e. Click Apply.
a
e
b
d
c
WS10A-28NAS120, Workshop 10A, January 2003
Step 10. Plot Displacements and Stresses
Attach the results filea. Analysis: Attach XDB /
Result Entities / Local.b. Click Select Results File.c. Choose the results file
clamp.xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS10A-29NAS120, Workshop 10A, January 2003
Step 10. Plot Displacements and Stresses
Create a deformation plot for the mid span result case
a. Results: Create / Quick Plot.
b. Select Stress Tensoras the Fringe Result.
c. Select Von Mises as the Fringe Result Quantity.
d. Select Displacements, Translational as the Deformation Result.
e. Click Apply.
a
d
c
e
b
WS10A-30NAS120, Workshop 10A, January 2003
WS10B-1
WORKSHOP 10B
2½ D CLAMP – ISO MESHER
NAS120, Workshop 10B, January 2003
WS10B-2NAS120, Workshop 10B, January 2003
WS10B-3NAS120, Workshop 10B, January 2003
Problem Description Analyze the clamp shown below:
60 mm
100 mm150 mm
200 mm
30 mm
30 mm
50 mmR = 10 mm
WS10B-4NAS120, Workshop 10B, January 2003
Problem Description (cont.) A pressure loading of 1 N/mm2 is applied to the top face. Constrain the bolt hole in all three translations. Material Properties:
E = 109 x 103 N/mm2
ν =0.3
WS10B-5NAS120, Workshop 10B, January 2003
Workshop Objectives Practice the construction of simple (blue) solids
WS10B-6NAS120, Workshop 10B, January 2003
Suggested Exercise Steps1. Create a new database. 2. Create surface geometry. 3. Extrude the surface geometry into solids.4. Mesh the solid geometry. 5. Create a boundary condition.6. Create a pressure load.7. Define material properties.8. Create Physical Properties.9. Run the finite element analysis using MSC.Nastran.10. Plot displacements and stresses.
WS10B-7NAS120, Workshop 10B, January 2003
a
b c
d
f
g
h
Step 1. Create New Database
Create a new database called clamp.db
a. File / New.b. Enter clamp as the file name.c. Click OK.d. Choose Tolerance Based on
Model.e. Enter 200 for the Approximate
Maximum Model Dimension.f. Select MSC.Nastran as the
Analysis Code.g. Select Structural as the
Analysis Type.h. Click OK.
a
e
WS10B-8NAS120, Workshop 10B, January 2003
Step 2. Create Surface Geometry
Create two arcsa. Geometry: Create / Curve
/ 2D ArcAngles.b. Enter 10 for the Radius.c. Enter 90 for the Start
Angle.d. Enter 135 for the End
Angle.e. Enter <50 50 0> for the
Center Point List.f. Click Apply.g. Repeat this procedure for
a Start Angle of 135 and an End Angle of 180.
a
b
c
d
e
f
WS10B-9NAS120, Workshop 10B, January 2003
Step 2. Create Surface Geometry
Create another curvea. Geometry: Create /
Curve / XYZ.b. Enter <0 50 0> for the
Vector Coordinates List.c. Enter [0 50 0] for the
Origin Coordinates List.d. Click Apply.
a
b
c
d
WS10B-10NAS120, Workshop 10B, January 2003
Step 2. Create Surface Geometry
Create another curvea. Geometry: Create / Curve
/ XYZ.b. Enter <50 0 0> for the
Vector Coordinate List.c. Click in the Origin
Coordinates List box.d. Screen Pick the origin at
the top of the left curve as shown.
a
c
b
d
WS10B-11NAS120, Workshop 10B, January 2003
Step 2. Create Surface Geometry
Create 2 surfacesa. Geometry: Create /
Surface / Curve.b. Screen Pick the arc
section and opposite curve as shown.
c. Repeat the procedure to create another surface between the other two curves
a
b
c
WS10B-12NAS120, Workshop 10B, January 2003
Step 2. Create Surface Geometry
Mirror the surfacesa. Geometry: Transform /
Surface / Mirror.b. Enter Coord 0.1 for the
Mirror Plane Normal.c. Enter 50 for the offset.d. Click in the surface list box
and screen pick both surfaces.
e. Repeat the procedure with Coord 0.2 as the mirror plane normal, 50 for the offset, and all four upper surfaces selected.
a
b
c
d
e
WS10B-13NAS120, Workshop 10B, January 2003
Step 2. Create Surface Geometry
Extrude two surfacesa. Geometry: Create /
Surface / Extrude.b. Enter <50 0 0> for the
Translation Vector.c. Click in the Curve List box
and select the two edges as shown.
a
b
c
WS10B-14NAS120, Workshop 10B, January 2003
Step 2. Create Surface Geometry
Extrude two more surfacesa. Geometry: Create /
Surface / Extrude.b. Enter <50 0 0> for the
Translation Vector.c. Click in the Curve List
box and select the two edges as shown.
a
b
c
WS10B-15NAS120, Workshop 10B, January 2003
Step 3. Create Solid Geometry
Create solidsa. Geometry: Create /
Solid / Extrude.b. Change to Isometric
view.c. Set the solid type to
IsoMeshable.d. Enter <0 0 30> for the
Translation Vector.e. Click in the Surface List
box and rectangular pick to select all surfaces.
f. Select the top surface of two solids, as shown.
a
b
c
d
e
f
WS10B-16NAS120, Workshop 10B, January 2003
Step 4. Create Mesh
Create mesh seedsa. Elements: Create /
Mesh Seed / Uniform.b. Set the Number of
Elements to 6.c. Click in the Curve List
box and select the two edges, as shown.
a
b
c
WS10B-17NAS120, Workshop 10B, January 2003
Step 4. Create Mesh
Create a solid mesha. Elements: Create /
Mesh / Solid.b. Select Hex as the
element shape.c. Set the Mesher to
IsoMesher.d. Click in the Solid List
box and select all solids.
e. Set the Global Edge Length to 10.
f. Click Apply.
a
bc
d
e
f
WS10B-18NAS120, Workshop 10B, January 2003
Step 4. Create Mesh
Equivalence the modela. Elements:
Equivalence / All / Tolerance Cube.
b. Click Apply.
a
b
WS10B-19NAS120, Workshop 10B, January 2003
Step 5. Create Boundary Condition
Set Picking Preferencesa. Select Preferences /
Picking b. Choose Enclose
Centroid for Rectangle/Polygon Picking.
c. Click Close.
a
b
c
WS10B-20NAS120, Workshop 10B, January 2003
Step 5. Create Boundary Condition
Create the boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter bolt_hole as the
New Set Name.c. Click Input Data.d. Enter <0 0 0> for
Translations e. Click OK.
a
b
c
d
e
WS10B-21NAS120, Workshop 10B, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Click on the Iso 3 View Icon.
d. Zoom in using View Corners.
e. Select the Surface or Face Icon.
f. Pick all eight surfaces that surround the bolt hole.
g. Click Add.h. Click OK. i. Click Apply.
Step 5. Create Boundary Condition
ah
i
g
b
cd
f
e
WS10B-22NAS120, Workshop 10B, January 2003
a
Step 6. Create Load
Create the pressure loada. Loads/BCs: Create /
Pressure / Element Uniform.b. Enter clamp_pressure as
the New Set Name.c. Click Input Data.d. Enter 1 for the Pressure.e. Click OK.
b
e
d
c
WS10B-23NAS120, Workshop 10B, January 2003
Apply the pressure loada. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Click on the Iso 3 View Icon.
d. Click on the Fit View Icon.
e. Pick the top surfaces of the solids as shown.
f. Click Add.g. Click OK. h. Click Apply.
Step 6. Create Load
a
b
cd
ef
g
h
WS10B-24NAS120, Workshop 10B, January 2003
Step 7. Define Material Properties
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter titanium as the
Material Name.c. Click Input Properties.d. Enter 109e3 for the elastic
modulus and 0.3 for the Poisson Ratio.
e. Click OK. f. Click Apply.
a
b
c
d
fe
WS10B-25NAS120, Workshop 10B, January 2003
Step 8. Create Physical Properties
Create element propertiesa. Properties: Create / 3D /
Solid.b. Enter solid as the Property
Set Name.c. Click Input Properties.d. Select titanium as the
material.e. Click OK.
a
b
e
dc
WS10B-26NAS120, Workshop 10B, January 2003
Step 8. Create Physical Properties
Apply the element propertiesa. Properties: Create / 3D /
Solid.b. Click on the Bottom View
icon.c. Click in the Select
Members box.d. Rectangular pick all solids
as shown.e. Click Add.f. Click Apply.
a
c
d
e
f
b
WS10B-27NAS120, Workshop 10B, January 2003
Step 9. Run Linear Static Analysis
Choose the analysis typea. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Type.c. Choose Linear Static.d. Click OK. e. Click Apply.
a
e
b
d
c
WS10B-28NAS120, Workshop 10B, January 2003
Step 10. Plot Displacements and Stresses
Attach the results filea. Analysis: Access Results /
Attach XDB / Result Entities.
b. Click Select Results File.c. Choose the results file
clamp.xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS10B-29NAS120, Workshop 10B, January 2003
Step 10. Plot Displacements and Stresses
Create a quick plota. Results: Create / Quick
Plot.b. Select Stress Tensor
as the Fringe Result.c. Select Von Mises as
the Fringe Result Quantity.
d. Select Displacements, Translational as the Deformation Result.
e. Click Apply.
a
d
c
e
b
WS10B-30NAS120, Workshop 10B, January 2003
WS11-1
WORKSHOP 11
SUPPORT BRACKET
NAS120, Workshop 11, January 2003
WS11-2NAS120, Workshop 11, January 2003
WS11-3NAS120, Workshop 11, January 2003
Problem Description A bracket is constructed from titanium alloy Ti-6Al-4V with the following
properties:E = 16 x 106 psi ν =0.31
A pressure load of 100 psi is applied to the top face of the support bracket.
The bracket is attached with two bolts. Model the bracket with tetrahedron elements.
WS11-4NAS120, Workshop 11, January 2003
Workshop Objectives Import a parasolid part
Mesh the part using TET 4 elements
Re-mesh the part using TET 10 elements
Evaluate the averaged and un-averaged stress results
WS11-5NAS120, Workshop 11, January 2003
Suggested Exercise Steps1. Create a new database and name it bracket_tet4.db. 2. Import the parasolid part file support_bracket.xmt. 3. Mesh the part using TET4 elements. Use a global edge length of 0.375 in. 4. Create material and element properties.5. Constrain the two cylindrical holes to react shear loads (x and y translations).6. Constrain the back face to react z loads (z translation).7. Apply 100 psi to the top bracket face.8. Run the finite element analysis using MSC.Nastran.9. Plot displacements and stresses (averaged, un-averaged, and difference). 10. File / save a copy as bracket_tet10.db.11. Close the database and open the bracket_tet10 database.12. Delete the original results file.13. Re-mesh the part with TET10 elements. Use a global edge length of 0.375 in.14. Re-run the analysis.15. Attach the new results file to the database.16. Plot displacements and stresses (averaged, un-averaged, and difference). 17. Compare the TET10 model results with the TET4 model results.18. If time permits, re-mesh the model with TET10 elements using a global edge
length of 0.125 and run the analysis. This finer mesh will generate more accurate stress results than the previous two models.
WS11-6NAS120, Workshop 11, January 2003
a
b c
d
f
g
Step 1. Create New Database
Create a new database called bracket_tet4.db
a. File / New.b. Enter bracket_tet4 as the file
name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
e
WS11-7NAS120, Workshop 11, January 2003
Step 2. Import Parasolid File
Import the Parasolid Filea. File: Import.b. Set the object to model
and the source to Parasolid.xmt.
c. Select support_bracket.xmt.
d. Click Apply.
ab
c
d
WS11-8NAS120, Workshop 11, January 2003
Step 3. Create Mesh
Create a solid mesha. Elements: Create / Mesh
/ Solid.b. Set the topology to
TET4.c. Select the entire solid.d. Enter 0.375 for the
Global Edge Length.e. Click Apply.
a
b
c
d
e
WS11-9NAS120, Workshop 11, January 2003
Step 4. Create Material and Element Properties
a
c
b
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter Ti-6Al-4V as the
Material Name.c. Click Input Properties.d. Enter 16e6 for the Elastic
Modulus and 0.31 for the Poisson Ratio.
e. Click OK. f. Click Apply.
d
fe
WS11-10NAS120, Workshop 11, January 2003
Step 4. Create Material and Element Properties
Create element propertiesa. Properties: Create / 3D /
Solid.b. Enter bracket_prop as the
Property Set Name.c. Click Input Properties.d. Select Ti-6Al-4V as the
material.e. Click OK.
a
b
c
e
d
WS11-11NAS120, Workshop 11, January 2003
Apply the element propertiesa. Properties: Create / 3D /
Solid.b. Click in the Select
Members box.c. Rectangular pick all
elements as shown.d. Click Add.e. Click Apply.
a
b
c
d
e
Step 4. Create Material and Element Properties
WS11-12NAS120, Workshop 11, January 2003
Step 5. Constrain Bolt Holes
a
b
Create a boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter bolt_hole as the
New Set Name.c. Click Input Data.d. Enter <0,0, > for
Translations e. Click OK.
b
c
d
e
a
WS11-13NAS120, Workshop 11, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Click on Iso 2 ViewIcon.
d. Click on the Smooth Shaded View Icon.
e. Set the Selection Filter to Surface or Face and shift click to select the surfaces of both bolt holes.
f. Click Add.g. Click OK. h. Click Apply.
Step 5. Constrain Bolt Holes
ag
h
f
b
cd
e
WS11-14NAS120, Workshop 11, January 2003
Step 6. Constrain the Back Face
a
Create a boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter back_face as the
New Set Name.c. Click Input Data.d. Enter < , ,0> for
Translations e. Click OK.
b
c
d
e
WS11-15NAS120, Workshop 11, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Select the Back Face.d. Click Add.e. Click OK. f. Click Apply.
ae
f
d
b
c
d
Step 6. Constrain the Back Face
WS11-16NAS120, Workshop 11, January 2003
a
Step 7. Create Pressure Load
Create the pressure loada. Loads/BCs: Create /
Pressure / Element Uniform.b. Enter top_pressure as the
New Set Name.c. Click Input Data.d. Enter 100 for the Pressure.e. Click OK.
b
e
d
c
WS11-17NAS120, Workshop 11, January 2003
Apply the pressure loada. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Select the top surface of the bracket.
d. Click Add.e. Click OK. f. Click Apply.
Step 7. Create Pressure Load
a
b
c
d
e
f
WS11-18NAS120, Workshop 11, January 2003
Step 8. Run Linear Static Analysis
Analyze the modela. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Type.c. Choose Linear Static.d. Click OK. e. Click Apply.
a
e
b
d
c
WS11-19NAS120, Workshop 11, January 2003
Step 9. Plot Displacements and Stresses
Attach the results filea. Analysis: Attach XDB /
Result Entities / Local.b. Click Select Results File.c. Choose the results file
bracket_tet4.xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS11-20NAS120, Workshop 11, January 2003
Step 9. Plot Displacements and Stresses
Create a quick plota. Results: Create / Quick
Plot.b. Select Stress Tensor
as the Fringe Result.c. Select Von Mises as
the Fringe Result Quantity.
d. Select Displacements, Translational as the Deformation Result.
e. Click Apply.
Maximum Averaged Stress:
__________________
Maximum Displacement:
___________________
a
d
c
e
b
WS11-21NAS120, Workshop 11, January 2003
Step 9. Plot Displacements and Stresses
Create a fringe plota. Results: Create /
Fringe.b. Select Stress
Tensor as the Fringe Result.
c. Select Von Mises as the Fringe Result Quantity.
d. Click on the Plot Options Icon.
e. Set the Averaging domain to none.
f. Click Apply.
a
d
c
b
Maximum Un-averaged Stress:
__________________
e
f
WS11-22NAS120, Workshop 11, January 2003
Step 9. Plot Displacements and Stresses
Create a fringe plota. Results: Create / Fringe.b. Select the Plot Options
tool.c. Set the Averaging
domain to All Entities and the Method to Difference.
d. Click Apply.
Maximum Stress Difference:
__________________
a
d
c
b
WS11-23NAS120, Workshop 11, January 2003
Step 10. Save a Copy
Save a copy of the filea. File: Save a Copy.b. Type bracket_tet10 as the
file name.c. Click Save.
a
b c
WS11-24NAS120, Workshop 11, January 2003
Step 11. Open the New Database
Close the original file and open the new file
a. File: Close.b. File: Open.c. Select the file:
bracket_tet10.db.d. Click OK.
ab
c
d
WS11-25NAS120, Workshop 11, January 2003
Step 12. Delete Old Results File
Delete XDB attachmenta. Analysis: Delete / XDB
Attachment.b. Select the
bracket_tet4.xdbattachment
c. Click Apply.d. Choose Yes to delete
the attachment.
a
b
cd
WS11-26NAS120, Workshop 11, January 2003
Step 13. Re-Mesh the Part
Create a solid mesha. Elements: Create / Mesh
/ Solid.b. Set the topology to
TET10.c. Select the entire solid.d. Enter 0.375 for the
Global Edge Length.e. Click Apply.f. Choose Yes to delete
the existing mesh.
a
b
c
d
ef
WS11-27NAS120, Workshop 11, January 2003
Step 14. Run Linear Static Analysis
Analyze the modela. Analysis: Analyze /
Entire Model / Full Run.
b. Change the job name to bracket_tet10.
c. Click Apply.
a
b
c
WS11-28NAS120, Workshop 11, January 2003
Step 15. Attach New Results File
Attach the results filea. Analysis: Attach XDB /
Result Entities / Local.b. Click Select Results File.c. Choose the results file
bracket_tet10.xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS11-29NAS120, Workshop 11, January 2003
Step 16. Plot Displacements and Stresses
a
d
c
e
b
Create a quick plota. Results: Create / Quick
Plot.b. Select Stress Tensor
as the Fringe Result.c. Select Von Mises as
the Fringe Result Quantity.
d. Select Displacements, Translational as the Deformation Result.
e. Click Apply.
Maximum Averaged Stress:
__________________
Maximum Displacement:
___________________
c
WS11-30NAS120, Workshop 11, January 2003
Step 16. Plot Displacements and Stresses
Create a fringe plota. Results: Create /
Fringe.b. Select Stress Tensor
as the Fringe Result.c. Select Von Mises as
the Fringe Result Quantity.
d. Click on the Plot Options Icon.
e. Set the Averaging domain to none.
f. Click Apply.
Maximum Un-averaged Stress:
__________________
a
d
c
be
f
WS11-31NAS120, Workshop 11, January 2003
Step 16. Plot Displacements and Stresses
Maximum Stress Difference:
__________________
a
d
c
b
Create a fringe plota. Results: Create / Fringe.b. Select the Plot Options
tool.c. Set the Averaging
domain to All Entities and the Method to Difference.
d. Click Apply.
WS11-32NAS120, Workshop 11, January 2003
NAS120, Workshop 12, January 2003 WS12-1
WORKSHOP 12
SPACECRAFT FAIRING
WS12-2NAS120, Workshop 12, January 2003
WS12-3NAS120, Workshop 12, January 2003
Problem Description In this exercise, a spacecraft fairing will be constructed. Curves and
surfaces will be used to define the fairing geometry. The finite element model will consist of 2-dimensional elements with 1-dimensional elements applied at various edges of the geometry. The 1-dimensional elements will represent stiffeners for the structure.
WS12-4NAS120, Workshop 12, January 2003
Workshop Objectives Learn to use Groups and Lists
WS12-5NAS120, Workshop 12, January 2003
Suggested Exercise Steps1. Create a new database called fairing.db and set the model preferences.2. Create the model geometry.3. Create the mesh seeds for the model.4. IsoMesh the model using Quad4 topology.5. Check the free edges, equivalence the model, and then check the free
edges again.6. Create a new group called FEM that contains only the finite elemental
model. Then post only the FEM group.7. Create two material properties, alum_1 and alum_2.8. Create two fields, one for temperature and the other for thickness.9. Create element properties.10. Create a temperature boundary condition.11. Create a series of lists containing elements that satisfy these following
requirements: 1) the elements are made up of the alum_1 material, 2) the elements are greater than 0.98 in thickness, and 3) the elements have a temperature greater than 230.0 degrees.
12. Intersect lists a and b to produce a list of elements that satisfy the first two conditions.
WS12-6NAS120, Workshop 12, January 2003
Suggested Exercise Steps (Cont.)13. Create another list that satisfies the third condition.14. Intersect the new list with the other list to produce a group of elements that
satisfy all three conditions. Then, place these elements in a separate group.
15. Post the group containing the elements produced in step 14.16. Create 2 new groups, each containing elements with different property sets.17. Change the display attributes for each group.18. Post each group separately, then post both groups together.
WS12-7NAS120, Workshop 12, January 2003
Step 1. Create New Database
Create a new database and set the model preferences.
a. File : New.b. Enter fairing for the File Name.c. Click OK.d. Set the Tolerance to Default.e. Make sure that the Analysis Code
and Analysis Type are set to MSC.Nastran and Structural,respectively.
f. Click OK.
a
b c
d
e
f
WS12-8NAS120, Workshop 12, January 2003
Step 2. Create Model Geometry
Create the points and curves that represent the outline of the fairing.
a. Geometry : Create / Point / XYZ.b. Enter [30 0 0] under Points
Coordinates List and click Apply.
c. Geometry : Create / Curve / XYZ.d. Enter <0 120 0> and [50 40 0]
under Vector Coordinates List and Origin Coordinates List,respectively.
e. Click Apply.f. Click on Show Labels icon.g. Click on Point Size icon to
increase the point size.h. Geometry : Create / Curve / Point.i. Click on Point 1 under Starting
Point List and click on Point 2 forEnding Point List.
j. Click Apply.
a
b
c
d
e
h
i
j
f g
WS12-9NAS120, Workshop 12, January 2003
Step 2. Create Model Geometry (Cont.)
Illustrated here are curves that represent the basic geometry for the fairing. These curves will be revolved 360º in order to get the final model.
WS12-10NAS120, Workshop 12, January 2003
Step 2. Create Model Geometry (Cont.)
Create the fairing by revolving curves 1 and 2 about the fairing’s vertical center line.
a. Geometry : Create / Surface / Revolve.
b. Enter Coord 0.2 for Axisc. Enter 360 for the Total
Angle.d. Shift-select curves 1 and 2.e. Click Apply.f. Viewing : Angles.g. Enter 30 0 0 under Angles.h. Click Apply.
a
b
c
de
f
g
h
WS12-11NAS120, Workshop 12, January 2003
Step 2. Create Model Geometry (Cont.)
Change the display preferences in order to get a clearer visual of the model.
a. Display : Geometry…b. Enter 3 for Number of
Display Linesc. Click Apply, then Cancel.
a
b
c
WS12-12NAS120, Workshop 12, January 2003
Step 3. Create Mesh Seeds
Create a finite element mesh so that 4 node Quad elements are created every 10° along
the circumferential edges.
a. Elements : Create / MeshSeed / Uniform.
b. Select Number of Elements and enter 36 for the Number.
c. Select the top circumferential edge of the fairing(Surface 1.3)and click Apply.
a
b
c
WS12-13NAS120, Workshop 12, January 2003
Step 3. Create Mesh Seeds (Cont.)
In the vertical direction (y-direction), define a smoothly transitioning mesh density. The elements along the top of the cylinder are 2.5 times as large as those along the bottom edge (tapered end) of the fairing.
a. Elements : Create / Mesh Seed / One Way Bias.
b. Select L1 and L2 and enter 7 and 10 for L1 and L2, respectively.
c. Under Curve List, Select Curve 1and click Apply.
d. Elements : Create / Mesh Seed / One Way Bias.
e. Select L1 and L2 and enter 4 and 7 for L1 and L2, respectively.
f. Under Curve List, Select Curve 2and click Apply.
a
c
b
d
e
f
WS12-14NAS120, Workshop 12, January 2003
Step 4. Create a Mesh for the Model
Now that the mesh seeds have been created, mesh the model using Quad4 topology.
a. Elements : Create / Mesh/ Surface.
b. Select Quad, IsoMesh,and Quad4.
c. Rectangular pick the entire model and clickApply.
d. Remove the display lines by clicking the on the Display lines icon.
e. Remove the labels byclicking the Hide labelsicon.
f. Decrease the point-sizeby clicking on the Point Size icon.
a
b
c
e df
WS12-15NAS120, Workshop 12, January 2003
Step 4. Create a Mesh for the Model (Cont.)
Mesh the horizontal (circumferential) edges of each surface with two-noded bar elements.
a. Click on Plot/Erase icon andclick on Erase under FEM.
b. Click OK.c. Elements : Create / Mesh /
Curve. d. Set Topology to Bar2e. Shift select the 3 curves (as
indicated).f. Click Apply. b
c
d
e
f
a
e
WS12-16NAS120, Workshop 12, January 2003
Step 5. Observe the Free Edges
Check the free edges of the model, equivalence, and then check the free edges again.
a. Elements : Verify / Element / Boundaries.
b. Select Free Edges underDisplay Type.
c. Click Apply.d. Elements : Equivalence / All /
Tolerance Cube.e. Click Apply.f. Repeat steps a through c.
a
b
c
d
e
WS12-17NAS120, Workshop 12, January 2003
Step 6. Create a New Group
Replot the FEM and create a group called FEM containing only the finite elemental model. Post only this new group to the viewport.
a. Click on the Plot/Erase icon.b. Under FEM, click Plot.c. Click OK.d. Group : Create…e. Enter FEM for the New Group
Name.f. Select Unpost All Other
Groups.g. Change Group Contents to
Add All FEM.h. Click Apply.
a
b
c
d
e
f
g
h
WS12-18NAS120, Workshop 12, January 2003
Step 7. Create Material Properties
Create the first material for the model. Material alum_1 will be applied to the top(cylindrical) portion of the fairing.
a. Materials : Create / Isotropic / Manual Input.
b. Enter alum_1 for the MaterialName.
c. Click on Input Properties.d. Select Linear Elastic and
enter 1.05E7, 0.33, and 2.6E-4, for Elastic Modulus,Poisson Ratio, and Density,respectively.
e. Click OK.f. Click Apply.
a
b
c
d
ef
WS12-19NAS120, Workshop 12, January 2003
Step 7. Create Material Properties (Cont.)
Create the second material for the model. Material alum_2 will be applied to the bottom(tapered) portion of the fairing.
a. Materials : Create / Isotropic / Manual Input.
b. Enter alum_2 for the MaterialName.
c. Click on Input Properties.d. Select Linear Elastic and
enter 1.18E7, 0.33, and 2.4E-4, for Elastic Modulus,Poisson Ratio, and Density,respectively.
e. Click OK.f. Click Apply.
a
b
c
d
ef
WS12-20NAS120, Workshop 12, January 2003
Step 8. Create Fields
Define a field that represents the varying thickness.
a. Fields : Create / Spatial / PCLFunction.
b. Enter thickness for the FieldName.
c. Enter 1.5-’Y/160 for the ScalarFunction and click Apply.
a
b
c
WS12-21NAS120, Workshop 12, January 2003
Step 8. Create Fields
Plot the function defined in the field.
A. Field : ShowB. Select thickness as the
field to show.C. Click Specify Range.D. Enter 160.0 for the
maximum and 20 for the number of points.
E. Click O.K.F. Click Apply.
a
bd
e c
f
WS12-22NAS120, Workshop 12, January 2003
Step 8. Create Fields
Delete the plot.A. XY Plot : Delete /
XYWindowB. Select XY Result
Window.C. Click Apply.D. Choose Yes to delete the
result window.
a
b
c
d
WS12-23NAS120, Workshop 12, January 2003
Define a field that represents the varying temperature distribution.
a. Fields : Create / Spatial / PCLFunction.
b. Enter temperature for the Field Name.
c. Enter 200.0-(150.0/160.0)*’Xfor the Scalar Function and click Apply.
Step 8. Create Fields
a
b
c
WS12-24NAS120, Workshop 12, January 2003
Step 8. Create Fields
Plot the function defined in the field.
A. Field : ShowB. Select temperature as
the field to show.C. Click Specify Range.D. Enter 50.0 for the
maximum and 10 for the number of points.
E. Click O.K.F. Click Apply.
bd
e c
a
f
WS12-25NAS120, Workshop 12, January 2003
Step 9. Create Element Properties
Create two element properties which include the material definitions and varying thickness.
a. Click on the Front view icon.
b. Properties : Create / 2D / Shell.
c. Enter prop_1 for the Property Set Name.
d. Click on Input Properties.e. Click on Material Name and
select alum_1 from the Material Property Setslist box.
a
b
c
d
e
WS12-26NAS120, Workshop 12, January 2003
Step 9. Create Element Properties (Cont.)
Finish creating the first property set.a. Click on Thickness and select
thickness from the FieldDefinitions list.
b. Click OK.c. Click on Select Members and
click on the Shell Element icon.
d. Select the top(cylindrical) portion of the fairing bydragging a box around thedesired section (as indicatedon next page).
e. Click Add, then Apply.
a
b
d
c
e
WS12-27NAS120, Workshop 12, January 2003
Step 9. Create Element Properties (Cont.)
Illustrated here is the desired application region for the first property set.
WS12-28NAS120, Workshop 12, January 2003
Step 9. Create Element Properties (Cont.)
Create the second property set.a. Properties : Create / 2D /
Shell.b. Enter prop_2 for the Property
Set Name.c. Click on Input Properties…d. Click on Material Name and
select alum_2 from the Material Property Sets.
e. Click on Thickness and selectthickness from the FieldDefinitions box.
f. Click OK.g. Click on Select Members and
select the bottom(tapered)portion of the fairing by dragging a box around it(as indicated on next page).
h. Click Add, then Apply.
a
b
c
d
e
f
g
h
WS12-29NAS120, Workshop 12, January 2003
Step 9. Create Element Properties (Cont.)
Shown here are the elements for the desired application region of the second property set.
WS12-30NAS120, Workshop 12, January 2003
Step 10. Create Temperature Boundary Conditions
Define the model’s varying temperature distribution.
a. Loads/BCs : Create / Temperature/ Nodal.
b. Enter temp for the New Set Name.
c. Click on Input Data.d. Click on Temperature and select
temperature from the Spatial Fields.
e. Click OK.f. Click on Select Application
Region.g. Under Geometry Filter, select
FEM.h. Click on Application Region and
select the entire model.i. Click Add, then, OKj. Click Apply.
a
b
c
d
e
f
g
h
i
j
WS12-31NAS120, Workshop 12, January 2003
Step 10. Create Temperature Boundary Conditions (Cont.)
Turn off the temperature labels in order to get a better visualization of the model.
a. Display : Load/BC/Elem. Prop…
b. Under Loads/BC’s remove check under Temperature.
c. Click Apply, then Cancel.
a
b
c
WS12-32NAS120, Workshop 12, January 2003
Step 11. Create Lists
Use Lists and groups to filter then group the quad elements that have the following attributes:Material : alum_1Thickness : > 0.98 Temperature : >230.0
a. Tools : List / Create…b. FEM / Element / Attributec. Under Attribute, select Material.d. Under Existing Materials, select
alum_1. e. Set the Target List to “A” and click
Apply.
a
b
c
d
e
The contents of List Acompose of elements that satisfy the first condition; they are made up of the alum_1 material.
WS12-33NAS120, Workshop 12, January 2003
Step 11. Create Lists (Cont.)
Define List B to include only the Quad elements that have a thickness greater than 0.98.
a. Properties : Show / Shell.b. Under Existing Properties,
select Thickness.c. Set Display Method to
Scalar Plot.d. Select Current Viewport,
select FEM and click Apply.
a
b
c
dShown above is a fringe plot the model by thickness. Those elements that are thicker than 0.98 will be included in the next list.
WS12-34NAS120, Workshop 12, January 2003
Step 11. Create Lists (Cont.)
After defining the list parameters, add the elements greater than 0.98 in thickness to list B.
a. Tools : List / Create…b. FEM / Element / Attribute.c. Under Attribute, select Fringe
Value.d. Under Fringe Tools, select
default_Fringe.e. Change the inequality to > and
enter 0.98.f. Select “B” for the Target List.g. Click on Apply.
a
b
c
d
e
f
g
The contents of List B include all elements thicker than 0.98.
WS12-35NAS120, Workshop 12, January 2003
Step 12. Intersect Lists
Intersect Lists A and B and replace the contents of List A with the elements found in the intersection.
a. Tools : List / Boolean…b. Click on the Intersect icon.c. Click on Replace A.
The new List A is composed of elements that satisfy both requirements: they are made up of alum
a
b
c
WS12-36NAS120, Workshop 12, January 2003
Step 13. Create More Lists
Perform a final classification of the elements. Isolate those elements that satisfy the third condition of the applied temperature load > 230.0.
a. Loads/BCs : Plot Contours / Temperature.
b. Select temp from the Existing Sets.
c. Select Temperature underSelect Data Variable.
d. Select the FEM group andclick Apply.
a
b
c
d
WS12-37NAS120, Workshop 12, January 2003
Step 13. Create More Lists (Cont.)
Clear the contents of List B and add the values obtained from the final classification.
a. Tools : List / Create.b. FEM / Element / Attribute.c. Select Fringe Value and
default_Fringe for Attribute and Fringe Tools respectively.
d. Change the inequality to > and enter230.0.
e. Select “B” for the Target List.f. Click on Clear on the List B formg. Click Apply on the List Create
form.
a
b
c
d
e
f
g
WS12-38NAS120, Workshop 12, January 2003
Step 14. Intersect Lists Again
Lists A and B will be intersected again to create a List C. This list will contain the elements that satisfy all three conditions. The contents of List C will then be placed into a new group called common_quads.
a. Tools : List / Boolean…b. Click Clear.c. Click on the Intersect icon(It
may be necessary to click onany of the other icons first).
d. Click on Add To Group…e. Enter common_quads for the
Group Name.f. Click Apply, then Cancel.
a
b
c
d e
f
WS12-39NAS120, Workshop 12, January 2003
Step 15. Post Group
Post the common_quad group. This is the group of elements that satisfy all three of the conditions defined earlier.
a. Group : Post…b. Select the
common_quads groupunder Select Groups toPost.
c. Click Apply, thenCancel.
d. Click on the Iso 1 viewicon.
a
b
c
d
WS12-40NAS120, Workshop 12, January 2003
Step 15. Post Group (Cont.)
This is the Iso 1 view of the elements in the common_quads group. These are all the elements that satisfied all three conditions.
WS12-41NAS120, Workshop 12, January 2003
Step 16. Create Two New Groups
Create two new groups, prop1_group and prop2_group. Then, change the display attributes for each group.
a. Click on the Reset Graphics icon.
b. Group : Create…c. Create / Property Set.d. Enter prop1_group for the
Group Name.e. Select prop_1 under Property
Sets and click Apply.f. Repeat steps b through e
entering prop2_group for theGroup Name and selecting prop_2 under Property Sets.
a
b
c
d
e
f
WS12-42NAS120, Workshop 12, January 2003
Step 17. Change the Display Attributes
Set the entity coloring and labeling to Group mode and then change the display attributes for each of the two new groups.
a. Display : Entity / Color / Label / Render…b. Select Group under Entity Color and
Labeling.c. Select the prop1_group under the Target
Group(s).d. Select HiddenLine for the Render Style
and select dark blue for the Shade Color.e. Click Apply.f. Select the prop2_group for the Target
Group(s).g. Select Wireframe for the Render Style and
select red for the Shade Color.h. Click Apply, then, Cancel.
a
b
c
d
e
f
g
h
WS12-43NAS120, Workshop 12, January 2003
Step 18. Post Groups
Change views and post the prop1_group.
a. Click on the Iso 3 view icon.b. Group : Post…c. Under Select Groups to
Post, select prop1_group.
d. Click Apply.
a
b
c
d
WS12-44NAS120, Workshop 12, January 2003
Step 18. Post Groups (Cont.)
Post only the prop2_group.a. Group : Post…b. Under Select Groups to
Post, selectprop2_group.
c. Click Apply.
a
b
c
WS12-45NAS120, Workshop 12, January 2003
Step 18. Post Groups (Cont.)
Post both the prop1_group and the prop2_group.
a. Group : Post…b. Under Select
Groups to Post, select both prop1_groupand prop2_group.
c. Click Apply.
a
b
c
WS12-46NAS120, Workshop 12, January 2003
WS13-1
WORKSHOP 13
RBE2 vs. RBE3
NAS120, Workshop 13, January 2003
WS13-2NAS120, Workshop 13, January 2003
WS13-3NAS120, Workshop 13, January 2003
Problem Description A rectangular plate is fixed at its left and right edges. A rigid body
element is in the middle of the plate. Model this two ways in one database using RBE2 and RBE3 elements.
E = 10 x 106 psi ν =0.33 t = 0.2 in
WS13-4NAS120, Workshop 13, January 2003
Workshop Objectives Practice constructing RBE2 and RBE3 in Patran.
Understand the difference between RBE2 and RBE3
WS13-5NAS120, Workshop 13, January 2003
Suggested Exercise Steps1. Create a new database and name it rbe2_vs_rbe3.db. 2. Create four rectangular surfaces.3. Mesh the surfaces to create plate elements. 4. Create two additional nodes.5. Create an RBE2 MPC. 6. Create an RBE3 MPC.7. Apply Loads and Boundary Conditions.8. Create material properties. 9. Create physical properties.10. Run analysis with MSC.Nastran.11. Read the results into MSC.Patran.12. Plot the Von Mises stress and displacement. 13. Create vector marker plots to compare the RBE2 and RBE3 elements.
WS13-6NAS120, Workshop 13, January 2003
a
b c
d
f
g
Step 1. Create New Database
Create a new database called rbe2_vs_rbe3.db
a. File / New.b. Enter rbe2_vs_rbe3 as the
file name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
e
WS13-7NAS120, Workshop 13, January 2003
Step 2. Create Rectangular Surfaces
Create a surfacea. Geometry: Create /
Surface / XYZ.b. Enter <10 10 0> for
the Vector Coordinates List.
c. Enter [0 0 0] [0 15 0] [20 0 0] [20 15 0] for the Origin Coordinates List.
d. Click Apply.b
d
a
c
WS13-8NAS120, Workshop 13, January 2003
Step 3. Mesh the Surfaces
Create a surface mesha. Elements: Create / Mesh
/ Surface.b. Select the surfaces.c. Enter 2.5 for the Global
Edge Length.d. Click Apply.
a
b
c
d
WS13-9NAS120, Workshop 13, January 2003
Step 4. Create Two Nodes
Create two nodesa. Elements: Create / Node
/ Edit.b. Enter 1000 for the Node
ID.c. Enter [15 5 0] for the
Node Location List.d. Click Apply.e. Repeat the procedure
with 2000 as the Node ID and [15 20 0] as the Node Location.
f. Click on the Node SizeIcon
a
b
c
d
f
WS13-10NAS120, Workshop 13, January 2003
Step 5. Create RBE2
Define dependent nodes.a. Elements: Create / MPC
/ RBE2.b. Enter 1000 for the MPC
ID.c. Click on Define Terms.d. Disable Auto Execute.e. Select the nodes on the
lower inner edges, as shown.
f. Select all six degrees of freedom in the DOFs list.
g. Click Apply.
a
b
c
d
e
f
g
WS13-11NAS120, Workshop 13, January 2003
Step 5. Create RBE2
Define independent nodesa. Select Node 1000 in
the Node List box.b. Click Apply.c. Click Cancel.d. Click Apply in the
Finite Elements form.
a
b c
d
WS13-12NAS120, Workshop 13, January 2003
Step 6. Create RBE3
Define dependent nodes.a. Elements: Create / MPC
/ RBE3.b. Enter 2000 for the MPC
ID.c. Click on Define Terms.d. Select Node 2000 in the
Node List box.e. Select all six degrees of
freedom in the DOFs list.f. Click Apply.
a
b
c
d
f
e
WS13-13NAS120, Workshop 13, January 2003
Step 6. Create RBE3
e
b
d
c
Define independent nodesa. Click on Create
Independent.b. Select the nodes on
the upper inner edges, as shown.
c. Select UX, UY, and UZ in the DOFs list.
d. Click Apply.e. Click Cancel.
a
WS13-14NAS120, Workshop 13, January 2003
Step 6. Create RBE3
Finish creating RBE3a. Elements: Create /
MPC / RBE3.b. Click Apply.
a
b
WS13-15NAS120, Workshop 13, January 2003
Step 7. Apply Loads and Boundary Conditions
Create a boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter fixed as the New Set
Name.c. Click Input Data.d. Enter <0 0 0> for
Translations and Rotations. e. Click OK.
b
c
d
e
a
WS13-16NAS120, Workshop 13, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Set the Selection Filter to Curve or Edge and select an outer edge, as shown.
d. Click Add.e. Repeat the procedure
until all four edges have been added.
f. Click OK. g. Click Apply.
af
g
d
b
Step 7. Apply Loads and Boundary Conditions
c
WS13-17NAS120, Workshop 13, January 2003
Step 7. Apply Loads and Boundary Conditions
Create a loada. Loads/BCs: Create / Force
/ Nodal.b. Enter point_load as the
New Set Name.c. Click Input Data.d. Enter <100 0 0> for Force. e. Click OK.
b
c
d
e
a
WS13-18NAS120, Workshop 13, January 2003
Apply the loada. Click Select
Application Region.b. For the Geometry
Filter select FEM.c. Select Nodes 1000
and 2000.d. Click Add.e. Click OK. f. Click Apply.
ae
f
d
b
Step 7. Apply Loads and Boundary Conditions
c
WS13-19NAS120, Workshop 13, January 2003
Step 8. Create Material Properties
a
c
b
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter aluminum for the
Material Name.c. Click Input Properties.d. Enter 10e6 for the Elastic
Problem Description A rectangular plate is simply supported at all edges. Find the first 10
normal modes for this plate. E = 10 x 106 psi ν =0.33 ρ = 0.101 lb/in3
t = 0.125 in
WS14-4NAS120, Workshop 14, January 2003
Workshop Objectives Perform a normal modes analysis on a rectangular plate.
Evaluate the quality of the normal modes solution graphically.
Compare analysis results to theoretical results.
Evaluate the effect of varying mesh density.
WS14-5NAS120, Workshop 14, January 2003
Suggested Exercise Steps1. Create a new database and name it rectangular_plate1.db. 2. Create a rectangular surface.3. Mesh the surface to create plate elements. 4. Create material properties. Don’t forget to enter density.5. Create physical properties.6. Apply Loads and Boundary Conditions.7. Perform a normal modes analysis to determine the first 10 modes for the plate.8. Read the results into MSC.Patran.9. Plot the mode shapes. Visually evaluate the quality of the mode shapes. 10. Compare the first natural frequency to theoretical results. 11. File / save a copy as rectangular_plate2.db.12. Close the database and open the rectangular_plate2 database.13. Delete the original results file.14. Re-mesh the surface. Use a global edge length of 0.5 in.15. Re-run the analysis.16. Attach the new results file to the database.17. Plot the mode shapes. 18. Compare the results from the finer mesh with the earlier results.
WS14-6NAS120, Workshop 14, January 2003
a
b c
d
f
g
Step 1. Create New Database
Create a new database called rectangular_plate1.db
a. File / New.b. Enter rectangular_plate1 as
the file name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
e
WS14-7NAS120, Workshop 14, January 2003
Step 2. Create a Rectangular Surface
Create a surfacea. Geometry: Create /
Surface / XYZ.b. Enter <12 8 0> for the
Vector Coordinates list.c. Click Apply.
b
c
a
WS14-8NAS120, Workshop 14, January 2003
Step 3. Mesh the Surface
Create a surface mesha. Elements: Create / Mesh
/ Surface.b. Select the surface.c. Enter 1.4 for the Global
Edge Length.d. Click Apply.
a
b
c
d
WS14-9NAS120, Workshop 14, January 2003
Step 4. Create Material Properties
a
c
b
Create an isotropic materiala. Materials: Create / Isotropic
/ Manual Input.b. Enter plate_material for
the Material Name.c. Click Input Properties.d. Enter 10e6 for the Elastic
Modulus.e. Enter 0.33 for the Poisson
Ratio.f. Enter 0.101 for the Density.g. Click OK. h. Click Apply.
Property Set Name.c. Click Input Properties.d. Select plate_material as
the material.e. Enter 0.125 for the
Thickness.f. Click OK.
a
b
c
f
d
e
WS14-11NAS120, Workshop 14, January 2003
Apply the physical propertiesa. Properties: Create / 2D
/ Shell.b. Click in the Select
Members box.c. Rectangular pick the
entire plate as shown.d. Click Add.e. Click Apply.
a
b
c
d
e
Step 5. Create Physical Properties
WS14-12NAS120, Workshop 14, January 2003
Step 6. Apply Loads and Boundary Conditions
Create a boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter simple_support as
the New Set Name.c. Click Input Data.d. Enter <0,0,0> for
Translations e. Click OK.
b
c
d
e
a
WS14-13NAS120, Workshop 14, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select Geometry.
c. Set the Selection Filter to Curve or Edge and select an edge.
d. Click Add.e. Repeat the procedure
until all four edges have been added.
f. Click OK. g. Click Apply.
af
g
d
b
Step 6. Apply Loads and Boundary Conditions
c
WS14-14NAS120, Workshop 14, January 2003
Step 7. Run Normal Modes Analysis
Analyze the modela. Analysis: Analyze / Entire
Model / Full Run.b. Click Solution Type.c. Choose Normal Modes.d. Click Solution Parameters.e. Enter 0.00259 for Wt.-Mass
conversion.f. Click OK.g. Click OK. h. Click Apply.
a
h
b
c
gf
e
d
WS14-15NAS120, Workshop 14, January 2003
Step 8. Read Results into MSC.Patran
Attach the results filea. Analysis: Access Results /
Attach XDB / Result Entities.
b. Click Select Results File.c. Choose the results file
Rectangular_plate1.xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS14-16NAS120, Workshop 14, January 2003
Step 9. Plot Mode Shapes
Create a quick plota. Results: Create / Quick
Plot.b. Select Eigenvectors,
Translational as the Deformation Result.
c. Click Apply.
First 10 modes:
1_________ 6_________
2_________ 7_________
3_________ 8_________
4_________ 9_________
5_________ 10________
a
c
b
WS14-17NAS120, Workshop 14, January 2003
Step 10. Compare to Theoretical Results
Theoretical results based on “Formulas for Natural Frequency and Mode Shape”, 1984 edition, Table 11-4, case 16
)( 2νγ −=
112tE
a2πλf
3
2
21
1
a = 12, b = 8, a/b = 1.5λ1
2 = 32.08E = 10 x 106
t = 0.125ν = 0.33ρ = 0.101/386.1 = 2.616 x 10-4
γ = ρ . t = 3.270 x 10-5
f1 = 265 Hz
WS14-18NAS120, Workshop 14, January 2003
Step 11. Save a Copy
Save a copy of the filea. File: Save a Copy.b. Type rectangular_plate2
as the file name.c. Click Save.
a
b c
WS14-19NAS120, Workshop 14, January 2003
Step 12. Open the New Database
Close the original file and open the new file
a. File: Close.b. File: Open.c. Select the file:
rectangular_plate2.db .d. Click OK.
ab
c
d
WS14-20NAS120, Workshop 14, January 2003
Step 13. Delete Old Results File
Delete XDB attachmenta. Analysis: Delete / XDB
Attachment.b. Select the
rectangular_plate1 .xdb attachment.
c. Click Apply.d. Choose Yes to delete
the attachment.e. Click on the front view
icon.
a
b
cd
e
WS14-21NAS120, Workshop 14, January 2003
Step 14. Re-Mesh the Surface
Create a finer mesha. Elements: Create / Mesh
/ Surface.b. Select the entire surface.c. Enter 0.5 for the Global
Edge Length.d. Click Apply.e. Choose Yes to delete
the existing mesh.
a
b
c
d
e
WS14-22NAS120, Workshop 14, January 2003
Step 15. Run Normal Modes Analysis
Analyze the modela. Analysis: Analyze /
Entire Model / Full Run.
b. Change the job name to: rectangular_plate2.
c. Click Apply.
a
b
c
WS14-23NAS120, Workshop 14, January 2003
Step 16. Attach New Results File
Attach the results filea. Analysis: Access Results /
Attach XDB / Result Entities.
b. Click Select Results File.c. Choose the results file
rectangular_plate2 .xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS14-24NAS120, Workshop 14, January 2003
Step 17. Plot Mode Shapes
a
c
b
Create a quick plota. Results: Create / Quick
Plot.b. Select Eigenvectors,
Translational as the Deformation Result.
c. Click Apply.
First 10 modes:
1_________ 6_________
2_________ 7_________
3_________ 8_________
4_________ 9_________
5_________ 10________
WS15-1
WORKSHOP 15
BUCKLING OF A SUBMARINE PRESSURE HULL
NAS120, Workshop 15, January 2003
WS15-2NAS120, Workshop 15, January 2003
WS15-3NAS120, Workshop 15, January 2003
Problem Description A submarine pressure hull is modeled by plate and bar elements. Check the pressure hull for buckling at an operating depth of 1000 ft
which is equivalent to an external pressure of 445 psi.
WS15-4NAS120, Workshop 15, January 2003
Workshop Objectives Create groups based on property sets.
Run a linear buckling analysis.
WS15-5NAS120, Workshop 15, January 2003
Suggested Exercise Steps1. Create a new database and name it submarine.db. 2. Import the MSC.Nastran input file pressure_hull.bdf.3. Create groups based on property sets.4. Post only the center pressure shell section.5. Apply boundary conditions.6. Post the entire pressure shell.7. Apply an external pressure of 445 psi to the pressure shell.8. Run a linear buckling analysis. Request the first 5 roots (buckled modes).9. Read the xdb file into MSC.Patran.10. Post all the groups.11. Plot the buckled mode shapes and identify which part of the pressure hull is
buckling for each mode.
WS15-6NAS120, Workshop 15, January 2003
a
b c
d
f
g
Step 1. Create New Database
Create a new database called submarine.db
a. File / New.b. Enter submarine as the file
name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
e
WS15-7NAS120, Workshop 15, January 2003
Step 2. Import File
ab
c
Import the Nastran Filea. File: Import.b. Set the object to model
and the source to MSC.Nastran Input.
c. Select pressure_hull.bdf.
d. Click Apply.
d
WS15-8NAS120, Workshop 15, January 2003
Step 3. Create Groups
Create a new groupa. Group: Create. b. Select Property Set as
the method.c. Select Multiple Groups.d. Click Apply.
bc
d
a
WS15-9NAS120, Workshop 15, January 2003
Step 4. Post Entire Pressure Shell
Post two groupsa. Group: Post. b. Shift click to select
pshell.1 and pshell.2.c. Click Apply. b
a
c
WS15-10NAS120, Workshop 15, January 2003
Step 5. Apply Boundary Conditions
Create a boundary conditiona. Loads/BCs: Create /
Displacement / Nodal.b. Enter xyzconstraint as the
New Set Name.c. Click Input Data.d. Enter <0 0 0> for
Translations and Rotations.e. Click OK.
b
c
d
e
a
WS15-11NAS120, Workshop 15, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select FEM.c. Select the node at the
tip of the shell as shown.
d. Click Add.e. Click OK. f. Click Apply.
ae
f
d
b
c
Step 5. Apply Boundary Conditions
WS15-12NAS120, Workshop 15, January 2003
Step 7. Apply Pressure Load
Create a pressure loada. Loads/BCs: Create /
Pressure / Element Uniform.
b. Enter pressure_load as the New Set Name.
c. Set the Target Element Type to 2D.
d. Click Input Data.e. Enter 445 for the Bottom
Surface Pressure.f. Click OK.
b
d
e
f
a
c
WS15-13NAS120, Workshop 15, January 2003
Apply the boundary conditiona. Click Select
Application Region.b. For the Geometry
Filter select FEM.c. Select the entire shell.d. Click Add.e. Click OK. f. Click Apply.
ae
f
d
b
Step 7. Apply Pressure Load
c
WS15-14NAS120, Workshop 15, January 2003
Step 8. Run Linear Buckling Analysis
Analyze the modela. Analysis: Analyze /
Entire Model / Full Run.
b. Click Solution Type.
c. Choose Buckling.d. Click Solution
Parameters.e. Enter 100 for the
Plate Rz Stiffness Factor.
f. Click Eigenvaule Extraction.
g. For the Number of Desired Roots, enter 5.
h. Click OK.i. Click OK.j. Click OK. k. Click Apply.
a
b
c
df
g
h
i
j
k
e
WS15-15NAS120, Workshop 15, January 2003
Step 9. Read Results into MSC.Patran
Attach the results filea. Analysis: Access Results /
Attach XDB / Result Entities.
b. Click Select Results File.c. Choose the results file
submarine.xdb.d. Click OK. e. Click Apply.
a
b
c
e
d
WS15-16NAS120, Workshop 15, January 2003
Step 10. Post All Groups
Post the default groupa. Group:Post.b. Select default_group.c. Click Apply.d. Click on the Reset Graphics
Icon.
a
b
c
d
WS15-17NAS120, Workshop 15, January 2003
Step 11. Plot Mode Shapes
Create a quick plota. Results: Create / Quick
Plot.b. Select a Mode.c. Select Eigenvectors,
Translational as the Deformation Result.
d. Click Apply.e. Repeat for other modes.
a
d
c
b
WS15-18NAS120, Workshop 15, January 2003
Step 11. Plot Mode Shapes
Record Data in the following table:
Mode: Factor: Region of Buckling:
1 ______ _____________________________________
2 ______ _____________________________________
3 ______ _____________________________________
4 ______ _____________________________________
5 ______ _____________________________________
WORKSHOP 16
PARASOLID MODELING
NAS120, Workshop 16, January 2003 WS16-1
WS16-2NAS120, Workshop 16, January 2003
WS16-3NAS120, Workshop 16, January 2003
Problem Description Create a parasolid model of a tension fitting using a number of the
parasolid tools in MSC.Patran
WS16-4NAS120, Workshop 16, January 2003
Suggested Exercise Steps1. Create a new database for the tension fitting model.2. Create all the necessary 2D Geometry.3. Extrude the surface to begin creating the solid model.4. Create a solid shell by removing part of the solid.5. Create fillets for all inside edges of the solid.6. Create holes for the model by creating solid cylinders that pass through it,
and then use boolean to subtract the cylinders.7. Create cylinders to imprint the model.8. Imprint the solid using the cylinders.9. Delete the cylinders used for imprinting.10. TetMesh the completed solid11. Create loads and constraints on the model that will be used in the analysis.12. Create material properties for the model.13. Create the 3D element properties.14. Check to see that the load case Default has the load and constraint.15. Run the analysis by sending the model to MSC.Nastran.16. Access the results by attaching the XDB file. 17. Post-process the results from MSC Nastran.
WS16-5NAS120, Workshop 16, January 2003
Step 1. Create New Database for Tension Fitting
Create a new database called tension_fitting.db.
a. File / New.b. Enter tension_fitting as the
file name.c. Click OK.d. Choose Tolerance Based on
Model.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
b c
d
e
f
g
WS16-6NAS120, Workshop 16, January 2003
Step 2. Create Surface
Create the Geometry for the tension fitting.
a. Geometry : Create / Surface / XYZ.
b. Enter <5 2 0> for Vector Coordinates List.
c. Enter [0 0 0] for Origin Coordinates List.
d. Click Apply.
a
b
c
d
WS16-7NAS120, Workshop 16, January 2003
Step 2. Create Surface (Cont.)
Copy points at opposite corners. a. Click increase Point Size icon
to show all points enlarged.b. Geometry : Transform / Point /
Translate.c. Enter <0.5 0 0> for
Translation Vector.d. Click in the Point List box.e. Click on the top-left corner.f. Enter <0 0.5 0> for
Translation Vector. g. Click in the Point List box.h. Click on the bottom-right
corner.
a
b
c f
e
h
d g
WS16-8NAS120, Workshop 16, January 2003
Step 2. Create Surface (Cont.)
Create a curve by connecting the two translated points and break the surface with the curve.
a. Geometry : Create / Curve / Point.
b. Click on one of the two translated points as the starting point and the other as the ending point.
a
b
b
WS16-9NAS120, Workshop 16, January 2003
Step 2. Create Surface (Cont.)
Break the surface and delete the upper portion of the original surface.
a. Geometry : Edit / Surface / Break.
b. Select the rectangular surface for the Surface List and the sloped curve for the Break Curve List.
c. Click Yes when message box appears.
d. Click the Refresh Graphics icon.
a
b
c
d
WS16-10NAS120, Workshop 16, January 2003
Step 2. Create Surface (Cont.)
Delete the upper surface (above the break curve).
a. Geometry : Delete / Surface.
b. Click on the triangularsurface for the Surface List.
c. Click Apply.
a
b
c
WS16-11NAS120, Workshop 16, January 2003
Create a parasolid solid by extruding the surface in the z-direction.
a. Geometry : Create / Solid / Extrude.
b. Make sure TetMeshable solidicon is selected.
c. Enter <0 0 2> for the TranslationVector.
d. Click in the surface list box and then click on the surface.
e. Click Iso1 view.f. Click the Smooth-
shaded icon.
Step 3. Extrude the Surface to Create Solid
a
b
c
d
ef
WS16-12NAS120, Workshop 16, January 2003
Step 4. Create a solid shell
Edit the solid using the shell method to create a shelled solid.
a. Geometry : Edit / Solid / Shell
b. Enter 0.25 forThickness and turn off Auto Execute.
c. Click on Solid Face List and hold down the shift key and select the top, sloped, and front faces of the solid.
d. Click Apply.
a
b
d
c
c
WS16-13NAS120, Workshop 16, January 2003
Step 5. Create Fillets
Create the fillets on the inner edges of the solid.
a. Geometry : Edit / Solid / Edge Blend.
b. Make sure that the constantradius icon is selected.
c. Enter 0.25 for ConstantRadius.
d. Make sure Edges of Solidicon is selected and turn Auto Execute off.
e. Click on Solid Edge List and use the shift-click technique and select the 5 edges on the inside of thesolid.
f. Click Apply.It may be necessary to rotate the object in order to see then inner edges more easily. This can be done by holding the middle mouse button and moving the mouse.
a
b
c
d
f
e
e
WS16-14NAS120, Workshop 16, January 2003
Step 6. Create Holes for the Tension Fitting
Create the holes for the tension fitting by creating primitive solids that pass through the solid, then subtracting them.
a. Geometry : Create / Solid /Primitive.
b. Select the cylinder iconc. Enter 2.0 for the Height and
0.25 for the radius.d. Enter [-1 1.25 1] for the Base
Center Point List and Coord0.1 for the Axis List.
e. Click Apply.f. Geometry : Edit / Solid /
Boolean.g. Select Subtract icon.h. Select the tension fitting for
the Target Solid.i. Select the cylinder for the
Subtracting Solid List.
a
b
c
d
e
f
g
h
i
WS16-15NAS120, Workshop 16, January 2003
Step 6. Create Holes for the Tension Fitting (Cont.)
Create the points where the three bottom holes will be placed by translating an existing point and, then translating again.
a. Click wireframe icon.b. Geometry : Create /
Point / Extract.c. Select the Curve Icon.d. Click in the curve list box
and select the curve as shown.
e. Geometry: Transform / Point / Translate.
f. Enter <-0.75 0.25 0> for Translation Vector.
g. Click in the point list box and select the new point.
h. Enter <-1.50 0 0> for Translation Vector.
i. Enter 2 for repeat count.j. Select the translated point.
a
b
c
d
h
i
e
f
g
j
WS16-16NAS120, Workshop 16, January 2003
Step 6. Create Holes for the Tension Fitting (Cont.)
Create cylinders using points as base centers and then create holes by subtracting them from the solid.
a. Geometry : Create / Solid / Primitive.
b. Select cylinder icon.c. Enter -1.0 for Height List
and 0.125 for Radius List.d. Turn off Auto Execute.e. Shift-click to select the three
It may be necessary to rotate the object several times in order to select the cylinders with ease
a
b
c
ef
h
ij
j
l
k
d
g
WS16-17NAS120, Workshop 16, January 2003
Step 7. Create Cylinders to Imprint Tension Fitting
Create points in the center of the holes in order to create cylinders to imprint onto the solid. Then create all four cylinders that will be used for Imprinting.
a. Click wireframe icon.b. Geometry : Create / Point /
ArcCenter.c. Select the four hole edges.d. Geometry : Create / Solid /
Primitive.e. Select cylinder iconf. Enter 1.0 for Height and
0.371 for Radius.g. Click on point in the center of
the big hole.h. Enter Coord 0.1 for Axis List.i. Click Apply.j. Click Smooth Shaded icon.
a
b c d
e
f
gh
i
j
c g
WS16-18NAS120, Workshop 16, January 2003
Step 7. Create Cylinders to Imprint Tension Fitting (Cont.)
Now, create the three cylindersthat will be used to imprint the base of the tension fitting.
a. Click wireframe icon.b. Geometry : Create / Solid /
Primitive.c. Select cylinder icond. Enter 0.5 for Height and
0.298 for Radius.e. Shift-click on point in the
center of each of the base holes.
f. Enter Coord 0.2 for Axis List.
g. Click Apply.h. Select Smooth Shaded
icon.
a
b
c
d
ef
g
h
WS16-19NAS120, Workshop 16, January 2003
Step 8. Imprint the Solid
Use the cylinders to imprint the solid and then delete the cylinders, resulting in the finished solid.
a. Geometry : Edit / Solid / Imprint.
b. Turn off Auto Execute.c. Shift-click all four
cylinders under Imprinting Solid List.
d. Select the tension fitting for the Imprinted Solid List.
e. Click Apply. The solid may seem unchanged, but the imprints on the solid will not be visible until the all the cylinders have been deleted.
a
c
d
e
b
WS16-20NAS120, Workshop 16, January 2003
Step 9. Delete the Cylinders
Delete the cylinders and make sure imprint method was completed.
a. Geometry : Delete / Solidb. Shift-click all four cylinders
for Solid List.c. Click Apply.
a
b
c
WS16-21NAS120, Workshop 16, January 2003
Step 10. TetMesh the Completed Solid
Create the TetMesh for the tension fitting.
a. Elements : Create / Mesh / Solid.
b. Make sure Tet, TetMesh, and Tet10are all selected.
c. Click on Input List andselect the solid.
d. Remove check for Automatic Calculationand enter 0.25 for Global Edge Length.
e. Click Apply.
a
b
c
d
e
WS16-22NAS120, Workshop 16, January 2003
Step 11. Create Loads and Constraints
Create the loads and constraints for the model.
a. Click Refresh Graphics iconb. Loads/BCs : Create / Total
Load / Element Uniform.c. Enter Force as the New Set
Name.d. Click Input Data…e. Enter <-5000 0 0> for the
Load and click OK.f. Click Select Application
Region…g. Select the annular face
created by imprinting at the larger hole, then click Add.
h. Click OKi. Click Apply.
a
b
c
d
e
f
g
h
i
Illustrated here is the desired application region.
g
WS16-23NAS120, Workshop 16, January 2003
Step 11. Create Loads and Constraints (Cont.)
WS16-24NAS120, Workshop 16, January 2003
Step 11. Create Loads and Constraints (Cont.)
Create the constraints on the base holes.a. Loads/BCs : Create /
Displacement / Nodal.b. Enter Fixed as New Set Name.c. Click Input Data…d. Enter <0 0 0> for Translation
only, and click OK.e. Click Select Application Region.f. Click on Select Geometry Entities.g. Select Surface or Face iconh. Shift-click the cylindrical surfaces at
the three holes on the base, andClick Add.
i. Click OK.j. Click Apply.
a
b
c
d
e
f
g
h
i
jh
Illustrated here is the desired application region for one of the three holes.
WS16-25NAS120, Workshop 16, January 2003
Step 11. Create Loads and Constraints (Cont.)
WS16-26NAS120, Workshop 16, January 2003
Step 12. Create Material Properties
Create the material properties for the model.
a. Materials : Create / Isotropic /Manual Input
b. Enter Aluminum for MaterialName.
c. Click Input Properties…d. Enter 10E6 for Elastic
Modulus and 0.3 for the Poisson Ratio.
e. Click OK f. Click Apply.
a
b
d
c
ef
WS16-27NAS120, Workshop 16, January 2003
Step 13. Create 3D Element Properties
Create the 3D element properties for the tension fitting.a. Properties : Create / 3D /
Solid.b. Enter 3D_tets for Property
Set Name.c. Click Input Properties…d. Select Aluminum from
Material Property Sets for Material Name.
e. Click OKf. Select the solid for
Application Region, and clickAdd.
g. Click Apply.
a
b
c d
ef
g
WS16-28NAS120, Workshop 16, January 2003
Step 14. Check the Load Case
Check the load case Default to make sure that the load and constraint are selected.
a. Load Cases : Modifyb. Click on the load case name
Default. c. Check to see that both the
load and constraints areassigned.
d. Click Cancel.
a
b
c
d
WS16-29NAS120, Workshop 16, January 2003
Step 15. Run the Analysis
Run the Analysis with MSC.Nastran.a. Analysis : Analyze / Entire
Model / Full Run.b. Click Translation
Parameters...c. Make sure XDB and Print is
selected.d. Click OK.e. Click Solution Type…f. Make sure LINEAR STATIC
is selected.g. Click OK.h. Click Apply.
a
b
c
d
e
f
g
h
WS16-30NAS120, Workshop 16, January 2003
Step 16. Access the Results
Attach the XDB file and access the results.
a. Analysis : Attach XDB / ResultEntities / Local.
b. Click Select Results File…c. Select tension_fitting.xdb
and click OK.d. Click Apply.
a
b
c
d
WS16-31NAS120, Workshop 16, January 2003
Step 17. Display Results
Create a deformation plota. Results : Create /
Deformation.b. Select Displacements,
Transitional from Select DeformationResult.
c. Click Apply.
a
b
c
WS16-32NAS120, Workshop 16, January 2003
Step 17. Display Results (Cont.)
Erase the geometry and do not show the undeformed model, so that only the deformed model is shown.
a. Display : Plot/Erase…b. Click Erase under Geometry.c. Click OK.d. Click Display Attributes.e. Remove check from Show
Undeformed.f. For the Render Style, choose
Shaded.g. Click Apply.
a
b
c
d
e
g
f
WS16-33NAS120, Workshop 16, January 2003
Step 17. Display Results (Cont.)
WS16-34NAS120, Workshop 16, January 2003
Step 17. Read Results (Cont.)
Plot the von Mises stress for the model.
a. Results : Create / Fringe.
b. Select Stress Tensor from Select Fringe Result.
c. Select DisplayAttributes, then setDisplay to ElementEdges
d. Click Apply.
It may also be helpful to change the view several times in order to get a better visualization of the deformations. This can be done either by holding down the middle button on the mouse, or using the view icons.
a
b
c
d
WS17-1
WORKSHOP 17STIFFENED PLATE
NAS120, Workshop 17, January 2003
WS17-2NAS120, Workshop 17, January 2003
WS17-3NAS120, Workshop 17, January 2003
Problem Description A thin plate is reinforced with two types of stiffeners. The outer edges of the plate are reinforced with I-beam
stiffeners. The interior of the plate is reinforced with three hat stiffeners. The structure is simply supported at two edges. A uniform pressure of 5 psi is applied to the surface of the
plate.
20.0
5.0 TYP
20.0
WS17-4NAS120, Workshop 17, January 2003
Problem Description (cont.)
The plate and stiffeners are constructed from aluminum alloy 7075-T73 with the following properties:
E = 10 x 106 psi
ν = 0.3
The plate is 0.100 in thick.
WS17-5NAS120, Workshop 17, January 2003
Problem Description (cont.)
The I-beam stiffener has the following cross section:
2.0
1.0
0.1 TYP
WS17-6NAS120, Workshop 17, January 2003
Problem Description (cont.)
The rolled hat stiffener has the following cross section:
B B
A
A
2.0
1.0
0.898
0.785
Cross-Sectional Area
0.504 in2
IAA 0.143 in4
IBB 0.174 in4
J 0.0016 in4
WS17-7NAS120, Workshop 17, January 2003
Suggested Exercise Steps1. Create surface geometric representing the plate.2. Mesh the geometry to create plate (CQUAD4) and bar (CBAR)
elements.3. Define material (MAT1) and element properties (PSHELL and
PBAR).4. Verify the Y-element axis and offset vectors for the bar elements.5. Define simply-supported boundary constraints (SPC1) and apply a
uniform pressure load to the plate (PLOAD4).6. Submit the model to MSC.Nastran for a linear static analysis.7. Post process the results.
WS17-8NAS120, Workshop 17, January 2003
CREATE NEW DATABASE
Create a new database called stiffened_plate.db.
a. File / New.b. Enter stiffened_plate as the
file name.c. Click OK.d. Choose Default Tolerance.e. Select MSC.Nastran as the
Analysis Code.f. Select Structural as the
Analysis Type.g. Click OK.
a
b c
d
e
fg
WS17-9NAS120, Workshop 17, January 2003
Step 1. Geometry: Create / Surface / XYZ
Create the surface.a. Geometry: Create /
Surface / XYZ.b. Enter <20 20 0> for the
Vector Coordinate List.c. Click Apply.
a
b
c
WS17-10NAS120, Workshop 17, January 2003
Step 1. Geometry: Create / Curve / XYZ
Turn on the Show Parametric Direction feature.
a. Display / Geometry...b. Check the Show
Parametric Direction box.
c. Click Apply.d. Click Cancel.
a
b
c d
WS17-11NAS120, Workshop 17, January 2003
Step 1. Geometry: Edit / Surface / Break
Break the surface in two in the v direction.
a. Edit / Surface / Break.b. Change the Option to
Parametric.c. Choose Constant u
Direction as the Break Direction.
d. Enter 0.5 as the Break Curve value.
e. Screen pick the surface created earlier.
f. Answer Yes when the question “Do you wish to delete the original surfaces?” appears.
a
b
c
d
e
WS17-12NAS120, Workshop 17, January 2003
Step 1. Geometry: Edit / Surface / Break
Break the Surfaces again in the v direction.
a. Screen pick the bottom surface.
b. Answer Yes when the question “Do you wish to delete the original surfaces?” appears.
c. Screen pick the top surface.
d. Answer Yes when the question “Do you wish to delete the original surfaces?” appears.
Define a material for the model. a. Material: Create / Isotropic /
Manual Input. b. Type in alum for the
Material Name.c. Click on the Input
Properties button to bring up the Input Option window.
d. Enter 10E6 for the Elastic Modulus and 0.3 for Poisson Ratio.
e. Enter 0.101 for the Density.f. Click OK to return to the
main material menu.g. Click Apply.
a
b
c
d
e
fg
WS17-17NAS120, Workshop 17, January 2003
Step 3. Element Properties: Create / 2D / Shell
Create element properties for the plate elements.
a. Properties: Create / 2D / Shell.
b. Enter plate as the Property Set Name.
c. Click on the Input Properties button.
d. Click on the alum in the Material Property Set Window.
e. Enter 0.1 as the thickness. f. Click OK.g. Select all surfaces for the
Application Region.h. Click Add.i. Click Apply.
a
b
c d
e
f
gh
i
WS17-18NAS120, Workshop 17, January 2003
Step 3. Element Properties: Create / 1D / Beam
Create element properties for the hat stiffeners.
a. Properties: Create / 1D / Beam.
b. Enter hat_stiffener as the Property Set Name.
c. Click on the Input Properties button.
d. Click on the alum in the Material Property Set Window.
e. Enter <0 0 1> for the Bar Orientation.
f. Enter <0 0 .948> for the offset at node 1 and node 2.
a
b
c
d
e
f
WS17-19NAS120, Workshop 17, January 2003
Step 3. Element Properties: Create / 1D / Beam
g. Scroll down the properties window to enter the following section properties:Area = .504Inertia 1,1 = ?Inertia 2,2 = ?Torsion Constant = .0016
h. Scroll further down to enter stress recovery point coordinates as shown on the right.
i. Click OK.
g
h
i
WS17-20NAS120, Workshop 17, January 2003
Step 3. Element Properties: Create / 1D / Beam
j. For the application region, select the three surface edges in the interior of the plate.
k. Click Add. l. Click Apply.
jk
l
WS17-21NAS120, Workshop 17, January 2003
Step 3. Element Properties: Create / 1D / Beam
Next, create element properties for the I-beam stiffeners.
a. Properties: Create / 1D / Beam.
b. Enter i_stiffener as the Property Set Name.
c. Click on the Input Properties button.
d. Click on the alum in the Material Property Set Window on the bottom section of the Input Properties window.
e. Enter <0 0 1> for the Bar Orientation.
f. Enter <0 0 1.05> for the Offset at both nodes.
g. Click on the Beam Library icon.
a
b
cd
e
f
g
WS17-22NAS120, Workshop 17, January 2003
Step 3. Element Properties: Create / 1D / Beam
h. Enter i_section for the New Section Name.
i. Select the I-Beam shape option.
j. Enter dimensions for the I-Beam as shown.
k. Click on Calculate/Displayto view the cross section.
l. Click OK.m. Click OK again.n. For the application region,
select the top and bottom edges of the plate.
o. Click Add.p. Click Apply.
h
i
j
k
m
no
p
WS17-23NAS120, Workshop 17, January 2003
Step 3. Viewing / Angles …
Change the viewing angle.a. Viewing/ Angles... b. Select Model Absolute.c. Input 23.0 34.0 0.0 as the
Angles.d. Click Apply.e. Click Cancel
a
b
c
d e
WS17-24NAS120, Workshop 17, January 2003
Step 4. Display / Load/BC/Elem Props…
Change the display settings to show beam offset.
a. Display / Load/BC/Elem Props...
b. Change Beam Display from 1D line to 1D line + offsets
c. Click Apply.d. Change Beam Display to
2D Mid-Span + Offsetse. Click Apply.f. Change Beam Display to
3D Full-Span + Offsetsg. Click Apply.h. Click Cancel.
a
b
c
df
h
WS17-25NAS120, Workshop 17, January 2003
Step 4. Display / Load/BC/Elem Props…
1D + Offsets
2D + Offsets 3D + Offsets
1D
WS17-26NAS120, Workshop 17, January 2003
Step 4. Element Properties: Show
Verify the orientation of the hat sections by plotting the element y axis.
a. Properties: Showb. Select Definition of XY
Plane in the properties window.
c. Select the default_group.d. Click Apply.
a
b
c
d
WS17-27NAS120, Workshop 17, January 2003
Step 4. Display / Load/BC/Elem Props…
Change the display of loads, boundary conditions, and element properties from geometry to finite elements.
a. Display / Load/BC/Elem Props...
b. Check the Show on FEM only box.
c. Click Apply.d. Click Cancel.e. Repeat steps from previous
page to plot the element y axis for the stiffeners.
a
b
c d
WS17-28NAS120, Workshop 17, January 2003
Step 5. Loads/BCs: Create / Displacement / Nodal
Create the boundary condition for the model.
a. Loads/BCs: Create / Displacement / Nodal.
b. Enter Simple_Support as the New Set Name.
c. Click on the Input Databutton.
d. Enter <0 0 0> for the Translations.
e. Click OK. f. Click on Select
Application Region. g. Select Geometry as the
geometry filter. h. Set the picking filter to
Curve or Edge.i. Select the left and right
edges of the plate.j. Click Add.k. Click OK.l. Click Apply.
a
b
c
d
ef
g
h
ij
k
l
WS17-29NAS120, Workshop 17, January 2003
Step 5. Loads/BCs: Create / Displacement / Nodal
Stiffened plate with two edges constrained.
WS17-30NAS120, Workshop 17, January 2003
Step 5. Loads/BCs: Create / Pressure / Element Uniform
Apply pressure to the model.a. Create / Pressure / Element
Uniform. b. Enter pressure as the New
Set Name.c. Select 2D as the Target
Element Type. d. Click on the Input Data
button.e. Enter 5 in the Top Surf
Pressure field. f. Click OK. g. Click on Select
Application Region button.
h. Select Geometry as the Geometry Filter.
i. Set the picking filter to Surface.
j. Select all the surfaces for the Application Region.
k. Click Add, and OK.l. Click Apply.
a
b
c
d
e
f
g
hi
j
kl
WS17-31NAS120, Workshop 17, January 2003
Step 5. Loads/BCs: Create / Pressure / Element Uniform
Stiffened plate model with applied pressure.
WS17-32NAS120, Workshop 17, January 2003
Step 6. Analysis: Analyze / Entire Model / Full Run
Submit the model for analysis. a. Analysis: Analyze / Entire
Model / Full Run. b. Click on the Solution
Type. c. Select LINEAR STATIC as
the Solution Type. d. Click OK.e. Click Apply.
a
b
c
d
e
WS17-33NAS120, Workshop 17, January 2003
Step 7. Analysis: Attach XDB / Result Entities / Local
After the job is completed, attach the XDB result file.
a. Access Results / Attach XDB / Result Entities.
b. Click on Select Result File.
c. Select the file called stiffened_plate.xdb.
d. Click OK.e. Click Apply.
a
b
c
d
e
WS17-34NAS120, Workshop 17, January 2003
Step 7. Results: Create / Quick Plot
Plot plate stress and deformation results.
a. Results: Create / Quick Plot.
b. Select the Default result case.
c. Select Stress Tensor for the Fringe Result.
d. Select Displacement, Translational for the Deformation Result.
e. Click Apply.
a
b
c
d
e
WS17-35NAS120, Workshop 17, January 2003
Step 7. Results: Create / Quick Plot
Plot bar stress results. a. Select Bar Stresses,
Maximum Combined for the Fringe Result.
b. Click Apply. c. Plot the remaining bar
stress components one at at time.
a
b
c
WS17-36NAS120, Workshop 17, January 2003
WORKSHOP 18
ANNULAR PLATE
WS18-1NAS120, Workshop 18, January 2003
WS18-2NAS120, Workshop 18, January 2003
WS18-3NAS120, Workshop 18, January 2003
Problem DescriptionShown below is a 2-D representation of the annular plate shown on the title page. The outer edge of the plate is simply supported and a uniform line load of 85 lb/in is applied a distance ro from the center of the plate.
w
b
a
row
simply supportedsimply suppor ted
WS18-4NAS120, Workshop 18, January 2003
Outer Radius, a 1.5 in
Inner Radius, b 0.375 in
Annular Line Load Radius, ro 0.75 in
Line Load, w 85 lb/in
Elastic Modulus, E 10E6 psi
Poisson’s Ratio, ν 0.3
Thickness, t 0.125 in
Problem Description (Cont.)The annular plate dimensions, material properties, and element properties are specified below:
WS18-5NAS120, Workshop 18, January 2003
Theoretical Results (R. J. Roark, “Formulas for stress and strain”, Table 24, case 1a ):
Displacement:
Plate constant:
Plate constants dependent on the ratio a/b:
Loading constants dependent upon the ratio a/ro:
−
−= 3
7
913
LC
LCDway
( )2
3
112 vEtD−
=
( )
−−=
−
−+
+=
ab
bavC
ab
bav
ba
abvC
27
1
121
41ln
21
−
−+
+=
−
+
+
=
20
0
09
20
0
200
3
14
1ln2
1
1ln14
arv
rav
arL
ar
ra
ar
arL
WS18-6NAS120, Workshop 18, January 2003
Theoretical Results (cont.):
Plate constant:
D = 1788.576
Plate constants dependent on the ratio a/b:
Loading constants dependent upon the ratio a/ro:
Maximum displacement:
y = -0.0218
C1 = 0.8815 C7 = 1.7063
L3 = 0.01455 L9 = 0.2909
WS18-7NAS120, Workshop 18, January 2003
Suggested Exercise Steps:
1. Create a geometry model of the annular plate. Build the model in sections to facilitate application of the line load.
2. Use Mesh Seeds to define the mesh density.
3. Create a finite element mesh. (GRID and CQUAD4)
4. Define material properties. (MAT1)
5. Define element properties and apply them to the model. (PSHELL)
6. Apply loads and boundary conditions to the model.
7. Submit the model to MSC.Nastran for analysis.
8. Post Process results using MSC.Patran.
WS18-8NAS120, Workshop 18, January 2003
Create New Database
Create a new database called annular_plate.db
a. File / New.
b. Enter annular_plate as the file name.
c. Click OK.
d. Choose Default Tolerance.
e. Select MSC.Nastran as the Analysis Code.
f. Select Structural as the Analysis Type.
g. Click OK.
WS18-9NAS120, Workshop 18, January 2003
Create the first curve
a. Geometry: Create / Curve / XYZ.
b. Enter <0.375 0 0> for the Vector Coordinate List.
c. Enter [0.375 0 0] for the Origin Coordinate List.
d. Click Apply.
e. Click the Show Labelsicon.
Step 1. Geometry: Create/Curve/XYZ
a
b
c
d
Show Labels Icon
WS18-10NAS120, Workshop 18, January 2003
Step 1.(Cont.) Geometry: Create/Curve/XYZ
a
b
c
Create the second curve.
a. Enter the second Vector Coordinate List: <0.75 0 0>.
b. Enter [0.75 0 0] as the new Origin Coordinate List.
c. Click Apply.
WS18-11NAS120, Workshop 18, January 2003
Create the surfaces by revolving the two curves 360 degrees.
a. Create / Surface / Revolve.
b. Set the Total Angle to 360.
c. Screen pick curve 1
d. Screen pick curve 2
Step 1. (Cont.) Create/Surface/Revolve
a
b
c d
WS18-12NAS120, Workshop 18, January 2003
Create mesh seeds that will be used to guide the mesh.
a. Finite Element: Create / Mesh Seed / Uniform.
b. Enter 40 as the Number of Elements.
c. Screen pick the inner edge of the plate for the Curve List.
Step 2. Finite Elements: Create/Mesh Seed/Uniform
a
b
c
d
WS18-13NAS120, Workshop 18, January 2003
Repeat the previous procedure to create 2 more sets of mesh seeds.