finite element analysis on aluminium alloy...
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ISSN: 2278 – 7798 International Journal of Science, Engineering and Technology Research (IJSETR)
Volume 5, Issue 5, May 2016
1295
All Rights Reserved © 2016 IJSETR
FINITE ELEMENT ANALYSIS ON
ALUMINIUM ALLOY COMPOSITE WITH
VARIOUS BOUNDARY CONDITIONS
L.Vijayabaskar1
Asst.Professor, CK College of Engineering & Technology, Cuddalore, India1
Abstract- Composite materials have interesting
properties such as high strength to weight ratio, ease
of fabrication, good electrical and thermal properties
compared to metals. Design engineer must consider
several alternatives such as best stacking sequence,
optimum fibre angles that are orientations. The
development of composite material with reduced
weight and increase strength relative to conventional
metals has played a critical role in achieving higher
operating performance, long life and reduced cost.
One such composite material is Boron/Aluminium
composite [1]. These materials are being widely used
in a variety of high performance structures. Reliable
use and optimum design requires accurate methods
for predicting their mechanical behaviour, among
other things. In this work, modelling of composite
specimen will be carried out by using ANSYS and by
finite element analysis stress and displacement
behaviour of such a specimen is analyzed with ansys
software. It is observed that the stress value is
maximum 15188 N/mm2 while considered the
boundary condition 2 at 30 degree. Also the stress
value is minimum 422 N/mm2 while considered
boundary condition 4 at 30 degree. It is also observed
that displacement value is maximum 17.525 mm while
considered boundary condition 2 at 60 degree. From
the result it is observed that the orientation at 30
degree with boundary condition 4 is safe while
comparing other boundary conditions. Index Terms- Boron/Aluminium composite, ANSYS,
finite element analysis, boundary condition 2 at 60
degree.
I INTRODUCTION
COMPOSITE MATERIALS
Composite materials have been used in
structures for long time. In recent times composite
parts have been used extensively in aircrafts,
automobiles, sporting goods, and many consumer
products.
Composite materials (also called
composition materials or shortened to composites)
are materials made from two or more constituent
materials with significantly different physical or
chemical properties, that when combined produce a material with characteristics different from the
individual components[1]. The individual
components remain separate and distinct within the
finished structure.
DIFFERENT TYPES OF FIBRE ORIENTATION
Fig.1 Unidirectional Laminate
Composites are used in the form of
unidirectional laminates, since one of their great
merits is that the fibers can be arranged so as to give specific properties in any desired direction.
Thus, in any given structural laminate,
predetermined proportions of the unidirectional
plies will be arranged at some specific angle, θ, to
the stress direction. In order to calculate the
properties of such a multi-ply laminate, it is first
necessary to know how the elastic response of a
single unidirectional lamina, such as that which we
have been considering so far, will vary as the angle
to the stress direction is changed. This is done by
transforming the axes through some arbitrary angle, θ, a procedure that will familiar to anyone who has
studied the derivation of the Mohr’s circle
construction.
II CHOOSING THE PROPER ELEMENT TYPE
The following element types are available
are available to model layered composite materials:
SHELL99, SHELL91, SHELL181, SOLID46, and
ISSN: 2278 – 7798 International Journal of Science, Engineering and Technology Research (IJSETR)
Volume 5, Issue 5, May 2016
1296 All Rights Reserved © 2016 IJSETR
SOLID191. Which element you choose depends on
the application the type of results that need to be
calculated and so on. Check the individual element
descriptions to determine if a specific element can
be used in your ansys product. All layered element allow failure criterion calculations.
SHELL99
Used for layered applications of a
structural shell model or for modeling thick
sandwich structures. Up to 100 different layers are
permitted for applications with the sandwich option
turned off. Allows more layers. The element has six degrees of freedom at each node: translations in the
nodal x, y, and z directions and rotations about the
nodal x, y, and z-axes [6].
Shell 99 IS AN 8 N0DE 3D shell element
with six degree of freedom at each node. For
structure with smaller ratios, you consider using
SOLID 46. The SHELL99 element allows a total of
250 uniform thickness layers.
III MATERIAL PROPERTIES
Two different orthotropic materials are
used to analysis the effect of fiber orientation. The
material properties are given in the table 1, where
E, G, represent modulus of elastically, modulus of
rigidity and poisons ratio respectively.
Table.1 Material Properties
Materials
Properties
Boron/Aluminium
Aluminium EX 235 GPa
EY 137Gpa
EZ 137 Gpa
GXY 47 Gpa
GYZ 47 Gpa
GZX 47 Gpa
µXY 0.3
µYZ 0.3
µZX 0.3
IV MODELING AND ANALYSIS
MODELING OF STRUCTURE
To study influence of fiber orientation up
on deflection and scf for different stresses. A
laminated composite plate of dimension 200mm×100mm×1mm with a unidirectional cross
section using the finite element analysis software.
The following figure illustrates the basic model of
the problem.
Fig. 2 Isometric View of Lamina Plate
MESHING MODEL
In this method, a body or structure in
which the analysis is carried out is subdivided in to
smaller elements of finite dimensions called finite
elements. Then the body is considered as an
assemblage of these elements connected at a finite
number of joints called nodes or nodal point. These
properties of each type of finite element is obtained
and assembled together and solved as whole to get
solution
Fig.3 Meshed View of Lamina Plate
Fig.4 Solve the Lamina Plate
Fig.5 Solved Lamina Plate
ISSN: 2278 – 7798 International Journal of Science, Engineering and Technology Research (IJSETR)
Volume 5, Issue 5, May 2016
1297 All Rights Reserved © 2016 IJSETR
V RESULTS AND DISCUSSION
BORON/ALUMINIUM STRESS RESULTS
The stress values of the lamina at different
boundary conditions at different orientations are shown in the Table 2.
Table.2 Stress Result of Boron/Aluminium
BOUNDARY
CONDITIONS 0° 30° 45° 60° 90°
B1 534.77 743.112 791.87 677.146 629.709
B2 11997 15188 13917 12208 11680
B3 857.55 745.174 633.13 544.495 559.941
B4 440.03
1
422.797 441.851 464.87 470.708
BORON/ALUMINIUM DISPLACEMENT RESULTS
The displacements values of the lamina at different boundary conditions at different orientations are
shown in the Table .3
Table. 3 Displacement Result of Boron/Aluminium
BOUNDARY
CONDITIONS 0° 30° 45° 60° 90°
B1 0.084049 .073604 .066993 .062143 .057395
B2 9.935 14.272 16.629 17.525 17.11
B3 .064126 .058969 .048966 .053663 .051065
B4 .020814 .019588 .017661 .015296 .012782
BORON/ALUMINIUM STRESS GRAPHS
Fig.6 Stress graph for the Boundary Condition 1
The stress values of the composite at
different orientation while considering the
boundary condition 1 is shown in figure 6. It is
observed that the while considering boundary
condition 1 stress value is maximum at the fiber orientation of 45 degree and it is very less when the
zero degree orientation is considered [8].
The stress values of the composite at different
orientation while considering the boundary
condition 2 is shown in figure 7. It is observed that
the while considering boundary condition 2 stress
value is maximum at the fiber orientation of 30 and
it is gradually decrease to 60 degree as shown
above.
Fig. 7 Stress graph for the Boundary Condition 2
The stress values of the composite at
different orientation while considering the
boundary condition 3 is shown in figure 8. It is
observed that the while considering boundary
condition 3 stress value is maximum at the fiber orientation of zero degree and is very low at 60 and
again increase in 90 degree orientations.
Fig. 8 Stress graph for the Boundary Condition
3
0
200
400
600
800
1000
STR
ESS
N/m
m2
B1
B1
0
5000
10000
15000
20000
0 d
egre
e
30d
egre
e
45d
egre
e
60d
egre
e
90d
egre
eSTR
ESS
N/m
m2
B2
B2
0200400600800
1000
STR
ESS
N/m
m2
B3
B3
ISSN: 2278 – 7798 International Journal of Science, Engineering and Technology Research (IJSETR)
Volume 5, Issue 5, May 2016
1298 All Rights Reserved © 2016 IJSETR
Fig.9 Stress graph for the Boundary Condition 4
The stress values of the composite at
different orientation while considering the
boundary condition 4 is shown in figure 9. It is
observed that the while considering boundary
condition 4 stress value is maximum at the fiber
orientation of 90 degree and is very low at 30
degree orientation. The safe stress value is 30
degree orientation.
BORON/ALUMINIUM DISPLACEMENT
GRAPHS
Fig.10 Displacement graph for the Boundary
Condition 1
The displacement values of the composite
at different orientation while considering te
boundary condition 1 is shown in figure 10. It is
observed that the while considering boundary
condition 1 displacement value is maximum at the
fiber orientation of 0 and is very low at 90 degrees
orientation. It is observed that the lamina which is
have 0 degree orientation have more displacement
and it able to withstand more time compared to
other orientations.
The displacement values of the composite
at different orientation while considering the boundary condition 2 is shown in figure 11. It is
observed that the while considering boundary
condition 2 displacement value is maximum at the
fiber orientation of 60 degree and is very low at 0
degree orientations. It is observed that the lamina
which is have 60 degree orientation have more
displacement and it able to withstand more time
compared to other orientations.
Figure.11 Displacement graph for the Boundary
Condition 2
Fig. 12 Displacement graph for the Boundary
Condition 3
The displacement values of the composite
at different orientation while considering te
boundary condition 3 is shown in figure 12. It is
observed that the while considering boundary
condition 3 displacement value is maximum at the
fiber orientation of zero degrees and is very low at
45 degree orientation. It is observed that the lamina
which is have zero degree orientation have more
displacement and it able to withstand more time
compared to other orientations.
380400420440460480
STR
ESS
N/m
m2
B4
B4
0
0.02
0.04
0.06
0.08
0.1
DIS
PLA
CEM
ENT
mm
B1
B1
0
5
10
15
20
DIS
PLA
CEM
ENT
mm
B2
B2
0
0.02
0.04
0.06
0.08
DIS
PLA
CEM
ENT
mm
B3
B3
00.005
0.010.015
0.020.025
DIS
PLA
CEM
ENT
mm
B4
B4
ISSN: 2278 – 7798 International Journal of Science, Engineering and Technology Research (IJSETR)
Volume 5, Issue 5, May 2016
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Fig.13 Displacement graph for the Boundary
Condition 4
The displacement values of the composite
at different orientation while considering te
boundary condition 4 is shown in figure 13. It is observed that the while considering boundary
condition 4 displacement value is maximum at the
fiber orientation of 0 and gradually decreased to 30
degree and in other degree orientations it is
gradually decreased as shown above. It is observed
that the lamina which is have 0 degree orientation
have more displacement and it able to withstand
more t4ime compared to other orientations.
SAFE MATERIAL TABULATION
Table. Safe Material Tabulation for
Boron/Aluminium
The analysis results are discussed below.
SAFE MATERIAL FOR BORON AND
ALUMINIUM
Fig. 14 Safe Material for Boundary Condition 1 at zero
Degree
The safe material limit while considering
boundary condition 1 at zero degree is shown in
figure 14. While all the load is applied at all the
directions equally, the material is getting weak at
the center of the lamina and also at the corner of the
lamina as shown in figure 14. The maximum stress
value obtained is 534 N/mm2.
Fig.15 Safe Materials for Boundary Condition 2
at 90 Degree
The safe material limit while considering
boundary condition 2 at 90 degree is shown in
figure 15. While the load is applied at only one
direction equal, the material is getting weaker at the
point of the lamina where it is fixed as shown in
figure 15. The maximum stress value obtained is
11680 N/mm2.
Fig. 16 Safe Material for Boundary Condition 3 at 60 Degree
The safe material limit while considering
boundary condition 3 at 60 degree is shown in
figure 16. While the load is applied at two opposite
directions equally, the material is getting weaker at
the point of the lamina where the load is applied
and also at the center of the lamina as shown in
figure 16. The maximum stress value obtained is
544 N/mm2.
ISSN: 2278 – 7798 International Journal of Science, Engineering and Technology Research (IJSETR)
Volume 5, Issue 5, May 2016
1300 All Rights Reserved © 2016 IJSETR
Fig. 17 Safe Material for Boundary Condition 4 at 30 Degree
The safe material limit while considering
boundary condition 4 at 30 degree is shown in
figure 17. While the load is applied at all directions
equally and all degrees of freedom are constrained,
the material is getting weaker at the point of the
lamina where the load is applied as shown in figure
17. The maximum stress value obtained is 422
N/mm2.
SAFE MATERIAL FOR BORON AND
ALUMINIUM GRAPH
Fig.18 Safe Material Graph for Boundary
Condition 1 at zero Degree
The displacement value when considering
boundary condition 1 at zero degree is shown in
figure 18. From the figure it is observed that the
displacement value is maximum and it is observed
that the lamina can withstand up to stress value of
534 N/mm2.
Fig. 19 Safe Material Graph for Boundary
Condition 2 at 60 Degree
The displacement value when considering
boundary condition 2 at 60 degree is shown in
figure 19. From the figure it is observed that the displacement value is maximum at 0 degree and it
is observed that the stress value of the lamina is
reduced while the displacement is increased and it
can be seen in figure 19.
Fig.20 Safe Material Graph for Boundary
Condition 3 at 60 Degree
The displacement value when considering
boundary condition 3 at 60 degree is shown in
figure 20. From the figure it is observed that as the
displacement value increases it leads to reduction of
stress value. After some time the stress value
increases gradually up to particular point and then
again it decreases. Finally, when the displacement
value increases the stress value is also increased as
shown above.
ISSN: 2278 – 7798 International Journal of Science, Engineering and Technology Research (IJSETR)
Volume 5, Issue 5, May 2016
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Fig.21 Safe Material Graph for Boundary
Condition 4 at 30 Degree
The displacement value when considering
boundary condition 4 at 30 degree is shown in
figure 21. From the figure it is observed that as the
displacement value increases it leads to reduction of
stress value. After some time the stress value
increases gradually upto to particular point and then
again it decreases. Finally, when the displacement
value increases the stress value is also increased as
shown above.
VI CONCLUSION
This experimental analysis of boron/aluminium
based composites using ANSYS leads to the
following conclusions:
Modeling of the composite structure in
ANSYS is possible.
Analysis of the composite at different orientations is possible using ANSYS.
The stress and displacement curves are
obtained are analysed using ANSYS.
It is observed that the stress value is
maximum 15188 N/mm2 while considered
the boundary condition 2 at 30 degree.
Also the stress value is minimum 422
N/mm2 while considered boundary
condition 4 at 30 degree.
It is also observed that displacement value
is maximum 17.525 mm while considered boundary condition 2 at 60 degree.
From the result it is observed that
the orientation at 30 degree with boundary
condition 4 is safe while comparing other
boundary conditions. From this it is
concluded that we can use the safe
orientation for better performance. The
default orientation of material is replaced
by safe orientation are show above results
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