115469704-ansys
TRANSCRIPT
DYNAMICS
for ANSYS 7.0
Workshop Supplement
Inventory Number: 001810
First Edition ANSYS Release: 7.0
Published Date: March 14, 2003
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Workshop Supplement
DYNAMICS
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Table of Contents
Introductory Workshop
Galloping Gertie -------------------------------------------- W-5
Modal Analysis Workshop
Plate with a Hole -------------------------------------------- W-17
Modal Analysis Workshop
Model Airplane Wing -------------------------------------------- W-23
Harmonic Analysis Workshop
Fixed-Fixed Beam -------------------------------------------- W-27
Transient Analysis Workshop
Bouncing Block -------------------------------------------- W-35
Restarting a Transient Workshop
Bouncing Block -------------------------------------------- W-43
Response Spectrum Workshop
Workbench Table -------------------------------------------- W-49
Random Vibration Workshop
Model Airplane Wing -------------------------------------------- W-55
Pre-stressed Modal Analysis Workshop
Pre-Stressed Disc -------------------------------------------- W-61
Modal Cyclic Symmetry Workshop
Spiral Bevel Gear -------------------------------------------- W-67
Introductory
Workshop
Galloping Gertie
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Introductory Workshop
… Galloping Gertie
Objective
• To get an idea of the steps involved in a typical dynamic analysis.
• The Tacoma Narrows bridge, also known as the Galloping Gertie
is famous for its spectacular collapse in 1940. In this workshop,
we will examine a model of the bridge and calculate its natural
frequencies and mode shapes. We will then simulate the wind
storm and vortex shedding that caused the bridge‟s collapse by
doing a harmonic analysis.
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Introductory Workshop
… Galloping Gertie
Instructions
1. Enter ANSYS in the working directory specified by your instructor.
2. Start by reading input from the file gallop.inp.
Utility Menu: File > Read Input from… choose gallop.inp
– This will create the model and perform a static analysis to prestress the bridge.
– The next step is to do a modal analysis.
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Introductory Workshop
… Galloping Gertie
3. Enter Solution and change analysis type to Modal:
Solution > Analysis Type > New Analysis… choose Modal.
4. Set the following analysis options.
Solution > Analysis Type > Analysis Options...
accept the default (Block Lanczos)
10 modes to extract
10 modes to expand
Calculate element stresses
Include prestress effects… press OK
Accept defaults on the next dialog (Options for Block Lanczos Modal Analysis)
5. Solve.
Solution > Solve > Current LS
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6. Plot the first few mode shapes.
General Postproc > Read Results > By Pick …
General Postproc > Plot Results > Contour Plot > Nodal Solu ...
Introductory Workshop
… Galloping Gertie
Mode 3 – SX stress Mode 1 – SX stress
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7. Enter Solution and choose harmonic analysis.
Solution > Analysis Type > New Analysis…
8. Set the following analysis options.
Solution > Analysis Type > Analysis Options...
Select the Mode superposition solution method
Defaults for all others (including subsequent dialog box)
9. Set frequency and substep options:
Solution > Load Step Opts > Time/Frequenc > Freq and Substps...
Harmonic frequency range = 0 to 0.4
Number of substeps = 40
Stepped boundary conditions
10. Set constant damping ratio = 0.01.
Solution > Load Step Opts > Time/Frequenc > Damping…
Introductory Workshop
… Galloping Gertie
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11. Apply a load vector for mode superposition
with a scale factor of 100. Solution > Define Loads > Apply > Load Vector > For Mode Super…
(close the warning message window)
12. Solve: Solution > Solve > Current LS
13. Save the ANSYS database for the Variable
Viewer in Step 14.
Utility Menu: File > Save as Jobname.db …
14. Enter POST26 (TimeHist Postproc). The
Variable Viewer will start automatically.
Specify the results file name, i.e. gallop.rfrq,
by clicking on File > Open Results) Select “gallop.rfrq” as the results file, then click [Open]
Select “gallop.db” as the ANSYS database, then click [Open]
Introductory Workshop
… Galloping Gertie
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15. Create a scalar parameter to represent the center node: At command
line type in ncen = node(0,0,0) .
16. Define a variable (a vector) using the Variable Viewer that will contain
the UZ displacements of the center node:
Introductory Workshop
… Galloping Gertie
a. Click on the “Add Data” button
b. Double click on “Nodal Solution”
and “DOF Solution”, select “Z-
Component of displacement” and
enter “uz_mid” for the Variable
Name, and then click [OK]
c. Enter “ncen” followed by [Enter] in
the ANSYS Picker Menu, then [OK]
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16. (cont‟d).
The Variable Viewer should appear as follows:
Introductory Workshop
… Galloping Gertie
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17. Graph the UZ-displacement vs frequency:
1. Select the line labeled “uz_mid” and then click on the “Graph Data” button
18. Close the Variable Viewer and then Exit ANSYS or go to step 19 if time
permits.
Introductory Workshop
… Galloping Gertie
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Optional: Continue with the following steps to review the
deformed shape and stresses at 0.07 Hz frequency.
19. Read Input from… gallop_more.inp.
20. Enter POST1, read results for load step 1 substep 7, and plot the deformed
shape and stress contours. Repeat for the imaginary part as well.
21. Exit ANSYS.
Real Part Imaginary Part
Introductory Workshop
… Galloping Gertie
SEQV stress SEQV stress
Modal Analysis
Workshop
Plate with a Hole
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Description:
Determine the first 10 natural
frequencies of the plate with a hole
shown. Assume the plate to be
radially constrained at the hole. The
plate is made of aluminum, with the
following properties:
– Young‟s modulus = 10 x 106 psi
– Density = 2.4 x 10-4 lbf-sec2/in4
– Poisson‟s ratio = 0.27
Modal Analysis Workshop
… Plate with a Hole
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Instructions
1. Clear the database and read input from plate.inp to create the model geometry and mesh.
Utility Menu: File > Clear & Start New… press OK, then answer Yes
Utility Menu: File > Read Input from… choose plate.inp
2. Define material properties.
Preprocessor > Material Props > Material Models…
• Double click through
– … Structural … Linear … Elastic … Isotropic
• EX = 10e6 (Young‟s modulus in psi)
• PRXY = 0.27 (Poisson‟s ratio)
• [OK]
– … Structural … Density
• DENS = 2.4e-4 (Density in lbf-sec2/in4)
• [OK]
• Exit the material GUI
Modal Analysis Workshop
… Plate with a Hole
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3. Choose modal analysis.
Solution > Analysis Type > New Analysis… choose Modal, then OK
4. Specify analysis options. Solution > Analysis Type > Analysis Options…
Use Block Lanczos method (default)
10 modes to extract
10 modes to expand
Yes to calculate element results… press OK
Accept defaults on the next dialog box
5. Radially constrain the hole. Utility Menu: Plot > Lines
Solution > Define Loads > Apply > Structural > Displacement > Symmetry B.C. > On Lines
Pick the lines around the hole and press OK in the Picker Menu
6. Start the solution. Solution > Solve > Current LS
Check solution information in the /STAT window, then press OK
Modal Analysis Workshop
… Plate with a Hole
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7. Review results. Start by listing the frequencies.
General Postproc > Results Summary
8. Plot the first mode shape.
General Postproc > Read Results > First Set
General Postproc > Plot Results > Deformed Shape
Choose “Def + undef edge” and press OK
Modal Analysis Workshop
… Plate with a Hole
Mode 1
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9. Plot and animate the next mode shape.
General Postproc > Read Results > Next Set
Utility Menu: Plot > Replot
Utility Menu: PlotCtrls > Animate > Mode Shape…
10 frames
Time delay = 0.05
(accept all other defaults)
10. Repeat above step for subsequent mode
shapes.
Modal Analysis Workshop
… Plate with a Hole
Mode 6
Modal Analysis
Workshop
Model Airplane Wing
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Description:
Determine the first five natural frequencies of the model airplane wing shown. Assume the wing to be fully fixed at Z=0. The wing has the following properties:
– Young‟s modulus = 38000 psi
– Poisson‟s ratio = 0.3
– Density = 1.033 x 10-3 slugs/in3 = (1.033E-3)/12 lbf-sec2/in4
Modal Analysis Workshop
… Model Airplane Wing
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Instructions
1. Clear the database and read input from wing.inp to create the model
geometry and mesh.
2. Define material properties. Remember to use British in-lb-sec units.
3. Apply boundary conditions. Hint: Choose Apply Displacements on
Areas, pick the Z=0 area, and fix it in all DOF.
4. Extract (and expand) the first four natural frequencies using the
Block Lanczos method.
Modal Analysis Workshop
… Model Airplane Wing
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5. Review all the mode shapes.
Modal Analysis Workshop
… Model Airplane Wing
Mode 1
Mode 3
Mode 2
Mode 4
Harmonic Analysis
Workshop
Fixed-Fixed Beam
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Harmonic Analysis Workshop
… Fixed-Fixed Beam
Description:
• Determine the harmonic response of a steel beam carrying two
rotating machines which exert a maximum force of 70 lb at
operating speeds of 300 to 1800 rpm. The beam, 10 feet long, is
fully fixed at both ends, and the machines are mounted at its
“one-third” points. Assume a damping ratio of 2%.
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Instructions 1. Clear the database and read input from beam.inp to create the
beam model.
2. Specify harmonic analysis (full method) .
3. Fix the two ends of the beam and apply the two in-phase harmonic
forces of FY=70 lbs each at the 40-inch and 80-inch points along
the beam.
4. Specify a damping ratio of 0.02 (i.e. 2%).
Solution > Load Step Opts > Time/Frequenc > Damping
5. Specify 25 solutions between 5 and 30 Hz (300-1800 rpm).
Remember to step apply the loading.
Solution > Load Step Opts > Time/Frequenc > Freq and Substps …
6. Obtain the harmonic solution.
Solution > Solve > Current LS
Harmonic Analysis Workshop
… Fixed-Fixed Beam
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Harmonic Analysis Workshop
… Fixed-Fixed Beam
7. In Time history post processor plot UY displacements versus frequency for the two nodes at which the forces were applied.
NOTE: Use (Utility Menu > PlotCtrls >
Style > Graphs ) for changing graph
style / settings.
8. Find the critical frequency and phase angle.
TimeHist Postpro > List Variables
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Harmonic Analysis Workshop
… Fixed-Fixed Beam
9. In General Post processor review the deformed shape of the beam
at the critical frequency and phase angle.
1. Find the load step and substep for the critical frequency:
General Postproc > Result Summary
2. Issue the HRCPLX command to read in the results at the critical
frequency and phase angle:
HRCPLX,1,4,-25.3743
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Harmonic Analysis Workshop
… Fixed-Fixed Beam
9. (continued).
3. Plot the UY displacement:
General Postproc > Plot Results > Contour Plot > Nodal Solu
plns,u,y
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Harmonic Analysis Workshop
… Fixed-Fixed Beam
10. If time permits, repeat the analysis with forces that are 180° out of
phase.
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Harmonic Analysis Workshop
… Fixed-Fixed Beam
10. (continued).
HRCPLX,1,21,-98.2155
plns,u,y
Transient Analysis
Workshop
Bouncing Block
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Description:
• A 6x6x1-inch block is dropped on a 100-
inch long beam from a height of 100 inches.
Obtain a graph of the motion of the block as
it bounces on the beam. Assume a gap
stiffness of 2000 lb/in. The beam is fully
fixed at both ends, and the only load is
gravity, 386 in/sec2. The beam and the
block are made of the same material:
– Young‟s modulus = 1,000,000 psi
– Density = 0.001 lbf-sec2/in4
– Poisson‟s ratio = 0.3
Transient Analysis Workshop
… Bouncing Block
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Instructions 1. Clear the database and read input from bounce.inp to build the
model.
2. Define a transient analysis (full method)
3. Fix the two ends of the beam in all directions.
4. Use APDL to calculate the integration time step (ITS):
kgap = 2000 - gap stiffness
mgap = 6*6*0.001 = 0.036 - mass of block
pi = acos(-1)
fgap = sqrt(kgap/mgap)/(2*pi) - gap frequency
its = 1/(fgap*30) - integration time step
Transient Analysis Workshop
… Bouncing Block
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5. Solve using two load steps.
• Load Step 1 (for non-zero initial acceleration):
– Fix all nodes of the block in all dofs.
– Apply an acceleration of 386 in/sec2
In Solution Control menu,
– Set analysis to “large displacement transient”.
– Set time=0.001.
– 2 substeps
– Request output of all results for all substeps on the results file
– Static solution (time integration effects off) with Step applied load.
– Set beta damping of .0003183.
• SOLVE
Transient Analysis Workshop
… Bouncing Block
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Load Step 2 ( transient):
Go back to solution control menu and
– Time=1.5
– Automatic time stepping on, with starting ITS = 0.02, minimum ITS =
its (from step 4) and maximum ITS = 0.02
– Transient solution (time integration effects “on”)
– Release the block
– SOLVE
Transient Analysis Workshop
… Bouncing Block
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Transient Analysis Workshop
… Bouncing Block
6. Review results:
– Plot the UY displacements of the beam mid-point and the block versus time.
– Plot the FY reaction force at one of the constraints versus time.
– Animate results over time. Note: To store all the frames needed for animation, you
may need to reduce the size of the graphics window.
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Transient Analysis Workshop
… Bouncing Block
8. Do not exit ANSYS:
– You will continue this workshop with a restart later on.
7. Animate results over time.
Note: To store all the frames
needed for animation, you
may need to reduce the size of
the graphics window.
/post1
/focus,,50,50
/dist,,70
/dsca,,1
/eshape,0
inres,nsol
set,first
pldisp
/noerase
*do,t,0.001,1.5,3/50
set,near,,,,t
pldisp
*enddo
/erase
Restarting a Transient
Workshop
Bouncing Block
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Restarting a Transient Workshop
… Bouncing Block
Description:
• Continue the bouncing block analysis from
the previous exercise. That analysis was
stopped at time=1.5. In this exercise we
will continue to follow the block‟s motion
up to time=3.0.
• The restart files needed (.r001 /.ldhi /.rdb )
are available from the previous workshop.
• The results file from the previous transient
analysis is also available. ANSYS will
append the new results to this RST file as
load step 3.
Time = 1.5
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Instructions:
1. Continue the ANSYS session from the previous workshop.
2. Solution > Analysis Type > Restart
This will bring up a lister window showing a summary of the
restart files available. Choose the load step and substep number
from this summary.
3. In Solution Control menu under the Time Control section: change
TIME to 3.0 and select “Time increment”.
4. Solve.
Restarting a Transient Workshop
… Bouncing Block
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Restarting a Transient Workshop
… Bouncing Block
• In Time History postprocessor graph the UY displacement of a
node on the block and a node on the beam again.
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Restarting a Transient Workshop
… Bouncing Block
• In the general postprocessor animate the bouncing of the block
again.
– Animate results over time. Note: To store all the frames needed for
animation, you may need to reduce the size of the graphics window.
Time = 1.5 to 3
Response Spectrum
Workshop
Workbench Table
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Description:
Determine the displacements
and stresses in a workbench
table due to the acceleration
spectrum shown below.
Accele
ration
Frequency
20 80 200 300
217 217
79.5
150.2
Response Spectrum Workshop
… Workbench Table
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Response Spectrum Workshop
… Workbench Table
Instructions
1. Clear the database and read input
from table.inp to create the model
geometry and mesh.
2. Obtain a modal solution (15
modes) and view the first few
mode shapes. Be sure to request
element stress calculations.
Mode 1 Mode 2
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Response Spectrum Workshop
… Workbench Table
3. Do a spectrum analysis for the
given acceleration spectrum
applied in the global X direction.
Use the SRSS method of mode
combination.
4. Review displacements and table
top stresses for each load step. pldisp,2
plns,u,x plns,s,1
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5. If time permits, repeat the analysis with the spectrum applied in the Y
direction, then in the Z direction.
Response Spectrum Workshop
… Workbench Table
Random Vibration (PSD)
Workshop
Model Airplane Wing
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Random Vibrations Workshop
… Model Airplane Wing
Description:
Determine the displacements and stresses of the model airplane
wing due to an acceleration PSD applied to the base of the wing in
Y direction. Assume the wing to be fully fixed at Z=0.
Accele
ration
(G2/H
z)
Frequency (Hz)
20 100 400 600
0.1 0.1
0.025
0.075
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Random Vibrations Workshop
… Model Airplane Wing
Instructions
1. Clear the database and read input from wing.inp to create the model geometry and mesh.
2. Define material properties.
Young‟s modulus = 38000 psi
Poisson‟s ratio = 0.3
Density = 1.033E-3/12 lbf-sec2/in4
3. Apply boundary conditions. Hint: Choose Apply Displacements on Areas, pick the Z=0 area, and fix it in all DOF.
4. Extract (and expand) the first 15 natural frequencies using the Block Lanczos method.
5. Review mode shapes.
Mode 1
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6. Perform a PSD Spectrum analysis using the acceleration PSD
shown.
Hint: Be sure to use G2/Hz as the units of the PSD.
7. Specify excitation in the Y direction (by applying unit
displacements in the Y direction at the base nodes).
8. Compute Participation factors.
9. Use PSD mode combination method and SOLVE.
Random Vibrations Workshop
… Model Airplane Wing
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Random Vibrations Workshop
… Model Airplane Wing
10. In the general postprocessor look at the relative displacements/ stresses (
Load step 3).
– Can you directly use stress contours for, say SZ, to compare to yield stress?
– What is in load step 1?
– Are equivalent/principal stresses derived from 1 sigma component stresses valid?
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Random Vibrations Workshop
… Model Airplane Wing
11. In Time History Postprocessor create the response PSD for UY at one of
the nodes of the wingtip. Plot on log-log scale.
– Hint: When you get into time history postprocessor first issue „Store Data‟ and
accept the default. This is required for computing Response PSD.
NODE 182
Pre-stressed Modal
Workshop
Pre-Stressed Disc
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Modal Analysis Workshop
… Pre-stressed Disc
Description:
• Determine the first ten natural frequencies and mode shapes of the
perforated aluminum disc shown. The disc is constrained at the central
hole both in the radial and out-of-plane directions. A pre-stress exists due
to a radial pressure load of -20 lbs/inch at the perimeter. Properties of the
disc are as follows:
– Young‟s modulus = 1.0 x 107 psi
– Density = 2.3 x 10-4 lbf-sec2/in4
– Poisson‟s ratio = 0.27
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Instructions
1. Clear the database and read input from disc.inp to create the model
geometry and mesh.
2. Apply displacement constraints: UZ=0 and symmetry b.c. (for radial
constraints) at the central hole. Hint: You will need to use two
menus:
Solution > Define Loads >Apply > Structural > Displacement > On Lines for the UZ
constraint
Solution > Define Loads > Apply > Structural > Displacement > Symmetry B.C. > On Lines
for symmetry b.c.
To pick the lines easily, switch to front view and use Circle picking.
Modal Analysis Workshop
… Pre-stressed Disc
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Modal Analysis Workshop
… Pre-stressed Disc
3. Apply the radial load as pressure on
the lines at the perimeter : -20
pounds/inch on the outer edges of the
disc.
Hint: Stay with the front view, use
Circle picking to pick the entire disc,
then use Circle unpicking to unpick all
except the outer edges.
4. Activate pre-stress effects (using the
Analysis Options dialog box), obtain a
static solution, and review results.
plns,s,1
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Modal Analysis Workshop
… Pre-stressed Disc
5. Switch to modal analysis,
activate pre-stress effects
(again), and extract the first 10
modes of the pre-stressed disc
using the Block Lanczos method.
6. Review the mode shapes.
7. If time permits, do a second,
stress-free modal analysis (with
pre-stress effects off) and
compare results. Shown to the
right is the first mode shape for
each case. Can you guess which
one is pre-stressed?
FREQ = 73.484
FREQ = 1.582
Modal Cyclic Symmetry
Workshop
Spiral Bevel Gear
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Description:
• Determine the first two natural frequencies
of nodal diameter 2 for the spiral bevel
gear shown. Assume a free-free condition
(i.e., no displacement constraints).
Material properties of the gear are as
follows:
– Young‟s modulus = 2.9 x 107 psi
– Density = 7.324 x 10-4 lbf-sec2/in4
– Poisson‟s ratio = 0.32
Modal Cyclic Symmetry Workshop
… Spiral Bevel Gear
Courtesy: Sikorsky Aircraft
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March 14, 2003
Inventory #001810
WS-69
Instructions
1. Clear the database and read input from
bevel.inp to create the basic sector and define
material properties.
2. Issue the CYCLIC command to automatically
detect the low and high edge components using
“BEVEL” as the Root name for the components
( Preprocessor > Modeling > Cyclic Sector > Cyclic
Model > Auto Defined )
Modal Cyclic Symmetry Workshop
… Spiral Bevel Gear
DY
NA
MIC
S 7
.0
Workshop Supplement
March 14, 2003
Inventory #001810
WS-70
3. Display the current cyclic status:
Preprocessor > Modeling > Cyclic Sector > Cyclic Model > Status
Modal Cyclic Symmetry Workshop
… Spiral Bevel Gear
DY
NA
MIC
S 7
.0
Workshop Supplement
March 14, 2003
Inventory #001810
WS-71
4. Define a modal analysis with the following options:
– Block Lanczos method
– Extract two modes in the frequency range 100 to 10,000
– Expand 2 modes
5. Solve for nodal diameter range 2 to 2:
1. Solution > Solve > Cyclic Options
2. Solution > Solve > Current LS
Modal Cyclic Symmetry Workshop
… Spiral Bevel Gear
DY
NA
MIC
S 7
.0
Workshop Supplement
March 14, 2003
Inventory #001810
WS-72
6. Expand results to all 53 sectors ( General Postproc > Cyclic Analysis > Cyc Expansion ). Then read in the results of the first mode shape (General Postproc > Read Results > First set ). Plot the nodal solution for UZ displacements.
NOTE: The /CYCEXPAND command actually creates new elements and
nodes for all 53 sectors.
Modal Cyclic Symmetry Workshop
… Spiral Bevel Gear
/gline,1,-1
plns,u,z
DY
NA
MIC
S 7
.0
Workshop Supplement
March 14, 2003
Inventory #001810
WS-73
7. Plot the vector sum displacement.
Modal Cyclic Symmetry Workshop
… Spiral Bevel Gear
plns,u,sum
DY
NA
MIC
S 7
.0
Workshop Supplement
March 14, 2003
Inventory #001810
WS-74
8. Execute the ANCYC traveling wave animation:
• Utility Menu > PlotCtrls > Animate > Cyc Traveling Wave
• No. of frames to create = 25
• Time delay = 0.1
• Animation Mode = Forward-Reset-Forward
• Nodal Solution Data
– DOF solution
– USUM
• [OK]
Modal Cyclic Symmetry Workshop
… Spiral Bevel Gear