**1. Introduction**

26 Will-be-set-by-IN-TECH

[33] Puri P (1972) Plane Waves in Thermoelasticity and Magnetothermoelasticity. Int. J. Eng.

[34] Puri P, Cowin SC (1985) Plane Waves in Linear Elastic Materials with Voids. J. of

[35] Sharma JN, Kaur D (2006) Plane Harmonic Waves in Generalized Thermoelastic

[36] Singh J, Tomar SK (2007) Plane Waves in Thermoelastic Material with Voids. Mechanics

[37] Manacorda T (1979) *Introduzione alla Termomeccanica dei Continui*. Quaderni UMI **14**

[38] Ie¸san D (1986) A Theory of Thermoelastic Materials with Voids. Acta Mechanica.

[39] Mariano PM, Sabatini L (2000) Homothermal Acceleration Waves in Multifield Theories

[40] Wright TW (1973) Acceleration Waves in Simple Elastic Materials. Arch. Rational Mech.

[41] Giovine P, Fiorino L (2008) Some Remarks on Acceleration Waves in Porous Solids. In: Manganaro N, Rionero S, editors. Proceed. 14th Int. Conf. on Waves and Stability in Continuous Media, Scicli (Ragusa). Singapore: World Scientific Publishing. pp. 280-286. [42] Giovine P, Fiorino L (2005) Nano-Pores in Thermoelastic Materials. Atti XVII*<sup>o</sup>* Congresso AIMETA 05 di Meccanica Teorica ed Applicata, Mini-symposium on "Nanotechnologies: Building up Structures at the Nano and Meso-Scales". Firenze

Sciences. 10:467-477.

Elasticity. 15:167-183.

of Materials. 39:932-940.

60:67-89.

Anal. 50:237-277.

(Pitagora Editrice, Bologna 1979)

Materials with Voids. Private communication.

of Continua. Int. J. Non-Linear Mech. 35:963-977.

(2005) p.283. Technical Note n.385 on the CD rom.

The dispersion relation of a circular cylindrical shell had been a subject of great interest for several decades [1-3]. In some earlier works, numerical procedures were used exclusively in the computation of dispersion relations. Recently, Karczub [4] obtained an analytical expression for the dispersion relations from Flügge shell theory by using a symbolic algebra package, Mathematica. Karczub's main concern was to check the agreement between his analytical results and results obtained previously from numerical methods, and limited to the harmonic orders *n*≧1. The agreement was excellent. The axisymmetric waves (*n*=0) are important in the transmission of longitudinal waves, and are particularly important in acoustics due to their high radiation efficiency. In order to have complete analytical solutions for the shell dispersion relations, the solutions for the *n*=0 case are included and discussed in this paper.

The solutions of the modal patterns for each of the propagating and non-propagating modes are also important and are not discussed in Karczub's paper. These solutions are crucial to determine the vibration of a finite shell under various admissible boundary conditions and arbitrary external forces. The dispersion relations and the associated eigenvectors are also the means by which to construct transfer matrices for vibroacoustic transmission in cylindrical shell structures or pipe-hose systems [5]. The traditional and standard method of finding eigenvectors was given in detail by Leissa [6]; the eigenvector was normalized in such a way that its radial component of the displacement was unity, while the longitudinal and circumferential components were expressed as displacement ratios relative to the radial displacement. In some cases, these ratios could become exceedingly large and the eigenvector thus could deviate significantly from the eigenvector commonly used in mathematical physics.

In order to improve this problem for finding the normalized eigenvectors with norms equal to unity, an alternative method by using the built-in eigenvalue problem in any numerical package is proposed. A continuous variation of mode patterns for all kind of wave types in

© 2012 Liu et al., licensee InTech. This is an open access chapter distributed under the terms of the Creative Commons Attribution License (http://creativecommons.org/licenses/by/3.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited. © 2012 The Author(s). Licensee InTech. This chapter is distributed under the terms of the Creative Commons Attribution License http://creativecommons.org/licenses/by/3.0), which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.

the desired frequency range will be rapidly obtained, and the physical meanings of wave propagation can also be shown more clearly and straightforward [8].

Dispersion Relations and Modal Patterns of Wave in a Cylindrical Shell 89

where *a* is the mean shell radius, *ν* is Poisson ratio, *E* is Young's modulus of elasticity, *ρ* is the mass density, *h* is the shell thickness, and *β*=*h*/(*a*(12)0.5) is a non-dimensional thickness

In order to transfer the expression from time and displacement domain into frequency and

( ) , ) (,,) *in ix t*

 

(, ) (, ) (, ) 0 1 0 , , 0

*a* is the dimensionless wavenumber, and *n* is the circumferential wavenumber,

 

2 2 23 22 2

2 2 2 2 2 4 22 4

 

 

[(1 ) / 2] , [(1 ) / 2](1 3 )

*L i ns s L s n*

*L in n s L n s ns n*

The relationship between *s* and Ω is so called dispersion relations of cylindrical shell. When a value of dimensionless angular frequency, Ω, is given, non-trivial solutions for the matrix form in the Eq.(4) exist at certain values of *s*. Finally, the specified roots can be integrated to the polynomial of *s*2. All the calculating processes and expressions can be rapidly built up by using any kind of symbolic algebra package, such as Matlab or Mathematica. According the physical characteristics of acoustic propagation, two conditions can further be separated and

When *n*=0, two independent sets of equations and corresponding characteristic equation can

*L sn L sn U s L sn L sn W s* 

(, ) (, ) 1 0 ,0, <sup>0</sup> (, ) (, ) 0 1 ,0,

11 13 2

13 33

[(3 ) / 2] , [1 (1 2 )] 2

 

 

 

2 ( )

(3)

*i x t in*

 

(5)

(4)

 

*f(x, t = e F n e d d*

*L sn L sn L sn V sn e e*

where Ω=(*ωa*/*cL*) is the dimensionless frequency, *cL* =[*E*/(ρ(1-ν2))]0.5 is the longitudinal wave

parameter which is proportional to the ratio between the thickness and radius.

*n*

The dimensionless spectral listed in Eq.(1) can becomes as following

11 12 13

12 22 23 13 23 33

speed, *s*=

discussed as following.

be calculated and shown as below:

1. For axial and radial displacements:

*2.2.1. n=0* 

wavenumber domain, the following spectral representation can be further to use [7]

 

(, ) (, ) (, ) 1 0 0 , ,

*L sn L sn L sn U sn*

(, ) (, ) (, ) 001 , ,

respectively. *Lij*, (*i*,*j*)=1~3, are the spectral spatial operators and listed as follow

[(1 ) / 2](1 ) , [(1 ) / 2]

 

13 22

 

*L s n Ln s*

2 2 2 11 12

> 

23 33

**2.2. Analytical expressions for dispersion relations** 

*L sn L sn L sn W sn*

## **2. Methods to determine the propagating mode wavenumbers**

#### **2.1. Expression of equation of motion of cylindrical shell**

The coordinate system which {*u*,*v*,*w*} are presented as the axial, circumferential, and radial direction, respectively, is shown in Fig. 1.

**Figure 1.** Coordinates and displacement orientation.

The equations of motion for the free vibration of a cylindrical shell can be written and shown as below

$$
\begin{bmatrix}
\begin{bmatrix}
\bar{L}\_{11} & \bar{L}\_{12} & \bar{L}\_{13} \\
\bar{L}\_{21} & \bar{L}\_{22} & \bar{L}\_{23} \\
\bar{L}\_{31} & \bar{L}\_{32} & \bar{L}\_{33}
\end{bmatrix} + \frac{\rho(1-\nu^{2})}{E} \frac{\partial^{2}}{\partial t^{2}} \begin{bmatrix}
1 & 0 & 0 \\
0 & 1 & 0 \\
0 & 0 & 1
\end{bmatrix} \begin{bmatrix}
u(\mathbf{x},\boldsymbol{\phi},t) \\
v(\mathbf{x},\boldsymbol{\phi},t) \\
w(\mathbf{x},\boldsymbol{\phi},t)
\end{bmatrix} = \begin{bmatrix}
0 \\ 0 \\ 0
\end{bmatrix} \tag{1}
$$

where *ij L* , (*i*,*j*)=1~3, are the spatial operators by using the Flügge theory. These parameters can be listed as below

22 2 2 11 2 22 12 3 3 2 2 13 3 2 22 2 21 12 22 2 22 3 2 23 2 2 31 13 32 23 (1 )(1 ) 1 , 2 <sup>2</sup> 1 2 (1 )(1 3 ) 1 , , 2 1 (3 ) 2 , , *L L x a a x L a a x x x a LL L x a L a x L LL L L* 2 44 4 2 2 2 33 2 4 22 2 4 2 1 1 *a* 2 1 2 *a xx a a* (2)

where *a* is the mean shell radius, *ν* is Poisson ratio, *E* is Young's modulus of elasticity, *ρ* is the mass density, *h* is the shell thickness, and *β*=*h*/(*a*(12)0.5) is a non-dimensional thickness parameter which is proportional to the ratio between the thickness and radius.

In order to transfer the expression from time and displacement domain into frequency and wavenumber domain, the following spectral representation can be further to use [7]

$$f(\mathbf{x}, \phi, t) = \sum\_{n=-\infty}^{\infty} e^{in\phi} \stackrel{\text{op}}{\underset{-\infty}{\longrightarrow}} \int \stackrel{\text{v}}{F}(\alpha, n, \alpha) e^{i(\alpha x - \alpha t)} da d\alpha \tag{3}$$

The dimensionless spectral listed in Eq.(1) can becomes as following

$$\begin{cases} \begin{array}{cccc} L\_{11} \text{(s,n)} & L\_{12} \text{(s,n)} & L\_{13} \text{(s,n)} \\ L\_{12} \text{(s,n)} & L\_{22} \text{(s,n)} & L\_{23} \text{(s,n)} \\ -L\_{13} \text{(s,n)} & -L\_{23} \text{(s,n)} & L\_{33} \text{(s,n)} \end{array} \end{cases} \begin{bmatrix} 1 & 0 & 0 \\ 0 & 1 & 0 \\ 0 & 0 & 1 \end{bmatrix} \cdot \begin{cases} \begin{bmatrix} L \text{(s,n,\Omega)} \\ V \text{(s,n,\Omega)} \end{bmatrix} \cdot e^{i(\alpha x - \alpha t)} \cdot e^{in\phi} = 0 \\ \begin{bmatrix} \alpha \end{bmatrix} \end{cases} \tag{4}$$

where Ω=(*ωa*/*cL*) is the dimensionless frequency, *cL* =[*E*/(ρ(1-ν2))]0.5 is the longitudinal wave speed, *s*=*a* is the dimensionless wavenumber, and *n* is the circumferential wavenumber, respectively. *Lij*, (*i*,*j*)=1~3, are the spectral spatial operators and listed as follow

$$\begin{aligned} L\_{11} &= s^2 + [(1 - \nu) / 2](1 + \beta^2)n^2 \quad , \quad L\_{12} = \eta[(1 + \nu) / 2]s \\ L\_{13} &= -i \left\langle \left(\nu - [(1 - \nu) / 2]\beta^2 n^2\right)s + \beta^2 s^3 \right\rangle \quad , \quad L\_{22} = [(1 - \nu) / 2](1 + 3\beta^2)s^2 + n^2 \\ L\_{23} &= -i \left\langle \eta + \eta[(3 - \nu) / 2]\beta^2 s^2 \right\rangle \quad , \quad L\_{33} = [1 + \beta^2(1 - 2n^2)] + \beta^2 \left(s^4 + 2n^2 s^2 + n^4\right) \end{aligned}$$

#### **2.2. Analytical expressions for dispersion relations**

The relationship between *s* and Ω is so called dispersion relations of cylindrical shell. When a value of dimensionless angular frequency, Ω, is given, non-trivial solutions for the matrix form in the Eq.(4) exist at certain values of *s*. Finally, the specified roots can be integrated to the polynomial of *s*2. All the calculating processes and expressions can be rapidly built up by using any kind of symbolic algebra package, such as Matlab or Mathematica. According the physical characteristics of acoustic propagation, two conditions can further be separated and discussed as following.

#### *2.2.1. n=0*

88 Wave Processes in Classical and New Solids

direction, respectively, is shown in Fig. 1.

**Figure 1.** Coordinates and displacement orientation.

*h*

*r* 

31 32 33

*L a*

*LL L*

*L*

*L*

 

shown as below

where *ij L*

can be listed as below

the desired frequency range will be rapidly obtained, and the physical meanings of wave

The coordinate system which {*u*,*v*,*w*} are presented as the axial, circumferential, and radial

The equations of motion for the free vibration of a cylindrical shell can be written and

22 2 2

(1 )(1 ) 1 , 2 <sup>2</sup>

*x a a x*

> 

3 3

1 2

3

(1 )(1 3 ) 1 , , 2

33 2 4 22 2 4 2

*a xx a a*

 

, (*i*,*j*)=1~3, are the spatial operators by using the Flügge theory. These parameters

*LLL ux t LLL vx t <sup>E</sup> <sup>t</sup> LLL wx t*

 

*x* 

(1)

(2)

100 , , 0

001 , , 0

> 

(1 ) 0 1 0 ,, 0

22 2

*x a*

2 44 4 2

*a* 2 1 2

propagation can also be shown more clearly and straightforward [8].

**2.1. Expression of equation of motion of cylindrical shell** 

11 12 13 2 2 21 22 23 2

 

11 2 22 12

*L L*

2 23 2 2

*a x*

, ,

1 (3 )

 

31 13 32 23

2 2

*L LL L*

2 2 13 3 2

*a x x x a*

2

1 1

21 12 22 2 22

  

 

**2. Methods to determine the propagating mode wavenumbers** 

*u*

*<sup>v</sup> <sup>w</sup>*

When *n*=0, two independent sets of equations and corresponding characteristic equation can be calculated and shown as below:

1. For axial and radial displacements:

$$
\begin{cases}
\begin{bmatrix}
L\_{11}(s,n) & L\_{13}(s,n) \\
\end{bmatrix} - \Omega^{2} \begin{bmatrix}
1 & 0 \\
0 & 1
\end{bmatrix}
\begin{bmatrix}
\mathcal{U}(s,0,\Omega) \\
\mathcal{W}(s,0,\Omega)
\end{bmatrix} = 0
\tag{5}
$$

For the non-trivial solution for {*U*(*s*,0,Ω), *W*(*s*,0, Ω)}, the determinant of matrix in Eq. (5) should be zero ad obtained as below:

$$
\mathcal{g}\_6(s^2)^3 + \mathcal{g}\_4(s^2)^2 + \mathcal{g}\_2(s^2) + \mathcal{g}\_0 = 0 \tag{6}
$$

Dispersion Relations and Modal Patterns of Wave in a Cylindrical Shell 91

 

8 6 4 20 *gs gs gs gs g* () () () () 0 (11)

1/2

1/2

1/2

(12)

1/2

 

*s AAA s AAA s AAA s AAA*

 

124

124

124

124

This torsional waves are known for being non-dispersive, since the wave speed is

Under the non-trivial solution of Eq. (4), a 4th polynomial of *s*2 can be obtained as

24 23 22 2

These roots yield eight branches of dispersion curves, which are grouped into four branch

where *gi* and *Ai* are the coefficients and listed in the Appendix. Since *Ai*'s are functions of *n* and Ω, these four branch pairs can be analytically determined once the given values of *n* and

As mentioned earlier, the solutions regarding the modal patterns (eigenvectors) for all four root branch pairs are important. The conventional method has been frequently used for a long time. In this method, the mode shapes are expressed as the ratios among *U*, *V* and *W*. By returning to Eq.(4) after each of the roots (±*si*, *i*=1 to 4 ) have been found for a given Ω, these ratios can be found by solving any two of the three simultaneous equations. Finally, the third can be discarded. Detail processes can be obtained from Leissa. Because the value of the ratio *U*/*W* or *V*/*W* can become quite large when either *U* or *V* is the predominant component of the mode, this method is not the most convenient and natural way to express the eigenvectors, particularly when eigenfunction expansion is used to solve vibration

A new alternative method, which solves for the eigenvectors by using a commercially available linear algebra package, will be introduced. This method is extremely simple and straightforward. The kernel of processing is by using the built-in formulation of eigenvalue

 

Branch pair 1 : Branch pair 2 : Branch pair 3 : Branch pair 4 :

**2.3. Methods to determine the propagating mode pattern** 

and eigenvector problem in the numerical package.

wave speed depends slightly on the thickness and radius ratio.

*2.2.2. n*

pairs:

≧*1* 

Ω are specified.

problems.

<sup>2</sup> / / 13 *T LS c c sc*

where *cS* is the shear wave speed. When the thickness is approximated to zero, torsional wave and shear wave speed will almost be the same. Therefore, in Flügge's theory, the shear

where the coefficients, *g*i, are the function of *n* and Ω, and shown as

$$\begin{aligned} \mathcal{g}\_6 &= \beta^2 \left( 1 + \beta^2 \right) \quad , \quad \mathcal{g}\_4 = \beta^2 \left( 2\nu - \Omega^2 \right) \\\mathcal{g}\_2 &= 1 + \beta^2 + \nu^2 - \Omega^2 \quad , \quad \mathcal{g}\_0 = \Omega^2 \left( \Omega^2 - \beta^2 - 1 \right) \end{aligned}$$

The solutions of Eq.(5) represent a combination of longitudinally and radially expanding and contracting motions; these are the so-called breathing-modes. The expressions of polynomial *s*2 is obtained in Eq.(6).

Six characteristic roots are given

$$\begin{aligned} \text{Branch pair 1}: & \mathbf{s} = \pm \sqrt{\Gamma\_1 + 2\Gamma\_2} \\ \text{Branch pair 2}: & \mathbf{s} = \pm \sqrt{\Gamma\_1 - \Gamma\_2 + \left(\sqrt{3}\Gamma\_3\right)i} \\ \text{Branch pair 3}: & \mathbf{s} = \pm \sqrt{\Gamma\_1 - \Gamma\_2 - \left(\sqrt{3}\Gamma\_3\right)i} \end{aligned} \tag{7}$$

where

$$\begin{aligned} \boldsymbol{\Gamma}\_{1} &= -\mathbf{g}\_{4} \left/ \left( 3 \mathbf{g}\_{6} \right) \right. \quad \boldsymbol{\Gamma}\_{2} = \boldsymbol{\Lambda}\_{2} - \boldsymbol{\Lambda}\_{3} \quad \quad \boldsymbol{\Gamma}\_{3} = \boldsymbol{\Lambda}\_{2} + \boldsymbol{\Lambda}\_{3} \\ \boldsymbol{\Lambda}\_{1} &= \left( \boldsymbol{\mathcal{J}}\_{2} + \sqrt{4 \boldsymbol{\mathcal{J}}\_{1}^{3} + \boldsymbol{\lambda}\_{2}^{2}} \right)^{1/3} \quad \boldsymbol{\Lambda}\_{2} = \boldsymbol{\Lambda}\_{1} / \left( 6 \mathbf{g}\_{6} \mathbf{2}^{\{1/3\}} \right) \quad \boldsymbol{\Lambda}\_{3} = \boldsymbol{\Lambda}\_{1} / \left( 3 \mathbf{g}\_{6} \boldsymbol{\Lambda}\_{1} \mathbf{2}^{\{2/3\}} \right) \\ \boldsymbol{\Lambda}\_{1} &= -\mathbf{g}\_{4}^{2} + 3 \mathbf{g}\_{2} \mathbf{g}\_{6} \quad \quad \boldsymbol{\Lambda}\_{2} = -2 \mathbf{g}\_{4}^{3} + 9 \mathbf{g}\_{2} \mathbf{g}\_{4} \mathbf{g}\_{6} - 27 \mathbf{g}\_{0} \mathbf{g}\_{6}^{2} \end{aligned}$$

2. For the circumferential displacement:

The 2nd equation in Eq. (4) can be separated and shown as:

$$\left\{L\_{22}(\mathbf{s},\mathbf{n})-\Omega^{2}\right\}\cdot\left[V\left(\mathbf{s},\mathbf{0},\Omega\right)\right]=\mathbf{0}\tag{8}$$

In the same way, under the non-trivial solution for *V*(*s*,0,Ω), the new relation can be rewritten as

$$\left[ (1 - \nu)(1 + 3\beta^2) / 2 \right] s^2 - \Omega^2 = 0 \tag{9}$$

Obviously, the solution of Eq.(8) represents a uniformly circumferential motion, which is therefore a torsional-mode. The corresponding characteristic roots may be considered the 4th branch pair and show as following

$$\text{Branch pair } 4: s = \pm \Omega \left/ \sqrt{(1-\nu)(1+3\beta^2)} / \sqrt{2} \tag{10}$$

This torsional waves are known for being non-dispersive, since the wave speed is

$$c\_T = \alpha / \,\alpha = c\_L \Omega / \,\text{s} = c\_S \sqrt{1 + 3\beta^2}$$

where *cS* is the shear wave speed. When the thickness is approximated to zero, torsional wave and shear wave speed will almost be the same. Therefore, in Flügge's theory, the shear wave speed depends slightly on the thickness and radius ratio.

#### *2.2.2. n*≧*1*

90 Wave Processes in Classical and New Solids

should be zero ad obtained as below:

polynomial *s*2 is obtained in Eq.(6).

 

*g g*

2. For the circumferential displacement:

branch pair and show as following

rewritten as

Six characteristic roots are given

where

For the non-trivial solution for {*U*(*s*,0,Ω), *W*(*s*,0, Ω)}, the determinant of matrix in Eq. (5)

6 4 20 *gs gs gs g* () () () 0 (6)

1 2

*s i*

*s i*

3 2 1/3 2/3

4 , / 6 2 , / 3 2

1 2 12 21 6 3 1 61

<sup>2</sup>

In the same way, under the non-trivial solution for *V*(*s*,0,Ω), the new relation can be

2 22 (1 )(1 3 ) / 2 0

Obviously, the solution of Eq.(8) represents a uniformly circumferential motion, which is therefore a torsional-mode. The corresponding characteristic roots may be considered the 4th

<sup>2</sup> Branch pair 4 : / (1 )(1 3 ) / 2 *s*

  12 3

12 3

*g g*

<sup>22</sup> *L sn V s* (, ) ,0, 0 (8)

*<sup>s</sup>* (9)

  (7)

(10)

23 22 2

1 , 2 ,

The solutions of Eq.(5) represent a combination of longitudinally and radially expanding and contracting motions; these are the so-called breathing-modes. The expressions of

2 2 2 22 2

 

1 , 1

22 2 2

where the coefficients, *g*i, are the function of *n* and Ω, and shown as

6 4

 

*g g*

 

2 0

Branch pair 1 : 2

1 4 6 223 323 1/3

/ 3 , ,

 

The 2nd equation in Eq. (4) can be separated and shown as:

2 32 1 4 26 2 4 246 06

3 , 2 9 27

*g gg g ggg gg*

*s*

Branch pair 2 : 3

Branch pair 3 : 3

*g g*

Under the non-trivial solution of Eq. (4), a 4th polynomial of *s*2 can be obtained as

$$g\_8(s^2)^4 + g\_6(s^2)^3 + g\_4(s^2)^2 + g\_2(s^2) + g\_0 = 0 \tag{11}$$

These roots yield eight branches of dispersion curves, which are grouped into four branch pairs:

$$\begin{aligned} \text{Branch pair 1}: s &= \pm \left( A\_1 + A\_2 + A\_4 \right)^{1/2} \\ \text{Branch pair 2}: s &= \pm \left( A\_1 + A\_2 - A\_4 \right)^{1/2} \\ \text{Branch pair 3}: s &= \pm \left( -A\_1 + A\_2 + A\_4 \right)^{1/2} \\ \text{Branch pair 4}: s &= \pm \left( -A\_1 + A\_2 - A\_4 \right)^{1/2} \end{aligned} \tag{12}$$

where *gi* and *Ai* are the coefficients and listed in the Appendix. Since *Ai*'s are functions of *n* and Ω, these four branch pairs can be analytically determined once the given values of *n* and Ω are specified.

#### **2.3. Methods to determine the propagating mode pattern**

As mentioned earlier, the solutions regarding the modal patterns (eigenvectors) for all four root branch pairs are important. The conventional method has been frequently used for a long time. In this method, the mode shapes are expressed as the ratios among *U*, *V* and *W*. By returning to Eq.(4) after each of the roots (±*si*, *i*=1 to 4 ) have been found for a given Ω, these ratios can be found by solving any two of the three simultaneous equations. Finally, the third can be discarded. Detail processes can be obtained from Leissa. Because the value of the ratio *U*/*W* or *V*/*W* can become quite large when either *U* or *V* is the predominant component of the mode, this method is not the most convenient and natural way to express the eigenvectors, particularly when eigenfunction expansion is used to solve vibration problems.

A new alternative method, which solves for the eigenvectors by using a commercially available linear algebra package, will be introduced. This method is extremely simple and straightforward. The kernel of processing is by using the built-in formulation of eigenvalue and eigenvector problem in the numerical package.

According to the eigenvalue problem, the eigenvectors can be found by solving the following homogeneous equations, and the simple flow can be introduce by following:

**Step 1.** For a specific frequency, dimensionless frequency, Ω, can be obtained and rewritten as Ω*s*. In this way, eight dimensionless wavenumber, *s*2, can be also found easily from Eqs. (7), (10), or (12). Then the homogeneous equation by substituting any one of *s*2 into Eq. (4) can be obtained as below:

$$
\begin{bmatrix}
\boldsymbol{L}\_{11}^{\*}(\mathsf{s},n)-\boldsymbol{\Omega}\_{s}^{2} & \boldsymbol{L}\_{12}^{\*}(\mathsf{s},n) & \boldsymbol{L}\_{13}^{\*}(\mathsf{s},n) \\
\boldsymbol{L}\_{12}^{\*}(\mathsf{s},n) & \boldsymbol{L}\_{22}^{\*}(\mathsf{s},n)-\boldsymbol{\Omega}\_{s}^{2} & \boldsymbol{L}\_{23}^{\*}(\mathsf{s},n) \\
\boldsymbol{\ast}^{\*} & \boldsymbol{\ast}^{\*} & \boldsymbol{L}\_{23}^{\*}(\mathsf{s},n) & \boldsymbol{L}\_{33}^{\*}(\mathsf{s},n)-\boldsymbol{\Omega}\_{s}^{2} \\
\end{bmatrix}
\begin{bmatrix}
\boldsymbol{U}(\mathsf{s},n,\boldsymbol{\Omega}) \\
\boldsymbol{V}(\mathsf{s},n,\boldsymbol{\Omega}) \\
\boldsymbol{W}(\mathsf{s},n,\boldsymbol{\Omega}) \\
\end{bmatrix} = \begin{bmatrix}
0 \\
0 \\
0 \\
\end{bmatrix} \tag{13}
$$

Dispersion Relations and Modal Patterns of Wave in a Cylindrical Shell 93


D isplacem ent ratio

characteristics and variations of cylindrical shell at specific circumferential number can be

Real Part

Imaginary Part

U V W

**Figure 2.** (a) The dispersion curve for Branch 1 roots; (b) The eigenvectors obtained from the current method expressed as [*U V W*]'; (c) Comparison between the eigenvectors (of Branch 1 roots) obtained

(a) (b) (c)

<sup>0</sup> 0.5 <sup>1</sup> 1.5 <sup>2</sup> 2.5 <sup>3</sup> 3.5 <sup>4</sup> -1

In order to discuss the characteristics of wave propagation in dispersion relations and modal pattern, the numerical results are calculated by assuming the dimensionless thickness parameter, *β*, to be equal to 0.0058, and the Poisson ratio equals to 0.3. According to Karczub and Leissa, for the usual range of parameters and *n*≧1, the roots of Eq.(11) were found to

> 1 : 2 : 3 : 4 :

*TYPE s b TYPE s ib TYPE s c id TYPE s c id*

 

where *b1*, *b2*, *c* and *d* are positive real numbers. The propagating wave of cylindrical shell is dedicated only by Type 1. Type 2 root constitutes no spatially oscillating term, which represents the nearfield distortion close to the boundary. Type 3 and Type 4 roots represent various types of evanescence waves. However, these four types of roots, do not have a oneto-one correspondence with the four branch pairs shown in Eq.(12). For example, in the case of *n*=2, the curve of Branch pair 1 begins as a Type 3 (evanescence waves) and then gradually turns into Type 1 (propagating waves) after crossing its cut-off frequency. When *n*=0 or *n*=1, the curves of branch pair 1 are Type 1 roots (do not have a cut-off frequency),

The dispersion curves for all the roots and the corresponding eigenvectors plotted in the figures shown hereafter are those with positive real parts only. In the case of Type 2 roots which have no real part, only the positive imaginary part will be plotted. The roots with

 

1 2

(16)

<sup>0</sup> 0.5 <sup>1</sup> 1.5 <sup>2</sup> 2.5 <sup>3</sup> 3.5 <sup>4</sup> -0.2

Real(U/W)-Conv. Real(U/W)-Alter. Real(V/W)-Conv. Real(V/W)-Alter. Imag(U/W)-Conv. Imag(U/W)-Alter. Imag(V/W)-Conv. Imag(V/W)-Alter.

obtained clearly and straightforward.

from the conventional and the current methods (*n*=2).

Imag.

Shear Long.

0

W V

U

1 -1

0

1

W U V

and they remain as Type 1 roots for all frequencies.

**3. Result and discussion** 

<sup>0</sup> 0.5 <sup>1</sup> 1.5 <sup>2</sup> 2.5 <sup>3</sup> 3.5 <sup>4</sup> <sup>0</sup>

Real

Real Imag. Plate Long. Shear

Plate

*s*

have the four following types:

where the asterisk in superscript of *Lij* represents that all the coefficients are known.

**Step 2.** After slightly rearranging, Eq.(13) can be further modified as

$$
\begin{bmatrix}
\begin{matrix}
\ast & \ast \\
L\_{11}(s,n) & L\_{12}(s,n)
\end{matrix} & \begin{matrix}
\ast & \ast \\
L\_{12}(s,n) & L\_{22}(s,n)
\end{matrix}
\end{bmatrix}
\begin{matrix}
\mathcal{U}(s,n,\Omega) \\
\mathcal{U}(s,n,\Omega) \\
\mathcal{V}(s,n,\Omega)
\end{matrix} = \mathcal{Q}\_{s}^{-2} \begin{bmatrix}
\mathcal{U}(s,n,\Omega) \\
\mathcal{V}(s,n,\Omega)
\end{bmatrix} \\
\begin{matrix}
\ast & \ast \\
L\_{13}(s,n) & L\_{23}(s,n)
\end{matrix}
\end{bmatrix} = \mathcal{Q}\_{s}^{-2} \begin{bmatrix}
\mathcal{U}(s,n,\Omega) \\
\mathcal{V}(s,n,\Omega)
\end{bmatrix}
\tag{14}
$$

**Step 3.** If Ω<sup>s</sup> 2 is assumed to be unknown for the time being, Eq.(14) can be rewritten to be a typical linear eigenvalue problem and shown as:

$$
\begin{bmatrix} L\_{11}^\*(s,n) & L\_{12}^\*(s,n) & L\_{13}^\*(s,n) \\ \ast & \* & \* \\ L\_{12}(s,n) & L\_{22}(s,n) & L\_{23}(s,n) \\ \ast & \* & \* \\ L\_{13}(s,n) & L\_{23}(s,n) & L\_{33}(s,n) \end{bmatrix} \begin{bmatrix} \mathcal{U}(s,n,\Omega) \\ \mathcal{V}(s,n,\Omega) \\ \mathcal{V}(s,n,\Omega) \\ \mathcal{W}(s,n,\Omega) \end{bmatrix} = 0 \tag{15}
$$

In most cases in Eq. (15), for any given value of *s* (the analytical root), there are three distinct eigenvalues in Ω2 by using the built-in eigenvector function in the numerical package, but only one of them will be equal to Ω<sup>s</sup> 2. Consequently, the eigenvector solution of Eq.(13) is one of the three eigenvectors of Eq.(15), which corresponding eigenvalue is equal to Ω<sup>s</sup> 2. This is because, among the three eigenvalues, only the one that is equal to Ωs will yield the specific *s* given here, the other two will yield different values of *s* and are not what we want. When *s* is specified, the corresponding eigenvector can further calculated by using the numerical solution package, such as MatLab.

#### **2.4. Comparsion between alternative and conventional method for modal pattern**

The dispersion relations were calculated using the thickness-radius factor *β*=0.0058 and the Poisson ratio *v*=0.3. For *n*=2, the dispersion relation and corresponding modal patterns of Branch pairs 1 are obtained in Fig. 2.(a) and 2(b). The consistency of modal patterns between the alternative and conventional method can also be demonstrated in Fig. 2.(c). The physical characteristics and variations of cylindrical shell at specific circumferential number can be obtained clearly and straightforward.

**Figure 2.** (a) The dispersion curve for Branch 1 roots; (b) The eigenvectors obtained from the current method expressed as [*U V W*]'; (c) Comparison between the eigenvectors (of Branch 1 roots) obtained from the conventional and the current methods (*n*=2).

### **3. Result and discussion**

92 Wave Processes in Classical and New Solids

**Step 3.** If Ω<sup>s</sup>

one of *s*2 into Eq. (4) can be obtained as below:

2

*s*

11 12 13

12 22 23 13 23 33

typical linear eigenvalue problem and shown as:

only one of them will be equal to Ω<sup>s</sup>

numerical solution package, such as MatLab.

11 12 13

13 23 33

**Step 2.** After slightly rearranging, Eq.(13) can be further modified as

11 12 13 12 22 23 13 23 33

12 22 23

According to the eigenvalue problem, the eigenvectors can be found by solving the following homogeneous equations, and the simple flow can be introduce by following:

**Step 1.** For a specific frequency, dimensionless frequency, Ω, can be obtained and rewritten as Ω*s*. In this way, eight dimensionless wavenumber, *s*2, can be also found easily from Eqs. (7), (10), or (12). Then the homogeneous equation by substituting any

> \* \*\* (, ) (, ) (, ) , , <sup>0</sup> \*\* \* (, ) (, ) (, ) , , 0 \* \*\* , , <sup>0</sup> (, ) (, ) (, )

\*\*\* (, ) (, ) (, ) , , , , \*\*\* (, ) (, ) (, ) , , , , \*\*\* , , , , (, ) (, ) (, )

*L sn L sn L sn U sn U sn L sn L sn L sn V sn V sn L sn L sn L sn W sn W sn*

\*\*\* (, ) (, ) (, ) , ,

*L sn L sn L sn U sn L sn L sn L sn V sn L sn L sn L sn W sn*

\*\*\* , , (, ) (, ) (, )

\*\*\* (, ) (, ) (, ) , , 0

In most cases in Eq. (15), for any given value of *s* (the analytical root), there are three distinct eigenvalues in Ω2 by using the built-in eigenvector function in the numerical package, but

one of the three eigenvectors of Eq.(15), which corresponding eigenvalue is equal to Ω<sup>s</sup>

This is because, among the three eigenvalues, only the one that is equal to Ωs will yield the specific *s* given here, the other two will yield different values of *s* and are not what we want. When *s* is specified, the corresponding eigenvector can further calculated by using the

**2.4. Comparsion between alternative and conventional method for modal pattern** 

The dispersion relations were calculated using the thickness-radius factor *β*=0.0058 and the Poisson ratio *v*=0.3. For *n*=2, the dispersion relation and corresponding modal patterns of Branch pairs 1 are obtained in Fig. 2.(a) and 2(b). The consistency of modal patterns between the alternative and conventional method can also be demonstrated in Fig. 2.(c). The physical

2

*L sn L sn L sn U sn L sn L sn L sn V sn L sn L sn L sn W sn*

*s*

where the asterisk in superscript of *Lij* represents that all the coefficients are known.

 

> 

2

*s*

 

2. Consequently, the eigenvector solution of Eq.(13) is

(13)

(14)

(15)

2.

2

*s*

 

2 is assumed to be unknown for the time being, Eq.(14) can be rewritten to be a

In order to discuss the characteristics of wave propagation in dispersion relations and modal pattern, the numerical results are calculated by assuming the dimensionless thickness parameter, *β*, to be equal to 0.0058, and the Poisson ratio equals to 0.3. According to Karczub and Leissa, for the usual range of parameters and *n*≧1, the roots of Eq.(11) were found to have the four following types:

$$\begin{aligned} \text{TYPE} - 1 & \quad s = \pm \begin{pmatrix} b\_1 \\ \end{pmatrix} \\ \text{TYPE} - 2 & \quad s = \pm \begin{pmatrix} id\_1 \\ ib\_2 \end{pmatrix} \\ \text{TYPE} - 3 & \quad s = \pm \begin{pmatrix} c + id \end{pmatrix} \\ \text{TYPE} - 4 & \quad s = \pm \begin{pmatrix} c - id \end{pmatrix} \end{aligned} \tag{16}$$

where *b1*, *b2*, *c* and *d* are positive real numbers. The propagating wave of cylindrical shell is dedicated only by Type 1. Type 2 root constitutes no spatially oscillating term, which represents the nearfield distortion close to the boundary. Type 3 and Type 4 roots represent various types of evanescence waves. However, these four types of roots, do not have a oneto-one correspondence with the four branch pairs shown in Eq.(12). For example, in the case of *n*=2, the curve of Branch pair 1 begins as a Type 3 (evanescence waves) and then gradually turns into Type 1 (propagating waves) after crossing its cut-off frequency. When *n*=0 or *n*=1, the curves of branch pair 1 are Type 1 roots (do not have a cut-off frequency), and they remain as Type 1 roots for all frequencies.

The dispersion curves for all the roots and the corresponding eigenvectors plotted in the figures shown hereafter are those with positive real parts only. In the case of Type 2 roots which have no real part, only the positive imaginary part will be plotted. The roots with negative real parts are not plotted; their eigenvectors are basically the same as those of positive real roots, except there will be sign changes in the longitudinal components if the signs of the radial and circumferential components are chosen to be the same as those plotted.

Dispersion Relations and Modal Patterns of Wave in a Cylindrical Shell 95

0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

U

0 0.5 1 1.5 2 2.5 3 3.5 4

Branch1 Branch2 Branch3

Branch1 Branch2 Branch3 Branch4

W

E igenvector

<sup>0</sup> 0.5 <sup>1</sup> 1.5 <sup>2</sup> 2.5 <sup>3</sup> 3.5 <sup>4</sup> <sup>0</sup>

U W

U W

**Figure 4.** The normalized eigenvectors of *n*=0 circular harmonic (no V component)

U

W

0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

E igenvector

**Figure 5.** The dispersion relations for *n*=1 circular harmonic

0 0.5 1 1.5 2 2.5 3 3.5 4

Branch3

Branch4 Shear

Branch1

Branch3

Branch1 Branch2 Branch3 Branch4 Plate Berbeam Long. Shear Timbeam

Plate

0

5

10

15

*s*

20

25

30

Fig. 5 and 6 show the dispersion relations and the associated eigenvectors, respectively, for the *n*=1 circular harmonics. The equivalent curves for Bernoulli beam (labeled as "Berbeam"), Timoshenko beam (labeled as "Timbeam"), and the longitudinal and shear wave curves of a plate are also shown for reference. Branch 1 has only real roots (Type 1 roots); the dispersion curve representing beam bending (when Ω<0.5) agrees well with that of the Timoshenko beam. The Bernoulli beam, on the other hand, agrees with the shell and Timoshenko beam curves only up to Ω=0.03; its applicable frequency range is therefore limited. At frequencies above Ω=0.5, the originally beam-like bending wave gradually transitions to a plate-like bending wave with a predominantly radial modal displacement.

(a) Branch 1 roots (b) Branch 2 roots (c) Branch 3 roots

<sup>0</sup> 0.5 <sup>1</sup> 1.5 <sup>2</sup> 2.5 <sup>3</sup> 3.5 <sup>4</sup> <sup>0</sup>

Below Ω=0.5, the Branch 2 curve is purely imaginary, and represents the Type 2 root. When Ω>0.5, the roots become positive real (Type 1) and gradually approach the shear wave

(a) Real part of the root (b) Imaginary part of the root




0

Branch1 Branch2 Branch3

Branch4

*s*

10

20

30

Branch2

Timbeam

Long. Berbeam

<sup>0</sup> 0.5 <sup>1</sup> <sup>0</sup>

*s*

Branch4

**3.2. The case when** *n***=1** 

<sup>0</sup> 0.5 <sup>1</sup> 1.5 <sup>2</sup> 2.5 <sup>3</sup> 3.5 <sup>4</sup> <sup>0</sup>

U W

U

W

0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

E igenvector

#### **3.1. The case when** *n***=0**

The dispersion relations and the associated eigenvectors are shown in Fig. 3 and 4, respectively. For simplicity, the eigenvectors [*U' V' W'*] are plotted by using the absolute values of the displacement components, i.e., [|*U*| |*V*| |*W*|]'. The dispersion relations for the longitudinal and bending waves of a plate, and those for shear waves are also shown for reference. It shows that at frequencies much lower than the ring frequency (Ω<<1), Branch 1 represents a non-dispersive longitudinal wave, from which it gradually deviates as Ω approaches the neighborhood of unity; Branch 1's wave eventually approaches that of a plate bending wave when Ω>>1. These are illustrated by the mode shapes shown in Fig. 4(a). Below ring frequency, see the mode shape in Fig. 4(b), Branch 2 (Branch pair 2 root with positive real part) represents the Type 4 root, but it becomes a Type 1 root after crossing the ring frequency and represents the longitudinal wave above the ring frequency, say Ω>1. Therefore, when Ω>1, the Branch 2 curve takes over the role of representing the longitudinal wave which was previously the role of Branch 1's curve. Below the ring frequency, Branch 3 (Branch pair 3 root with positive real part) represents the Type 3 root, but above the ring frequency, it represents the Type 2 root. The modal components of the Branch 3 roots are predominantly radial (see Fig. 4(c)). Branch 4 (Branch pair 4 root with positive real part) represents the characteristic roots of Eq. (13), which therefore represents the non-dispersive torsional wave and has nearly the same dispersion relation as shear waves. The mode shape of torsional mode is not shown; it is simply [*U V W*]'=[0 1 0]'.

**Figure 3.** The dispersion relations for *n*=0 circular harmonic

**Figure 4.** The normalized eigenvectors of *n*=0 circular harmonic (no V component)

#### **3.2. The case when** *n***=1**

94 Wave Processes in Classical and New Solids

**3.1. The case when** *n***=0** 

plotted.

negative real parts are not plotted; their eigenvectors are basically the same as those of positive real roots, except there will be sign changes in the longitudinal components if the signs of the radial and circumferential components are chosen to be the same as those

The dispersion relations and the associated eigenvectors are shown in Fig. 3 and 4, respectively. For simplicity, the eigenvectors [*U' V' W'*] are plotted by using the absolute values of the displacement components, i.e., [|*U*| |*V*| |*W*|]'. The dispersion relations for the longitudinal and bending waves of a plate, and those for shear waves are also shown for reference. It shows that at frequencies much lower than the ring frequency (Ω<<1), Branch 1 represents a non-dispersive longitudinal wave, from which it gradually deviates as Ω approaches the neighborhood of unity; Branch 1's wave eventually approaches that of a plate bending wave when Ω>>1. These are illustrated by the mode shapes shown in Fig. 4(a). Below ring frequency, see the mode shape in Fig. 4(b), Branch 2 (Branch pair 2 root with positive real part) represents the Type 4 root, but it becomes a Type 1 root after crossing the ring frequency and represents the longitudinal wave above the ring frequency, say Ω>1. Therefore, when Ω>1, the Branch 2 curve takes over the role of representing the longitudinal wave which was previously the role of Branch 1's curve. Below the ring frequency, Branch 3 (Branch pair 3 root with positive real part) represents the Type 3 root, but above the ring frequency, it represents the Type 2 root. The modal components of the Branch 3 roots are predominantly radial (see Fig. 4(c)). Branch 4 (Branch pair 4 root with positive real part) represents the characteristic roots of Eq. (13), which therefore represents the non-dispersive torsional wave and has nearly the same dispersion relation as shear

waves. The mode shape of torsional mode is not shown; it is simply [*U V W*]'=[0 1 0]'.

Branch4

Branch2 Long.

Branch3

(a) Real parts of the root (b) Imaginary part of the root




0

Branch4 Branch1

Branch3

Branch2

*s*

10

20

30

0 0.5 1 1.5 2 2.5 3 3.5 4

Branch1 Branch2 Branch4

Branch1 Branch2 Branch3 Branch4

**Figure 3.** The dispersion relations for *n*=0 circular harmonic

0 0.5 1 1.5 2 2.5 3 3.5 4

Branch1

Branch3 Shear

Branch2

Branch1 Branch2 Branch3 Branch4 Plate Long. Shear

Plate

0

5

10

15

*s*

20

25

30

Fig. 5 and 6 show the dispersion relations and the associated eigenvectors, respectively, for the *n*=1 circular harmonics. The equivalent curves for Bernoulli beam (labeled as "Berbeam"), Timoshenko beam (labeled as "Timbeam"), and the longitudinal and shear wave curves of a plate are also shown for reference. Branch 1 has only real roots (Type 1 roots); the dispersion curve representing beam bending (when Ω<0.5) agrees well with that of the Timoshenko beam. The Bernoulli beam, on the other hand, agrees with the shell and Timoshenko beam curves only up to Ω=0.03; its applicable frequency range is therefore limited. At frequencies above Ω=0.5, the originally beam-like bending wave gradually transitions to a plate-like bending wave with a predominantly radial modal displacement.

**Figure 5.** The dispersion relations for *n*=1 circular harmonic

Below Ω=0.5, the Branch 2 curve is purely imaginary, and represents the Type 2 root. When Ω>0.5, the roots become positive real (Type 1) and gradually approach the shear wave curve, with a predominantly circumferential displacement component when Ω>1.5 (see Fig. 6(b)). Obviously, this branch has a cut off frequency which is about Ω=0.5.

Dispersion Relations and Modal Patterns of Wave in a Cylindrical Shell 97

0 0.5 1 1.5 2 2.5 3 3.5 4

Branch1 Branch2 Branch3

Branch1 Branch2 Branch3 Branch4

The dispersion relations for the *n*=2 circular harmonic case are shown in Fig. 7. At very low frequencies, say Ω<0.016, the roots in Branch 1 are the Type 3 roots. At higher frequencies, the roots become Type 1 and represent propagating waves (which thus have a cut off frequency at Ω≒0.016). Fig. 8(a) shows that below ring frequency, Ω<1, the modal patterns of Branch 1 roots have three well-coupled displacement components, although the predominant component is radial. When Ω>1, the modal displacement becomes predominantly radial and the propagating speed asymptotically approaches that of a plate.

(a) Real part of the root (b) Imaginary part of the root




0

Branch1 Branch2

Branch4

Real Branch1 Real Branch2 Imag Branch1 Imag Branch2

Branch3

*s*

10

20

30

Shear Branch2

Branch4

Long.

<sup>0</sup> 0.5 <sup>1</sup> <sup>0</sup>

*s*

(c) The dispersion curves of Branch 1 and 2 below Ω=0.02

0 0.002 0.004 0.006 0.008 0.01 0.012 0.014 0.016 0.018 0.02

**3.3. The case when** *n***=2** 

**Figure 7.** The dispersion relations for *n*=2 circular harmonic


0 0.5 1 1.5 2 2.5 3 3.5 4

Branch3

Branch1

Branch3 Branch4

Branch1 Branch2 Branch3 Branch4 Plate Long. Shear

Plate

*s*

0

5

10

15

*s*

20

25

30

Below the ring frequency, the Branch 3 curve indicates a Type 3 root with a slow and exponentially diminishing wave. When Ω>1.4 it becomes a Type 1 root, and the Branch 3 curve approaches that of longitudinal wave (see Fig. 5 and 6(c)) at further higher frequencies. The propagating waves in Branch 3 thus has a cutoff frequency of about Ω=1.4. The Branch 4 curve indicates a Type 4 root below the ring frequency, but above ring frequency it has only the imaginary part (Type 2) and represents the transversal near field distortion (see Fig. 6(d)).

**Figure 6.** The normalized eigenvectors of *n*=1 circular harmonic.

#### **3.3. The case when** *n***=2**

96 Wave Processes in Classical and New Solids

distortion (see Fig. 6(d)).

W

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

E igenvector U V

E igenvector

curve, with a predominantly circumferential displacement component when Ω>1.5 (see Fig.

Below the ring frequency, the Branch 3 curve indicates a Type 3 root with a slow and exponentially diminishing wave. When Ω>1.4 it becomes a Type 1 root, and the Branch 3 curve approaches that of longitudinal wave (see Fig. 5 and 6(c)) at further higher frequencies. The propagating waves in Branch 3 thus has a cutoff frequency of about Ω=1.4. The Branch 4 curve indicates a Type 4 root below the ring frequency, but above ring frequency it has only the imaginary part (Type 2) and represents the transversal near field

(a) Branch 1 roots (b) Branch 2 roots

U V W

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

0 0.1 0.2 0.3 0.4 0.5 0.6 0.7 0.8 0.9 1

(c) Branch 3 roots (d) Branch 4 roots

E igenvector E ig e nvecto r

0 0.5 1 1.5 2 2.5 3 3.5 4

U

V

U V W

W

<sup>W</sup> <sup>U</sup>

V W

0 0.5 1 1.5 2 2.5 3 3.5 4

U V

6(b)). Obviously, this branch has a cut off frequency which is about Ω=0.5.

U V W

**Figure 6.** The normalized eigenvectors of *n*=1 circular harmonic.

0 0.5 1 1.5 2 2.5 3 3.5 4

0 0.5 1 1.5 2 2.5 3 3.5 4

U

V

W

The dispersion relations for the *n*=2 circular harmonic case are shown in Fig. 7. At very low frequencies, say Ω<0.016, the roots in Branch 1 are the Type 3 roots. At higher frequencies, the roots become Type 1 and represent propagating waves (which thus have a cut off frequency at Ω≒0.016). Fig. 8(a) shows that below ring frequency, Ω<1, the modal patterns of Branch 1 roots have three well-coupled displacement components, although the predominant component is radial. When Ω>1, the modal displacement becomes predominantly radial and the propagating speed asymptotically approaches that of a plate.

(c) The dispersion curves of Branch 1 and 2 below Ω=0.02

**Figure 7.** The dispersion relations for *n*=2 circular harmonic

Dispersion Relations and Modal Patterns of Wave in a Cylindrical Shell 99

At very low frequencies, say Ω<0.016, the roots in Branch 2 are the Type 4 roots. Between say Ω=0.016 and the ring frequency, the roots of this branch are Type 2; they represent the near field distortion of the three coupled components. When Ω >1.15, they become Type 1 propagating waves with the wave speeds that asymptotically approach that of the shear wave, and their modal patterns reflect predominantly circumferential shear motions. The curve of Branch 3 indicates a Type 3 root when 0<Ω<1.15, a Type 2 root when 1.15<Ω<2.2, and a Type 1 root when Ω>2.2. This is a propagating wave with a high cutoff frequency (at Ω≒2.2), and at higher frequencies its wave speed approaches asymptotically to that of the longitudinal wave. Branch 4 represents the Type 4 root when 0<Ω≦1.15, which, however, turns into Type 2 and represents the near field

The classic problem of the dispersion of waves in a cylindrical shell had been re-examined with analytical solutions obtained by using a symbolic algebra package. The previous work by Karczub did not include the analytical solutions for the dispersion relations of axisymmetric waves (of circular harmonic order n=0). An axisymmetric wave contains both longitudinal and transverse components; the former are important in the transmission of longitudinal vibration, and the latter are particularly important in acoustics due to their higher acoustic radiation efficiency than the corresponding waves of higher circular harmonic orders (*n*>0). In this way, a complete set of analytical solutions which based on Flügge shell theory is now available for all orders of circular harmonics,

A considerable effort has been expended on the solutions for the modal patterns of all propagating and non-propagating modes, because a complete set of properly normalized eigenvectors is crucial to the solution of the vibration problem of a finite shell under various admissible boundary conditions. The eigenvectors obtained by the conventional method are not conveniently normalized as are those commonly used in mathematical physics. A new alternative method to find normalized eigenvectors with norms equal to unity has been

Use of analytical solutions has demonstrated the capability of a straightforward continuous tracking on the frequency-dependent changes of the root types and of the corresponding modal patterns for each branch of the dispersion curves associated with a particular analytical root. Therefore, a parallel display of the dispersion curves and of the associated modal patterns used in this paper has provided more insight about the wave phenomena in

distortion when Ω>1.15.

**4. Conclusion** 

*n*=0, 1, 2, …, ∞.

proposed and discussed.

a cylindrical shell.

The coefficients in Eq. (11) are listed as follows:

**Appendix** 

**Figure 8.** The normalized eigenvectors of *n*=2 circular harmonic

At very low frequencies, say Ω<0.016, the roots in Branch 2 are the Type 4 roots. Between say Ω=0.016 and the ring frequency, the roots of this branch are Type 2; they represent the near field distortion of the three coupled components. When Ω >1.15, they become Type 1 propagating waves with the wave speeds that asymptotically approach that of the shear wave, and their modal patterns reflect predominantly circumferential shear motions. The curve of Branch 3 indicates a Type 3 root when 0<Ω<1.15, a Type 2 root when 1.15<Ω<2.2, and a Type 1 root when Ω>2.2. This is a propagating wave with a high cutoff frequency (at Ω≒2.2), and at higher frequencies its wave speed approaches asymptotically to that of the longitudinal wave. Branch 4 represents the Type 4 root when 0<Ω≦1.15, which, however, turns into Type 2 and represents the near field distortion when Ω>1.15.
