**DOI :**

**10.17577/IJERTV9IS110025**

**Open Access****Authors :**Venkat , Dr. S. R. Ranganatha**Paper ID :**IJERTV9IS110025**Volume & Issue :**Volume 09, Issue 11 (November 2020)**Published (First Online):**11-11-2020**ISSN (Online) :**2278-0181**Publisher Name :**IJERT**License:**This work is licensed under a Creative Commons Attribution 4.0 International License

Vibration Analysis of Rectangular Solid Plates and Plates with Surface Cracks

Venkat

Microwave Tube Research and Development Centre

DRDO, Bangalore, India

Dr. S.Ranganatha

Mechanical department

Universuty Visvesvaraya College of Engineering Bangalore University, Bangalore, India

Abstract— Plate members are used in automobile and aerospace structures. These structures are subjected to dynamic forces with variable frequencies due to engines used for propelling. These variable frequencies of dynamic forces cause resonance of plate elements in the structure. The resonance phenomenon leads to the fatigue of plate structures thus the instability of the flight in space.

In the present investigation an attempt has been made to characterize dynamic response, which controls the fatigue phenomenon of rectangular plates and plate with surface cracks oriented in different directions. The clamped-clamped-free-free (CCFF) boundary condition is incorporated. The vibration shaker is used to introduce exciting forces. The frequency of the exciting force is varied from 20 Hz to 2000 Hz. The amplitude, modal frequency, phase angle and damping factor are monitored at various resonant frequencies.

It is found from the experimental results that, amplitude of vibration, modal frequency, phase angle and damping factor are dependent on surface crack with longitudinal axis and its orientations.

Keywords— Surface crack, modal frequency, amplitude, damping factor,phase, vibration.

I. INTRODUCTION

An aerospace and automobiles engineering industry utilize a system in which major sub components are plate structured elements. More specifically in aerospace, plate panels are used to a large extent. These plate elements are subjected to different frequencies and of varying range due to high speeds of aero engines. The large range of variable speeds of aero engines introduces forced excitation on plate panels. The plate experience response at specific frequencies called modal frequencies. The modal frequencies at higher modes in engineering structure, results in fatigue failure of the components.

Both experimental and numerical attempts are made by researchers to understand the dynamic response of plate structure.

IVO Senjanovic made an attempt for estimating the natural frequency of free thin rectangular plate based on Rayleigh quotient method. The analytical estimated natural frequencies are compared with numerical obtained natural frequencies (1). Viswas and Ranjith studied both analytically and numerically methods to characterize free vibration of plates. Parameters like boundary conditions and plate thickness were considered for characterizing the dynamic response of the plate. The experimental method results were compared with results of numerical methods (2).Ibearugbulem and Owus studied the dynamic response of plate using energy method. The natural frequency was obtained by using Taylor’s series shape function and Ritz energy method. The results were compared with experimental work (3). Ilook Park and Usik lee studied dynamic response of plate using frequency dynamic spectral elements modeling and analysis method. The results were compared with exact solutions and numerical solutions (4). Khiem and Lien made an attempt in obtaining natural frequencies of beam with arbitrary number of cracks. The new method analyzed the effect of crack and boundary condition on natural frequencies (5). Zarza and Naimi made an attempt dynamic characteristic of isotropic and orthotropic cracked plate using energy approach. The results were comparable with numerical methods (6). Asif Israr et al., attempted a analytical modeling vibration analysis of partially cracked plate with different boundary condition. The method of multiple scales an approximate method was applied for solving the problem of cracked plate. The results were analyzed for both cracked length and plate thickness (7). Gharaibeh and Obeidat studied analytically the dynamic response of the rectangular plates. Rayleigh-Ritz method was used to calculate the first natural frequency. They used the results to characterize dynamic response in the presence of extra masses on the rectangular plates (8). Joshi et al., made analytical an attempt in characterizing, the dynamic response of internally cracked rectangular plate. They found that natural frequencies are more affected when cracks are internal and symmetrical about the mid plate of the plate. The influence was found that orientation of cracks with respect to longer edge of the crack was found to be more effective (9). Tushar choudary and Kumar made analytical attempts in predicting dynamic response of plate with circular hole. The results show that the natural frequency of the plates decreased with increased hole diameter (10). Ali and Atwal made analytical attempts to characterize the dynamic response of the rectangular plates with rectangular cut outs. They used the Rayleigh-Ritz method for finding the natural frequency. The results were compared with numerical methods (11). Ramamurthy et al., made attempts experimental attempt to find damping ratio. Such found damping ratio was used in numerical analysis (12). Maruyama and Ichinomiya conducted experiment for characterizing the dynamic response of clamped rectangular plates with straight narrow slits. Real time technique of the average interferometery was used to find the natural frequencies and mode shapes. The effect of the length of slit, position and inclination angle of slit on dynamic response was evaluated. They found that the above said parameters alter the dynamic response (13). Yin and lam developed analytical method for characterizing dynamic response of rectangular plates with two parallel cracks. The energy method was used for calculating natural frequencies

and also concluded that time domain response of the plate can be calculated using mode super position method (14). Gade and Khatode made analytical attempts for predicting dynamic response of beams with open edge crack. Parameters like varying crack, depth and location of the cracks were incorporated and studied the dynamic response of the beam. The result showed that the above parameter affects the dynamic response of the beam (15).

II. EXPERIMENTAL SETUP

The experiments are conducted using a 4-channel vibration controller, vibration shaker with accelerometer. The schematic experimental setup is shown Fig. 1.

Fig. 1. Schematic of electrodynamics vibration set up

The details of the equipment/instruments used are shown in Table I. The solid rectangular plate and plate with surface cracks are shown in Fig. 2. The fixture used for obtaining clamped-clamped-free-free boundary condition is shown in Fig. 4 and Fig. 5.

TABLE I. SPECIFICATION OF SHAKER AND SUBSYSTEM

Subsystem

Model

Parameter

Specification

Electro dynamic Shaker

SEV 060

Rated force

600 Kgf (Peak Sine)

Digital

power amplifier

DAS 3K6

Operating frequency

5 Hz to 3000 Hz

Vibration controller

Spandon

Stroke

30 mm (p-p)

Piezo electric accelerometers

M353B04 (2 no’s)

Acceleration bare table

75 g

RSTD package

Maximum velocity

1.5 m/sec

Moving platform diameter

180 mm

Fig. 2. Solid plate

Fig. 3. Surface crack at 0° with longitudinal axis

Fig. 4. Assembly fixture with specimen

Fig. 5. 2 D drawing of vibration fixture

Fig. 6.

IMG_20200702_160416.jpg

Fig. 7. Vibration shaker with plates for CCFF boundary condition

The experiments are conducted with different orientation direction of the surface cracks. The different orientations of the crack with longitudinal axis used in experiments are

1. Solid plate

2. Surface crack at 00 with longitudinal axis

3. Surface crack at 200 with longitudinal axis

4. Surface crack at 400 with longitudinal axis

5. Surface crack at 600 with longitudinal axis

6. Surface crack at 800 with longitudinal axis

7. Surface crack at 900 with longitudinal axis

III. RESULTS AND DISCUSSION

A. Solid plate

Rectangular plate with clamped-clamped-free-free (CCFF) boundary condition was subjected to forced vibration. The experiment was repeated for three times and average values of parameters; modal frequency, amplitude, phase angle and damping factor were estimated. A typical plot of experimental results is shown in Fig. 8.

Fig. 8. Experimental results for solid plate for CCFF condition

The Fig. 8 shows different magnitude of amplitude, modal frequencies and phase angle at resonance. All the details regarding resonance frequencies, amplitude at resonance, phase angle and Q-factor s are also shown in Fig. 8. These data are used for drawing Fig. 9 which shows detailed information inclusively dependence of amplitude with exciting frequency.

Fig. 9. Dependency of amplitude with excitation frequency for solid plate

The data of phase angle dependency on excitation frequencies are extracted from the Fig. 8 and drawn a new figure shown in Fig. 10 for the detailed information on phase angle of vibration.

Fig. 10. Dependency of phase angles with modal frequency for solid plate

The experimental data in Fig. 8 are rounded off to nearest number. The amplitude is rounded up to full number, phase angle rounded up to full number. The frequencies are rounded up to full number and Q-factor rounded up to full number. The rounded off data of frequencies, amplitudes, phase angles and Q-factors are tabulated and shown in Table II. The damping factor (ξ) was found from the tabulated Q-factor values in the Table II. The damping factor (ξ) was estimated using formula: ξ=1/2Q the estimated damping factors (ξ) are tabulated in Error! Reference source not found..

TABLE II. AMPLITUTE, MODAL FREQUENCY, PHASE, Q-FACTOR AND DAMPING FACTOR FOR SOLD PLATE

Solid plate

Mode

No.

Amplitude

(g/g)

Modal

Frequency (Hz)

Phase angle (0)

Q-Factor

Damping

factor (ξ)

1

70

188

-90

49

0.02

2

2

292

-165

55

0.02

3

1

522

171

24

0.04

4

49

661

67

63

0.02

5

3

715

-129

148

0.01

6

5

954

119

14

0.07

7

25

1065

61

25

0.04

8

30

1132

-60

89

0.01

B. Surface crack at 00 with longitudinal axis

A typical plot of experimental results is shown in Fig. 11.

Fig. 11. : Experimental results for surface crack at 00 for CCFF conditions

The Fig. 11 shows different magnitude of amplitude, modal frequencies and phase angle at resonance. All the details regarding resonance frequencies, amplitude at resonance, phase angle and Q-factor are also tabulated in Fig. 11.

The data of amplitude dependency on excitation frequencies are extracted from the Fig. 11. These data is used for drawing Fig. 11 which shows information inclusively on dependency of amplitude with exciting frequency.

Fig. 12. : Dependency of amplitude with excitation frequency for surface crack at 00

The data of phase angle dependency on excitation frequencies are extracted from the Fig. 11 and drawn a new figure shown in Fig. 13 for the detailed information on phase angle of vibration.

Fig. 13. Dependency of phase angles with excitation frequency for surface crack at 00

The experimental data of table in Fig. 11 are rounded off to nearest number. The amplitude is rounded up to first number, phase angle rounded up to full number. The frequencies are rounded up to full number and Q-factor rounded up to full number. The rounded off data of frequencies, amplitudes, phase and Q-factors are tabulated and shown in Error! Reference source not found.. The damping factor (ξ) was found from the tabulated Q-factor values in the Error! Reference source not found.. The damping factor (ξ) was estimated using formula: ξ=1/2Q. The estimated damping factors (ξ) are tabulated in Error! Reference source not found..

TABLE III. AMPLITUDE, MODAL FREQUENCY, PHASE AND Q-FACTOR FOR SURFACE CRACK AT 00

Surface crack at 0

Mode

No.

Amplitude (g/g)

Modal

Freq.(Hz)

Phase (0)

Q-Factor

Damping

Factor (ξ)

1

103

186

-86

41

0.01

2

3

276

141

45

0.01

3

22

634

77

89

0.01

4

7

666

-72

89

0.01

5

17

1109

-74

45

0.01

6

6

1319

-70

44

0.01

7

26

1434

-96

63

0.01

8

48

1824

-162

32

0.02

The Error! Reference source not found. shows the highest magnitude of amplitude 70g/g at resonance frequency was found in first mode which is 188 Hz. Other lesser magnitude of amplitude was found 49, 25 and 30 g/g at the resonance frequencies of 661, 1065 and 1132 Hz in mode 4, 7 and 8 respectively. The other minimum magnitude of amplitude were found 2, 1, 3 and 5 g/g at the resonance frequencies 292, 522, 715 and 954 Hz in modes 2, 3, 5 and 6 respectively.

The Error! Reference source not found. shows highest magnitude of amplitude 103g/g at resonance frequency was found in first mode which is 186 Hz. Other lesser magnitude of amplitude was found 22, 17, 26 and 48 g/g at the resonance frequencies of 634, 1109, 1434 and 1824 Hz in mode 3, 5, 7 and 8 respectively. The other minimum magnitude of amplitude was found 3.2, 6.9 and 5.8g/g at the resonance frequencies 276, 666 and 1319 Hz in modes 2, 4 and 6 respectively.

The Error! Reference source not found. shows the phase angles at the resonance modes. The phase angles at the resonance modes were found to be 141 and 770 at the modes 2 and 3respectively. The response during these modes is lagging to forcing disturbance. The lagging found to be maximum in mode 2 and minimum in mode 2. The mode angles were found to be -86, -72, -74, -70, -96 and -1620 at the modes 1, 4, 5, 6, 7 and 8 respectively. The response of the system during negative phase angle represents the leading of the system with respect to disturbing force. The leading was found to be highest in mode 8 and leading of the system gets reduced in modes 1, 4, 5, 6 and 7

The Error! Reference source not found. shows damping factor (ξ) varies from 0.01 to 0.02. The maximum damping factor was found 0.02 in mode 8 and minimum damping factor 0.01 were found in mode 1 to 8.

C. Surface crack at 200 with longitudinal axis

A typical plot of experimental results is shown in Fig. 14

Fig. 14. : Experimental results for surface crack at 200 for CCFF conditions

The Fig. 14 shows different magnitude of amplitude, modal frequencies and phase angle at resonance. All the details regarding resonance frequencies, amplitude at resonance, phase angle and Q-factor are also tabulated in Fig. 14. The data of amplitude dependency on excitation frequencies are extracted from the Fig. 14. These data is used for drawing Fig. 15 which shows information inclusively on dependency of Amplitude with exciting frequency.

Fig. 15. Dependency of amplitude with excitation frequency for surface crack at 200

The data of phase angle dependency on excitation frequencies are extracted from the Fig. 14 drawn a new figure shown in Fig. 16 for the detailed information on phase angle of vibration

Fig. 16. Dependency of phase with excitation frequency for surface crack at 200

The experimental data of table in Fig. 14 are rounded off to nearest number. The amplitude is rounded up to first digit, phase angle rounded up to full number. The frequencies are rounded up to full number and Q-factor rounded up to full number. The rounded off data of frequencies, amplitudes, phase and Q-factors are tabulated and shown in Error! Reference source not found. . The damping factor (ξ) was estimated using formula: ξ=1/2Q. The estimated damping factors (ξ) are tabulated in Error! Reference source not found..

TABLE IV. AMPLITUDE, MODAL FREQUENCY, PHASE AND Q-FACTOR FOR SURFACE CRACK AT 200

Surface crack at 20

Mode

No.

Amplitude (g/g)

Modal Freq.(Hz)

Phase (0)

Q-Factor

Damping

factor (ξ)

1

77

177

-112

50

0.01

2

6

610

99

74

0.01

3

1

661

135

50

0.01

4

2

672

94

89

0.01

5

10

888

91

21

0.02

6

14

1077

-50

28

0.02

7

152

1414

-159

74

0.01

8

22

1644

-128

17

0.03

The Error! Reference source not found. highest magnitude of amplitude 77g/g at resonance frequency was found in first and magnitude of 152g/g at resonance frequency was found in seventh mode which is 1414 Hz. Other lesser magnitude of amplitude was found 6, 10, 14 and 22 g/g at the resonance frequencies of 610, 888, 1077 and 1644 Hz in mode 2, 5, 6 and 8 respectively. The other minimum magnitude of amplitude was found 01 and 2g/g at the resonance frequencies 661and 672 Hz in modes 3 and 4 respectively.

The Error! Reference source not found. shows the phase angles at the resonance modes. The phase angles at the resonance modes were found to be 99, 135, 94 and 910 at the modes 2, 3, 4 and 5 respectively. The response during these modes is lagging to forcing disturbance. The lagging found to be maximum in mode 3 and minimum in mode 5. The mode angles were found to be -112, -50, -159and -1280 at the modes 1, 6, 7 and 8 respectively. The response of the system during negative phase angle represents the leading of the system with respect to disturbing force. The leading was found to be highest in mode 7 and leading of the system gets reduced in modes 1, 4, 5, 6 and 8.

The Error! Reference source not found. shows damping factor (ξ) varies from 0.01 to 0.03. The maximum damping factor was found 0.03 in mode 8 and minimum damping factor were found in mode 1 to mode 4, 7 and also damping factor was found 0.02 in mode 5 and mode 6 respectively.

D. Surface crack at 400 with longitudinal axis

A typical plot of experimental results is shown inError! Reference source not found.

Fig. 17. Experimental results for surface crack at 400 for CCFF

The Fig. 17 shows different magnitude of amplitude, modal frequencies and phase angle at resonance. All the details regarding resonance frequencies, amplitude at resonance, phase angle and Q-factor are also tabulated in Fig. 17.

The data of amplitude dependency on excitation frequencies are extracted from the Fig. 17. These data is used for drawing Fig. 18 which shows information inclusively on dependency of Amplitude with exciting frequency.

Fig. 18. Dependency of amplitude with excitation frequency for surface crack at 400

The data of phase angle dependency on excitation frequencies are extracted from the Fig. 17 and drawn a new figure shown in Fig. 19 for the detailed information on phase angle of vibration.

Fig. 19. Dependency of phase with Excitation frequency for surface crack at 400

The experimental data of table in Fig. 17 are rounded off to nearest number. The amplitude is rounded up to full digit, phase angle rounded up to full number. The frequencies are rounded up to full number and Q-factor rounded up to full number. The rounded off data of frequencies, amplitudes, phase and Q-factors are tabulated and shown in Error! Reference source not found. . The damping factor (ξ) was estimated using formula: ξ=1/2Q . The estimated damping factors (ξ) are tabulated in Error! Reference source not found. .

TABLE V. AMPLITUDE, MODAL FREQUENCY, PHASE AND Q-FACTOR FOR SURFACE CRACK AT 400

Surface crack at 400

Mode No.

Amplitude (g/g)

Modal Freq.(Hz)

Phase (0)

Q-Factor

Damping

factor (ξ)

1

89

168

-84

26.35

0.02

2

5

259

111

74.25

0.01

3

3

606

142

49.67

0.01

4

6

649

94

55.69

0.01

5

14

862

96

21.09

0.02

6

11

1044

-49

24.86

0.02

7

6

1206

-37

31.82

0.02

8

36

1424

-156

63.57

0.01

The Error! Reference source not found. shows highest magnitude of amplitude 89g/g at resonance frequency was found in first mode which is 168 Hz. Other lesser magnitude of amplitude was found 14, 11 and 36 g/g at the resonance frequencies of 862, 1044 and 1424 Hz in mode 5, 6 and 8 respectively. The other minimum magnitude of amplitude was found 5, 3, 6 and 6g/g at the resonance frequencies 259, 606, 649 and 1206 Hz in modes 2, 3, 4 and 7 respectively.

The Error! Reference source not found. shows the phase angles at the resonance modes. The phase angles at the resonance modes were found to be 111, 142, 94 and 96 at the modes 2, 3, 4 and 5 respectively. The response during these modes is lagging to forcing disturbance. The lagging found to be maximum in mode 3 and minimum in mode 4. The mode angles were found to be -84, -49, -37and -1560 at the modes 1, 6, 7 and 8 respectively. The response of the system during negative phase angle represents the leading of the system with respect to disturbing force. The leading was found to be highest in mode 7 and leading of the system gets reduced in modes 1, 4, 5, 6 and 8.

The Error! Reference source not found. shows damping factor (ξ) varies from 0.01 to 0.02. The maximum damping factor was found 0.02 in mode1, 5, 6 and 7 and minimum damping factor were found in mode 2, 3, 4 and 8 respectively.

E. Surface crack at 600 with longitudinal axis

A typical plot of experimental results is shown in Fig. 20.

Fig. 20. Experimental results for surface crack at 600 for CCFF boundary

The Fig. 20 shows different magnitude of amplitude, modal frequencies and phase angle at resonance. All the details regarding resonance frequencies, amplitude at resonance, phase angle and Q-factors are also shown in Fig. 20.

The data of amplitude dependency on excitation frequencies are extracted from the Fig. 20. These data is used for drawing Fig. 21 which shows information inclusively on dependency of amplitude with exciting frequency.

Fig. 21. dependency of amplitude with excitation frequency for surface crack at 600

The data of phase angle dependency on excitation frequencies are extracted from the Fig. 20 and drawn a new figure shown in Fig. 22 for the detailed information on phase angle of vibration.

Fig. 22. Dependency of phase angles with excitation frequency for surface crack at 600

The experimental data of table in Fig. 20 are rounded off to nearest number. The amplitude is rounded up to first full number, phase angle rounded up to full number. The frequencies are rounded up to full number and Q-factor rounded up to full number. The rounded off data of frequencies, amplitudes, phase and Q-factors are tabulated and shown in Error! Reference source not found. . The damping factor (ξ) was estimated using formula: ξ=1/2Q. The estimated damping factors (ξ) are tabulated in Error! Reference source not found..

The Error! Reference source not found. highest magnitude of amplitude 95.6g/g at resonance frequency was found in first mode which is 190 Hz. Other lesser magnitude of amplitude was found 27.9, 27.8 and 17.8 g/g at the resonance frequencies of 654, 1051 and 1411Hz in mode 4, 7 and 8 respectively. The other minimum magnitude of amplitude was found 4.9, 1.7, 2.4 and 5.4g/g at the resonance frequencies 291, 523, 707 and 946 Hz in modes 2, 3, 5 and 6 respectively

TABLE VI. AMPLITUDE, MODAL FREQUENCY, PHASE AND Q-FACTOR FOR SURFACE CRACK AT 600

Mode

Amplitu

Modal

Phase (0)

Q-Factor

Damping

1

96

190

-82

49

0.01

2

5

291

-127

63

0.01

3

2

523

141

37

0.01

4

28

654

74

89

0.01

5

2

707

-104

89

0.01

6

5

946

120

11

0.04

7

28

1051

52

21

0.02

8

18

1411

-76

89

0.01

.

The Error! Reference source not found. shows the phase angles at the resonance modes. The phase angles at the resonance modes were found to be 141, 74, 94,120 and 52 at the modes 3, 4, 6 and 7 respectively. The response during these modes is lagging to forcing disturbance. The lagging found to be maximum in mode 6 and minimum in mode 7. The mode angles were found to be -82, -127, -104and -760 at the modes 1, 2, 5 and 8 respectively. The response of the system during negative phase angle represents the leading of the system with respect to disturbing force. The leading was found to be highest in mode 2 and leading of the system gets reduced in modes 1, 5 and 8.

The Error! Reference source not found. shows damping factor (ξ) varies from 0.01 to 0.04. The maximum damping factor was found 0.04 in mode 6 and minimum damping factor was found 0.01 in mode 1, 2, 3, 4 and 5 respectively and also damping factor 0.02 found minimum in mode 7.

F. Surface crack at 800 with longitudinal axis

A typical plot of experimental results is shown in Fig. 23.

Fig. 23. Experimental results for surface crack at 800 for CCFF boundary conditions

The Fig. 23 shows different magnitude of amplitude, modal frequencies and phase angle at resonance. All the details regarding resonance frequencies, amplitude at resonance, phase angle and Q-factor are also tabulated in Fig. 23.

The data of amplitude dependency on excitation frequencies are extracted from the Fig. 23. These data is used for Fig. 24 which shows information inclusively on dependency of amplitude with exciting frequency.

Fig. 24. Dependency of amplitude with excitation frequency for surface crack at 800

The data of phase angle dependency on excitation frequencies are extracted from the Fig. 23 and drawn a new figure shown in Fig. 25 for the detailed information on phase angle of vibration.

Fig. 25. Dependency of phase angles with excitation frequency for surface crack at 800

The experimental data of table in Fig. 23 are rounded off to nearest full number. The amplitude is rounded up to first number, phase angle rounded up to full number. The frequencies are rounded up to full number and Q-factor rounded up to full number. The rounded off data of frequencies, amplitudes, phase and Q-factors are tabulated and shown in Error! Reference source not found. . The damping factor (ξ) was estimated using formula: ξ=1/2Q. The estimated damping factors (ξ) are tabulated in Error! Reference source not found..

TABLE VII. : AMPLITUDE, MODAL FREQUENCY, PHASE AND Q-FACTOR FOR SURFACE CRACK AT 800

Mode

Amplitude

Modal

Phase (0)

Q-Factor

Damping

1

89

168

-84

26

0.02

2

5

259

111

74

0.01

3

3

606

142

50

0.01

4

6

649

94

56

0.01

5

14

862

96

21

0.02

6

11

1044

-49

25

0.02

7

6

1206

-37

32

0.02

8

36

1424

-156

64

0.01

The Error! Reference source not found. shows highest magnitude of amplitude 89g/g at resonance frequency was found in first mode which is 168 Hz. Other lesser magnitude of amplitude was found 14, 10 and 36 g/g at the resonance frequencies of 862, 1044 and 1424Hz in mode 5, 6 and 8 respectively. The other minimum magnitude of amplitude was found 5, 3, 6 and 6 g/g at the resonance frequencies 259, 606, 649 and 1206 Hz in modes 2, 3, 4 and 7 respectively.

The Error! Reference source not found. shows the phase angles at the resonance modes. The phase angles at the resonance modes were found to be 111, 142, 94 and 960 at the modes 2, 3, 4 and 5 respectively. The response during these modes is lagging to forcing disturbance. The lagging found to be maximum in mode 3 and minimum in mode 4. The mode angles were found to be -84, -49, -37and -1560 at the modes 1, 6, 7 and 8 respectively. The response of the system during negative phase angle represents the leading of the system with respect to disturbing force. The leading was found to be highest in mode 8 and leading of the system gets reduced in modes 1and 2.

The Error! Reference source not found. shows damping factors (ξ) varies from 0.01 to 0.02. The maximum damping factor was found 0.04 in mode 1, 5, 6 and 7 and minimum damping factor was found 0.01 in mode 2, 3, 4 and 8respectively.

G. Surface crack at 900 with longitudinal axis

A typical plot of experimental results is shown in Fig. 26

Fig. 26. Experimental results for surface crack at 900 for CCFF

The Fig. 26 shows different magnitude of amplitude, modal frequencies and phase angle at resonance. All the details regarding resonance frequencies, amplitude at resonance, phase angle and Q-coefficients are also tabulated in Fig. 26.

The data of amplitude dependency on excitation frequencies are extracted from the Fig. 26. These data is used for drawing Fig. 27 which shows information inclusively on dependency of Amplitude with exciting frequency.

Fig. 27. Dependency of amplitude with excitation frequency for surface crack at 900

The data of phase angle dependency on excitation frequencies are extracted from the Fig. 26 and drawn a new figure shown in Fig. 28 for the detailed information on phase angle of vibration.

Fig. 28. Dependency of phase on excitation frequency for surface crack at 900

The experimental data of table in Fig. 26 are rounded off to full number. The amplitude is rounded up to full number, phase angle rounded up to full number. The frequencies are rounded up to full number and Q-coefficient rounded up to full number. The rounded off data of frequencies, amplitudes, phase and Q-coefficients are tabulated and shown inError! Reference source not found.. The damping coefficient (ξ) was estimated using formula: ξ=1/2Q. The estimated damping factors (ξ) are tabulated in Error! Reference source not found..

TABLE VIII. AMPLITUDE, MODAL FREQUENCY, PHASE AND Q-COEFFICIENT FOR SURFACE CRACK AT 900

Surface crack at 90

Mode

No.

Amplitude

(g/g)

Modal

Freq.

(Hz)

Phase

(0)

Q-Coefficient

Damping

coefficient (ξ)

1

77

174

-90

37

0.01

2

4

279

-132

74

0.01

3

1

587

178

6

0.08

4

9

661

72

63

0.01

5

5

888

104

20

0.02

6

20

1072

26

20

0.02

7

4

1184

-18

34

0.01

8

7

1225

-28

23

0.02

H. Estimated average magnitude of amplitudes

The Error! Reference source not found. shows estimated average values of magnitude of amplitude from the three different trials for different modes of solid plates and plates with surface cracks oriented in different direction with longitudinal axis of the plates are tabulated in Error! Reference source not found..

TABLE IX. AVERAGE AMPLITUDE RESPONSE OF SOLID & ARBITRARY ORIENTED SURFACE CRACKS

Average Amplitude (g/g)

Solid plate

Surface cracks

Mode No

–

00

200

400

600

800

900

1

92

96

72

52

98

74

77

2

1

3

3

3

3

3

2

3

4

8

1

13

6

2

1

4

34

15

2

13

15

20

4

5

4

16

12

10

1

6

22

6

2

2

10

5

3

5

7

7

10

9

8

3

12

4

2

8

5

18

1

3

7

14

5

The average magnitudes amplitudes tabulated in Error! Reference source not found. are used for drawing bar chart and shown in Fig. 29.

Amplitude (g/g)

Modes

Surface cracks-Amplitude

Solid plate

Surface crack at 0 Degree

Surface crack at 20 Degree

Surface crack at 40 Degree

Fig. 29. Average magnitude of amplitude with modal number of solid & arbitrary oriented surface cracks

The average values magnitude of amplitudes in mode1 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate lies between 92 and 52 g/g. The average magnitude of amplitude in mode 4 for solid plate and plate with surface crack oriented differently with longitudinal axis of the plate lies 34 and 2 g/g. The average value magnitude of amplitudes in mode 2, 3, 5, 6, 7, 8 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate lies between 22 and 1.

In general the fluctuations in magnitude of average amplitudes of vibration of solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate fluctuates larger extent in mode1 and mode 4. The extent of fluctuation, the magnitude of average amplitude in mode2, 3, 5, 6, 7 and 8 is found to be narrow down compared to the mode1 and mode 4.

The presence of surface crack and its orientation with respect longitudinal axis was found to alter the amplitude of vibration in first mode compared to solid plate. The magnitudes of amplitude in first mode for surface cracked plate were found to be less than solid plate except for 00 and 600 oriented surface crack. This could be attributed to alter the potential energy of the plate due to surface crack. Such generalization not found at higher modes

I. Estimated average magnitude of amplitude

The Error! Reference source not found. shows estimated average values of magnitude of amplitude from the three different trials for different modes of solid plates and plates with surface cracks oriented in different direction with longitudinal axis of the plates are tabulated in Error! Reference source not found..

TABLE X. AVERAGE MODAL FREQUENCIES OF SOLID & ARBITRARY ORIENTED SURFACE CRACKS

Average Modal frequency

Solid plate

Surface cracks

Mode No

–

00

200

400

600

800

900

1

188

183

175

169

191

170

176

2

303

282

397

390

313

281

281

3

504

460

436

432

606

535

412

4

651

649

554

707

670

647

558

5

696

819

733

800

724

741

720

6

835

894

807

929

847

869

816

7

1004

1013

938

1011

1056

1023

926

8

1110

1319

1025

1114

1247

1145

1058

The average magnitudes of modal frequencies tabulated in Error! Reference source not found. are used for drawing bar chart and shown in Fig. 30.

Fig. 30. Average magnitude of modal frequency of solid & arbitrary oriented surface cracks

The average values magnitude of modal frequencies in mode1 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate in the range 169 and 191Hz. The average values magnitude of modal frequencies in mode2 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate in the range 281and 390Hz. The average values magnitude of modal frequencies in mode3 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate in the range 412 and 606Hz.The average values magnitude of modal frequencies in mode4 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate in the range 554 and 707Hz. The average values magnitude of modal frequencies in mode5 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate in the range 554 and 707Hz. The average values magnitude of modal frequencies in mode6 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate in the range 807-and 869Hz. The average values magnitude of modal frequencies in mode7 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate in the range 926 and 1056Hz. The average values magnitude of modal frequencies in mode8 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate in the range 1025and 1319Hz respectively.

The modal frequencies in general increased with mode numbers irrespective of surface crack its orientation. This could be attributed to storing the potential energy due to mode configuration.

J. Estimated average magnitude of Phase angle

The Error! Reference source not found. shows estimated average values of magnitude amplitude from the three different trials for different modes of solid plates and plates with surface cracks oriented in different direction with longitudinal axis of the plates are tabulated in Error! Reference source not found..

TABLE XI. AVERAGE PHASE ANGLE OF SOLID & ARBITRARY ORIENTED SURFACE CRACKS

Average phase angles

Solid plate

Surface cracks

Mode No

–

00

200

400

600

800

900

1

-87

-85

-114

-91

-87

-90

-95

2

-56

49

-59

-61

-154

-75

132

3

39

27

-69

-92

123

-35

-165

4

5

-11

-46

88

49

89

138

5

-93

-13

80

-64

59

-8

65

6

111

-23

-49

112

125

59

-88

7

112

-31

21

100

77

53

112

8

32

-52

39

31

14

0

74

The average magnitudes of modal frequencies tabulated in Error! Reference source not found. are used for drawing bar chart and shown in Fig. 31.

Fig. 31. : Average magnitude of phase angles of solid & arbitrary oriented surface cracks

The average values magnitude of phase angles in mode1 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate lies between -85 and -900. The average magnitude of amplitude in mode 4 for solid plate and plate with surface crack oriented differently with longitudinal axis of the plate lies 5 and 1380. The average value magnitude of amplitudes in mode 2, 3, 5, 6, 7, 8 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate lies between 0 and -1650.

The system irrespective orientation of surface crack was found to lagging in first mode. The phase angle was found to be positive and negative in higher modes. Such behavior also could be attributed to storage of potential energy due to configuration of the plate.

K. Estimated average magnitude of damping factor

The Error! Reference source not found. shows estimated average values of magnitude damping coefficient from the three different trials for different modes of solid plates and plates with surface cracks oriented in different direction with longitudinal axis of the plates are tabulated in Error! Reference source not found..

TABLE XII. AVERAGE MAGNITUDE OF DAMPING COEFFICIENT OF SOLID & ARBITRARY ORIENTED SURFACE CRACKS

Average Damping coefficient

Solid plate

Surface crack

Mode No

–

00

200

400

600

800

900

1

0.01

0.01

0.01

0.02

0.01

0.01

0.01

2

0.04

0.01

0.01

0.01

0.02

0.02

0.01

3

0.01

0.01

0.02

0.01

0.01

0.01

0.04

4

0.01

0.01

0.01

0.02

0.01

0.01

0.02

5

0.01

0.01

0.01

0.01

0.01

0.01

0.01

6

0.02

0.01

0.01

0.01

0.02

0.01

0.01

7

0.01

0.01

0.01

0.01

0.02

0.04

0.01

8

0.03

0.04

0.03

0.04

0.01

0.02

0.03

The average magnitudes of damping coefficient in different modes of vibration are used for drawing bar and shown in TABLE XII. .

Fig. 32. Average magnitude of damping coefficient of solid & arbitrary oriented surface cracks

The average values magnitude damping factor in mode1 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate lies between 0.01 and 0.02. The average magnitude of amplitude in mode 4 for solid plate and plate with surface crack oriented differently with longitudinal axis of the plate lies 0.01and 0.02. The average value magnitude of amplitudes in mode 2, 3, 5, 6, 7, 8 for solid plate and plate with surface cracks oriented differently with longitudinal axis of the rectangular plate lies between 0.01 and 0.04.

The damping coefficient found to be in the order of 0.01 except in the case of in mode 2 of solid plate and surface crack with arbitrary oriented 900 in mode 3 and surface crack with arbitrary oriented 40 in mode 4 and surface crack with arbitrary oriented 400 and 900 in mode 4 and surface crack with arbitrary oriented 600 in mode 6 and surface crack with arbitrary oriented 800 in mode 7 and surface crack with arbitrary oriented 00 and 400 in mode 3

IV. CONCLUSION

❖ The amplitude of vibration was found to be influenced by the surface cracks and its orientation with respect to longitudinal axis.

❖ The modal frequencies, irrespective of cracks and its orientations, in general increased with mode number.

❖ The system was found to be lagging in mode 1and both lagging and leading in other modes,

❖ The redistribution of potential energy which depends on the mode configuration was found to be a factor influencing the dynamic response.

REFERENCE:

[1] Vibration analysis of plates with one free edge using energy method (CCCF plate). Ibearugbulem et al. s.l. : International journal of engineering and technology, 2014, Vols. 4, No.1.