COMPUTATIONAL ENGINEERING OF FINITE ELEMENT MODELLING FOR AUTOMOTIVE APPLICATION USING ABAQUS

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International Journal of Advanced Research in Engineering and Technology

(IJARET) Volume 7, Issue 2, March-April 2016, pp. 30–52, Article ID: IJARET_07_02_004

Available online at

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ISSN Print: 0976-6480 and ISSN Online: 0976-6499

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___________________________________________________________________________

COMPUTATIONAL ENGINEERING OF

FINITE ELEMENT MODELLING FOR

AUTOMOTIVE APPLICATION USING

ABAQUS

Praveen Padagannavar

School of Aerospace, Mechanical & Manufacturing Engineering

Royal Melbourne Institute of Technology (RMIT University)

Melbourne, VIC 3001, Australia

ABSTRACT

Modals with complicated geometry, complex loads and boundary

condition are difficult to analyse and evaluate in the terms of strain, stress,

displacement and reaction forces by using theoretical methods. A given modal

can be analysed by using Finite Element Method easily with the help of

computer software ABAQUS CAE and can get approximate solutions. This

report is about modelling two dimensional and three dimensional analyses

with the ABAQUS CAE for plane stress, plane strain, shell, and beam and 3d

solid modal elements. The report will show hand sketch, procedure to simulate

and solve the problems, submit and monitor analysis jobs and view results

using ABAQUS CAE software for different elements and compare with

theoretical calculation. The result also gives the information of stresses and

strains generated in the Plate and its deformation for different boundary

conditions and loads. In addition, this report will analyse the data, compare

results and validate theoretical results, this will help us to understand the

software, its capabilities and accuracy.

Cite this Article: Praveen Padagannavar, Computational Engineering of

Finite Element Modelling For Automotive Application Using Abaqus.

International Journal of Advanced Research in Engineering and Technology,

7(2), 2016, pp. 30–52.

http://www.iaeme.com/IJARET/issues.asp?JType=IJARET&VType=7&IType=2

Computational Engineering of Finite Element Modelling For Automotive Application Using

Abaqus


1. INTRODUCTION

Finite Element Analysis is an approach that uses mathematical approximation to

simulate geometry and load conditions. ABAQUS is powerful finite element software

for engineers which can solve linear analysis to nonlinear problems. This software

will guide engineers to simulate, analyse and evaluate the results produced by

modelling for different kinds of structures and can modify current modal. ABAQUS

software used to analyse and investigate problems for two dimensional and three

dimensional modelling with different element types based on the given theoretically

structure. Finite Element Analysis is important tool to carry out results with using

numerical method to solve engineering problems; it can solve any complex geometry.

Finite element analysis is to identify the weakness of design and validate the proper

material property required for particular modal. The ABAQUS/CAE has been

designed for finite element analysis and to simulate two dimensional and three

dimensional models for plane stress, plane strain, shell, beam and 3D model and shell

elements and analyse the results.

Objective: The objective is to analyse stresses and deformations under F1 and F2

loads and compare the model for plane stress, plane strain elements (2-D modelling),

shell element, beam element and 3D model using ABAQUS/CAE and validate the

results by comparing theoretical solution.

1.1 Requirements

1. Use the ABAQUS/CAE software to evaluate the stresses and deformations of the

given load.

2. Compare the performance and suitability for the following modelling:-

Plane stress elements

Plane strain elements

Shell elements

Beam elements

3D solid elements

3. Validate the results by comparing with the theoretical.

2. MODAL DEVELOPMENT

2.1 HAND SKETCH



Figure 1 Hand sketch (full and half model)

Figure 2 Hand sketch (beam model)

2.2 STEPS FOR MODELLING AND IT’S EXPLANATIONS:

Step 1: Go to program and select Abaqus CAE then the Abaqus window will open

select for “with standard modal”.

Step 2: Start with first part “Module Part” in this module we need to modal the

frame, in this we can create, edit, and manage the part. This is functional units of

Abaqus called modules. In our case we are creating modal.

Click on part and then select part manager.

For PLANE STRESS, PLANE STRAIN MODEL In the part manager click on

create then the part create new window will open select for 2D planar modelling

space, deformable type, Shell feature and approximate size and then continue and

dismiss the previous window.

For SHELL MODEL In the part manager click on create then the part create new

window will open select for 3D planar modelling space, deformable type, Shell

feature and approximate size and then continue and dismiss the previous window.

Each node of the shell element can move in U1, U2,U3 and UR1, UR2,UR3

For BEAM In the part manager click on create then the part create new window will

open select for 2D planar modelling space, deformable type, wire feature and

approximate size and then continue and dismiss the previous window.

For 3D element In the part manager click on create then the part create new window

will open select for 3D planar modelling space, deformable type, Solid feature—

extrusion and approximate size and then continue and also add the value of depth.

Create points in the grid coordinates points then create the line by selecting the

coordinate’s points.

Then at the bottom click on done. Now we created the modal frame.

We need to create partition in the modal so that we can apply boundary condition,

forces and also important for proper meshing and its structure. The partition is created

by using datum and partition feature which is in main toolbar tools.


Abaqus


Figure 3 3D, shell, beam geometry

Step 3: Select the second part that is “Property Module” in this module we need to

apply material properties to the given modal frame that is define materials, material

behaviour and define section. Assigning each material property and region the part.

Start with Material which is located at the top main menu toolbar, click on it and then select on create. Here we are defining material.

Edit material new window box will open.

Select on mechanical, change to elasticity – elastic. Linear elastic modal is

isotropic and have elastic strain.

Put the values of Young’s Modulus and Poisson’s Ratio and then click OK. These are parameter area to be defined.

Secondly, select Section in this feature we need to apply cross sectional of the modal frame.

For PLANE STRESS, PLANE STRAIN MODEL: Create section dialogue box will open then click on solid—homogeneous and continue and also put the

values of thickness.

For SHELL MODEL: Create section dialogue box will open then click on

solid—homogeneous and continue and also put the values of thickness and also

create the shell—homogeneous and continue.

For BEAM MODEL: Create section dialogue box will open then click on beam—beam. Edit beam section window will open. Click here to create beam

profile, select rectangular profile and continue. Rectangular profile is geometric

data of rectangle solid.

For 3D MODEL: Create section dialogue box will open then click on solid—

homogeneous and continue.

Finally, select Assign and click on section and then select the region to be

assigned select entire modal frame and click Done at the bottom. Section

properties that have assigned to the part assigned automatically to all instance.

Step 4: The third part is “Assembly Module”. In our modal we have only one

assembly.



Select Instance and click on create-Instance means own coordinate system.

In this new window we need to select parts and dependent instance type and click

OK. Click only OK, because if we click apply and ok means then we are creating two

instances and one is sitting behind the modal, so here is important to click only ok.

Dependent is the original part.

Step 5: The fourth part is “Step Module”

Select step which is located at the top of the toolbar and click on create. In step we

can edit or manipulate the current modal.

In this new window box change the setting to linear perturbation procedure type and

static, linear perturbation and click Continue. Linear perturbation analysis provides

linear response of the modal.

Give description to the step-1 and click Ok.

Step 6: The fifth part is “Load Module” in this module we will apply boundary

condition and load to the modal frame. Boundary condition fixes the degree of

freedom and has two types rotational and translational degree of freedom.

Select BC which is located at the top of the toolbar and click on create. Then create

boundary condition dialogue box will open and then change the settings to Initial --

mechanical category – displacement/ rotation and then click continue. Select the

region to apply BC. Displacement / rotation means holding the movement of selected

nodes dof to 0

Select the two corner points to of the modal frame.

Now it’s time to apply Load select for it which is located at the top. We should name

the load, type of load and apply.

Then click on create load, change the setting to Step-1, mechanical and concentrated

force (applied to vertices) and click continue. Concentrated force is to the nodes

Now pick up the points to apply load.

After picking the points when you click done, another window will open this window

will show the direction of the load.

Figure 4 load and boundary condition

Step 7: The sixth part is “Mesh Module” in this module we will mesh the modal

frame according to the requirement to get proper results. Mesh means converting

whole material into small network and also we can define mesh density, mesh shape


Abaqus


(1 or 2 or 3 dimensional) and mesh element. The main aim of mesh is to reduce the

error while solving the results. We can also mesh by partition so that the mesh

structure will be finer and perfect shape. Mesh is created to confirm the node position

and element.

Click on Part-1

First, select seed which is located at the top and click on part and put the values of

approximate global size seeds and then click OK and Done. Seeding is used to

specify mesh density. Seeds are only located at the edges. While, putting the value we

need to select properly otherwise it will show deformation size is large error, that

time we must decrease the number.

Secondly, select Mesh and click on element type. Select the region to be assigned

element type, select the entire modal frame and click Done. We need to compare the

performance, relevance and suitability of modelling.

The new window box will open that is element type, change the settings:

Element type:

Plane stress modal – the family is plane stress.

Plane strain modal – the family is plane strain.

Plane shell modal – the family is shell and quadratic.

Beam modal – the family is beam.

Finally, again select Mesh and click on part and then click yes at the bottom mesh

the part.

Step 8: The final part is “Job Module” in this module we will submit the modal

frame for analysis and evaluation and get the results. This is the last step.

Select the Job located at the top and click on create. In this dialogue box name the

job and click continue and OK.

Again select job and click on manager and submit the job (modal frame) for

evaluation.

Check for the command “completed successfully”

Then click on results to view the results.

Then click on report which is at the top and then click on field output. Give the

location to save the abaqus.rpt, so that we can check the report.

Save the modal.

Results can also be viewed in visualisation module. We can see deformed shape,

undeformed shape and contours.

2.3 MODEL GEOMETRY DETAILS:

Load for condition (i) F1=50 and F2=0 AND (ii) F1=50 and F2=50 (Depends upon

condition)

F1 is in y- direction and F2 is in x direction

Poisson ratio v = 0.33 and E=200Gpa 200000 Mpa

Thickness = 2X, X=1.0 + 0.001*101

Thickness = 2.202mm

Full model or half model is done depending on required conditions



2.4 BOUNDARY CONDITION

Roller support means fixing and making the model movable only in the x direction

and constrained at y-axis.

Fixed support means fixing in the respective x and y direction making the structure

rigid. Translational motion in axis 1 and 2 are constrained for both the nodes.

Mesh: Finite Element Method involves breaking a given structure into smaller

element with simple geometry and theoretical solution. The elements are joined to

each other at Nodes, this procedure is called Meshing. According to this paper, there

are three types of mesh element type: - (1) Linear Reduced Integration (2) Linear and

(3) Quadratic. Geometric order of the mesh elements: There are two types of mesh

elements, namely linear order and Quadratic order. Linear means first order elements

and Quadratic means second order elements.

3. ABAQUS RESULTS

3.1 Element Type: Plane Stress

Model: Full Model (case (i) F1=50, F2=0)

Figure 6 Deformation of plane stress element (full model case (i))

Table 2 Output data of plane stress element (full model case (i))

Node

Label1 U.U1 @Loc 1 U.U2 @Loc 1 E.E11@Loc 1 E.E22@Loc 1 S.S11 @ Loc 1 S.S22 @ Loc 1

48 -89.7189E-03 17.2076E-03 61.4229E-06 -19.2167E-06 12.3626 236.312E-03

Min -201.026E-03 -132.191E-03 -62.2530E-06 -61.9905E-06 -12.3626 -12.3626

Node 42 42 58 83 59 86

Max 21.5887E-03 17.2076E-03 62.2047E-06 61.9844E-06 12.3626 12.3626

Node 34 48 49 112 51 116

Total -11.0354 -2.71256 7.72109E-06 -2.10283E-06 1.57719 99.9056E-03


Abaqus


The table shows the ABAQUS results that is displacement, strain components and

stress components. In order to analyse the stress we need to select top middle point

that is node label 48. The upper layer of the model is tension and bottom layer is

compression. Further, consider the nodal label 48 stress values that are S11 and

compare this value with calculated theoretical values at the same point.

3.2 Element Type: Plane Stress

Model: Full Model (case (ii) F1=50, F2=50)

Figure 7 Deformation of plane stress element (Full model case (ii))

Table 3 Output data of plane stress element (full model case (ii))



that is node label 48. The upper layer of the model is compression and bottom layer is

tension. Further, consider the nodal label 48 stress values that is S11 and compare this

value with calculated theoretical values at the same point.

Node

Label1 U.U1 @Loc 1 U.U2 @Loc 1 E.E11@Loc 1 E.E22@Loc 1 S.S11 @ Loc 1

S.S22 @ Loc

1

48 8.80298E-03 -4.59340E-03 -25.7902E-06 8.45758E-06 -5.16199 -11.9397E-03

Min -3.37425E-03 -20.0261E-03 -65.5699E-06 -65.8945E-06 -13.1476 -13.2216

Node 27 33 106 86 258 226

Max 21.2447E-03 1.50473E-03 78.1199E-06 73.3243E-06 16.9613 15.9758

Node 19 112 231 301 231 301

Total 2.87065 -1.27619 536.124E-06 -279.710E-06 99.6117 -23.0702



3.3 Element Type: Plane Strain

Model: Half Model (case (i) F1=50, F2=0)

Figure 8 Deformation of plane strain element (half model case (i))

Table 4 Output data of plane strain element (Half model case (i))



that is node label 9. Further, consider the nodal label 9 stress value that is S11 and


Node


9 -7.29777E+09 -23.5482E+09 -476.837E-09 0. -141.301E-03 -69.5959E-03

Min -7.29777E+09 -23.5482E+09 -85.8307E-06 -86.7844E-06 -19.6577 -19.4531

Node 448 374 601 162 601 162

Max 39.7986E+09 32.9674E+09 167.847E-06 115.514E-06 39.5073 27.8447

Node 770 780 576 236 576 236

Total 92.1331E+12 14.4068E+12 29.5301E-03 -18.4810E-03 6.05326E+03 -1.16646E+03


Abaqus


3.4 Element Type: Plane Strain


Figure 9 Deformation of plane strain element (full model case (ii))

Table 5 Output data of plane strain element (full model case (ii))




tension. Further, consider the nodal label 48 stress values that are S11 and compare

this value with calculated theoretical values at the same point.

Node

Label1 U.U1 @Loc 1 U.U2 @Loc 1 E.E11@Loc 1 E.E22@Loc 1 S.S11 @ Loc 1

S.S22 @ Loc

1

48 7.86787E-03 -4.13520E-03 -22.9843E-06 11.2756E-06 -5.16520 -13.3498E-03

Min -2.96999E-03 -17.9085E-03 -58.2581E-06 -58.4818E-06 -13.1768 -13.2484

Node 27 33 258 86 258 226

Max 18.9327E-03 1.29836E-03 66.5917E-06 62.4790E-06 17.1062 16.1314

Node 19 112 231 301 231 301

Total 2.56519 -1.14894 494.012E-06 -319.806E-06 99.7134 -22.6652



3.5 Element Type: Shell


Figure 10 Deformation of shell element (half model case (i))

Table 6 Output data of shell element (half model case (i))



that is node label 15. Further, consider the nodal label 15 stress values that are S11

and compare this value with calculated theoretical values at the same point.

Node


15 -3.31248E+09 -2.67484E+09 -2.06013E-06 1.45504E-06 -354.610E-03 173.987E-03

Min -3.31248E+09 -2.67484E+09 -45.3654E-06 -45.8914E-06 -9.06656 -9.16343

Node 1764 1536 204 109 204 109

Max 2.03719E+09 3.74477E+09 84.0251E-06 79.3060E-06 18.4686 17.5681

Node 1867 1868 1149 856 1149 856

Total -667.591E+09 695.458E+09 1.75692E-03 -225.538E-06 377.620 79.5071


Abaqus


3.6 Element Type: Shell


Figure 11 Deformation of shell element (full model case (ii))

Table 7 Output data of shell element (full model case (ii))




tension. Further, consider the nodal label 71 stress values that are S11 and compare

this value with calculated theoretical values at the same point.

Node


71 8.83807E-03 -4.56279E-03 -25.7786E-06 8.50727E-06 -5.15570 73.3625E-06

Min -3.41915E-03 -20.3119E-03 -68.7583E-06 -69.2517E-06 -13.7846 -13.8854

Node 35 39 249 219 249 219

Max 21.6098E-03 1.52797E-03 105.182E-06 99.8439E-06 23.2439 22.1278

Node 1172 939 791 978 791 978

Total 10.9089 -4.70201 2.33775E-03 -912.499E-06 457.104 -31.6556



3.7 Element Type: Beam

Model: Full Model (case (i) F1=50, F2=0)

Figure 12 Deformation of Beam element (full model case (i))

Table 8 Output data of Beam element (full model case (i))



that is node label 50. The upper layer of the model is tension and bottom layer is

compression. Further, consider the nodal label 50 stress values that are S11 and


Node

Label1 U.U1 @Loc 1 U.U2 @Loc 1 E.E11@Loc 3 S.S11 @ Loc 3

50 -73.5695E-03 12.6669E-03 -92.8064E-06 -18.5613

Min -147.139E-03 -109.373E-03 -92.8064E-06 -18.5613

Node 89 8 76 76

Max 147.753E-21 12.7725E-03 5.18786E-18 1.03757E-12

Node 9 49 89 89

Total -6.54768 -1.49692 -6.58925E-03 -1.31785E+03


Abaqus


3.8 Element Type: Beam


Figure 13 Deformation of Beam element (full model case (ii))

Table 9 Output data of Beam element (full model case (ii))




tension. Further, consider the nodal label 50 stress value that is S11 and compare this

value with calculated theoretical values at the same point.

Node

Label1 U.U1 @Loc 1 U.U2 @Loc 1 E.E11@Loc 3 S.S11 @ Loc 3

50 11.7168E-03 -4.22231E-03 36.0914E-06 7.21827

Min -367.162E-06 -23.5415E-03 -89.3030E-06 -17.8606

Node 23 8 3 3

Max 23.7492E-03 93.8106E-18 36.0914E-06 7.21827

Node 75 5 59 59

Total 1.04357 -385.139E-03 -1.45912E-03 -291.825



3.9 Element type: 3D Solid


Figure 14 Deformation of 3d solid element (half model case (i))

Table 10 Output data of 3D solid element (full model case (i))



that is node label 45. Further, consider the nodal label 45 stress values that are S11

and compare this value with calculated theoretical values at the same point.

Node


45 46.5913E-36 25.7211E-03 172.172E-06 -61.4683E-06 33.1248 -2.00910

Min -166.067E-03 -198.457E-03 -204.305E-06 -203.279E-06 -40.0039 -39.7541

Node 34 35 258 110 258 110

Max 9.62380E-03 26.0663E-03 175.976E-06 205.100E-06 33.7750 40.0031

Node 8 276 269 223 269 223

Total -30.9161 -13.1518 19.8220E-06 -3.90064E-06 4.08532 518.038E-03


Abaqus


3.10 Element type: 3D Solid


Figure 15 Deformation of 3d solid element (full model case (ii))

Table 11 Output data of 3D solid element (full model case (ii))



that is node label 284. The upper layer of the model is compression and bottom layer

is tension. Further, consider the nodal label 284 stress values that are S11 and


Node

Label1 U.U1 @Loc 1

U.U2 @Loc

1 E.E11@Loc 1 E.E22@Loc 1 S.S11 @ Loc 1 S.S22 @ Loc 1

284 8.16678E-03 -4.50405E-03 -21.1726E-06 8.14680E-06 -3.80248 606.446E-03

Min -3.17635E-03 -18.8591E-03 -54.0453E-06 -54.0850E-06 -9.75359 -9.76004

Node 115 23 169 235 169 235

Max 19.7896E-03 1.38045E-03 64.1838E-06 59.2142E-06 12.0111 11.0205

Node 32 131 197 127 197 127

Total 3.02545 -1.41562 535.810E-06 -352.985E-06 100.649 -33.0047



4. THEORETICAL CALCULATION


Abaqus



Abaqus


The calculation is done on the element point C



5. VALIDATION

Comparison between theoretical and ABAQUS for values Half or full

model Case (i) F1=50, F2=0

ELEMENT TYPE STRESS THEORETICAL ABAQUS (S11)

Plane stress 18.5613 Mpa 12.3626 Mpa

Plane strain 18.5613 Mpa -141.301E-03 Mpa

Shell 18.5613 Mpa -354.610E-03 Mpa

Beam 18.5613 Mpa -18.5613 Mpa

3D solid 18.5613 Mpa 33.1248 Mpa

Table 12 Theoretical and ABAQUS results for case (i) F1=50, F2=0

The table shows theoretical and ABAQUS values for the case (i) F1=50 and F2=0

for full or half model. According to theoretical calculation the stress value is

18.5613Mpa and ABAQUS results vary. In the case of beam the theoretical and

Abaqus results are same that is 18.5613. In the case of plane stress, the theoretical

stress value is 18.5613Mpa and Abaqus value is 12.3626, the values are not accurate.

Comparison between theoretical and ABAQUS values for full model Case

(ii) F1=50, F2=50

ELEMENT TYPE STRESS THEORETICAL ABAQUS (S11)

Plane Stress 6.187Mpa -5.16199 Mpa

Plane Strain 6.187Mpa -5.16520 Mpa

Shell 6.187Mpa -5.15570 Mpa

Beam 6.187Mpa 7.21827 Mpa

3D solid 6.187Mpa -3.80248 Mpa

Table 13 Theoretical and ABAQUS results for case (ii) F1=50, F2=50

The table shows theoretical and ABAQUS values for the case (ii) F1=50 and

F2=50. According to theoretical calculation the stress value is 6.187Mpa and

ABAQUS results more or less similar. In the case of beam the theoretical values is

6.187Mpa and Abaqus result is 7.21827Mpa, the values are closer. In the case of

plane stress, the theoretical stress value is 6.187Mpa and Abaqus value is -

5.16199Mpa which is almost similar.


Abaqus


Comparison between theoretical and ABAQUS values for Beam model

Case (i) F1=50, F2=0

ELEMENT TABLE BEAM THEORETICAL BEAM ABAQUS S11

(CASE i)

16 18.56 -18.5613

17 18.56 -18.5613

18 18.56 -18.5613

19 18.56 -18.5613

20 18.56 -18.5613

21 18.56 -18.5613

22 18.56 -18.5613

23 18.56 -18.5613

24 18.56 -18.5613

25 18.56 -18.5613

Table 14 Beam Theoretical and ABAQUS results for case (i) F1=50, F2=0

The table shows theoretical and ABAQUS values for the Beam case (i) F1=50 and

F2=0 model. According to theoretical calculation, the stress value is 18.56Mpa and

ABAQUS results are -18.5613 which exactly the same is.

6. DISCUSSION

The Purpose of this paper is to compare the results from ABAQUS and theoretical

calculation. Though hand calculations are accurate but it is more complicated or

nearly impossible to do it in some cases and time consuming and also increases

computational cost. The use of ABAQUS software is much easier and reliable.

Plane stress, plane strain and beam elements were modelled in 2D analysis while

Shell and 3D Solid elements were modelled in 3D elements. Different types of 2D

and 3D elements can be selected for model analysis in ABAQUS/CAE.

It was observed that out of plane normal and shear stresses are equal to zero.

For Plane Stress elements, linear analysis was used and since 2D modelling was done

on it, it is less expensive and less time consuming than 3D or Shell elements.

Although the results were highly accurate.

For Beam Elements, transverse shear deformations were allowed since element type

for the given model was B21-linear node. This type of elements uses linear

interpolation method for analysis. Also, results were very accurate.

For 3D solid Elements, reduced integration was used. Also these elements do not

have rotational degrees of freedom. The computational time is high. Also the bending

behaviour is much stiffer.

When we have a fine mesh it is best recommended to have the reduced integration

method. In linear elements when there is no bending moment we use full integration

point method. This happens because the element has edges that are unable to curve.

The simulation gives values that are closer to the theoretical values.

Stress Distribution: the stresses are mostly distributed/induced in the middle point of

the full model because the force generated is higher in this point. The different forces

would generate different stress.

The beam element is most accurate because it is similar to the theoretical results. In

contrast, the Shell and 3D model would have relatively more error when compared



with the theoretical results, this is due to three components x, y, and z directions of

the displacement.

Model simplification technique is used to simplify complex structural applications.

This can be done without considering the thickness of the model and the forces can be

assumed on respective nodes. To simplify the model analysis, we use step as linear

perturbation for linear problems.

Quadratic reduced-integration is the method that does not pose locking when there

are stresses present. Thus these methods are used for simulation of stresses, strains

and displacements.

There are 2 types of shell elements, mainly linear full integration and reduced

integration of elements. By using the linear reduced integration method and

appropriately sizing the mesh distortion could be identified clearly. When the mesh is

finely created the values are more accurate. This is experienced because the elements

used here are tolerant to distortion. Shell elements are two types’ i.e. linear full and

reduced integration elements. In linear elements when bending moment is not present

we use full integration point.

The element type for structure is kept same throughout the analysis. Manual

calculations for these structures are done using theoretical and mathematical

formulas. These are then compared.

7. CONCLUSION

ABAQUS is a tool that is comprehensive and powerful that provide various analysis

of structures by changing the modelling process during designing to get different

results. This report analyses the deformations in a 2D planar, plane stress element,

plane strain element, 3D shell element, beam element and 3D solid element. The

values were manually calculated and the values were obtained by using ABAQUS.

These were compared and assessed. These values and figures are tabulated and

presented above. The simulations and calculations were performed for planar stresses,

strains and the deformation in the shell structures. As seen in the above sections the

figures clearly show sections with more stress/strain and deformations. During

analysis it was understood that the techniques chosen such as linear or quadratic could

influence the result of the analysis performed. Also different modules such as seeding,

meshing, boundary conditions etc. need to be assigned carefully to get the best results.

Compared values from ABAQUS and theoretical calculations nearly match each

other. However there was slight difference. Since calculating the stresses/strain in real

life structures is difficult and complex more accurate values could be obtained by

using FEA with quadratic element method. Thus FEM using ABAQUS helps us in

understanding the deformations and strength of the different engineering materials

used more accurately and easily.

REFERENCE

[1] Takla, M 2015, “Introduction to the finite element method”, Lecture notes at

RMIT University, Melbourne, Australia.

[2] Takla, M 2015, “Introduction to ABAQUS/CAE”, Lecture notes at RMIT

University, Melbourne, Australia.

[3] Abaqus Version6.7 “ABAQUS Analysis User Manual Engineering forums”

COMPUTATIONAL ENGINEERING OF FINITE ELEMENT MODELLING FOR AUTOMOTIVE APPLICATION USING ABAQUS

Engineering

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