Finite Element Analysis Lab

8/7/2019 Finite Element Analysis Lab

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FgA TEATETA MA]TI}AL'S NNGI1TEENTNGCBE-,LEGH, IIELGAUM - T6.

NYI}NXi\i nI\iifBATCH :ROLL No:aL

CLASS :DIVISION:

NAME OF THE EXPERIMENTS

i-l-,-.-,,--I


3/83

FeE & HATEHA IYIANI}AL'S E ITGI1TE E HIINGCOLLEGI'. IIELGAUUI . I 6.TIYDEX

NAI'VIE :BATCH :ROLI Nlo:

CLASS :DIVISION:

NAME OF THE EXPERIMENTS

l-..l-__IIIIt---,---III

SL.No.


4/83

COMPUTER AIDED MODELING AND ANALYSISFII\ITE ELEME,NT METHOT)

I rrtroductit;n:-Mathematically. the finite eletrent method (FEM) is used for finding approxitnate

solution of Partial Differential Equations (PDE) as well as of Integral equations such as the heattransport equation. The solution approach is based either on eliminating the differential equationcornpleteh, (steadl' state problerns), or rendering the PDE into an equivalent ordinary differenti4_lqcl-Uqlialt" which is then solved r-rsing standard techniques such as finite ditl'erences, etc.

In solving Partial Differential Ecluations, the primary challenge is to create an equationtvhich approximates the equation to bc studied, but which is numerically stable, meaning thatcl'rors irl the ittput data and interurediate calculations do not accuurulate and cause the resultingoutpttt to be rneauingless. There are many ways of doing this, all with advantages anddisadvantages. The Finite Elernent Method is a good choice for solving parlial differentialequations over compiex domains (like cars and oil pipelines) or when the desired precision variesover the entire dornain. F'or instance, in simulating the weather pattern on Earth, it is moreintportant to harze acculate preclictions over land than over the wide-open sea, a dernand that isachievable using the finite element method.

Finite element analvsislrinite Elenteut Analysis (FEA) is a computer simulation technique used in engineering

analysis. It r"tses a riur.nerical technique called the finite element rnethod (FEM). In general, thereare three phases in any computer-aided engineering task: . Pre-processing - defining the finiteelerlent model ancl environmental 1-actors to be applied to it. . Analysis solver (solution of finiteclement moclel) ' Post-processing of results (using visualization tools)

II:EAIIAT'IIA IIIA:YDAL'S ENGINEEIilNG COLLEGE BELGAIilI-DEPARTMENT OF MECHANICAL ENGINEERING Pagc 1


5/83

COMPUTER AIDED MODELING AND ANALYSISGENERIC STEPS TO SOLVING ANY PROBLEM II\

A1\SYSIntroduction:-It is r-rot alrvays possible to obtain the exact analytical solution at any location in

the bocly, especially fbr those elemenls having complex shapes or geometries. Always lvhatmatters are the boundary conditions and material properlies. In such cases, the analytical soh-rtionthat satisfies lhe governing equation or gives extreme values for the governing functional isdilficLrlt to obtain. Hence for most oI'the practical problems, the engineers resort to numericalnrethods like tire finite element methocl to obtain approximate but most probable solutions.

Finite element procedures are at present very widely used in engineering analysis.T'he procedures ale ernployecl extensivc'l-v in the analysis of solids and structures and of heattransl'er and fiuids. and indeed. finite element methods are useful in virtually every field of'enginecring analysis.

Description of the method:-In anv analysis u,e always select a mathematical model of a physical problem, and

thcn r'i'e solve lhat nTociel. Although the finite element method is employed to solve very complexrt'iathematical rnodels, bLrt it is important to realize that the finite element solution can never givemore infonlation tiran that contained in the mathematical model.ilhysical problems, mathcmatical models, and the finite clcmcnt.;ul tt iiutifhe physical problem typically involvqs an actual structure or structural componentsubjected to cefiain loads. The idealization of the physical problem to a mathematical modelrequires certain assumptions that together lead to differential equations governing thetnatherratical model. 'fLrc 1'rnite eleu.ient analysis solves this mathematical model. Since the finiteelemeitt solutron tecl-rnique is a numerical procedure, it is necessary to access the solutionaccuracy. lf the accuracy criteria are not met, the numerical solution has to be repeated rvithref-rned solution parameters (such as finer meshes) until a sufhcient accuracy is reached.

DEPARTMENT OF MECHANICAL ENGINEERING Pagc 2


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COMPUTER AIDED MODELING AND ANALYSISIt is clcar that the finite element solution will solve only the selecred mathematical model

and that ail assumptions in this model will be reflected in the predicted response. Hence, thecl.roice of an appropriate mathematic'al model is crucial and completely determines the insightinto tl're actual phy'sicaI problcnt that rve tibtain by the analysis.

Once the mathenatical model has been solved accurately and the results have beeninterpreted, we may well decide to consider next a refined mathematical model in ordel tcrincrease our insight into the response of the physical problem. Further more, a change in theph1''sical probiem ntav be necessar)'. and this in turn will also lead to additional mathematicalnrociels ancl fitite elenrent solutions. Fig.l. depicts the process of finite element analysis. The keystep in engineering analysis is therefore choosing appropriate mathematical models. Thesemodels will clearly be selected depencling on what phenomena are to be predicted.

Change ofphysicalproblemMathematical modelGoverneci by differential equationsAssumptions on. Geometry. Kinernatics- Material law. Loading- Boundary conditions. Etc.

lmprovemathematicalmodel

Finits elomeChoice of. Finite ele. ll{esh der. SolutionRepresental. Loading. Boundar,. Etc.

nt solutionmentsr sityparametersion of/ conditions [- nrr,"" '.,'.=nl-I solution parameters,l_ etc.

Aelemr ,ssessment of ccuracy of finitt solutron ot rrathematical modelI

-----J

lnterpretario,, ol .".rlt. l--J RefineI I analysisDesign improvementsStructural optimization

Fig 1: Finite element process.

Finiteeler:rentsolr;tionofmathernaticalmodel

MTIIIATITA I}IANI)AL,S ENGtrNICEI,ING COLLEGE BELGAITU.DEPARTMENT OF MECHANICAL ENGINEERING Page 3


7/83

COMPUTER AIDED MODELING AND ANALYSISimportani features of finite clement method:-The ftnite element rnethod is a technique in which a given domain is represented as acoliection of simple domains, called frnite elements. The following are the three basic features ofthe f,rnite element method.a) Division o./ whole into parl.s'; rvhich allows representation of geometrically complex domains:ts collection of'simpie don-rains Lhat enable a systematic derivation of the approximationtiructions.b) Derivcttion of upltroxintations /unclirms over each element; the approximation functions areoftert algebraic poiynornials that are derjved using interpolation theory.c) As.scmbl,v t,f elerncnl.r. u,l-iich is based on continuity of the solution and balance of internalf-iuxesThe basic equation used to solve the static analysis problem is:

{a} :tKl {6}where, i a ) : the equivaient vector which is obtained by lumping the

[ 6 ] : the unknown nodal displacement vector.Finitc elemcnt modclling and analysis:-'I'hree phases of analysis:-fior determinirrg stresses ancl deflections the foilowing steps of the analysis are essential:a) Preparation of input data: The recluisite data for the given problem is geometry (i.e.mociel),

,r-raterial propefiies and bor-rndai'y conditions (i.e. loads and constraints).b) SolLrtion: Tiris involr.'es solving the necessary equations to calculate the unknown parameters.c) Arrangements of results: The results obtained for stress analysis may be presented in the fonnof tables or graphical irnages like stress patterns, displacement patterns.

tt'EAEtAfIIA ]xl{tINTII;li 'S II-NC{N{EIIING COLLEGE BELGAIM- Pagc 4.DEPARTMENT OF MECHANICAL ENGINEERING

element atrd edge loads at the nodes,

iK ] : tl're global stil'lhess matrix of the system, and


8/83

COMPUTER lTIDED MODELING AND ANALYSISSteps followed in ANSYS program:-The three important steps in ANSYS programming are:a) Preprocessingb) Solr-rtionc) Post-processingu) Preprocessing:'Ihis phase consists of making available the input data such as geometly,material properties, meshing olthe model. boundary conditions and has the following steps:

1) Set up: Het'e we enter the analysis type, the material properties, and the geometry (i.e.prepare tl-re model). The rnodel may be built parametrically or a model from other softwarepaclia-qe can be in-rportccl.

2) Create FE n-roclel: In this step r,ve divide the total volume into small simple regularvoltttnes, which can be easily meshed. Then we define the mesh size for each small volurne byvirtr-rally dividing all the edges of the smalI volume into same divisions.

3) Loaciing: ln this step the boirndarl'conditions are imposed, i.e. forces and constraints, onthe nrodel are defineci.b) Solution: In this phase a solver is used to solve the basic equation for the analysis type and tocompute the results. This phase is tahen care by the software programme. In the solution process,the solver goes throLrgh fbllowing steps to compute the solution for a steady state analysis,

i) Iiormulate elcment matrices,2) Assen:bly and triangularise the overall stiffness matrix,3) calculate the solLrtion by bacl< slrbstitntion,

4) Conrpute the stresses. displaoements, etc.c) Postproces,sing. This is the phase lvhere the results are reviewed for the analysis done, byobtair-ring graphic displays, vector-plots and tabular reports of stress and displacement, etc.

MArtA'rrrA tlwANrDAr,'s ENG{tYEIErtrtY{} COLLEGE BELGArnr. pagc 5DEPARTMENIT OF MECHANICAL ENGINEERING


9/83

COMPUTER AIDED MODELING AND ANALYSISLihe solving an)' problen-r analytically. you need to define (1) your solution domain, (2)

the phvsical model, (3) boundary conditions and (a) the physical properties. You then solve theproblem and present the results. In numerical methods, the main difference is an extra step calledmesh generation. This is the step that divides the complex model into small elements thatbecome solvable iu an otherr,vise too complex situation. Below describes the processes ilrierminology slightl,v ntol'e attulte to the sofiware.Builtl Ceometry:-

Llotrstruct a two or three dimensional representation of the object to be modeled andtcstecl r-rsing the wolk plane coordin:ites system within ANSYS.Define Material Properties:-

Now tl-rat the palt exists, define a library of the necessary materials that compose theobject (or project) being n.iodelecl. T'his includes thermal and mechanical properties.Generate Mesh:-

At this point ANSYS understancls the makeup of the part. Now define how tl-re modeledsystem should be broken down irrto finite pieces.

Apply Loads:-Once the system is fully designed, the last task is to burden the system with constraints,

such as phl,sicai loadings or boundary conditions.Cbtain Solution:-'firis is actually a step, because ANSYS needs to understand within what state (steadystate, transient... etc.) the problem must be solved.Present the Results:-

Atier the solutiotr has been obteLined, there are many ways to present ANSYS' results,choose liorn many options such as tables, glaphs, and contour plots.

,7EtXEi,?'E'IIA !|{,En'gAzg,'S EN{;!NE:Egttir-*{; COLLEGE BELGAIIIW- pagc (rDEPARTMENT OF MECHANICAL ENGINEERING


10/83

COMPUTER AIDED MODELING AND ANALYSISFE MESH GE,NERATIOI{

Afier validation of the model rrext step is generation of Finite Element Mesh. For the casingSOLID elements are used tbl meshing. A very f-rne mesh creates the hardware space oroblem becausethe computations become voluminous. As the number of nodes increases, the total degrees offreedom of the model increases Hence a designer has to model it optimally i.e. placing fine meshonl,v at critical area. anc'l coarse mesh at other. So that the run time is less and also the accuracyis nut rrrrch affect.'il.

The various types of solid elements are shown in the Fig.2. Each element type has its ownproperties depending upon its geometrical shape.

1 [t ri,i,ie,i 3t ratie,:Q o)alE.na,ie brick:ii--

4 nrrded tetrahedra

Ei rir:rderJ rr'r'-rditred bric:k!1jErl r_lE

Fig.2. Various types of SOLID finite elements

IUIAIIA.I,IIA IWANI,AL,S ENGINNENINQ COLLEGE I,ELGAInT.DEPARTMENT OF MECHANICAL ENGINEERING Pag,e 7


11/83

COMPT]TER AIDED MODELING AND ANALYSISF-Gc:sh relinenrent:-

After generation of coarse mesh. it is refined as per the geometry and critical sections of themodel. It can be refined in three different ways as follows'i h-refinement : Here eiement size is changed (decreased) without changing the element type.F p-refinement : Ilere element type is changed (to higher order) without changing element

size.

size.A p refinement converges to the solr-rtion fbster than h - refinement. Fig.3. shor.vs tl're

above-cliscussed r.r,ays ol mesh refinement, 'h' refinement is used near the fillet area and 'r'refinement used at other locations.

Original mesh Uniform h-refinement Uniform p-refinementliig.3. Dilferent lvays of mesh refinements

r-refinement

Mesh transition:-Mesh transition occurs when refined mesh interfaces with coarse mesh. It connects

different types of elements. One comrnon method of performing a transition is to use an intermediatebelt of different elements as shown in the Fig.4.

I,'ig..t. Mesh transition

a'-

tl'tAItAT'IIA ilLNLUIAL'S ENGINEEITING COLLEGE BELCAIM.DEPARTMENT OF MECHANICAL ENGINEERING Pagc 8


12/83

COMPUTER AIDED MODELING AND ANALYSISMesh generation:-Entroduction:

In order to carry out a finite element analysis, the model we are using must be dividedinto a number of srnall pieces known as f-rnite elements. Since the model is divided into a numberoi discrete parts. FEA can be described as a discretization technique. In simple terms, antatltematicai net or "rnesh" is required to carry out a finite element analysis. If the system underinvestigation is 1D in rrature. we nrav use line elements to represent our geometry and to carr\rot"tt our anal,vsis. If the problem can be described in two dimensions, then a 2D mesh is reqtiired.(iorrespottdingly, if the problern is complex and a 3D representation of the continuum isrcclr"rirc-d. then lve nse a 3D mesh.Arca meshing:-

Area elements can be triangular or quadrilateral in shape. The selection of the elementshape and order is based otr considerations relating to the complexity of the geometry and then.ttllre of tite problent being modcled. Membrane elements don't have any thickness. As acorlseqllence they have no bending stiffness; loads can only be carried in the element plane. Plate& Shell eiements are used to model thin walled regions in 3D space. The plate element isforrnulated around plate theory. u,hich assLrmes that the load is carried via bending. Shellelemcrtts are usecl to model shells, where there is combination of flexure & membrane action.Plate elet-nents are considered applicable where the out of plane distortion is little more than theplate thickness. There are also special elements,.which facilitate accurate modeling of thickplates. If the deflection is greater than the plate thickness, membranes action should beconsidered, and so shell elements should be used. Shell element nodes have five degrees ofh'eeciotn; tl're missing is the in-plane rotational lreedom (sometimes referred to as the drillinglieedon'r). Solid elements come in diiferent varieties. Axis symmetric elements are used todescribe the cross-section of an axially symmetric parI. Plane strain elements are used to describesection of long ob.iects (such as a shaft or wall cross-section). The strain in the out-of-planeclirection is taken to bc zero, rcl'lcctins the assumption that the strain is in one Plnne strcsselements are used lo describe sections o1'thir-r objects (such as a wrench). The stress in the or.tt-ol--

filAIill'I'IIA IIIANI)I\L'S ENGINEEHING COLLEGE BEt GAtItW-DEPARTMENT OF MECHANICAL ENGINEERING Page 9


13/83

COMPUTER AIDED MODELING AND ANALYSISplane direction is takeu to be zero, r:eflectir,g the assumption that the stress is in one plane. Thetrvo dimensional elements are shown in Fig .5.trelow.

Linear element Quadratic element Cubic element

Itig.5. I'lvo dimensional elementI'LANE 42 Element Descriptions:

PLANE42 is used fbr 2-D modeling of solid structures. The element can be used either asa plane element (plane stress or plane strain) or as an axisymmetric element. The element isdeflned by four nodes having two clegrees of freedom at each node: translations in the nodal xand y directions. The element has plasticity, creep, swelling, stress stiffening, large deflection,and large strain capabilities shown in fig.beiow.

trr.a.i,.[lllt

IIL -----F ','

+ - -------rf''-lL r_---- i!',i,.r\ ,.. 1l4,l t" I'-'_ ,k_f ,1' Eleriient []u,rrdirirte 1 ie)+ / , ,, S1,,:rtetTt i5hor,r'rrt f61 i '-l.i' ..-'L' l.r.E\ L-tFTr,l) = 1 i iJ' "*---- i.:l' )1,--- -ttti

K.L..t\s, \.:'' 1t'I.,/ \rtf- \--+

,.]tJ rian qu la r Optiu rr -nut re co mrnen de d)

inr Flrrdi;.il'r

fiEiartti rrrtl ivrtlh'ff,tlr,'s ENG rtvllErtrNilJ 0OLLEGD BELGAutur.DEPARTMENT OF MECHANICAL ENGINEERING Page 10


14/83

COMPUTER AIDED MODELING AND ANALYSISVolumc meshing:-

3D elements take the form of cubes called hexahedrons (hexes), 3D triangles calledtctrahedrons (tets) and iD u,edges lmown as pentahedrons. Decisions on element selectionhinge on understanding the role of the element shape and order of interpolation.

Modeling with 3D-Elements is t1're most llexible approach. These types of elements areLisecl tbt'thicli str"irclures that have neither a constant cross section nor an axis of symmetry. Solidnrocieling u'ili nearly alr,vays make anai.r'sis preparation easier. Meshing and solving can take zrlong time, particularly if the structure is thin-walled (large numbers of elements are requirecl tcrproduce a rnesh). The three dimensional element are shown in Fig.6. below.

TetraheclraI Prismatic Hexahedral

l'ig.6. l'hree dimensional elements.

fr'ATIA'TIIA fuLINI)AL'S ENG INT]ENILTC COLI,EGE BELGALDW.DEPARTMENT OF MECHANICAL ENGINEERING Page 11


15/83

COMPUTER AIDED MODELING AND ANALYSISPART-A

Exp No:- Ir\lM:- Determine the nodal displacement, stress & strain for given sketch.F,... 2.1r 105 N,'rlnr2 . pr- 0.25

1500N

PROBLEM SPECIFICATION

D= 50 mm

300 mm

r\pplicable A\SYS ProdLrct ANSYS multi-physic. ANSYS MechanicalANSYS Structural, ANSYS ED

Level of Difficultv EasyInteractirre time reqr,rired

Analysis typeElement typesANSYS Featu res I)emonstrated 1-D modeling including primitives, Boolean

operation, Load-Force/Moment., deformedsl-rape & Stress display. listing of reactionfbrces.

IYZATTATIIA IIWANI)AI,.S ENG]LTIIDBING COLLEGE BELGAUIW.DEPARTMENT OF MECHANICAL ENGINEERING

60 to 90 minutesStructuralLi""ar rt"ti.LrrI"2D sparl

Page 12


16/83

COMPUTER AIDED MODELING AND ANALYSIS

TTANATruA J}IANT'AL'S DNGINEBNING COLLDGE BELGAUDT.DEPARTMENT OF MECHANICAL ENGINEERING Page 13


17/83


REACTION ATTHE SUPPORTPRINT REACTION SOLUTIONS PER NODE***** POST1 TOTAL REACT]ON SOLUTION LISTING *****LOAD STEP: 1 SUBSTEP: 1TrME: 1. 0000 LOAD CASE: 0THE EO],],OV{fNG X, Y, Z SOLUTIONS ARE IN THE GLOBAL COORDINATE SYSTEM

NODE FX FY1 -1500.0 0 .0000TOTAL VALUESVALUE -1500.0 0. 0000

DrAnArruA LITANDAL'J nNerNDEnrNG coLLDeB BBLGAaM. page 14DEPARTMENT OF MECHANICAL ENGINEERING


18/83


I!ODAL LOAD

PRfNT SUMMED NODAL LOADS'***** POST1 SUMMED TOTAL NODAL LOADS LISTfNG *****LOAD STEP: 1 SUBSTEP: 1TIME= 1.0000THE EOLLOWfNG X,Y,Z

\TnnE rv1 1500.02 -1500.0TOTAL \/AIUESVALUE O. OOOO

LOAD CASE=SOLUTIONS ARE

FY

0.0000

0IN THE GLOBAL COORDINATE SYSTEM

NODAL SOLUTION

***** POSTI1 NODA], DEGREE OE FREEDOM LISTING *****LOAD STEP= 1 SUBSTEP=TIME= l-.0000 LOAD CASE= 0

RESULTS ARE IN THEHE FOLLOWING DEGREE OF TREEDOMNODE tIX1 0. 00002 0.LO9748-O2MAXIMUM ABSOLUTE VAIUESNODE 2VALUE 0.10914E-02

GLOBAI COORDINATE SYSTEM

D,TANATIIA I}TANDAI,'S ENGIiUEENING COLLDGE BELGAIWT.DEPARTMENT OF MECHANICAL ENGINEERING Page 15


19/83

COMPUTER AIDED MODELING AND ANALYSISL..xp No:- 2AIM:- Determine the nodal displacement, stress & strain for given sketch.E;)xl05 N/mm',E1-- 0.7x10s N/mm2

, AL = 90C mm2Lt = 0.25 s00 N

600 mmPROBLEM SPECIFICAT'ION

500 mm

Applicable ANSYS Product ANSYS multi-physic, ANSYS MechanicalANSYS Structural, ANSYS ED

i- e ve I i, t'Dlti.,ttti: Easy

StructuralLinear static

Element types Link-2D sparlANSYS Features Demonstrated 1-D modeling including primitives, Boolean

operation & Load-Force/Moment, deformedshape & Stress display, listing of reactionforces.

iTErtrtAT'rrA tuL'INDAL's ENGTIYEETITNG OOLLEGE rrELGAtuw-DEPARTMENT OF MECHANICAL ENGINEERING

Az= 600 mm2[=0.3

Interactirze time req uired 60 to 90 minutes

Page 16


20/83


,., i

RESULT:.

DIANAlruA J}IANI'AL'S DNEINDDNING COLLDGN BDLGAAM.DEPARTMENT OF MECHANICAL ENGINEERING Page17


21/83


*-.*_x: ,i l.:. i : :'-",.:r i:::: ,,i.

DIANAAruA DIANDAL'S ENIEINEENING COLLEGE BNLGAIIfuT.DEPARTMENT OF MECHANICAL ENGINEERING Page 1B


22/83


23/83


NODAL LOADPRINT SUMMED NODAI LOADS***** POST!1 SUMMED TOTAL NODAL LOADS LIST'ING *****LOAD STEP= 1 SUBSTEP:TIME= 1.0000THE FOLLOWING X/Y/Z

NODE FXl- s00 .003 -500 .00TOTAL VALUESVALUE -0 .56843E-l-3

L(rAlt (_A5F,=

SOLUTIONS AREFY

0IN THE GLOBAL COORDINATE SYSTEM

0. oooo

NODAL SOLUTIONPRINT U NODAL SOLUTION PER NODE***** POST1 NODAL DEGREE OF TREEDOM LISTING *****LOAD STEP= 1 SUBSTEP= 1TIME= 1.0000 LOAD CASE= 0THE EOLLOWING DEGREE OE TREEDOM RESULTS ARE TN THE GLOBAL COORDINATE SYSTEM

1 0.00002 0.166618-023 0.761908-02MAXIMUM ABSOLUTE VALUESNODE 3VALUE 0.76190E-02

IIIAIIA:I,IIA IYIANI)AL,S DNGIIYEEITIIYG COLLEGE BELGATUW.DEPARTMENT OF MECHANICAL ENGINEERING Page 20


24/83

COMPUTER AiDED MODELING AND ANALYSISExp No:- 3AIM:- Determine the nodal displacement, stress & strain for given sketch.E:2,105. pr: 0.25

Azs.a 1000N

PROBLEM SPECIFICATIONApplicable ANSYS Product

EasyInteractive time requfu 60 to 90 minutesDiscipline Structural

ANSYS multi-physic, ANSYS MechanicalANSYS Structural, ANSYS ED

1-D modeling including primifives, Booleanoperation & Tapered, Load-Force/Moment,deformed shape & Stress display, listing ofreaction forces.

res l)emonstrated

nalysis typeement typesuSvs e*t,

lAIiIilt,tl^

375 mm 375 mm

Linear staticBeam - Taper 54

fr,TAIIAT:IIA IW^4IYDAL,S ENGLNEEITING COLLEGE BELGATDT.DEPARTMENT OF MECHANICAL ENGINEERING Page 21


25/83

COMPUTER AIDED MODELING AND ANALYSISRESULT:-

!tcf,&L i:*l,t_tTiCl!i:TF D= l

!t 1 !-., ,?

I'l'1.': =. n0 3 l 3Il.li: *, rrii5(t:

tlAT i 3 :rji.rtr

1,, .'..

n .,;+l::l; .i'!r:5'l$ ,1]'.llaa:.{:1fl,-_i3 ,n+1*.$1 ,,.,11111 .,,rrl,l 3E!i{orlal- diisp}afemenf, s!r+s"s i sil;ri:'i f+r gi'.'en s}:etii'. , i:,)54-ii

DTANATruA DIANI'AL'S DNGINBEruNG COLLEGE BELGAAPT.DEPARTMENT OF MECHANICAL ENGINEERING Page22


26/83


PRINT U NODAL SOLUTION PER NODE***** POST1 NODA], DEGREE OF FREEDOM LISTING *****LOAD STEP: 0 SUBSTEP: 1TIME: 1. OOOO LOAD CASE: OTHE F"OLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORD]NATE SYSTEM

NODE UX1 0.00002 0.788318-023 0. 56431E-02MAXIMUM ABSOLUTE VALUESNODE 3VALUE 0.56431E-02

fuIANATruA DTATW'AL'S DNGINDENING COLLEGE NELGAUDI.DEPARTMENT OF MECHANICAL ENGINEERING Page 23


27/83


I\IODAI- LOADPRINT SUMMED NODAL LOADS***** POST1 SUM},IED TOTAI NODAI LOADS LISTING *****LOAD STEP= 0 SUBSTEP: 1TIME: 1.0000 LOAD CASE: 0THE FOLLOWING X,Y,Z SOLUTfONS ARE IN

NODE1 1000.0" -1000.0\TATrmq0.11369E-12 0.0000 0.0000

REACTION AT THE SUPPORT

GLOBAI COORDINATE SYSTEMHEMZ

TOTALVALi'E

PRINT R.EACTION SOLUTIONS PER NODE***** POST1 TOTAL REACTION SOLUTIOIJ LISTING *****LOAD STEP= 0 SUBSTEP: 1TIME= 1.0000 LOAD CASE= 0THE FOLLOWING X/Y/Z SOLUTIONS ARE TN THE GLOBAL COORDINATE SYSTEM

NODE FX FY MZ1 -r-000.0 0.0000 0.0000TOTAL VALUESVALUE *1000.0 0.0000 0.0000

ITANA'rIIA IWANDAL'S ENCINDENTIryG COLLEGE BELGAIMT.DEPARTMENT OF MECHANICAL ENGINEERING Page 24


28/83

COMPUTER AiDED MODELING AND ANALYSISExp No:- 4AIM :- Determine the nodal displacement, stress in each node element for the sketch givenbelow. E:2x105 N/mm2, Ar:1500 mrn2. Ar: A:l:2000 mm2

I)ROB LEM SPEC IFICATIONApplicable ANSYS Prodr-rct ANSYS multi-physic, ANSYS MechanicalANSYS Structural. ANSYS ED[,evel of Dil]'icultv EasyI nteracti ve titr-re requirecl 60 to 90 minutesDisciplineAnalysis typeI lcnrcnt typ.i -ANSYS Features l)emonstrated 2-D modeling including primitives, Booleanoperation & Load-Force/Moment, deformedshape & Stress display, listing of reactionforces.

_l:llArttlT1rtl rvAm*r),tLL's ENGLUEBBLNG 0OLLEGE t Er,Garnw.DEPARTMENT OF MECHANICAL ENGINEERING

150 KN

StructuralLrr*, stati.Link-2D sparl

Page 25


29/83


NODAL SOTUTIONPRINT U NODAL SOLUTION PER NODE***** POST1 NODAL DEGREE OF EREEDOM LISTING *****LOAD STEP: 1 SUBSTEP: 1TIME= 1.0000 LOAD CASE: 0THE FOLLOW]NG DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM

NODE UX1 0.00002 0.200003 0. 10000

MAXIMUM ABSOLUTE VALUESNODE 2VALUE O .2OOOO

DTABATTA DTANTTAL'j DNGTNBBBTNE ODLLBGD BELeaaDr. pagez6DEPARTMENT OF MECHANICAL ENGINEERING


30/83

COMPUTER AIDED MODELING AND ANALYSISREACTTON AT THE SUPPORTPRTNT REACTION SOLUTIONS PER NODE

***** posTl ToTAI RXACTION SOLUTION LISTING *****LOAD STEP= L SITBSTEP= 1TIME= 1.0000 LOAD CASE: 0THE FOLLOWING X,Y,Z SOLUTIONS ARE IN THE GLOBAL COORDINATE SYSTEM

NODE EX FY1 -0.145528-10 75000.2 75000.TOTAI VALIIESvAruE -0.145528-l_0 0.150008+06

turArlATrrA IWANDAL'j ENGTNBEhTNG OOLLEGE BnLGarm[. page 27DEPARTMENT OF MECHANICAL ENGINEERING


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COMPUTER AiDED MODELING AND ANALYSISErp No:- 5AIM:- Determine the nodal displacement, stress in each element for the sketch given below. E:21105 N/mm2

2000N

400 mmPI{OBLEM SPECI]TICA IION

?tArtATTrA tlrilNrlar,'s ENGTIYEETiTNG 00LLDGB rtELGArnr-DEPARTMENT OF MECHANICAL ENGINEERING

2500 N

Applicable ANSYS Product ANSYS multi-physic, ANSYS MechanicalANSYS Structural, ANSYS EDLevel of Difficultl, EasyIntelactive time requireclt-liscipiirre

60 to 90 minutes *--Analysis type Linear staticEler-nent types Link-2D sparlANSYS Features Demonstrated 2-D modeling including primitives, Booleanoperation & load- Force/Moment, defbrmedshape & Stress display, listing of reactionforces.

Page 2t)


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__*rt

MANATHA DIANDAL'S BNGINBDNING COLLEGE BELGAIIDI.DEPARTMENT OF MECHANICAL ENGINEERING Page 30


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COMPUTER AIDED MODELING AND ANALYSISE,xp No:- 6aAIM:- Determine the nodal shear force" bending moment diagram & reaction for the following.

?o N/m/

PROBLEM SPECIFICATIONApplicable ANSYS Prodr-rct

Lcvcl ol' Dilficultlinteractive time requiredDisciplineAnalysis type

Element types

Features I)ernonstrated

ANSYS multi-physic, ANSYS MechanicalANSYS Structural, ANSYS EDEasy

1-D modeling including primitives, Booleanoperation & Pressure load, deformed shape &Stress display, listing of reaction forces.

60 to 90 minutes

Linear static

Be"*rD etast*.3

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COMPUTER AIDED MODELING AND ANALYSIS= i:-t*i i*G idOMENT DIAGRAM AN

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COMPUTER AiDED MODELING AND ANALYSISExp No:- 6bAIM:- Determine the nodal shear force, bending moment diagram & reaction for the following

PI{OI}LEN4 SPI]CII;ICA IION

IITAIIA'IIIA TIANI'AL'S ENGINI]ENING COLLEGE BELGAIMT.DEPARTMENT OF MECHANICAL ENGINEERING

i.I

l

Applicable ANSYS Prodr-rct

Level of Difficuity

ANSYS multi-physic, ANSYS MechanicaiANSYS Structural, ANSYS ED

lnte ractrve time recluired 60 to 90 minutesDisciplineArrb,s" typ"'-'-__-..L- lernenl types

StructuralLr"."*1"1*B.r-rD "trrti. 3

r\NSYS Features Dernonstrated 1-D modeling including primitives, Booleanoperation, Load-Force/Moment., defor-medshape & Stress display, listing of reactionforces.

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COMPUTER AtrDED MODELING AND ANALYSISREACTION AT THE SUPPORT

ruODAL LOAD

PRINT REACTION SOLUTIONS PER NODE***** POST1 TOTAL REACTfON SOLUTION LISTING *****LOAD STEP= 1- SUBSTEP: 1TIME: 1.0000 LOAD CASE= 0THE FOLLOWING X,y,Z SOLUTIONS ARE IN THE GLOBAL COORDINATE SYSIEM

NODE FX EY MZr- t-333.32 2666.7TOTAL VALUESVALUE 0.0000 4000.0 0.0000

PRINT FY SUMMED NODAL LOADS***** POST1 SUMMED TOTAL NODAL LOADS LISTING *****LOAD STEP= 1 SUBSTEP= 1TIME= 1.0000 LOAD CASE= 0THE FOLLOi^IrNG X,Y,Z SOLUTIONS ARE IN THE GLOBAL COORDfNATE SYSTEM

NODE FY1 -1333.32 -2666.7TOTAL VALUESVALUE -4OOO. O

:Y{AEtr\ frrA trrANrilll'S ENGINIIEhING COLLDGD I}DLGAIWLDEPARTMENT OF MECHANICAL ENGINEERING Pagc 3B


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COMPUTER AIDED MODELING AND ANALYSISExp No:- 6cAIM:- Determine the nodal shear force. bending moment diagram & reaction for the following.

P RO B L,EN4 SPEC LI,-ICATION

60 to 90 minutes

StructuralLinear static

lrlement types

ANSYS Features Demonstrated

.r\pplicabie ANSYS Product

I-cvel of DifficultyInteractirze time requiredDisciplineAnalvsis type

ANSYS multi-physic, ANSYS MechanicalANSYS Structural. ANSYS ED

Beam- 2D elastic 31-D modeling including primitives, Booleanoperation & Pressure Load- Force/Moment,deformed shape & Stress display, listing ofreaction forces.

DTANA'rIIA,IYIANDAL'S ENGINEEITING COLLEGN BELGAT]fuI.DEPARTMENT OF MECHANICAL ENGINEERING Page 39


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COMPUTER AIDED MODELING AND ANALYSISRESUTT:-SHEAR FORCE DIAGRAM

ilIANATUA D{ANI'AL'S DNGINNBTN1E COLLDGB BreLGAUilT.DEPARTMENT OF MECHANICAL ENGINEERING Page 40


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{:OMPUTER AIDED MODELING AND ANALYSISBENDING MOMENT DIAGRAM

Atu

frIANAIWA IEANNAL'S BNQINGBNNG COLLEGE BDLGAUDT.DEPARTMENT OF MECHAN]CAL ENGlNEERING Page 41


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COMPUTER AIDED MODELING AND ANALYSISExp No:- 6dAIM:- Determine the nodal shear force. bending moment diagram & reaction for the following.

PROI]LEM SPECIITICA'I'IONi\pplicable ANSYS Produrct ANSYS multi-physic, ANSYS MechanicalANSYS Structural, ANSYS EDLevel of Difficulty EasyI nteractive tirne req uirecll)rsc'r;tlrne

60 to 90 minutesSt.l,ctumt

Analysis type Linear staticElement types,rx.ivi f.itrr.i rlen.,irnriiii.d -- -- -

Beam- 2D elastic 31-D modeling including primitives, Booleanoperation & Pressure Load- Force/Moment,deformed shape & Stress display, listing ofreaction forces.

llftlllA'IIIA ILINI)AL'S ENGLTEEfiING COLLEGD BELGAIIIW-DEPARTMENT OF MECHANICAL ENGINEERING Page 43


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I\N:,:,'.': ;

.WANAIWA MATW'AL'S ENGINEENINIE CIDLLBGB BfrLGAUIW.DEPARTMENT OF MECHANICAL ENGINEERING Page 44


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COMPUTER AIDED MODELING AND ANALYSISREACTION AT THE SUPPORTPRINT REACTION SOLUTIONS PER NODE

***** POST1 TOTAI REACTTON SOLUTION LISTINGLOAD STEP: l- SUBSTEP=TIME= 1 " 0000 LOAD CASE=THE FOLLOWING X,Y,Z SOLUTIONS ARE

0IN THE GLOBAL

MZCOORDINATE SYSTEM

NODE FX.1 0.0000TOTAL VALUESVALUE O. OOOO

r'Y2500 . 0

2500.00.416678+06

0.416678+06I

l

trl,\rlATYrA trrlNN/./c.L's ENGTNEETiTNG COLLEGE BELGarmr-DEPARTMENT OF MECHANICAL ENGINEERING Page 4.6


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COMPUTER AIDED MODELING AND ANALYSISExp No:- 6eAlNz[:- i)etermir-re ihe nodai shear fbrce, bending moment diagram & reaction for the following

300 mm

PROBI,EM SPIICIFICATION,qppt,.;b1E ANS Y.{ P.;d.or ANSYS multi-physic, ANSYS MechanicalANSYS Structural, ANSYS EDLevel of Difficultv EasyInteractive tir-r-re requirecl

Analysis typeE6;rt ryp.r -ANSYS Features ])emonstrated

25 N/m

60 to 90 minutesStructuralLinear staticBeam- 2D elastic 31-D modeling including primitives, Booleanoperation & Pressure Load- Force/Moment,deformed shape & Stress display, listing ofreaction forces.

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:,{ANATUA frTANI'AL'S ENGINDEruNG CIOLLDGB BfrLGAAilIDEPARTMENT OF MECHANICAL ENGINEERING Page 48


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ANlr.i: _.

MANATruA MANNAL'S ENGINBENING COLLDAN BFT.GAIIDT.DEPARTMENT OF MECHANICAL ENGINEERING Page 50


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COMPUTER AIDED MODELING AND ANALYSISREACTION AT THE SUPPORTPRINT REACTION SOLUTIONS PER NODE

***** posI'1 ToTAI REACTION SOLUI,ION LISTING *****LOAD STEP= l- SUBSTEP= 1TIME= 1 " 0000 LOAD CASE=THE FOLLOWTNG X/Y.Z SOLUTTONS ARE

NODE FX FY

0IN THE GIOBAL

t'12COORDINATE SYSTEM

14

TOTAL VAI,UESVALUE O, OOOO

1887.5662 .502550.0 0.0000

i\iODAI- SOi-UTlOruPRINT U NODAL SOLUTION PER NODE

***** POST1 NODAL DEGREE OF FREEDOM LISTING *****LOAD STEP= 1 SUBSTEP= ITIME= l-.0000 LOAD CASE= 0THE EOLLOWING DEGREE OF FREEDOM RESULTS ARE IN THE GLOBAL COORDINATE SYSTEM

1 0.00002 -0.295't2E-053 -0.19329E-0s4 0.00005 -O.746748-066 -0.1439lE-057 -0.203328-0sB -0.24970E-059 -0 .28097E-0s10 -0.296238-05MAXIMUM ABSOLUTE VALUESNODE 10VALUE -O.29623I.-05

ii,fiTI T TA 7,IIA LIANIiA L'S ENGIIYD D BTNG COL LE GE BEL GA I]1vI.DEPARTMENT OF MECHANICAL ENGINEERING Page 51


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COMPUTER AIDED MODELING AND ANALYSISNODAL LOAD

PRINT SUMMED NODAL***** POST'I- ST MMEDLOAD STEP= 1TIME: 1.0000THE FOLLOWING X,Y,

LOADSTOTAL NODAL LOADS LISTING *****

SUBSTEP= LLOAD CASE:Z SOLUTIONS ARE

0IN THE GIOBAL COORDINATE SYSTEM

MZODE12346789

10

F'Y-1887.550.000-662 - sO

-0. 10851E-090.29831E-09-0.58208E-10-0.23283E-09-0.116428-080.4l-327E-08-0.116428-08-0.649028-080.16735E-07

0.l-1948E-07TOTAI VAI,UESVAITIE O. OOOO -2s00.0

trIAITATIIA T}IANI'AL'S ENGINEBNING COLLDGE BELGAIM.DEPARTMENT OF MECHANICAL ENGINEERING Page 52


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COMPUTER AIDED MODELING AND ANALYSISIrxp No:- 6fAIM:- Determine the nodal shear force, bending moment diagram & reaction for the following.

PROBLEM SPECIFTCAI'IONApplicable ANSYS Prodr-rct

Level of DiflicultyInteri.ti.,e tim. r"qui*.at)iii'pt,,re -Analysis typeL:lement types Beam- 2D elastic 3ANSYS Features Demo;strated 1-D modeling including primitives, Booleanoperation & Pressure Load- Force/Moment,deformed shape & Stress display, listing ofreaction forces.

rettlltil'l'IlA i?IANDtIL'S ENGITYEEITING COLLDGE BELCAIM-DEPARTMENT OF MECHANICAL ENGINEERING

ANSYS multi-physic, ANSYS MechanicalANSYS Structural. ANSYS ED

60 to 90 minutesStructuralLinear static

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{:OMPUTER AIDED MODELING AND ANALYSIS

ilIANAIruA frIANT'AL'S ENIEINBENING COLLDGE NBLGAAM.DEPARTMENT OF MECHANICAL ENGINEERING Page 54


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COMPUTER AIDED MODELING AND ANALYSISSHEAR FORCE DIAGRAM

,\N

ilTANAT'HA DTANNAL'S ENGINEBNING COLLBGE BGI GAIIM.DEPARTMENT OF MECHANICAL ENGINEERING Pase 55


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COMPUTER AIDED MODELING AND ANALYSISNODAL LOADPRINT SUMMED NODAL LOADS***** POST1 SUMMED TOTAL NODAL LOADS LISTING *****LOAD STEP= l_ SUBSTEP: 1TIME= 1.0000 LOAD CASE= OTHE EoLLowrNG x/Y,z SoLUTroNs ARE rN THE GLOBAT CoORDINATE sysTEM

NODE FX TY MZ1 -s92.39 _0.363808_112 -0.58208E-103 6 " 618468_094 -L2A2 .6 _0. l-l-792E_095 9.84401_E-096 -o.t22248-O87 _0.46566E_09B _0,23283E_099 9.69849E-09r-0 0.232838-09

TOTAL VALI-IESvALrrE 0.0000 -1875.0 0.2931-?E-09

1|rArlATrrA TTANDAL'j ENfiTNDEfiTNG OOLLEGE BELGAUfrT. page 58DEPARTMENT OF MECHANICAL ENGINEERING


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COMPUTER AIDED MODELING AND ANALYSISPART-B

Bxp No:- 7AIM:- Determine the stress. deformation & strain for thecircular hole^ following rectangular plate with

?5 mm

30 mm---------)

->Pressu re300 w/mm2

PROI]LEM SPEC]IFICATIONApplicable ANSYS Product ANSYS multi-physic, ANSYS Mechanical

ANSYS Structural, ANSYS EDLwcr J'Di{'llcLrlr}i;6iact*e tilr-rcqirii;?DisciplineAnalvsis typeElement typesANSYS Features Demonstrated

,|'lArlAll'rrA turttNDAl's ENGTNEEBTNO OOLLEGE BDLGALTIT.DEPARTMENT OF MECHANICAL ENGINEERING

0tomm

60 to 90 minutesSt.*t"""lLinear staticSolid-Quad,4 node422-D modeling including primitives, Booleanoperation, Load-Force/Moment., deformedshape & Stress display, listing of reactionforces.

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COMPUTER AIDED MODELING AND ANALYSISRESULT:.DEFORMED SHAPE

i.: f!.,tr!'"1" -: -,! 1:-.=1t:i.:!: .- -

DTANA1WA DIANI'AL'S DNQINN&NING CALLBGE BELGAADIDEPARTMENT OF MECHANICAL ENGINEERING Page 60


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I:OMPUTER AIDED MODELING AND ANALYSISDEFORMED SHAPE WITH UNDEFORMED MODET

:. r r.t i

.la{ .:'rl {i-i-l.i-llrl.l9i :.t-ii.1,.i-i ':-!.-r,';1,. -*i...r.i:*itr.f.r, r-it,fcrrnal-i::1 .:, slt*it-, i,:: lH,.'ii::rt.tl,,rr 1;i.+t*',iiii: i.:ii'',"',,11.ir itl;i*a,:. I * .-.(

DTANA'WA MANDAL'S BNGINrureNING COLLDGU NDLGAUDT.DEPARTMENT OF MECHANICAL ENGINEERING Page 61


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COMPUTER AIDED MODELING AND ANALYSISNODAL LOADPRINT SUMMED NODAL LOADS***** POSTI- SUMMEDLOAD STEP= 1TrME= 1.0000

TOTAL NODAL LOADS LISTING *****SUBSTEP= 1LOAD CASE= 0

IN THE GLOBAL COORDINATE SYSTEMHE FOLLOWING X,Y/ZNODE FX-J. -4602.2. 4 -4601.666 -724A.267 -6641.568 -6378. 669 -6065. 6'10 -57 60 . 077 -5594.872 -5536. 0

73 -5592.07 4 -5"t 56 .27 5 -6007 .77 6 -6320 .777 -6643.078 -7252.O

SOLUTIONS AREEY-L131.41131.4

7 60 .42445.L61otr 1054.234-LO.770-20.554-L .4546L7 .1378.1000-54.561-190.40-442.33-7 60 .14

TOTA], VALUESVALUE -9OOOO 0.35425E-09

tj'rArtA'rrrA llrttwDAl's ENGTNEE&TNG coLLEGn BELGarmr.DEPARTMENT OF MECHANICAL ENGINEERING Page 62


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COMPUTER AIDED MODELING AND ANALYSISExp No:- 8AIM:- Find the temperature at each node & temperature gradient & displacement of givensl


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COMPUTER AIDED MODELING AND ANALYSISRESU[T:-NODAL TEMPERATURE:l : i..; .::Ll.lT i .:::TEF-:T ll'lfl-l

ilIAnAImA fr{ANlrAL'S ENeINnDfrING COLLDGU nET,GAUN{. Pase G+DEPARTMENT OF MECHANICAL ENGINEERING


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COMPUTER AIDED MODELING AND ANALYSIS--Exp No :- 10AIM :- Find the tetrperature of each node & stress & deformation of node for given sketch.iri - 30 r,r,/mk. K:20 rv/rn2k

{- Tz =15" c

Tr = 900"c

I)I{OB LEM SPECIFICATION

L.iement typesANSYS Features Demonstrated

IITATTA.IIIA IWANDAL,S ENGIIYEEI,ING C0LLEGE I,DLGAIDI.DEPARTMENT OF MECHANICAL ENGINEERING

Applicable ANSYS Product

Level of DiflicultyInteractive time required


60 to 90 minutes

Link-2D sparl1-D modeling including primitives, Booleanoperation, Nodal temperature & Temperaturegradient.

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70


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COMPUTER AIDED MODELING AND ANALYSISl-.xp No:- 1 IAIM :- Harmonic Analysis of Stepped Bar

il., 2 x I 0r I N/nr2, pL-. 0.3. fieq- 0-.5000I{2. Ioad: cyclic & magnitude: 150N

1000 N

PI{OBLEM SPEC IFICATIONApplicable ANSYS Product

Level of Difficulty

Analysis typeElen.rent types Link-2D sparlANS YS l--eatures l)emonstrated 1-D modeling including primitives, Boolean

operation, Load-Force/Moment, Nodaldisplacement, amplitude & timehistoryprocess.

,Y,IAIiTI.IIIA DIAIYDAL,S ENGIVEDfuING COLLEGE BELGAI]DT.DEPARTMENT OF MECHANICAL ENGINEERING

Ar= 1m2Az= 0.05 m2


60 to 90 minutesSt.*t"*lHarmonic

Pag,e 7 2


76/83


il'1P],1TUDE

.l1.-,*{'Jilrll5ari'l:,j ll !l

,,r&j,t,! :; :;J j.!._,iit,01 5aL)

-!,l a r-i;i j"'i'l

l+itri :0+0 ]t1irji5,r* :50ir dlj i+15,.,r {',rr-, 5i; il,j!aiJ

;; .. r!r. 1 i -,r'-- 1 ,r-. i -' r.+ d !ij.1.r*rr iri*ppeii bill

l.ttr'. 1 I fi",fr(.-.- ! 1 ! a I

*TANATruA LTANI'AL'S ENGINDDruNG COLLEGB NULGAADT.DEPARTMENT OF MECHANICAL ENGINEERING Page73


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{OMPUTER AIDED MODELING AND ANALYSIS

liarm+ni,: "tr-ti,ri:/'aiis,if ,j.

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COMPUTER AIDED MODELING AND ANALYSISExp No:- 12AIM:- HarmonicIr. 2,I0r' N/m'.

Analysis of Unifbrm Barp- 0.3, freq: 0-800H2. Ioad: cyclic & magnitudr 200N.

200N

05mPI{OI] LEM SPECIF ICATION

IIIAIIAITIIA IWAND/LL'S I]NGLryEENTNG COLLEGE BELGAINT.DEPARTMENT OF MECHANICAL ENGINEERING

Applicable ANSYS Product ANSYS multi-physic, ANSYS MechanicalANSYS Structural, ANSYS ED

Level of Difficultl, EasyInteractive time reqr-rired

-rscrphneAli"l.vs,s typ.-

60 to 90 minutesSt.rct".rtHarmor..rrc

[rlenient types Link-2D sparlANSYS Features Demonstrated 1-D modeling including primitives, Boolean

operation, Load-Force/Moment, Nodaldisplacement, amplitude & timehistoryprocess.

Pagc. 75


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COMPUTER AIDED MODELING AND ANALYSISIi.: 1- '

9':iii

4jil5a+iii"}

;.1l

-'_l

i. i i:i:+

(t lit llt .il:,:, {.Irl ir,: ,,,in :qii ;'.it :{(i ::n" *.L.*

liarmonic 4rnd1".;sis cf $i=..eri iidt

ilA'i i. t :or:,'l3: lir5I

DlAfrATruA ilTANI'AL'S ENGINUNNING CAI,LNGG NGLGAADI.DEPARTMENT OF MECHANICAL ENGINEERING Page 7r


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COMPUTER AIDED MODELING AND ANALYSISF,- 'a T' .' AN

l3:1.q:{l

ilIANATruA DIANDAL'S ENGTNUDNING COLLUAD NNT.GAIIDI.DEPARTMENT OF MECHANICAL ENGINEERING Page77


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COMPUTER AIDED MODELING AND ANALYSISi:.xp No:- 13AIM:- HarmonicE-- 2xi0rrN/m2,

0.5 mPROBLEM SPECIFICATIONApplicable AN

Level of DitfictlitGftt*e tir";Discipline

,YfrTIIIIIT,IIA /UI-,I1UI/AL,S ENGNVN EHILTG COLLEEE ITELGAT/IW.DEPARTMENT OF MECHANICAL ENGINEERING

Analysis of Beam with both and fixed.pL:0.25" fr.q:0-500FI2, Ioad: cyclic & magnitude: 150N.

Analysis typeElernent typesANS\s-F;"t,

SYS Product ANSYS multi-physic, ANSYS MechanicalANSYS Structural, ANSYS ED

ult1, Easyreqr-rired 60 to 90 minutes

StructuralHarmonicLink-2D sparl

ies l)emonstrated 1-D modeling including primitives, Booleanoperation, Load-Force/Moment, Nodaldisplacement, amplitude & timehistoryprocess.

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COMPUTER AIDED MODELING AND ANALYSISP.-.:iT: idlt Lt i ugg

It..,rfmorl.iar dnnil,rsi.i 5f g-i,:,'en hc4m

i,rl',' I t ^ari'(,irii r 03::1

ilTANAT:UA frIANNAL'S ENGINEENING COI,LGGE BM,AAT]DT.DEPARTMENT OF MECHANICAL ENGINEERING Page 79


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il'tPn,r?Lr!E

'.n"Li,l ,l. _nE-n:

irarmonir: an,rL,;::is c: ci'.'.rr1 b*am

ii frj-f.c:ril-:rr1t{l

Finite Element Analysis Lab

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Transcript of Finite Element Analysis Lab