all expt sadd

8/6/2019 All Expt SADD

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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


SelectFYand give the value below as14672, Apply


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


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


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

all expt sadd

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