finite element analysis of laminated hybrid · pdf filesimulation software ansys workbench...

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International Journal of Civil Engineering and Technology (IJCIET) Volume 8, Issue 4, April 2017, pp. 916–934 Article ID: IJCIET_08_04_106

Available online at http://www.iaeme.com/IJCIET/issues.asp?JType=IJCIET&VType=8&IType=4

ISSN Print: 0976-6308 and ISSN Online: 0976-6316

© IAEME Publication Scopus Indexed

FINITE ELEMENT ANALYSIS OF LAMINATED

HYBRID COMPOSITE PRESSURE VESSELS

Eswara Kumar. A

Mechanical Engineering Department,

K. L. University, Guntur - 522502, A.P, India.

G R Sanjay Krishna



Shahid Afridi. P



Nagaraju. M


DIET, Ganguru-521139, A.P, India

ABSTRACT

In the present work an attempt has been made to numerically investigate the

response of the hybrid composite material in different load conditions. Here a pressure

vessel made of hybrid composite was chosen and analyzed by using the finite element

simulation software Ansys workbench with ACP module. Two cases of hybrid composite

materials are considered. Each case will contain 8 layers of composite material aligned

in 0 deg direction. In the first case, each 4 layers are considered as one set and in the

second case each two layers are considered as one set. E-glass, S-glass, Kevlar and

graphite fibers with epoxy material were chosen as composite material. Static

structural, free vibration and buckling analysis were performed. In view of these three

analysis best composite combination was recommended.

Key words: Hybrid Composite, Buckling Analysis, Ansys Workbench, ACP, Free

Vibration.

Cite this Article: Eswara Kumar. A, G R Sanjay Krishna, Shahid Afridi. P and

Nagaraju. M, Finite Element Analysis of Laminated Hybrid Composite Pressure

Vessels. International Journal of Civil Engineering and Technology, 8(4), 2017, pp.

916–934.

http://www.iaeme.com/IJCIET/issues.asp?JType=IJCIET&VType=8&IType=4

Eswara Kumar. A, G R Sanjay Krishna, Shahid Afridi. P and Nagaraju. M


1. INTRODUCTION

A composite material is made by combining of two or more distinct materials which are

reinforcement and matrix each of which retains its distinctive properties to create a new

material. From past few decades, most of the aerospace vehicles are using the composite

materials. But these are not satisfying the different load conditions. So from few years onwards

to get better properties in different working conditions, hybrid composites are using. It is

combination of more than one composite layer in view of macro mechanics. In view of micro

mechanics, it contains different fibers. Hybrid composites are more advanced composites as

compared to conventional fiber reinforced polymer composites. They have better flexibility as

compared to other fiber reinforced composites. Normally it contains a high modulus fiber along

with low modulus fiber. The high-modulus fiber provides the stiffness and load bearing

qualities, whereas the low-modulus fiber makes the composite more damage tolerant and keeps

the material cost low. The mechanical properties of a hybrid composite can be varied by

changing volume fraction ratio and stacking sequence of different plies.

Gassan and Bledzki [1] said that coupling methods are used to modify the natural

reinforcing fibers which improve the properties of the composites. Interfacial adhesion of the

fiber is improved due to the reaction of the chemical groups in the coupling agent with polymer.

Rana et al. [2] introduced a new type of low energy and low cost composites having very good

properties which would be more preferable than the costly and high energy reinforcing fiber.

M. Xia, H. Takayanagi, K. Kemmochi [3] developed two methods which are used for the

analysis of the multi-ply cylindrical pipes to detect the deformations and stresses generated

when they are subjected to transverse loading. M. Xia, H. Takayanagi and K. Kemmochi [4]

done analysis on the multi layered filament wound structures and found that the hoop to axial

stresses in every layer are different in cylindrical pressure vessels with different ply

orientation.N. Venkateshwaran [5] found that the analytical tensile properties of hybrid

materials which are estimated by the rule of hybrid composites equation are higher than the

experimental properties.

2. PROBLEM STATEMENT

To study the effect of hybrid composite materials on the pressure vessels in Static Structural,

Pre-Stressed Modal analysis and Eigen value Buckling Analysis point of view.

2.1. Methodology:

Ansys workbench 17.2 which is finite element method simulation software was used to

perform the analysis. A hybrid composite pressure vessel was modelled using Ansys Composite

Pre-Post (ACP) 17.2.

The schematic view of the static structural, pre-stressed and Eigen value buckling were

shown in the figure 1, 2.

Figure 1 Schematic view of the structural & Modal Analysis for hybrid composite pressure vessel in

Ansys Workbench 17.2.

Finite Element Analysis of Laminated Hybrid Composite Pressure Vessels


Figure 2 Schematic view of the structural &Buckling Analysis for hybrid composite pressure vessel

in Ansys Workbench 17.2.

3. PROBLEM MODELLING

3.1. Geometry

The hybrid composite pressure vessel was modelled using finite element simulation software

Ansys workbench 17.2. The Pressure vessel was modelled in such a way that the both ends are

opened [6].

Figure 3 Geometry and Dimensions of Vessel

Figure 4 3D-View of the hybrid composite pressure vessel

The thickness of the pressure vessel is 42.25 mm. This thickness was modelled as 8

composite layers which are aligned in 0 deg direction. Here two cases are considered. In the

first case, four layers are assigned with one composite material and remaining with another

composite material among the considered materials. In the second case, each two layers are

assigned with different composites. The combinations of the two cases are listed in the section

3.1.1



3.1.1. Combinations considered

Case-1

Four layers are considered as one set and assigned with one composite material. Remaining

four layers are considered as another set and assigned with other composites. Based on the

permutations and combinations methods the following combinations are listed.

• 8 layers are E-glass epoxy

• 8 layers are S-glass epoxy

• 8 layers are Kevlar epoxy

• 8 layers are Graphite epoxy

• 4 layers E-glass epoxy+4 layers S-glass epoxy

• 4 layers E-glass epoxy +4 layers Kevlar epoxy

• 4 layers E-glass epoxy +4 layers Graphite epoxy

• 4 layers S-glass epoxy +4 layers E-Glass epoxy

• 4 layers S-glass epoxy +4 layers Kevlar epoxy

• 4 layers S-glass epoxy +4 layers Graphite epoxy

• 4 layers Kevlar epoxy +4 layers E-Glass epoxy

• 4 layers Kevlar epoxy +4 layers S-Glass epoxy

• 4 layers Kevlar epoxy +4 layers Graphite epoxy

• 4 layers Graphite epoxy +4 layers E-Glass epoxy

• 4 layers Graphite epoxy +4 layers S-Glass epoxy

• 4 layers Graphite epoxy +4 layers Kevlar epoxy

Case-2

Each Two layers are considered as one set and assigned with one composite material. Based on

the permutations and combinations methods the following combinations are listed.

1. 2 layers E-glass epoxy +2 layers S-Glass epoxy+ 2 layers Kevlar epoxy+2 layers Graphite

epoxy

2. 2 layers E-glass epoxy +2 layers S-Glass epoxy+ 2 layers Graphite epoxy +2 layers Kevlar

epoxy

3. 2 layers E-glass epoxy +2 layers Kevlar epoxy+ 2 layers Graphite epoxy +2 layers S-Glass

epoxy

4. 2 layers E-glass epoxy +2 layers Kevlar epoxy+ 2 layers S-Glass epoxy+2 layers Graphite

epoxy

5. 2 layers E-glass epoxy +2 layers Graphite epoxy + 2 layers S-Glass epoxy+2 layers Kevlar

epoxy

6. 2 layers E-glass epoxy +2 layers Graphite epoxy + 2 layers Kevlar epoxy +2 layers S-Glass

epoxy

7. 2 layers S-Glass epoxy +2 layers E-glass epoxy +2 layers Kevlar epoxy + 2 layers Graphite

epoxy

8. 2 layers S-Glass epoxy + 2 layers E-glass epoxy +2 layers Graphite epoxy + 2 layers Kevlar

epoxy



9. 2 layers S-Glass epoxy +2 layers Kevlar epoxy + 2 layers E-glass epoxy+2 layers Graphite

epoxy

10. 2 layers S-Glass epoxy +2 layers Kevlar epoxy + 2 layers Graphite epoxy + 2 layers E-glass

epoxy

11. 2 layers S-Glass epoxy + 2 layers Graphite epoxy +2 layers Kevlar epoxy+ 2 layers E-glass

epoxy

12. 2 layers S-Glass epoxy +2 layers Graphite epoxy +2 layers E-glass epoxy+2 layers Kevlar

epoxy

13. 2 layers Kevlar epoxy +2 layers E-glass epoxy +2 layers S-Glass epoxy +2 layers Graphite

epoxy

14. 2 layers Kevlar epoxy +2 layers E-glass epoxy + 2 layers Graphite epoxy +2 layers S-Glass

epoxy

15. 2 layers Kevlar epoxy +2 layers S-Glass epoxy + 2 layers E-glass epoxy +2 layers Graphite

epoxy

16. 2 layers Kevlar epoxy +2 layers S-Glass epoxy + 2 layers Graphite epoxy +2 layers E-glass

epoxy

17. 2 layers Kevlar epoxy +2 layers Graphite epoxy +2 layers E-glass epoxy +2 layers S-Glass

epoxy

18. 2 layers Kevlar epoxy +2 layers Graphite epoxy + 2 layers S-Glass epoxy +2 layers E-glass

epoxy

19. 2 layers Graphite epoxy +2 layers E-glass epoxy +2 layers S-Glass epoxy +2 layers Kevlar

epoxy

20. 2 layers Graphite epoxy +2 layers E-glass epoxy + 2 layers Kevlar epoxy +2 layers S-Glass

epoxy

21. 2 layers Graphite epoxy + 2 layers S-Glass epoxy +2 layers E-glass epoxy +2 layers Kevlar

epoxy

22. 2 layers Graphite epoxy +2 layers S-Glass epoxy + 2 layers Kevlar epoxy +2 layers E-glass

epoxy

23. 2 layers Graphite epoxy +2 layers Kevlar epoxy +2 layers E-glass epoxy +2 layers S-Glass

epoxy

24. 2 layers Graphite epoxy +2 layers Kevlar epoxy +2 layers S-Glass epoxy +2 layers E-glass

epoxy

25. 8 layers are E-glass epoxy

26. 8 layers are S-glass epoxy

27. 8 layers are Kevlar epoxy

28. 8 layers are Graphite epoxy

3.2. Finite Element Meshing

This method is used for converting of the geometrical entities to finite element entities.

Cylindrical coordinate system was assigned for cylinder and spherical coordinate system was

assigned to the ends of the vessel in order to orient the nodes and elements.8 node shell element

was used with layer option.



Figure 5 Meshed View of the Pressure Vessel

3.3. Loads and Boundary Conditions:

Both ends of the pressure vessel were given as cylindrical supports. Inner surface of the

pressure vessel was subjected to a Pressure load of magnitude 50 MPa. The schematic view of

loads was shown in the figure 6.

a) Internal Pressure

b) Cylindrical Supports

Figure 6 Loads & Boundary Conditions

3.4. Material Properties

The composites materials considered for the analysis were listed in the table 1.



Table 1 Material properties

Properties E-Glass S-Glass Kevlar Graphite

Volume Fraction (%) 60 60 60 60

Density (Kg/m3) 2100 2000 1400 1600

Exx(MPa) 45000 55000 76000 145000

Eyy (MPa) 12000 16000 5500 10000

Ezz(MPa) 12000 16000 5500 10000

νxy 0.19 0.28 0.34 0.25

νyz 0.31 0.31 0.31 0.31

νzx 0.30 0.3 0.3 0.25

Gxy (MPa) 5500 7600 2100 4800

Gyz (MPa) 5000 5000 2100 3000

Gzx (MPa) 5500 7600 1500 4800

4. RESULTS AND DISCUSSION

Case-1:

In this all layers are arranged in the 0 deg orientation. As mentioned earlier, four layers are

considered as one set and remaining four layers are considered as another set. Each set was

assigned with different composite materials. For the combinations listed in section 3.1.1. Static

structural, pre-stressed modal analysis and Eigen valve buckling analysis were performed. Best

combination from these three analysis was recommended.

4.1. Static Structural Analysis

4.1.1. Total Deformation

Total Deformation indicates the stiffness of the structure. The variation of the total deformation

w.r.t the various hybrid composite materials in static structural analysis was plotted in the figure

7. In this the deformations are also compared with pure composite materials which are

considered in case 1.

Figure 7 Variation of Total Deformation w.r.t hybrid composite material combination

From the above figure 7 it was observed that among the hybrid materials considered,

combination - e has a lower total deformation of 2.2403 mm. This is higher than combination

- b (All layers S-glass). In view of the hybrid composite material - e has higher stiffness.

0

1

2

3

4

5

6

7

a b c d e f g h i j k l m n o p

To

tal

de

form

ati

on

(m

m)

Hybrid composite material combination



Figure 8 Total deformation of combination - e

The figure 8 shows the schematic view of the total deformation of combination - e. The

maximum deformation was observed in the spherical domes.

4.1.2. Hoop Stress

Hoop stress is the vital component in the pressure vessels. It is also called as circumferential

stress. The variation of the hoop stress w.r.t the different hybrid composites were plotted in the

figure 9.

Figure 9 Variation of the hoop stress w.r.t hybrid composite material combination

From the figure 9, it was observed that the combination - j has lower hoop stresses of 315.5

MPa among the hybrid material considered. The hoop stress of this material is high compared

to pure composite material of S-glass whose combination is b. In view of the hybrid composite

material combination - j will be recommended.

Figure 10 Schematic View of Hoop Stresses, combination -j

The figure 10 shows the schematic view of the hoop stresses generated in combination - j.

The maximum hoop stresses was observed in the cylindrical surface.

0

100

200

300

400

500

600

700

800


Str

ee

ses

(MP

a)




4.2. Pre-stressed Modal Analysis

It is used to find out the natural frequencies of the structure. Generally the natural frequencies

should be higher enough to avoid the resonance. Here pre-stress represents there is some load

acting on the structure. To find out natural frequencies of the structure with load, pre-stresses

modal analysis will be done. Number of natural frequencies of the structure will depends on

the degrees of freedom of the structure. In this work first three mode shapes were considered

for analysing purpose.

4.2.1. Mode-1

The variation of the mode-1 natural frequencies w.r.t the hybrid composite materials were

plotted in the figure 11.

Figure 11 Variation of the mode-1 w.r.t hybrid composite material combination

From the figure 11 it was observed that the combination - j & o has the highest natural

frequency of 212.34 Hz among the hybrid composites considered. It is lower than combination

- b (All layers S-Glass). The figure 12 shows the schematic view of mode -1 for natural

frequency of combination – j.

Figure 12 Schematic View of Mode Shape 1, combination - j

4.2.2. Mode-2



100

150

200

250


Fre

qu

en

cy (

Hz)





From the figure 13 it was observed that among the hybrid materials considered, The

combination – j has the highest natural frequency of 285.54 Hz which is less compared to the

natural frequency of combination - b (All layers S-Glass). So in hybrid composite material

point of view, combination- j was recommended.

The figure 14 shows the schematic view of mode -2 for natural frequency of combination -

j.

Figure 14 Schematic View of Mode Shape 2, combination - j

4.2.3. Mode-3:




From the figure 15 it was observed that among the hybrid material considered, The

combination – j has the highest natural frequency of 285.54 which is less compared to the

natural frequency of combination – b (All layers S-Glass).

170

190

210

230

250

270

290

310


Fre

qu

en

cy (

Hz)


170

190

210

230

250

270

290

310


Fre

qu

en

cy (

Hz)




The figure 16 shows the schematic view of mode -2 for natural frequency of the

combination - j.

Figure16 Schematic View of Mode Shape 3, combination - j

4.3. Buckling Analysis

It is used to find the stability of the structure. The first two buckling modes were analysed for

hybrid composite cylinder.

4.3.1. Buckling load-1

The variation of the Buckling loads -1 w.r.t the hybrid composite materials were plotted in the

figure 17.

Figure 17 Variation of buckling load-1 w.r.t hybrid composite material combination

From the figure 17 it was observed that the combination - o shows the highest buckling

load of 265.585 MPa among the hybrid materials considered. But it is lesser than the pure

graphite composite combination - d. But in hybrid point of view combination – o i.e. 4 layers

graphite and 4 layers S-glass.

The figure 18 shows the schematic view of buckled mode of combination - o .The maximum

load is concentrated at certain zones of the cylinder.

100

150

200

250

300

350


Bu

ckli

ng

Lo

ad

(M

Pa

)




Figure18 Schematic View of Buckling load-1, combination - o


The variation of the Buckling load -2 w.r.t the hybrid composite materials were plotted in the

figure 19.

Figure 19 Variation of buckling load-2w.r.t hybrid composite material combination

From the figure 19 among the Hybrid material considered, it was observed that the

combination - o shows the highest buckling strength of 264.94 MPa. But it is lesser than the

pure graphite composite combination-d. But in hybrid point of view combination - o i.e. 4

layers graphite and 4 layers S-glass.

The figure 20 shows the schematic view of buckled mode of combination - o. The maximum

load is concentrated at certain zones of the cylinder.

Figure 20 Schematic View of Buckling load-2, combination – o

Case 2

In this all the 8 layers are arranged in the 0 deg orientation. As mentioned earlier, every two

layers are considered as one set. Each set was assigned with different composite materials. The

combinations are listed in section 3.1.1. Static structural, pre-stressed modal analysis and Eigen

100

150

200

250

300

350


Bu

ckli

ng

Lo

ad

(M

Pa

)




valve buckling analysis were performed. Best combination from these three analysis was

recommended.

4.4. Static Structural Analysis

4.4.1. Total Deformation

Total Deformation indicates the stiffness of the structure. The variation of the total deformation

w.r.t the various hybrid composite materials in static structural analysis was plotted in the figure

21. In this the deformations are also compared with pure composite materials which are

considered in case 2.

Figure 21 Variation of Total Deformation w.r.t hybrid composite material combination

From the figure 21 it was observed that among the hybrid material considered, The

combination - 19 has a lowest deformation of 2.8374 mm .The deformation of this hybrid

composite is high when compared to pure composite combination - 25 & 26 (All layers E-

glass& All layers S-glass).

The figure 22 shows the schematic view of total deformation of combination number 19.

The maximum deformation is observed at spherical domes.

Figure 22 Total deformation of combination – 19

4.4.2. Hoop Stress

Hoop stress is the vital component in the pressure vessels. It is also called as circumferential

stress. The variation of the hoop stress w.r.t the different hybrid composites were plotted in the

figure 23.

1.82

2.22.42.62.8

33.23.43.63.8

44.24.44.64.8

55.25.45.65.8

6

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28

To

tal

De

form

ati

on

(m

m)

Hybrid composite material combinnation



Figure 23 Variation of the hoop stress w.r.t hybrid composite material combination

From the figure 23 it was observed that the combination - 6 has lower hoop stress of 233.69

MPa among the hybrid composites considered. This hoop stress is even lower than the pure

composite materials.

The figure 24 shows the schematic view of hoop stresses of combination - 6.The stresses

generated are very less in combination - 6.

Figure 24 Schematic View of Hoop Stresses, combination - 6

4.5. Modal Analysis

It is used to find out the natural frequencies of the structure. Generally the natural frequencies

should be higher enough to avoid the resonance. Here pre-stress represents there is some load

acting on the structure. To find out natural frequencies of the structure with load, pre-stresses

modal analysis will be done. Number of natural frequencies of the structure will depends on

the degrees of freedom of the structure. In this work first three mode shapes were considered

for analysing purpose.

4.5.1. Mode-1



100

200

300

400

500

600

700

800

900

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28

Ho

op

Str

ess

es

(MP

a)





From the figure 25 it was observed that the combination - 8 has higher natural frequency of

193.93 Hz among the hybrid composites considered. All hybrid composites have a slight

variation in the natural frequencies of mode-1. The natural frequency of this combination - 8 is

less than combination – 26 &28 (All layers S-Glass & All layers Graphite). In view of hybrid

materials combination 8 was recommended.

The figure 26 shows the schematic view of mode -1 for natural frequency of combination -

8.

Figure 26 Schematic View of Mode Shape 1, combination – 8

4.5.2. Mode-2



130

140

150

160

170

180

190

200

210

220

230

240

250

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28

Fre

qu

en

cy (

Hz)





From the figure 27 it was observed that the combination – 8 has higher natural frequency

of 261.21 Hz among the hybrid composites considered. All hybrid composites have a slight

variation in the natural frequencies of mode-2. The natural frequency of combination - 8 is less

than combination - 26& 28 (All layers S-Glass & All layers Graphite).


combination - 8.

Figure 28 Schematic View of Mode Shape 2, combination – 8

4.5.3. Mode-3




180

210

240

270

300

330

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28

Fre

qu

en

cy (

Hz)


180

210

240

270

300

330

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28

Fre

qu

en

cy (

Hz)




From the figure 29 it was observed that the combination - 8 has higher natural frequency of

261.22 Hz among the hybrid composites considered. All hybrid composites have a slight

variation in the natural frequencies of mode-3. The natural frequency of combination - 8 is less

than pure composite combination -26&28 (All layers S-Glass & All layers Graphite).


combination - 8.

Figure 30 Schematic View of Mode Shape 3, combination - 8

4.6. Buckling Analysis

It is used to find the stability of the structure. The first two buckling modes were analyzed for

hybrid composite cylinder.


The variation of the Buckling loads -1 w.r.t the hybrid composite materials were plotted in the

figure 31.

Figure 31 Variation of the Buckling Load-1 w.r.t hybrid composite material combination

From the figure 31 it was observed that the combination - 19 shows the highest buckling

load of 260.53 MPa among the hybrid materials considered. But it is lesser than the pure

composite combination - 28 (All layers Graphite) In view of the hybrid materials, the

combination - 19 was recommended.

100

150

200

250

300

350

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28

BU

ckli

ng

Lo

ad

(M

Pa

)




The figure 32 shows the schematic view of buckled mode -1 of combination - 19. The

maximum load is concentrated at certain zones of the cylinder.

Figure 32 Schematic View of Buckling mode-1, combination - 19


The variation of the Buckling loads -2 w.r.t hybrid composite materials were plotted in the

figure 33.

Figure 33 Variation of the Buckling Load-2 w.r.t hybrid composite material combination

From the figure 33 it was observed that the combination - 19 shows the highest buckling

strength of 259.985 MPa among the materials considered. But it is lesser than the pure

composite combination-28 (All layers Graphite). In view of the hybrid materials, the

combination -19 was recommended.

The figure 34 shows the schematic view of buckled mode -2 of combination number 19.

The maximum load is concentrated at certain zones of the cylinder.

Figure 34 Schematic View of Buckling mode-2, combination – 19

100

150

200

250

300

350

0 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28

Bu

ckli

ng

Lo

ad

(M

Pa

)




5. CONCLUSION

From the observations of case-1 and case-2, in stiffness point of view composite made up of 4-

layers E-glass and 4-layers s-glass was recommended. In view of stress, composite with 2layers

E-glass+ 2layers graphite + 2layers Kevlar+ 2 layers s-glass was recommended. In view of

natural frequencies, composite with 4 layers s-glass + 4layers graphite was recommended. In

view of buckling 4 layers graphite + 4 layers s glass was recommended. From these

recommendations, each combination will behave in different manner for different analysis. It

is not possible for a hybrid composite if all layers are in 0 deg orientation, to act as best material

for different load conditions.

REFERENCES

[1] Jochen Gassan, Andrzej K. Bledzki, Possibilities for improving the mechanical properties

of jute/epoxy composites by alkali treatment of fibres, Composites Science and Technology

59 (1999) 1303-1309.

[2] A. K. Rana, A. Mandal, B.C. Mitra, R. Jacobson, R. Rowell, A. N. Banerjee, Short Jute

Fiber-Reinforced Polypropylene Composites: Effect of Compatibilizer, Journal of Applied

Polymer Science, Vol. 69, 329-338 (1998).

[3] XIA, M., Takayanagi, H., Kemmochi, K., Analysis of Transverse Loading for Laminated

Cylindrical Pipes, Ministry of International Trade and Industry, 2001.

[4] XIA, M., Takayanagi, H., Kemmochi, K., Analysis of multi layered filament- wound

composite pipes under internal pressure. Composite structures 53(2001) 483-491.

[5] N. Venkateshwaran, A. Elayaperumal, G.K. Sathiya, Prediction of tensile properties of

hybrid-natural fiber composites. Composite part B engineering 43(2).2012.

[6] Amin Paykani, Javad Marzbanrad, Finite element analysis of composite high-pressure

hydrogen storage vessels. J. Mater. Environ. Sci. 4 (1) (2013) 63-74.

[7] AbhijitDeya, GauravChaudharyb, P.L.Choudhuryc, K.M.Pandeyd, Study of Post Buckling

Behavior of Carbon-Epoxy Composite Pressure Vessel Subjected to Hydrostatic Pressure”

IJTEMT; EISSN: 2321-5518; Vol. III, Issue I, Feb 2014 Under Internal Pressure, Ministry

of International Trade and Industry, 2001.

[8] R.Sakthivela, D.Rajendranb Experimental Investigation and Analysis a Mechanical

Properties of Hybrid Polymer Composite Plates, International Journal of Engineering

Trends and Technology (IJETT) – Volume 9 Number 8 - Mar 2014.

[9] Sayan Banerjee, Bhavani V. Sankar, Mechanical properties of hybrid composites using

finite element method based micromechanics, Composites Part B ISSN: 13598368.

[10] Eswara Kumar.A, Nagaraju.M, Static and dynamic analysis of motor cycle wheel designs,

Applied mechanics and materials Vols 813-814 (2015) pp 915-920.

[11] Rakesh Potluri, Eswara Kumar A, Buckling Analysis of ring stiffened hybrid composite

cylinder”, IOP Con. series: Material science and engineering 149 (2016) 012.

[12] Eswara Kumar A, Balakrishna Murthy V, Effect of Shim Percentage on Non-Linear Static

Behavior of Flex Seal of Rocket Nozzle, Materials Today: Proceedings 2(2015) 1427-1434

[13] Eswara Kumar A, Balakrishna Murthy V, Study of Non-Linear Static Behavior of Flex Seal

of Rocket Nozzle by Varying Number of Shims, Materials Today: Proceedings 2 (2015)

1613-1621.

[14] A Eswara Kumar, Naveen Janjanam, Buckling Analysis of composite cylinders subjected

to axial compressive loads, IJERT Vol.4, Issue 04, April-2015.

[15] A. Eswara Kumar, Somanadha Sastry.K, Manideep.K, Dynamic analysis of flex seal of

solid rocket motor nozzle, Materials Today: Proceedings 4/Issue 2PA (2017) pp. 1590-

1597.

[16] A. Eswara Kumar, Rakesh Potluri, M. Naga Raju Finite Element Analysis of Cellular Foam

Core Sandwich Structures, Materials Today: Proceedings 4/Issue 2PA (2017) pp. 2501-

2510.

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