fatigue characterization of laminated composites used in …no.5(2020)/384-399.pdf · 2020. 7....

Journal of Mechanical Engineering Research and Developments ISSN: 1024-1752

CODEN: JERDFO

Vol. 43, No. 5, pp. 384-399

Published Year 2020

384

Fatigue Characterization of Laminated Composites used in

Prosthetic Sockets Manufacturing

Ehab N. Abbas†, Muhsin J. Jweeg‡, Muhannad Al-Waily‡†*

†Ministry of Higher Education and Scientific Research, Studies & Planning & Follow-Up Directorate, Iraq ‡Al-Farahidi University, College of Technical Engineering, Iraq

‡†Department of Mechanical Engineering, Faculty of Engineering, University of Kufa, Iraq

*Corresponding Author Email: [email protected]

ABSTRACT: The below knee Prostheses sockets are subjected to varying loading conditions during the gait cycle.

This will cause a fatigue in the sockets due to the induced tension and compression stresses developed during the

gait cycle. Recently, the using of the laminated composites are widely used in the rehabilitation centers. The

engineer should be based his design on the endurance stress level instead of the allowable stresses which are

higher than the endurance level. The Prosthesis engineer should be given these levels of stresses for safe and

durable product and cheap at the same time. In this work, five types of stacking sequence were chosen based upon

a previous work of the authors. These are arranged (4 perlon+4 glass+ 4 perlon), (4 perlon+4 carbon+4 perlon)

and three mixed samples (3perlon+2 kevlar+2 perlon+2 carbon+3 perlon), (3 perlon+2 kevlar+2 perlon+2

carbon+3 perlon), and (3 perlon+2 kevlar+2 perlon+3 carbon+2 perlon). The matrix which has been proved

effective is the Ortocryl. A comprehensive program of fatigue experiments were achieved to predict the suitable

type of laminate for the socket prostheses manufacturing which can sustain the dynamic fatigue during the gait

cycle in addition to the finite element modeling. The experimental results have a good agreement with those

obtained using the Finite Element Method with a maximum discrepancy not exceed 12%. It was found that the

sample No. 2 has the maximum decay factor = −2.706 with a maximum number of cycles up to failure =

21.35 × 105 cycle for the constant amplitude test and the damage factor in the variable amplitude test is increased

with the increasing the number of cycles at each test. The obtained results indicate that they can be used or

manufacturing the socket prostheses depending upon the required sustainability, age of the patient and the daily

work type.

KEYWORDS: Fatigue, composites, amplitude stress, Sockets, prostheses.

INTRODUCTION

The laminated composite materials are widely used in socket prostheses manufacturing in rehabilitation centers

of people of special needs. The reason behind it is the high strength/weight ratio, comfort and reliable to be used

in this respect. The amputees may suffer a dynamic loading through the gait cycle. Recently, this subject was

deeply studied by many researchers [1-5]. The fatigue is considered one of the main sources of failure of the

sockets which create unreliable wearing and causes a socket failure in addition to the cost required to be replaced.

M.J. Jweeg et al. [6] carried out an experimental investigation of the fatigue of fiber glass with polyster resin

taking into consideration the reversal bending loading. The results have shown that the composites fail under

different damages due to the delamination caused by shear and fatigue loading. K.R. Al-Rawi et al. [7] dealt with

the fatigue of three layers glass and Kevlar woven roving [00 – 900] using the epoxy matrix. They concluded that

the reinforcement has increased the fatigue strength of the composites. The side of the glass fibers has shown a

more fatigue strength compared to the Kevlar side. A.M.A. Al-Nassrawi [8] investigated the characterization of

fatigue behavior of PEEK matrix composites and studying the effects of notched created due to fatigue and their

effects on fatigue strength of materials taking into consideration the temperature effects. The research was

conducted experimentally and numerically using the finite element technique.

A.A. Al-Assadi [9] entered the effects of high-low and low-high cycle fatigue on rubber materials in addition to

the constant amplitude tests. He derived the life of the rubber materials formula for prediction the number of

cycles up to failure and concluded that the variable amplitude testing is important in defining the rubber life and

385

Fatigue Characterization of Laminated Composites used in Prosthetic Sockets Manufacturing

should be considered. E.K. Gamstedt et al. [10] investigated the fatigue behavior of glass fibers reinforced

polypropylene. The results indicated that the young’s modulus degrades for materials glass fibers/polypropylene

due to fatigue effects. W. Hawang and K.S. Han [11] investigated the cumulative damage due to fatigue high-low

and low-high cycle fatigue and suggested three models which are fatigue mode I and the resultant strain modes II

and III. They concluded that the stress resultant could be employed to define cumulative damage models and the

fatigue damage can be predicted with the stress – number of cycles curve (S-N). The also reached to conclusion

that the cumulative damage model can give an explanation to the multi stress state and the number of cycles up

to failure.

L.M. Andre et al. [12] studied the fatigue damage loading due flexion and the effects of stress amplitude on the

accumulative damage at room temperature. They compared their results with Minor’s fatigue life. They concluded

that the damage factor may be more than unity. H. Mao and S. Mahadevan [13] conducted a work related to the

fatigue of composite materials and the mechanisms of the induced damage . They proposed a mathematical model

based upon the experimental results. They concluded that the growth of the damage passes through stages, stage

I, the damage grows rapidly due to multi types of damages, stage II, the damage grows steadily and the third stage

III. The damage again grows fast due to the fibre fracture which reduces the fatigue strength. W.V. Paepegem and

J. Degrieck, [14] investigated the fatigue characteristics of plain woven glass/epoxy. An experimental program

and a numerical solution were employed in this work. The samples [# 00 ] and [# 450 ] were prepared using the

bending fatigue experiments. It was found that there is a degradation of the stiffness due to fatigue effects. They

reached to a useful model for the composite materials fatigue characterization.

This work aims to refill the research gaps in the fatigue characterization of laminates used for the prostheses socket

manufacturing for people of special needs. It is an extension of a previous work for the authors [15] related to a

mechanical properties finding specially used in rehabilitation centers to modify their life and durability and

reliability of these types of structures in which the fatigue is not well understood yet.

FINITE ELEMENT MODELING

The finite element technique was used to calculate the fatigue behavior for composite laminate materials, [16-21].

These, the behavior calculated included evaluated the stress-number of cycle relation for composite materials. In

addition, the numerical results evaluated comparison with experimental results will calculating, [22-27]. There,

the Ansys 14 software was used using the general procedure and defining the geometry and material properties,

[28-31]. The modulus of elasticity, poison’s ratio, ultimate stress, amplitude stress, will be calculated in the

experimental work, [32-36]. In addition to the support conditions and the loading causing the cyclic behavior of

the sample in order to obtain the numerical S-N curve, [37-40]. The model to be tested experimentally is drawn

by using solid work software as shown in Fig. 1, and supported as shown in Fig. 2. The solid 45 brick element 8

nodes was used for modeling the tested sheets, as shown in Fig. 3. The total number of nodes is (1148522) and

the total number of elements is (269110) required for the solution convergence, according to use mesh generation,

[41-46], and the fatigue samples with its selected mesh given in Fig. 4.

Figure 1. Fatigue sample dimensions.

386


Figure 2. Fixed fatigue sample.

Figure 3. Solid brick element.

Figure 4. Mesh fatigue sample.

THEORETICAL ANALYSIS

In fatigue analysis, the stress amplitude is given by,

σa =(σmax−σmin)

2 (1)

Where, σa, σmax, σmin are the stress amplitude, maximum stress and minimum stress for a complete fatigue cycle,

as shown in Figure 5.

387


Figure 5. Stress for a Complete Fatigue Cycle.

The relation between the stress amplitude σa and the number of cycle Nf is given by, [6],

σa = K. Nfm (2)

Where, K and m are constants.

They are found empirically based upon the experimental results according to Miner’s,

∑ni

Nf

ri=1 = D (3)

Where, n is the number of cycles and D is the damage factor and r is the number of loading turns. Using the

formula derived by,

χi =Nf(σi−σL)

(σH−σL) (4)

Where, σH, σL are the maximum and minimum stresses for the variable amplitude stress and χ is the number of

cycles up to failure under constant amplitude stress, σi and,

D = (n

Nf(σH)+

n

Nf(σL)) χ (5)

EXPERIMENTAL PROGRAM AND RESULTS

The work is concentrated on the types of laminates composite materials used in manufacturing the prostheses for

people of special needs. They are chosen from previous work of the authors. The fatigue specimens were cut

according to the machine fatigue sample, [47-53], as show in Figs. 6 and 7. The testing will be achieved for

constant and variable amplitude in order to estimate the life of the material in order to be taken into consideration

in designing the prostheses for the amputees, [54-60]. The types of the specimens and the stacking sequence are

shown in Table 1, [15]. Ten specimens testing to calculate the fatigue behavior for samples, [61-66].

Figure 6. Fatigue specimens.

388


Figure 7. Fatigue test machine.

Table 1. Fatigue test specimens.

No. Laminate stacking sequence σult (MPa) E (GPa) G (GPa) ν

1 (4) Perlon+(4) Glass Fiber+(4) Perlon 98.8 25.4 10.08 0.26

2 (4) Perlon+(4) Carbon Fiber+(4) Perlon 124.7 25.6 10 0.28

3 (3) Perlon+(2) Kevlar Fiber+(2)

Perlon+(2) Glass Fiber+(3) Perlon 118.3 31.5 12.12 0.3

4 (3) Perlon+(2) Carbon Fiber+(2)

Perlon+(2) Glass Fiber+(3) Perlon 95.3 24.6 9.5 0.29

5 (3) Perlon+(2) Kevlar Fiber+(2)

Perlon+(2) Carbon Fiber+(3) Perlon 102.3 26.3 10.35 0.27

The experimental results are divided into two types:

1. Constant amplitude test.

2. Variable amplitude test.

For sample No. 1, the laminate is manufacture as shown in Table 1 and tested using the constant amplitude for

each test. Ten specimens were decided from the previous work. The results of the constant amplitude used with

the number of cycles up to failure is shown in Table 2. The amplitude versus the number of cycle is shown in

Figure 8. In addition, the finite element results are added on the same figure.

Table 2. Results of the constant amplitude for the laminate ((4) Perlon+(4) Glass Fiber+(4) Perlon).

No. Constant amplitude (MPa) No. of cycles Nf

1 25.8 4.3 × 105

2 21.8 4.9 × 105

3 15.6 5.31 × 105

4 12.5 5.7 × 105

5 9.6 7.2 × 105

6 7.2 8.8 × 105

7 4.8 10.35 × 105

8 3.5 12.35 × 105

9 2.4 15.4 × 105

10 1.68 16.8 × 105

389


Figure 8. Experimental and Numerical Results for Stress σa with Number of cycle Nf for the laminate No. 1.

Using the curve fitting formula, the equation that fit the experimental results is, σa = K. Nfm, Where, K =

1 × 1012, m = −1.897. The variable amplitude fatigue test by choosing two cases, Low-High and High-Low to

show the effectiveness of the variable amplitude stress are shown in Table 3.

Table 3. Vairable amplitude fatigue for the laminate ((4) Perlon+(4) Glass Fiber+(4) Perlon).

No.

Amplitude fatigue

Low-High High-Low

σa (MPa) Nf No. of Cycles. χ D σa (MPa) Nf No. of Cycles. χ D

1 1.68 4.6 × 106 23 1.11 25.8 3.8 × 106 19 1.08

2 5.7 4.8 × 106 24 1.12 19.4 4.01 × 106 20 1.13

3 10.2 4.5 × 106 22 1.09 14.8 3.62 × 106 18 0.99

4 14.8 3.98 × 106 20 1.03 10.2 3.3 × 106 17 0.97

5 19.4 3.2 × 106 16 0.98 14.8 3.8 × 106 19 1.08

6 25.8 4.23 × 106 21 1.07 1.68 3.92 × 106 20 1.12

For sample No. 2, the stacking sequence together with the material properties are shown in Table 1. The results

of the amplitude with the number of cycles are shown in Table 4 and the plots of the experimental and the

numerical results are shown in Figure 9.

Table 4. Results of constant amplitude for the laminate ((4) Perlon+(4) Carbon Fiber+(4) Perlon).

No. Constant stress σa amplitude (MPa) No. of cycles Nf

1 32.35 5.95 × 105

2 25.84 6.42 × 105

3 19.71 7.86 × 105

4 17.47 8.23 × 105

𝜎1 = 25.8 𝑀𝑃𝑎

𝜎2 = 1.68 𝑀𝑃𝑎

𝑛 = 104 𝑛 = 104

𝜎2 = 1.68 𝑀𝑃𝑎

𝑛 = 104

𝜎1 = 25.8 𝑀𝑃𝑎

𝑛⬚ = 104

390


5 12.65 9.07 × 105

6 8.4 11.26 × 105

7 5.72 13.03 × 105

8 3.5 15.62 × 105

9 1.8 19.25 × 105

10 0.504 21.35 × 105



2 × 1017, m = −2.706. The variable stress amplitude σa for Low-High and High-Low are shown in Table 5.

Table 5. Amplitude fatigue for the laminate ((4) Perlon+(4) Carbon Fiber+(4) Perlon).

No.

Amplitude fatigue

Low-High High-Low


1 0.504 6.82 × 105 35 1.05 32.35 5.62 × 105 29 1.03

2 8.48 6.45 × 105 33 1.03 29.19 5.83 × 105 30 1.03

3 15.10 5.98 × 105 29 0.97 21.93 4.98 × 105 24 0.96

4 21.93 7.03 × 105 38 1.09 15.10 4.88 × 105 24 0.98

5 29.19 6.92 × 105 36 1.08 8.48 5.23 × 105 26 0.99

6 32.35 6.4 × 105 31 0.99 0.504 6.03 × 105 33 1.1

For sample No. 3, laminate ((3) Perlon+(2) Kevlar Fiber+(2) Perlon+(2) Glass Fiber+(3) Perlon). The results of

the constant amplitude is shown in Table 6. The σa amplitude values against the number of cycles are shown in

Fig. 10 together with the numerical results.

𝜎1 = 32.35 𝑀𝑃𝑎

𝜎2 = 0. 504𝑀𝑃𝑎

𝑛 = 104 𝑛 = 104

𝜎2 = 0.504𝑀𝑃𝑎

𝑛 = 104

𝜎1 = 32.35 𝑀𝑃𝑎

𝑛 = 104

391


Table 6. Results of the constant amplitude fatigue test.

No. Constant amplitude σa (MPa) No. of cycles Nf

1 27.98 4.5 × 105

2 21.72 5.38 × 105

3 17.16 5.91 × 105

4 12.64 6.61 × 105

5 9.97 8.45 × 105

6 6.35 10.3 × 105

7 5.13 12 × 105

8 4.67 14.33 × 105

9 3.42 17.86 × 105

10 2.33 19.48 × 105


The equation that describes the constant amplitude fatigue test is obtained by curve fitting as follows, σa = K. Nfm,

Where, K = 3 × 1010, m = −1.595. The variable amplitude tests are, Low-High and High-Low fatigue test and

the results are shown in Table 7.

Table 7. Amplitude fatigue for the laminate No.3.

No.

Amplitude fatigue

Low-High High-Low


1 2.33 5.8 × 106 28 0.97 27.98 5.12 × 106 28 1.09

2 5.1 5.64 × 106 27 0.96 21.41 4.83 × 106 23 0.96

3 11.87 6.81 × 106 38 1.12 16.64 5.65 × 106 32 1.13

4 16.64 6.4 × 106 32 1.00 11.87 5.2 × 106 29 1.11

𝜎1 = 27.98 𝑀𝑃𝑎

𝜎2 = 2.33 𝑀𝑃𝑎

𝑛 = 104 𝑛 = 104

𝜎2 = 27.98 𝑀𝑃𝑎

𝑛 = 104

𝜎1 = 2.33 𝑀𝑃𝑎

𝑛 = 104

392


5 21.41 6.93 × 106 39 1.12 5.1 4.98 × 106 24 0.96

6 27.98 6.45 × 106 33 1.03 2.33 4.63 × 106 25 1.08


each test. The results of the amplitude used with the number of cycles up to failure is shown in Table 8. The

constant amplitude versus the number of cycle is shown in Fig. 11 together with the numerical results.

Table 8. Results of the constant amplitude for the laminate No. 4.


1 24.8 5.95 × 105

2 21.16 6.98 × 105

3 18.52 7.32 × 105

4 15.98 7.62 × 105

5 12.98 8.82 × 105

6 9.35 10.27 × 105

7 6.98 11.98 × 105

8 3.532 14.5 × 105

9 2.4 17.87 × 105

10 1.58 19.42 × 105



8 × 1014, m = −2.327. The variable amplitude fatigue test by choosing two cases, low-high and high-low to


Table 9. Amplitude fatigue for the laminate No. 4.

No. Amplitude fatigue

Low-High High-Low

393



1 1.58 5.7 × 105 29 1.01 24.8 4.52 × 105 23 1.02

2 4.38 5.35 × 105 27 1.02 19.68 4.73 × 105 25 1.06

3 9.46 4.98 × 105 24 0.96 14.54 4.14 × 105 19 0.93

4 14.54 6.01 × 105 34 1.13 9.46 4.2 × 105 19 0.9

5 19.68 5.98 × 105 32 1.07 4.38 4.48 × 105 21 0.94

6 24.8 5.3 × 105 25 0.94 1.58 5.32 × 105 30 1.13


each test. The results of the amplitude used with the number of cycles up to failure is shown in Table 10. The

constant amplitude versus the number of cycle is shown in Fig. 12. The numerical results were also plotted on the

same figure.

Table 10. Results of the constant amplitude for the laminate No. 5.


1 28.6 4.9 × 105

2 25.82 5.62 × 105

3 22.42 6.35 × 105

4 19.63 7.3 × 105

5 16.16 8.28 × 105

6 13.48 9.35 × 105

7 10.12 11.86 × 105

8 7.06 14.34 × 105

9 5.53 16.83 × 105

10 3.48 17.35 × 105


𝜎1 = 4.98 𝑀𝑃𝑎

𝜎2 = 0.24 𝑀𝑃𝑎

𝑛⬚ = 104 𝑛 = 104

𝜎2 = 0.24 𝑀𝑃𝑎

𝑛 = 104

𝜎1 = 4.98 𝑀𝑃𝑎

𝑛 = 104

394



1 × 1010, m = −1.518. The variable amplitude fatigue test by choosing two cases, low-high and high-low to


Table 11. Amplitude fatigue for the laminate No. 5.

No.

Amplitude fatigue

Low-High High-Low


1 3.48 6.2 × 105 34 1.09 28.6 3.92 × 105 21 1.08

2 8.28 7.1 × 105 40 1.13 23.78 4.1 × 105 23 1.12

3 13.01 5.2 × 105 27 1.04 18.92 4.6 × 105 27 1.14

4 18.92 4.9 × 105 23 0.94 13.01 3.6 × 105 17 0.94

5 23.78 3.2 × 105 16 0.93 8.28 3.4 × 105 15 0.88

6 28.6 4.96 × 105 24 0.97 3.48 3.1 × 105 13 0.84

DISCUSSION OF RESULTS

The presented experimental and finite element technique to estimate the life of the materials to be used specifically

for manufacturing the prosthetic sockets. This a part of the research work deals with the fatigue characterization

to prostheses materials to sustain the dynamic loading facing the patient during the gait cycle. Five types of

materials tested by E.N. Abbas et al. [15] were chosen for testing in this work. The materials were tested

experimentally using two types of loading systems, constant amplitude and variable amplitude schemes in order

to obtain results approximately similar to the real life results.

The first set of specimens (4 layers of perlon + 4 layers of fiber glass and 4 perlon layers). The constant amplitude

results are shown in Fig. 8 together with the finite element result. They have shown a good agreement with a

discrepancy less than 12%. The suggested experimental model is shown on Fig. 8 with K = 1 × 1012 and m =

−1.897. The minus sign indicates that the life is increased with the amplitude decreasing which is compatible

with the logic of material behavior. The number of cycles to failure was 16.8*105 cycle. For using the variable

amplitude stress shown in Table 3 indicates that the number of cycles to failure in case of Low- High cycle is

higher than those obtained from High–Low regime with maximum numbers of cycles = 4.6 × 106, 3.8 × 106,

respectively. The results for the damage indicates that the expected life is increasing with the increase the damage

factor D obtained by using Eq. (2). This is illustrated in Table 3.

The sample No. 2 is composed of (4 perlon layers + 4 carbon fiber layers + 4 perlon layers). The number of cycles

obtained against the constant amplitude model results in K = 2 × 1017, m = −2.706 as shown in Fig. 9 and Table

4 which has a similar behavior for the specimen No.1. Using the variable amplitude test, Table 5, it was found

that the maximum number of cycles to failure is equal to 7.03 × 105 with a damage factor equal to 1.09 using

Low–High scheme compared to 6.03 × 105 cycle in High–Low with a damage factor equal to 1.1. For the sample

No. 3 in which the laminate is composed of Kevlar fibers in addition to fiber glass fibers, a noticeable number of

cycles to failure is obtained as shown in Table 6 and Fig. 10. For constant amplitude test as shown in Table 7, the

maximum number of cycles reached 19.48 × 105 cycle and in using the Low-High test the number of cycles to

failure is equal to 6.93 × 106 with a damage factor D = 1.03 and in High–Low test the number of cycles to failure

is equal to 5.102 × 106 with a damage factor D = 1.09. The index for the decay in the number of cycles in

constant test indicate high rate (−2.327) and the corresponding number of cycles up to failure reaches

𝜎1 = 28.6 𝑀𝑃𝑎

𝜎2 = 3.48 𝑀𝑃𝑎

𝑛 = 105 𝑛 = 105

𝜎2 = 3.48 𝑀𝑃𝑎

𝑛 = 105

𝜎1 = 28.6 𝑀𝑃𝑎

𝑛 = 105

395


19.42 × 105 compared to the other samples which may be recommended for socket manufacturing.

For the sample No. 4 in which the laminate is composed of carbon fibers in addition to kevlar fibers, the maximum

number of cycles reached 19.42 × 105 cycle for a constant amplitude test shown in Table 8 and Fig. 11 and in

using the Low-High test the number of cycles to failure is equal to 6.01 × 106 with a damage factor D = 1.13

and in High–Low test the number of cycles to failure is equal to 5.3 × 106 with a damage factor D = 1.13 as

shown in Table 9. For the laminate (specimen No. 5) (3 perlon + 2 kevlar + 2 perlon + 2 carbon + 3 perlon) layers

the maximum number of cycles to failure for constant amplitude test is 17.35 × 105 as shown in Fig. 12 and

Table 10. For the variable test amplitude as shown in Table 11, the maximum number of cycles to failure is

7.1 × 105 with a damage factor D = 1.13, and 4.6 × 105 for a damage factor D = 1.14 for the tests respectively

Low – High and High – Low tests respectively. The number of cycles to failure is used as an indication to the

stiffness degradation. The fatigue failure causes initiation of cracks in the sockets prostheses due to the increasing

the number of cycles beyond the fatigue strength for a typical laminate. The determination of the endurance of the

laminate before manufacturing the sockets, therefore, this work is considered as a guide for the Prostheses

engineers.

CONCLUSION

The research conducted here deals with the determination of the endurance limits for the materials used for

manufacturing the prostheses sockets. The results may be used to avoid the failure of sockets and get rid of the

stiffness degradation due to unexpected loading faces the patient during the gait cycle by using the models

suggested in this work with the corresponding the number of cycles up to failure according to the age and the

activity of the patient during the normal daily work. The results of the constant amplitude with the number of

cycles for all the samples have a good agreement with those obtained numerically using the finite element method.

It was noticed that using the variable stress amplitude Low - High, the number of cycles are higher than those

obtained for the case High – Low. The damage factor was also increased as the number of cycles up to failure is

increased.

REFERENCES

[1] M.J. Jweeg, A.A. Ahumdany, and A.F.M. Jawad, “Dynamic Stresses and Deformations Investigation of the

Below Knee Prosthesis using CT-Scan Modeling,” International Journal of Mechanical & Mechatronics

Engineering, Vol. 19, No. 1, 2019.

[2] M.J. Jweeg, A.A. Alhumandy, and H.A. Hamzah, “Material Characterization and Stress Analysis of

Openings in Syme’s Prosthetics,” International Journal of Mechanical & Mechatronics Engineering, Vol.

17, No. 04, 2017.

[3] M.J. Jweeg, and S.H. Ameen, “Experimental and theoretical investigations of dorsiflexion angle and life of

an ankle-Foot-Orthosis made from (Perlon-carbon fibre-acrylic) and polypropylene materials,” 10th IMEKO

TC15 Youth Symposium on Experimental Solid Mechanics, 2011.

[4] M.J. Jweeg, Z.S. Hammoudi, and B.A. Alwan, “Optimised Analysis, Design, and Fabrication of Trans-Tibial

Prosthetic Sockets,” IOP Conference Series: Materials Science and Engineering, 2nd International

Conference on Engineering Sciences, Vol. 433, 2018.

[5] M.J. Jweeg, M. Al-Waily, A.K. Muhammad, and K.K. Resan, “Effects of Temperature on the

Characterisation of a New Design for a Non-Articulated Prosthetic Foot,” IOP Conference Series: Materials

Science and Engineering, 2nd International Conference on Engineering Sciences, Kerbala, Iraq, Vol. 433,

Pp. 26–27, 2018.

[6] M.J. Jweeg, A.H. Al-Hilli, and H.M. Sukar, “Experimental Study of Characteristics of Laminated Composite

Plates,” Journal of Engineering, Al-Nahrain University, Vol. 16, No. 2, Pp. 5185-5198, 2010.

[7] K.R. Al-Rawi, H.I. Jaafar, and H.W. Abdullah, “The Study of Fatigue Behavior of Epoxy Composites

Reinforced by Glass and Kevlar Fibers,” Journal of Deyala University, Vol. 3, No. 3, Pp. 120-132, 2012.

http://iopscience.iop.org/journal/1757-899Xhttp://iopscience.iop.org/journal/1757-899X

396


[8] A.M.A. Al- Nassrawi, “Characterization of Fatigue Behavior of PEEK Matrix Materials,” University of

Babylon, College of Materials, 2015.

[9] A. A. Al-Asadi, “Study of Mechanical Properties of Rubber Under Constant and Variable Stress amplitudes,”

Ph.D. Thesis, University of technology, Iraq, 2008.

[10] E.K. Gamstedt, L.A. Berglund, and T. Peijs, “Studying Fatigue Mechanisms in Unidirectional Glass-Fiber-

Reinforced Polypropylene,” University of Technology, Vol. 59, No. 5, Pp. 759-708, 1999.

[11] W. Hawang, and K.S. Han, “Cumulative Damage Models and Multi stress Fatigue Life Prediction,”

Pennsylvania University State, 2016.

[12] A.L.M. Carvalhoa, J.P. Martins, and H.J.C. Voorlwad, “Fatigue damage accumulation in aluminum 7050-

T7451 alloy subjected to block programs loading under step-down sequence,” Procedia Engineering, Vol.

2, Fatigue, Pp. 2037-2043, 2010.

[13] H. Mao, and S. Mahadevan, “Fatigue damage modelling of composite materials,” Composite Structures,

Vol. 58, Pp. 405–410, 2002.

[14] W.V. Paepegem, and J. Degrieck, “Numerical Modeling of Bending Fatigue Experiments on Plain Woven

Glass Epoxy Composites,” Composite Structures, Vol. 51, No. 1, Pp. 1-8, 1995.

[15] E.N. Abbas, M.L. Al-Waily, T.M. Hammza, and M.J. Jweeg, “An Investigation to the Effects of Impact

Strength on Laminated Nothed Composites Used in Prosthetic Sockets Manufacturing,” Sent to Publication

in Journal Periodicals of Engineering and Natural Sciences, 2020.

[16] M.J. Jweeg, “Application of finite element analysis to rotating fan impellers,” Doctoral Thesis, Aston

University, 1983.

[17] M. Al-Waily, M.A.R. Sadiq Al-Baghdadi, and R.H. Al-Khayat, “Flow Velocity and Crack Angle Effect on

Vibration and Flow Characterization for Pipe Induce Vibration,” International Journal of Mechanical &

Mechatronics Engineering, Vol. 17, No. 05, Pp.19-27, 2017.

[18] R.H. Al-Khayat, M.A.R. Sadiq Al-Baghdadi, R.A. Neama, and M. Al-Waily, “Optimization CFD Study of

Erosion in 3D Elbow During Transportation of Crude Oil Contaminated with Sand Particles,” International

Journal of Engineering & Technology, Vol. 07, No. 03, Pp. 1420-1428, 2018.

[19] M.A. Al-Shammari, L.Y. Zedan, and A.M. Al-Shammari, “FE simulation of multi-stage cold forging process

for metal shell of spark plug manufacturing,” 1st International Scientific Conference of Engineering

Sciences-3rd Scientific Conference of Engineering Science, ISCES 2018–Proceedings, 2018.

[20] R.A. Neama, M.A.R. Sadiq Al-Baghdadi, and M. Al-Waily, “Effect of Blank Holder Force and Punch

Number on the Forming Behavior of Conventional Dies,” International Journal of Mechanical &

Mechatronics Engineering, Vol. 18, No. 04, 2018.

[21] M. Al-Waily, E.Q. Hussein, and N.A. Aziz Al-Roubaiee, “Numerical Modeling for Mechanical

Characteristics Study of Different Materials Artificial Hip Joint with Inclination and Gait Cycle Angle

Effect,” Journal of Mechanical Engineering Research & Developments, Vol. 42, No. 04, Pp. 79-93, 2019.

[22] M.J. Jweeg, A.S. Hammood, and M. Al-Waily, “Experimental and Theoretical Studies of Mechanical

Properties for Reinforcement Fiber Types of Composite Materials,” International Journal of Mechanical &


[23] M.A. Al-Shammari, and M. Al-Waily, “Theoretical and Numerical Vibration Investigation Study of

Orthotropic Hyper Composite Plate Structure,” International Journal of Mechanical & Mechatronics


https://research.aston.ac.uk/portal/en/organisations/aston-university(a4a3d3f0-941e-4b15-a631-9a45ca5ad360).htmlhttps://research.aston.ac.uk/portal/en/organisations/aston-university(a4a3d3f0-941e-4b15-a631-9a45ca5ad360).html

397


[24] M.J. Jweeg, M. Al-Waily, and A.A. Deli, “Theoretical and Numerical Investigation of Buckling of

Orthotropic Hyper Composite Plates,” International Journal of Mechanical & Mechatronics Engineering,

Vol. 15, No. 4, 2015.

[25] A.A. Alhumdany, M. Al-Waily, and M.H.K. Al-Jabery, “Theoretical and Experimental Investigation of

Using Date Palm Nuts Powder into Mechanical Properties and Fundamental Natural Frequencies of Hyper

Composite Plate,” International Journal of Mechanical & Mechatronics Engineering, Vol. 16, No. 1, 2016.

[26] E.N. Abbas, M.J. Jweeg, and M. Al-Waily, “Analytical and Numerical Investigations for Dynamic Response

of Composite Plates Under Various Dynamic Loading with the Influence of Carbon Multi-Wall Tube Nano

Materials,” International Journal of Mechanical & Mechatronics Engineering, Vol. 18, No. 6, pp. 1-10,

2018.

[27] H.J. Abbas, M.J. Jweeg, M. Al-Waily, and AA. Diwan, “Experimental Testing and Theoretical Prediction

of Fiber Optical Cable for Fault Detection and Identification,” Journal of Engineering and Applied Sciences,

Vol. 14, No. 2, Pp. 430-438, 2019.

[28] N.A. Mahmood, M.J. Jweeg, and M.Y. Rajab, “Investigation of partially pressurized thick cylindrical

shells,” Modelling, simulation & control. B. AMSE Press, Vol. 25, No. 03, Pp. 47-64, 1989.

[29] M.M. Abdulridha, N.D. Fahad, M. Al-Waily, and K.K. Resan, “Rubber Creep Behavior Investigation with

Multi Wall Tube Carbon Nano Particle Material Effect,” International Journal of Mechanical Engineering

and Technology, Vol. 9, No. 12, Pp. 729-746, 2018.

[30] M.J. Jweeg, K.K. Resan, E.A. Abbod, and M. Al-Waily, “Dissimilar Aluminium Alloys Welding by Friction

Stir Processing and Reverse Rotation Friction Stir Processing,” IOP Conference Series: Materials Science

and Engineering, International Conference on Materials Engineering and Science, Istanbul, Turkey, 8

August, Vol. 454, 2018.

[31] M.R. Ismail, Z.A.A.A. Ali, and M. Al-Waily, “Delamination Damage Effect on Buckling Behavior of

Woven Reinforcement Composite Materials Plate,” International Journal of Mechanical & Mechatronics

Engineering, Vol. 18, No. 05, Pp. 83-93, 2018.

[32] M.J. Jweeg, S.Z. Said, “Effect of rotational and geometric stiffness matrices on dynamic stresses and

deformations of rotating blades,” Journal of the Institution of Engineers (India): Mechanical Engineering

Division, Vol. 76, Pp. 29-38, 1995.

[33] M. Al-Waily, A.A. Deli, A.D. Al-Mawash, and Z.A.A.A. Ali, “Effect of Natural Sisal Fiber Reinforcement

on the Composite Plate Buckling Behavior,” International Journal of Mechanical & Mechatronics


[34] K.K. Resan, A.A. Alasadi, M. Al-Waily, and M.J. Jweeg, “Influence of Temperature on Fatigue Life for

Friction Stir Welding of Aluminum Alloy Materials,” International Journal of Mechanical & Mechatronics


[35] W. Hussein, and M.A. Al-Shammari, “Fatigue and Fracture Behaviours of FSW and FSP Joints of AA5083-

H111 Aluminium Alloy,” IOP Conference Series: Materials Science and Engineering, International

Conference on Materials Engineering and Science, Vol. 454, 2018.

[36] Y.J. Mahboba, and M.A. Al-Shammari, “Enhancing wear rate of high-density polyethylene (HDPE) by

adding ceramic particles to propose an option for artificial hip joint liner,” IOP Conference Series: Materials

Science and Engineering, ICMSMT, Vol. 561, 2019.

[37] M.J. Jweeg, K.K. Resan, and M.T. Ismail, “Study of Creep-Fatigue Interaction in a Prosthetic Socket Below

Knee,” ASME International Mechanical Engineering Congress and Exposition, 2012.

http://iopscience.iop.org/journal/1757-899Xhttp://iopscience.iop.org/journal/1757-899X

398


[38] A.A. Kadhim, M. Al-Waily, Z.A.A.A. Ali, M.J. Jweeg, and K.K. Resan, “Improvement Fatigue Life and

Strength of Isotropic Hyper Composite Materials by Reinforcement with Different Powder Materials,”

International Journal of Mechanical & Mechatronics Engineering, Vol. 18, No. 2, 2018.

[39] A.K. Abdulameer, and M.A. Al-Shammari, “Fatigue Analysis of Syme’s Prosthesis,” International Review

of Mechanical Engineering, Vol. 12, No. 3, 2018.

[40] S.M. Abbas, K.K. Resan, A.K. Muhammad, and M. Al-Waily, “Mechanical and Fatigue Behaviors of

Prosthetic for Partial Foot Amputation with Various Composite Materials Types Effect,” International

Journal of Mechanical Engineering and Technology, Vol. 09, No. 09, Pp. 383–394, 2018.

[41] M.J. Jweeg, A.S. Hammood, and M. Al-Waily, “A Suggested Analytical Solution of Isotropic Composite

Plate with Crack Effect,” International Journal of Mechanical & Mechatronics Engineering, Vol. 12, No.

05, 2012.

[42] L.S. Al-Ansari, M. Al-Waily, and A.M.H. Yusif, “Vibration Analysis of Hyper Composite Material Beam

Utilizing Shear Deformation and Rotary Inertia Effects,” International Journal of Mechanical &


[43] M. Al-Waily, and Z.A.A.A. Ali, “A Suggested Analytical Solution of Powder Reinforcement Effect on

Buckling Load for Isotropic Mat and Short Hyper Composite Materials Plate,” International Journal of

Mechanical & Mechatronics Engineering, Vol. 15, No. 04, 2015.

[44] M.J. Jweeg, “A Suggested Analytical Solution for Vibration of Honeycombs Sandwich Combined Plate

Structure,” International Journal of Mechanical & Mechatronics Engineering, Vol. 16, No. 2, 2016.

[45] M.A. Al-Shammari, and M. Al-Waily, “Analytical Investigation of Buckling Behavior of Honeycombs

Sandwich Combined Plate Structure,” International Journal of Mechanical and Production Engineering

Research and Development, Vol. 8, No. 4, Pp. 771-786, 2018.

[46] J.S. Chiad, M. Al-Waily, and M.A. Al-Shammari, “Buckling Investigation of Isotropic Composite Plate

Reinforced by Different Types of Powders,” International Journal of Mechanical Engineering and

Technology, Vol. 09, No. 09, Pp. 305–317, 2018.

[47] G.G. Hameed, M.J. Jweeg, and A. Hussein, “Springback and side wall curl of metal sheet in plain strain

deep drawing,” Research Journal of Applied Sciences, Vol. 04, No. 05, Pp. 192-201, 2009.

[48] M.A. Al-Shammari, E.Q. Hussein, and A.A. Oleiwi, “Material Characterization and Stress Analysis of a

Through Knee Prosthesis Sockets,” International Journal of Mechanical & Mechatronics Engineering, Vol.

17, No. 06, 2017.

[49] S.M. Abbas, A.M. Takhakh, M.A. Al-Shammari, and M. Al-Waily, “Manufacturing and Analysis of Ankle

Disarticulation Prosthetic Socket (SYMES),” International Journal of Mechanical Engineering and

Technology, Vol. 09, No. 07, Pp. 560-569, 2018.

[50] M.A. Al-Shammari, “Experimental and FEA of the Crack Effects in a Vibrated Sandwich Plate,” Journal of

Engineering and Applied Sciences, Vol. 13, No. 17, Pp. 7395-7400, 2018.

[51] F.M. Kadhim, A.M. Takhakh, and A.M. Abdullah, “Mechanical Properties of Polymer with Different

Reinforcement Material Composite That used for Fabricates Prosthetic Socket,” Journal of Mechanical

Engineering Research and Developments, Vol. 42, No. 4, Pp. 118-123, 2019.

[52] M.A. Al-Shammari, Q.H. Bader, M. Al-Waily, and A.M. Hasson, “Fatigue Behavior of Steel Beam Coated

with Nanoparticles under High Temperature,” Journal of Mechanical Engineering Research and

Developments, Vol. 43, No. 4, Pp. 287-298, 2020.

399


[53] M.J. Jweeg, S.N. Alnomani, and S.K. Mohammad, “Dynamic analysis of a rotating stepped shaft with and

without defects,” 3rd International Conference on Engineering Sciences, IOP Conference Series: Materials

Science and Engineering, Vol. 671, 2020.

[54] M.A. Al-Shammari, and S.E. Abdullah, “Stiffness to Weight Ratio of Various Mechanical and Thermal

Loaded Hyper Composite Plate Structures,” IOP Conference Series: Materials Science and Engineering, 2nd

International Conference on Engineering Sciences, Vol. 433, 2018.

[55] F.M. Kadhim, J.S. Chiad, and A.M. Takhakh, “Design And Manufacturing Knee Joint for Smart

Transfemoral Prosthetic,” IOP Conference Series: Materials Science and Engineering, International

Conference on Materials Engineering and Science, Vol. 454, 2018.

[56] A.A. Taher, A.M. Takhakh, and S.M. Thahab, “Study and optimization of the mechanical properties of

PVP/PVA polymer nanocomposite as a low temperature adhesive in nano-joining,” 3rd International

Conference on Engineering Sciences, IOP Conference Series: Materials Science and Engineering, Vol. 671,

2020.

[57] S.G. Hussein, M.A. Al-Shammari, A.M. Takhakh, and M. Al-Waily, “Effect of Heat Treatment on

Mechanical and Vibration Properties for 6061 and 2024 Aluminum Alloys,” Journal of Mechanical

Engineering Research and Developments, Vol. 43, No. 01, Pp. 48-66, 2020.

[58] M. Al-Waily, M.A. Al-Shammari, and M.J. Jweeg, “An Analytical Investigation of Thermal Buckling

Behavior of Composite Plates Reinforced by Carbon Nano Particles,” Engineering Journal, Vol. 24, No. 3,

2020.

[59] H.I. Mansoor, M.A. Al-shammari, and A. Al-Hamood, “Experimental Analysis of Cracked Turbine Rotor

Shaft using Vibration Measurements,” Journal of Mechanical Engineering Research and Development, Vol.

43, No. 2, Pp. 294-304, 2020.

[60] E.E. Kader, A.M. Abed, and M.A. Al-Shammari, “Al2O3 Reinforcement Effect on Structural Properties of

Epoxy Polysulfide Copolymer,” Journal of Mechanical Engineering Research and Developments, Vol. 43,

No. 4, Pp. 320-328, 2020.

[61] A.M. Takhakh, and S.M. Abbas, “Manufacturing and Analysis of Carbon Fiber Knee Ankle Foot Orthosis,”

International Journal of Engineering & Technology, Vol. 07, No. 04, pp. 2236-2240, 2018.

[62] A.M. Takhakh, S.M. Abbas, and A.K. Ahmed, “A Study of the Mechanical Properties and Gait Cycle

Parameter for a Below-Knee Prosthetic Socket,” IOP Conference Series: Materials Science and

Engineering, 2nd International Conference on Engineering Sciences, Vol. 433, 2018.

[63] E.A. Abbod, M. Al-Waily, Z.M.R. Al-Hadrayi, K.K. Resan, and S.M. Abbas, “Numerical and Experimental

Analysis to Predict Life of Removable Partial Denture,” IOP Conference Series: Materials Science and

Engineering, 1st International Conference on Engineering and Advanced Technology, Egypt, Vol. 870, 2020.

[64] S.E. Sadiq, S.H. Bakhy, and M.J. Jweeg, “Effects of Spot Welding Parameters on the Shear Characteristics

of Aluminum Honeycomb Core Sandwich Panels in Aircraft structure,” Test Engineering and Management,

Vol. 83, Pp. 7244 – 7255, 2020.

[65] H.I. Mansoor, M. Al-shammari, and A. Al-Hamood, “Theoretical Analysis of the Vibrations in Gas Turbine

Rotor,” 3rd International Conference on Engineering Sciences, IOP Conference Series: Materials Science

and Engineering, Vol. 671, 2020.

[66] M.A. Husain, and M.A. Al-Shammari, “Analytical Solution of Free Vibration Characteristics of Partially

Circumferential Cracked Cylindrical Shell,” Journal of Mechanical Engineering Research and

Developments, Vol. 43, No. 3, Pp. 442-454, 2020.

fatigue characterization of laminated composites used in …no.5(2020)/384-399.pdf · 2020. 7....

Documents