Post on 07-Apr-2018
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1) Start > mechanical design >wire frame and surface design > Ok2) Select ZX plane from the tree and click on Sketch
3) Click on snap to grid in sketch tools toolbar.
4) From the profile toolbar select spline, put the first point at (70,0), turn off the grid snap byrepeating step 3 again, place three points as shown in the figure and place the last point over
the 1st
point.
Note: The mouse pointer automatically changes to hand symbol
1
2
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5) Press Esc twice6) Drag each point to get the required aerofoil profile
7) Copy the aerofoil profile and click exit work bench
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8) Select ZX plane from the tree and select plane from the wireframe toolbar
9) Set the offset distance to 200mm and click Ok
10)Select Fit all In from the view toolbar
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11)Now select the plane, click on Sketch and press Ctrl+v (Paste) and Exit Workbench
12)Double click the aerofoil at the origin then click fit all In from the view toolbar.13)Click on the small black arrow pointing down besides the mirror command in the operations
toolbar and select rotate from the drop down menu.
14)Unselect the duplicate mode, select the aerofoil then select the point at the trailing edge of theaerofoil and place the next point somewhere behind the trailing edge
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15)Tilt the profile till the angle in the dialog box changes to 300deg, Ok and exit work bench16)Repeat the above stated procedure for the other aerofoil, but the tilt the profile only to 345deg17)Start > mechanical design >part design > Ok18)Now select the command Multi-section solid from the sketch based features toolbar, select the
two profiles, then click on spine and select H direction as shown
19)Save the file with .model extension
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FUSELAGE
MODELLING PROCEDURE IN CATIA:-Start > mechanical design >wireframe and surface design
1. Create a point at (0, 0, 0) using wire frame option
2. From surface tool bar click on cylinder
i. Select the point at the origin.ii. Select the yz-planeiii. At the radius give fuselage radius 381mm.iv.
Length 1= 5000mm.Length 2= ocm.
v. Ok.3. File > save as > (save as type model)
ANALYSIS PROCEDURE IN ANSYS:-Main menu > file > import> CATIA
Browse to the model file of the fuselage
Preferences > structuralPreprocessor> element type > add/edit/del > add >
Selectbeam then3node 189, Apply
Selectshell then8node93, OkReal constant > add/edit/del > add>
Selectshell 93, Ok
Give the thickness of the fuselage ati, j, k, las 0.8 leave the lasttwo columns blank)>Ok
Material properties> material models > structural > linear>elastic>isotropic>
EXY = 7.2e4, PRXY = 0.33, Exit
Sections>beams>common sections>Sub type Solid circle
R 7.97
N 24 click OkModeling >operate > Booleans> divide > lines w/options
Selectthe four semi-circles, Ok
Change the No of lines to create 8, Ok
Modeling> create > lines > lines >straight line >Create lines in place of stringers (16 lines will be created)
Main menu > select > entities
Select lines from the drop down menu,Select attached to from the drop down menu,
Select Areas
Select Unselected, Apply then OkPlot > lines
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Preprocessor> modeling > operate > Booleans> divide> area by line>
Select the area, clickOkand select the 7 lines on thecorresponding area, Ok
Repeat the process for the other area
Main menu> select > every thing
Plots > multi plot
Preprocessor> meshing>mesh attributes> all areas
Element typeshell 93>okMeshing>mesh attributes>picked lines>
Pick the16lines corresponding to stringers, Ok
Element typebeam 189Meshing>size control>manual size>lines>all lines
Element edge length = 100
Leave no of divisions tab blank (not Zero or anything else), Ok
Meshing> mesh>lines >Select the 16line corresponding to stringers, Ok
Meshing> mesh > areas > mapped > 3 or 4 sided >
Select the 16 areas, Ok
Main menu> plot control > style > size and shape >
Click in the box againstdisplay of elements (On)
Change the real constant multiple to 1, Apply then OkSolution> define loads> apply > structural > displacement > on nodes
Select the front view
Select all the nodes in the YZ-plane using box type selection, Ok
SelectAll DOF, Ok
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Solution > define loads > apply > structural > force/moment > on nodes >Select the front view
Select the nodes on the free end of the fuselage using box type
selection, Ok
SelectFY divide the load by no. of nodes selected and apply theresult as force.
Solution> solve> current LS > Ok
General Postproc > plot results > contour plot > element solu > Von Mises stresses > Ok
Boom area 200mm2
Thickness of
fuselage 0.8 mm
Length 5000 mm
Load = FY 100KN
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LANDING GEAR
Preferences > Structural
Preprocessor> Element Type> Add/Edit/Delete > Add >
SelectLink thenspar 8, apply
SelectBeam then2 node 188, Ok then Close
Real Constants > Add/Edit/Delete> Add >
SelectLINK8, Ok
Give area = 1, Ok then close
Material Props > Material Models > Structural > Linear > Elastic > IsotropicEXY = 3e7
PRXY = .3
Sections> Beam > Common Sections >
Selectsubtype solidcircle
R = 1
N = 24
T = 0, ClickOk
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Preprocessor>Modeling > Create > Keypoints > In Active Cs>
Createthe keypoints accordingto the table
KP no X Y Z
1 0 0 0
2 8 0 0
3 0 26 04 0 50 0
5 -6 50 0
6 14 50 0
7 16 50 0
8 14 48 0
9 3 26 0
10 0 26 -3
11 0 50 -24
Modeling > Create > Lines > Lines > Straight Lines >
Join the keypoints according to table
Line no join1 1& 2
2 1 &3
3 3 &4
4 4 &5
5 4 &6
6 6 &7
7 6 &8
8 3 &9
9 3 &10
10 8 &9
11 10& 11Mainmenu> Plot Ctrls > Numbering >
Click in the box againstLine Numbers, Apply then Ok
Plots > Lines
Preprocessor > Meshing > Mesh Attributes > All Lines >
Selectelement type Beam 188, Ok
Meshing > Mesh Attributes >Picked Lines >
Picklines 11&10, Ok
Selectelement type Link8, Ok
Meshing > Size Cntrls > Manual Size > Lines > All Lines>
Edge length = 1
No of divisions should be left blank (not zero or anything else)Meshing > Size Cntrls > Manual Size > Lines > Picked Lines>
Picklines 11 & 10, Ok
Edge length should be left blank (not zero or anything else)
No of divisions = 1
Meshing > Mesh > Lines
Pick allLines, Ok
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Mainmenu > Plot Ctrls > Style > Size and Shape >
Click in the box againstDisplay Element Type,
Change the Real Constant Multiplier to1, Apply then Ok
Plot Ctrls > Numbering >
Click in the box againstKeypoint Numbers
Click in the box againstLine Numbers (off), Apply then Ok
Plots > Keypoints > Keypoints
Solution > Define Loads > Apply > Structural > Displacement > On Key Points >
Selectkeypoints 5&7, Ok
SelectUY&UZ, Apply
SelectKeypoint 11, Ok
SelectUX, UY&UZ, Ok
Solution > Define Loads > Apply > Structural > Force/Moment > On Keypoints
SelectKeypoint 2, Ok
SelectFYand give the value below as14672, Apply
SelectKeypoint 2, Ok
SelectFZand give the value below as3119, Ok
Mainmenu > Plots > MultiplotsSolutions > solve > current LS > Ok
If any error dialog box pops us! ClickYes
Close the Status Command window after solving is complete.
Generalpostproc > Plot Results > Contour Plots > Element Solu > Stress > Von Mises Stress
ClickOk
Element Table > Define Table >
ClickAdd,
From the list to the left selectBy Sequence Number,
From the list to the right selectSMISC, type1besideSMISC,Apply
From the list to the left selectBy Sequence Number,
From the list to the right selectLS, type1besideLS, Ok then
Close
(NOTE: LS1-Axial stress, SMISC1- Axial Force)
Element Table > List Elem Table >
SelectLS1from the list, Apply
SelectSMISC1from the list and unselectLS1, Ok
Design iterations:
Directly edit any design variables like area of cross section of links or the cross section properties
of the beam and then solve again.
To change the external loading
Delete the loads by using delete instead of apply in Solution > Define Loads
Apply the loads
Then solve
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Nose Cone
Procedure for modeling in CATIA:
1. Start > mechanical design > Wireframe and Surface Design > Ok2. Select XY plane and click on sketch
3. Click on the Snap to grid from the Sketch tools toolbar
4. Click on the down arrow beside ellipse and from the drop down menu select parabola by focus
5. Now select the focus of the parabola at (0, 50), Apex at the origin, select the starting point ofthe parabola as the origin and select the end point somewhere in the 1
stquadrant
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6. Double click on the end point of the parabola. A dialog box appears in which the change H to the
radius of the nose cone and V to the height of the nose cose, Ok
7. Exit workbench to switch back to wireframe and surface design
8. Select the revolve command from surfaces toolbar9. Select the profile first and select the V-direction handle on the profile, then click preview
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10.Double click on the angle (by default the angle is 180o), change the value in the dialog box to360
o, Ok and Ok
11.Save the file with .model extension and exit. (e.g. nose cone.model)
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Nose cone
Procedure for analysis in ANSYS:
Mainmenu > file > import > CATIA >
Browse to the .modelfile containing the nose cone
Preferences > Structural
Preprocessor > Element Type > Add/Edit/Delete > Add >
Selectshell and the 8node 93, Ok andClose
Real Constants > Add/Edit/Delete > Add > Ok
Givethethicknessatnodes i, j, k, l as 2leave the rest two blank
Material Props > Material Models > Structural > Linear > Elastic > Isotropic
EXY = 7.2e4; PRXY = 0.33, Ok then Exit
Meshing > Size Cntrls > Manual Size > Areas > All Areas >
Give the EdgeLength as 20
Meshing > Areas > Free
Select the two areas andOk
Mainmenu > Plot Ctrls > Style > Size and Shape >
Click in the box againstDisplay Element Type,
Change the Real Constant Multiplier to1, Apply then Ok
Select the front view
Solution > Define Loads > Apply >Structural > Displacement > On Nodes >
Choose box type selection and select all the nodes on the base, Ok
SelectAllDOF andOk
Solution > Define Loads > Apply >Structural > Pressure > On Areas >
If any error message pops up clickClose
Select the two areas andOk, give the value as 0.5
Solutions > solve > current LS > Ok
Close the Status Command window
Generalpostproc > Plot Results > Contour Plots > Element Solu > Stress > Von Mises Stress >
ClickOk
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SHAFT
Preferences > structural
Preprocessor> element type > Add/Edit/Delete > Add >
SelectBeam then 2 node 188, Ok
Material props > Material Models > Structural > Linear > Elastic > Isotropic >EXY = 2e5,
PRXY = 0.3, Okthen close
Sections > Beam > Common sections >Select the Sub-type hollow circle,
Give Ri = 15; Ro = 25; N = 24, Ok
Modeling > create > keypoints > In Active CS >
Create keypoints at(0, 0, 0) and(300, 0, 0)Modeling > Create > lines > Lines > Straight line >
Pick the two keypoints andOk
Meshing > Size Cntrls > Manual Size > All Lines >Leave the Element Edge Length column blank (not zero or
anything else)
Give the No of Divisions as 50Meshing > Mesh > Lines >
Pick the line, Ok
Main menu > Plot Ctrls > Style > Size and Shape >
Tick in the box againstDisplay of Element (on),Change the Real Constant Multiplier to 1
Main menu > Plots > Multi Plots
Solution > Define Loads > Apply > Structural > Displacement > On Keypoints >
Select the keypoint at the origin, Ok
SelectAll DOF, Ok
Solution > Define Loads > Apply > Structural > Force/Moment > on keypoints >Select the keypoint at the free end, Ok
SelectFX and give the value as 1e5, Apply
Select the same Keypoint, OkSelectMX and give the value as 5000, Ok
Solution > solve > Current LS > Ok
If any errors messages pop up! ClickYesAfter the solution is done, Close the Status Command window
General Postproc > Plot results > Contour Plot > Element Solu > Stress >Von Mises Stress
ClickOk
Design iterations:
Directly edit any design variables like the cross section properties of the beam and then
solve again.
To change the external loading
Delete the loads by using delete instead of apply in Solution > Define Loads
Apply the loads
Then solve
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Modal Analysis of Wing of Model Airplane
Preferences > Structural
Preprocessor > Element Type > Add/Edit/ Delete > Add >SelectSolidform the left column and
Select8 node 82from right column, Apply
Select20 node 95from right column, Ok then Close
Material Props > Material Models > Structural > Linear > Elastic > Isotropic >
EXY = 38e3; PRXY = 0.3then Ok
Double-clickDensity and give the Density as 8.5e-5, Close
Modeling > Create > Keypoints > In Active CS
Create the Keypoints as below
sl.no x y z
1 0 0 0
2 2 0 03 2.3 0.2 0
4 1.9 0.45 0
5 1 0.25 0
Modeling > Create > Lines > Splines > With Options > segmented spline >
Select the Keypoints inthe following Order; 1, 2, 3, 4&5, Ok
Give the Tangent Points as below, Ok
-1 0 0
-1 -0.25 0
Modeling > Create > Lines > Lines > Straight Line >
Join5&1, Ok
Modeling > Create > Areas > Arbitrary > By Lines >
Pick all the lines, Ok
Meshing > Size Cntrl > Manual Size > Areas > All Areas >
Give the Edge Length as 0.1, Ok
Meshing > Mesh > Areas > Free >
Pick the area, Ok
Modeling > Operate > Extrude > Elem Ext Opts >
Changethe element type number toSOLID95,
Also the no. Elem divs to 10, leave everything else intact, Ok
Modeling > Operate > Extrude > Areas > By XYZ Offset >
Pick the area, Ok thenchange the Z Value to10, Ok
Solution > Define Loads > Apply > Structural > Displacement > On Nodes >Select all the nodes in the XY Plane (use box type selection), Ok
SelectAll DOF, Ok
Analysis Type > New Analysis > Modal
Analysis Type > Analysis Options >
Change the no. Of modes to extract to10
No. Of modes to expand to10, leave everything else intact, Ok
Setthe start andEnd frequencies to0, Ok
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Solution > solve > Current LS > Ok
GeneralPostproc > Result Summary >
This will display the natural frequencies in all the Mode Shapes
Read result > first set >
Mainmenu > plot ctrls > animate > mode shape > Ok
This will animate the First Mode Shape
GeneralPostproc > Read Result > Next Set >
Mainmenu > plot ctrls > animate > mode shape > Ok
This will animate the Next (second) Mode Shape,
Repeat the procedure to animate the successive Mode Shape