# Vibration Analysis of Conical Shells by the Improved Fourier Expansion-Based Differential Quadrature Method

Authors: Wanyou Li; Gang Wang; Jingtao Du
Journal: Shock and Vibration
 (2016)

---

## Abstract

An improved Fourier expansion-based differential quadrature (DQ) algorithm is proposed to study the free vibration behavior of truncated conical shells with different boundary conditions. The original function is expressed as the Fourier cosine series combined with close-form auxiliary functions. Those auxiliary functions are introduced to ensure and accelerate the convergence of series expansion. The grid points are uniformly distributed along the space. The weighting coefficients in the DQ method are easily obtained by the inverse of the coefficient matrix. The derivatives in both the governing equations and the boundaries are discretized by the DQ method. Natural frequencies and modal shapes can be easily obtained by solving the numerical eigenvalue equations. The accuracy and stability of this proposed method are validated against the results in the literature and a very good agreement is observed. The centrosymmetric properties of these newly proposed weighting coefficients are also validated. Studies on the effects of semivertex angle and the ratio of length to radius are reported.


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## Body

## 1. Introduction

Conical shells are widely used in various engineering fields, such as aerospace and ship industries. The development of accurate shell theories has been the subject of significant research interest for many years, and a large number of shell theories based on different approximations and assumptions have been proposed. However, more work is focused on the vibration of cylindrical shells compared with the conical shell. Since the conical coordinate system is function of the meridional direction, the equations of motion for conical shells consist of a set of partial differential equations with variable coefficients. Current methods for the free vibration analysis of thin conical shells can be classified as to analytical methods and numerical methods. Saunders et al. [1], Garnet and Kempner [2], Siu [3], and Lim and Liew [4] have studied the free vibration of uniform conical shells by Rayleigh-Ritz method. Ueda [5] analyzed the same problems using the finite element method. Irie et al. [6] studied a conical shell with variable thickness by the transfer matrix method. The DQ method was employed to analyze the free vibration of a uniform conical shell [7]. Jin et al. [8] studied the free and forced vibration of conical shell using the improved Fourier series method by considering the general boundary conditions. The kernel particle (k-p) functions were employed in hybridized form with harmonic functions to study the vibration of the conical shell based on Ritz method [9].Besides the studies of the isotropic conical shells, laminated and functional graded conical shells have also been fully studied by various methods [10–16]. The differential quadrature (DQ) method was adopted to solve the differential governing equations of the conical shell in those researches [10–13]. For the vibration of the rotating conical shell, in which the centrifuge force should be taken into consideration, the DQ method was also extensively used to study those problems [10, 17]. The reason that the DQ method is widely adopted to study the vibration behavior of the conical shell is the convenience of transforming the partial differential governing equations approximately into a set of linear algebraic governing equations. Imposing the given boundary conditions, the numerical eigenvalue equations for the free vibration of the (rotating or composite) conical shell are derived and solved.The differential quadrature method is a numerical technique for solving the differential equations. It was first developed by Bellman et al. [18, 19] and their associates in the early 1970s. The DQ method, akin to the conventional integral quadrature method, approximates the derivative of a function at any location by a linear summation of all the functional values along a mesh line. The key procedure in the DQ method applications lies in the determination of the weighting coefficients. Shu [7, 12, 20, 21] proposed two types of weighting coefficients obtained by the polynomials and the truncated Fourier series, among which the Lagrange interpolation functions are widely used for their simplicity explicitness [7, 21]. Although it is well known that Lagrange interpolation functions are limited by the number of interpolation points and severe oscillation may take place if the order is large, the use of the Gauss-Chebyshev points [7, 21] can accelerate the convergence rate of the DQ method. Some works focusing on improving the accuracy and stability of the DQ method are presented by proposing different ways to generate the weighting coefficients and to determine the distribution of grid points [22–24].The Fourier series with auxiliary functions was first proposed by Li [25] to study the vibration problems of the beam structure. This method is extensively used to study the 2D and 3D structural vibration and vibroacoustic problems [26–30]. The auxiliary functions are introduced to accelerate the convergence and deal with all the possible discontinuities, at the end points or edges, associated with the original Fourier cosine series. This improved Fourier series method becomes a promising method to study the structural vibration problems.In this paper, the improved Fourier expansion-based differential quadrature method is proposed to solve the free vibration behavior of the truncated conical shell. The weighting coefficients are obtained based on this improved Fourier series in a much easier way. The centrosymmetric properties of these newly proposed weighting coefficients are also validated. The following sections will illustrate the development of this hybrid method, and numerical results are then presented to validate the effectiveness, accuracy, and stability of this current method on predicting the modal characteristics of the conical shell.


## 2. Theoretical Formulation

For a continuous functionf(x) defined on [0,L] with an absolutely integrable derivative, it can be expanded in Fourier cosine series:(1)fx=∑m=0∞amcos⁡mπLx,0<x<L.The first-order derivative off(x) can be done term-by-term:(2)f′x=-∑m=0∞ammπLsin⁡mπLx.The second-order derivative off(x) cannot be obtained term-by-term, which is shown as(3)f′′x=-f′L-f′0L-∑m=1∞2L-1mfL-f0+mπLammπLcos⁡mπLx.These formulations basically tell that while a cosine series can always be differentiated term-by-term, this can be done to a sine series only iff′(0)=f′(L)=0. To implement the differential quadrature algorithm, the auxiliary functions are added to traditional Fourier cosine series to cover the discontinuity of the function at the end points and to get the derivatives term-by-term. A function can be expanded as [27](4)fx=∑m=0∞amcos⁡mπLx+∑t=14Ctξtx,where(5a)ξ1x=9L4πsin⁡πx2L-L12πsin⁡3πx2L(5b)ξ2x=-9L4πcos⁡πx2L-L12πcos⁡3πx2L(5c)ξ3x=L3π3sin⁡πx2L-L33π3sin⁡3πx2L(5d)ξ4x=-L3π3cosπx2L-L33π3cos3πx2L,where am and Ct represent the unknown Fourier expansion coefficients. The supplementary functions ξt(x) can be represented as arbitrary continuous functions, regardless of the boundaries. It is easy to verify that ξ1′(0)=ξ3′′′(0)=ξ2′′(0)=ξ4′′′(0)=1 and all the other 1st-order and 3rd-order derivatives are identically equal to zero at both ends. The main purpose of introducing these supplementary functions to standard Fourier series is to get the first four derivatives of the Fourier cosine series term-by-term. As an immediate numerical benefit, the Fourier series in (4) will converge uniformly at an accelerated rate.To implement the differential quadrature method,N points are equally distributed on [0,L]: (6)xi=i-1LN-1,i=1,2,3,…,N.The functional values at those grid points can be determined as(7)fxi=∑m=0∞amcos⁡mπLxi+∑t=14Ctξtxi.The Fourier series is truncated tom=M. Rewrite (7) into the matrix form (8)
f
x
1
f
x
2
⋮
f
x
N
=
cos
⁡
0
π
L
x
1
c
o
s
1
π
L
x
1
⋯
cos
⁡
M
π
L
x
1
ξ
1
x
1
ξ
2
x
1
ξ
3
x
1
ξ
4
x
1
cos
⁡
0
π
L
x
2
c
o
s
1
π
L
x
2
⋯
cos
⁡
M
π
L
x
2
ξ
1
x
2
ξ
2
x
2
ξ
3
x
2
ξ
4
x
2
⋮
⋮
⋱
⋮
⋮
⋮
⋮
⋮
cos
⁡
0
π
L
x
N
c
o
s
1
π
L
x
N
⋯
cos
⁡
M
π
L
x
N
ξ
1
x
N
ξ
2
x
N
ξ
3
x
N
ξ
4
x
N
a
0
a
1
⋮
a
M
C
1
C
2
C
3
C
4
.The Fourier series coefficients can be obtained by the inverse of the matrix(9)a0a1⋮aMC1C2C3C4=R-1fx1fx2⋮fxN,in which(10)
R
=
c
o
s
0
π
L
x
1
c
o
s
1
π
L
x
1
⋯
c
o
s
M
π
L
x
1
ξ
1
x
1
ξ
2
x
1
ξ
3
x
1
ξ
4
x
1
c
o
s
0
π
L
x
2
c
o
s
1
π
L
x
2
⋯
c
o
s
M
π
L
x
2
ξ
1
x
2
ξ
2
x
2
ξ
3
x
2
ξ
4
x
2
⋮
⋮
⋱
⋮
⋮
⋮
⋮
⋮
c
o
s
0
π
L
x
N
c
o
s
1
π
L
x
N
⋯
c
o
s
M
π
L
x
N
ξ
1
x
N
ξ
2
x
N
ξ
3
x
N
ξ
4
x
N
.In this proposed method, the number of truncated Fourier series and the number of grid points follow the relation thatN=M+5 to ensure R is a square matrix to let the inverse be more accurate. Once the constant matrix R is determined, the approximated Fourier series coefficients are obtained. When the DQ method was first developed, polynomials were adopted to follow this procedure to generate weighting coefficients which would lead to highly ill condition when N is large. The Fourier series, however, show much more stability to derive the coefficients by the inversion of R which will be validated in the results section.The first-order derivatives at those grid points are(11)f′xi=∑m=0Mam-mπLsin⁡mπLxi+∑t=14Ctξt′xi,i=1,2,3,…,N.Rewrite (11) into the matrix form, (12)f′x1f′x2⋮f′xN=R1∗a0a1⋮aMC1C2C3C4=R1∗R-1∗fx1fx2⋮fxN=c1∗fx1fx2⋮fxN,in which R(1) is the first-order derivative of R and c(1) is the first-order weighting coefficient matrix of the DQ method: c(1)=R(1)∗R-1. It is obvious from the above equation that the weighting coefficients of the second- and higher-order derivatives can be completely determined through the same way, which are expressed as (13)fix1fix2⋮fixN=Ri∗R-1∗fx1fx2⋮fxN=ci∗fx1fx2⋮fxN,in which R(i) (i=1,2,3,4) is the ith-order derivative of R and c(i) is the ith-order weighting coefficient matrix of the DQ method: c(i)=R(i)∗R-1.In this paper, only four supplementary functions are added to the Fourier cosine series, which will ensure the first-four-order derivatives to converge at a high rate and to keep stability of the Fourier series. Consequently first-four-order weighting coefficient matrixes can be obtained which are sufficiently enough to study the vibration of a conical shell. Adding more supplementary functions to the Fourier cosine series will give the capability to study the corresponding higher-order partial differential equations.


## 3. Free Vibration Behavior of a Conical Shell

The free vibration behavior of conical shells has been studied by Shu [7] by the DQ method. This model is adopted again to validate the efficiency, accuracy, and stability of this proposed method.Consider a conical shell structure with semivertex anglea and the radius of the large edge is R0, as shown in Figure 1. The displacement fields of the conical shell in x, θ, and r directions are denoted by u, v, and w, respectively. If the couplings between these three displacement components are ignored, the field functions can be expressed as(14)u=Ux·cos⁡nθcos⁡ωt,v=Vx·sin⁡nθcos⁡ωt,w=Wx·cos⁡nθcos⁡ωt,in which n and ω are the circumferential wave number and the frequency in rad/sec, respectively.Figure 1
Geometry of a conical shell and the coordinate system.The differential governing equations of the conical shell based upon Flügge theory are written as(15)L11u+L12v+L13w=-ρhω2U,L21u+L22v+L23w=-ρhω2V,L31u+L32v+L33w=-ρhω2W,in which ρ and h denote the density of the shell and the shell thickness, respectively. The differential operators Lij (i,j=1,2,3) can be referred to [7].Substituting (14) into (15) and applying (13), then (16a)S110Ui+∑k=1NS111cik1+S112cik2Uk+S120Vi+∑k=1NS121cik1Vk+S130Wi+∑k=1NS131cik1Wk=-ρhω2Ui(16b)S210Ui+∑k=1NS211cik1Uk+S220Vi+∑k=1NS221cik1+S222cik2Vk+S230Wi+∑k=1NS231cik1+S232cik2Wk=-ρhω2Vi(16c)S310Ui+∑k=1NS311cik1Uk+S320Vi+∑k=1NS321cik1+S322cik2Vk+S330Wi+∑k=1NS331cik1+S232cik2+S333cik3+S334cik4Wk=-ρhω2Wi,where cij(n) represents the weighting coefficients, i=3,4,…,N-2.The boundary conditions for the conical shell are as follows:simple-supported boundary condition (S):(17)V=0,W=0,Nx=0,Mx=0,clamped boundary condition (C):(18)V=0,W=0,U=0,W1=0.The boundary conditions can also be expressed in the differential forms by substituting (13) into them. Simple supported condition at the small edge is chosen as an example:(19a)V1=0(19b)W1=0(19c)vsin⁡aR1+c111U1+c1N1UN=-∑k=2N-1c1k1Uk(19d)vsin⁡aR1c121+c122W2+vsin⁡aR1c1N-11+c1N-12WN-1=-∑k=3N-2c1k2+vsin⁡aR2c1k1Wk.Other boundary conditions can also be formulated in similar forms. Those four boundary formulations are applied at the grid points ofi=1,2,N-2,N. Rewrite (16a), (16b), (16c), (19a), (19b), (19c), (19d), and boundary conditions into the matrix form(20)PX=ΩX,where Ω=ρhω2, P is a matrix with the dimension of 3N×3N, and(21)X=U1,U2,…,UN,V1,V2,…,VN,W1,W2,…,WNT.It is clear from (20) that the natural frequencies and modal shapes for the conical shell can now be directly obtained by solving the standard matrix eigenvalue problem. The natural frequency parameter is defined as(22)Ωi=R0ωiρ1-v2E.


## 4. Numerical Results and Discussion

### 4.1. Convergence Study

To study the convergence of this proposed method, different numbers of grid points or truncated Fourier series (N=M+5) are selected. The geometric and material parameters of the conical shell are Young’s modulus E=70 GPa, Poisson’s ratio v=0.3, ρ=2700 kg/m3, h/R0=0.01, a = 45°, and Lsin⁡a/R0=0.5. The effect of the number of grid points that affects the natural frequencies is studied. The results derived by finite element method (FEM) are adopted to compare with those obtained by this method. Figure 2 shows the natural frequency parameters under S-S boundary conditions when the circumferential wave number is n=0 and axial number is m=1,2,3. Figure 3 shows the natural frequency parameter under S-C boundary condition when the circumferential wave number is n=3 and axial number is m=1,2,3. By comparing the results derived by this method and FEM, the fast convergence behavior and high stability of this method are observed. The natural frequency parameters keep stable even with a large number of grid points. In the following calculation, the number of grid points will be chosen as N=30.Figure 2
Natural frequency parameters under S-S boundary conditions (n=0, m=1,2,3).Figure 3
Natural frequency parameters under S-C boundary conditions (n=3, m=1,2,3).


### 4.2. Validation of This Proposed Method

To validate the accuracy of the present method, an example reported by Irie et al. [6] and Shu [7] is adopted again. Shu [7] studied the free vibration behavior of this problem by the DQ method, in which Lagrange interpolation functions and Gauss-Chebyshev points are employed. The geometric parameters are a=45°, Lsin⁡a/R0=0.5, and h/R0=0.01. Table 1 shows the comparison between current natural frequency parameters and results studied by Irie et al. [6] and Shu [7] for the conical shells with C-C, S-S, F-C, and F-S boundary conditions. The small discrepancies show a good agreement. Figures 4 and 5 show some selected modal shapes of the conical shell with different parameters.Table 1
Comparison of the natural frequency parameters under variable circumferential wave numbers (a=45°, Lsin⁡a/R2=0.5, and h/R0=0.01).
n
C-C
S-S
F-C
F-S
Present
Shu [7]
Irie et al. [6]
Present
Shu [7]
Irie et al. [6]
Present
Irie et al. [6]
Present
Irie et al. [6]
0
0.8731
0.8732
0.8731
0.2234
0.2233
0.2233
0.8696
0.8696
0.1435
0.1441
1
0.8120
0.8120
0.8120
0.5460
0.5463
0.5462
0.7634
0.7634
0.1660
0.1667
2
0.6696
0.6696
0.6696
0.6307
0.6310
0.6310
0.5289
0.5292
0.1152
0.1158
3
0.5430
0.5428
0.5430
0.5063
0.5062
0.5065
0.363
0.3637
0.1007
0.1017
4
0.4568
0.4566
0.4570
0.3944
0.3942
0.3947
0.2818
0.2829
0.1467
0.1474
5
0.4092
0.4089
0.4095
0.3341
0.3340
0.3348
0.2767
0.2779
0.2089
0.2093
6
0.3965
0.3963
0.3970
0.3239
0.3239
0.3248
0.3184
0.3196
0.2729
0.2743
7
0.4144
0.4143
0.4151
0.3512
0.3514
0.3524
0.3762
0.3775
0.3345
0.3361
8
0.4569
0.4568
0.4577
0.4019
0.4023
0.4033
0.4398
0.4411
0.3970
0.3985
9
0.5177
0.5177
0.5186
0.4670
0.4676
0.4684
0.5103
0.5116
0.4655
0.4670Figure 4
Modal shapes of the conical shell under S-S boundary conditions.
(a)
n
=
1, m=2
(b)
n
=
2, m=2
(c)
n
=
4, m=3Figure 5
Modal shapes of the conical shell under F-C boundary conditions.
(a)
n
=
3, m=1
(b)
n
=
3, m=2
(c)
n
=
3, m=4


### 4.3. Effects of the Auxiliary Functions

To study the advantage of introducing the auxiliary functions, the weighting coefficients obtained without auxiliary functions are adopted to study the eigenvalue problems. The constant matrixR without the auxiliary functions can be rewritten as(23)
R
c
o
s
=
c
o
s
0
π
L
x
1
c
o
s
1
π
L
x
1
⋯
c
o
s
M
π
L
x
1
c
o
s
0
π
L
x
2
c
o
s
1
π
L
x
2
⋯
c
o
s
M
π
L
x
2
⋮
⋮
⋱
⋮
c
o
s
0
π
L
x
N
c
o
s
1
π
L
x
N
⋯
c
o
s
M
π
L
x
N
.The weighting coefficient matrix is then derived in the same way as (13):(24)ccosi=Rcosi∗Rcos-1,in which ccos(i) is the ith-order weighting coefficient matrix and Rcos(i) is the ith-order derivative of Rcos. By using this type of weighting coefficients, natural frequency parameters are derived again to compare with the results obtained before. Table 2 shows the frequency comparison between the results derived by these two types of weighting coefficients. The number of grid points is chosen as N=35. It is clear that the introduction of auxiliary functions will improve the accuracy of this method.Table 2
Natural frequency parameters under different boundary conditions obtained by two types of weighting coefficients (n=0, m=0).
F-S
S-S
F-C
With auxiliary functions
0.1435
0.2234
0.8696
Without auxiliary functions
0.8442
0.8772
0.8403
Irie et al. [6]
0.1441
0.2233
0.8696


### 4.4. Relation between the Numbers of Truncated Fourier Series and Grid Points

For the study above, the numbers of truncated Fourier series and grid points follow the relation thatN=M+5 to ensure that R is a square matrix. It is well known that pseudoinverse of R could also be adopted to derive weighting coefficients even when N≠M+5. Figure 6 shows the natural frequency parameters when M is set to M=30 and N=10–100. It is clear that only if N=35, that is, N=M+5, the accurate results could be obtained. To implement this method, the relation between the numbers of truncated Fourier series and grid points should be strictly set to N=M+5.Figure 6
Natural frequency parameters derived by different numbers of grid points whenM=30 ((a) C-C, (b) F-S).
(a)
C-C
(b)
F-S


### 4.5. The Centrosymmetric Properties of the Weighting Coefficients

When DQ method was developed, the centrosymmetric and skew centrosymmetric properties were observed shown as [21](25)ci=ci-1∗c1.Equation (25) shows that the DQ weighting coefficient matrix is skew centrosymmetric for odd derivatives (i is odd) and centrosymmetric for even order derivatives (i is even) when the grid distribution is symmetric with respect to the center point. This conclusion is true for both uniform and nonuniform grids.In this proposed method, the centrosymmetric properties are also validated. Two types of weighting coefficients calculated in different ways are employed to study the eigenvalue problems; those are(26)ci=Ri∗R-1,(27)ci=ci-1∗c1.To implement (27), c(1) is first derived based on (26). Table 3 shows the natural frequency parameters obtained by these two types of weighting coefficients. The small discrepancies between these two results show a good agreement. It is concluded that the weighting coefficient matrix derived by this proposed method also obeys the centrosymmetric property.Table 3
Natural frequency parameters obtained by employing (26) and (27) (n=0, m=0).
F-C
C-C
F-S
By employing (27)
0.8689
0.8730
0.1440
By employing (26)
0.8689
0.8731
0.1435
Irie et al. [6]
0.8689
0.8731
0.1441


### 4.6. Effects of Geometric Parameters

The geometric parameters play an important role in affecting the natural frequencies of a conical shell. In this part, two parameters are studied to study their effects on the free vibration behavior of the conical shells. Figure7 shows the natural frequency parameters changing with variable ratio of length to radius of the conical shell under C-C and F-C boundary conditions. The geometric parameters are chosen as a=45°, h/R2=0.01, and variable Lsin⁡a/R0=0.5–0.9. The frequency parameters nearly keep constant when n=0 as increasing the ratio of length to radius. The frequency parameters decrease when n=1,2, except for the case of n=2 for F-C boundary conditions. Next, the effect of semivertex angle is studied with the geometric parameters h/R0=0.01, Lsin⁡a/R0=0.5, and variable semivertex angle a = 30°–90°. Figure 8 shows the natural frequency parameters of different circumferential wave numbers. As semivertex angle increasing to 90°, the frequencies converge to one value. This phenomenon can be explained by the fact that the conical shell degenerates to a circular plate when semivertex angle is 90°.Figure 7
Natural frequency parameters for the conical shell with variation of length to radius (a=45°, h/R2=0.01; (a) C-C, (b) F-C).
(a)
(b)Figure 8
Natural frequency parameters of the conical shell with the variation of semivertex angle (h/R2=0.01, Lsin⁡a/R2=0.5; (a) S-S, (b) S-C).
(a)
(b)


## 4.1. Convergence Study

To study the convergence of this proposed method, different numbers of grid points or truncated Fourier series (N=M+5) are selected. The geometric and material parameters of the conical shell are Young’s modulus E=70 GPa, Poisson’s ratio v=0.3, ρ=2700 kg/m3, h/R0=0.01, a = 45°, and Lsin⁡a/R0=0.5. The effect of the number of grid points that affects the natural frequencies is studied. The results derived by finite element method (FEM) are adopted to compare with those obtained by this method. Figure 2 shows the natural frequency parameters under S-S boundary conditions when the circumferential wave number is n=0 and axial number is m=1,2,3. Figure 3 shows the natural frequency parameter under S-C boundary condition when the circumferential wave number is n=3 and axial number is m=1,2,3. By comparing the results derived by this method and FEM, the fast convergence behavior and high stability of this method are observed. The natural frequency parameters keep stable even with a large number of grid points. In the following calculation, the number of grid points will be chosen as N=30.Figure 2
Natural frequency parameters under S-S boundary conditions (n=0, m=1,2,3).Figure 3
Natural frequency parameters under S-C boundary conditions (n=3, m=1,2,3).


## 4.2. Validation of This Proposed Method

To validate the accuracy of the present method, an example reported by Irie et al. [6] and Shu [7] is adopted again. Shu [7] studied the free vibration behavior of this problem by the DQ method, in which Lagrange interpolation functions and Gauss-Chebyshev points are employed. The geometric parameters are a=45°, Lsin⁡a/R0=0.5, and h/R0=0.01. Table 1 shows the comparison between current natural frequency parameters and results studied by Irie et al. [6] and Shu [7] for the conical shells with C-C, S-S, F-C, and F-S boundary conditions. The small discrepancies show a good agreement. Figures 4 and 5 show some selected modal shapes of the conical shell with different parameters.Table 1
Comparison of the natural frequency parameters under variable circumferential wave numbers (a=45°, Lsin⁡a/R2=0.5, and h/R0=0.01).
n
C-C
S-S
F-C
F-S
Present
Shu [7]
Irie et al. [6]
Present
Shu [7]
Irie et al. [6]
Present
Irie et al. [6]
Present
Irie et al. [6]
0
0.8731
0.8732
0.8731
0.2234
0.2233
0.2233
0.8696
0.8696
0.1435
0.1441
1
0.8120
0.8120
0.8120
0.5460
0.5463
0.5462
0.7634
0.7634
0.1660
0.1667
2
0.6696
0.6696
0.6696
0.6307
0.6310
0.6310
0.5289
0.5292
0.1152
0.1158
3
0.5430
0.5428
0.5430
0.5063
0.5062
0.5065
0.363
0.3637
0.1007
0.1017
4
0.4568
0.4566
0.4570
0.3944
0.3942
0.3947
0.2818
0.2829
0.1467
0.1474
5
0.4092
0.4089
0.4095
0.3341
0.3340
0.3348
0.2767
0.2779
0.2089
0.2093
6
0.3965
0.3963
0.3970
0.3239
0.3239
0.3248
0.3184
0.3196
0.2729
0.2743
7
0.4144
0.4143
0.4151
0.3512
0.3514
0.3524
0.3762
0.3775
0.3345
0.3361
8
0.4569
0.4568
0.4577
0.4019
0.4023
0.4033
0.4398
0.4411
0.3970
0.3985
9
0.5177
0.5177
0.5186
0.4670
0.4676
0.4684
0.5103
0.5116
0.4655
0.4670Figure 4
Modal shapes of the conical shell under S-S boundary conditions.
(a)
n
=
1, m=2
(b)
n
=
2, m=2
(c)
n
=
4, m=3Figure 5
Modal shapes of the conical shell under F-C boundary conditions.
(a)
n
=
3, m=1
(b)
n
=
3, m=2
(c)
n
=
3, m=4


## 4.3. Effects of the Auxiliary Functions

To study the advantage of introducing the auxiliary functions, the weighting coefficients obtained without auxiliary functions are adopted to study the eigenvalue problems. The constant matrixR without the auxiliary functions can be rewritten as(23)
R
c
o
s
=
c
o
s
0
π
L
x
1
c
o
s
1
π
L
x
1
⋯
c
o
s
M
π
L
x
1
c
o
s
0
π
L
x
2
c
o
s
1
π
L
x
2
⋯
c
o
s
M
π
L
x
2
⋮
⋮
⋱
⋮
c
o
s
0
π
L
x
N
c
o
s
1
π
L
x
N
⋯
c
o
s
M
π
L
x
N
.The weighting coefficient matrix is then derived in the same way as (13):(24)ccosi=Rcosi∗Rcos-1,in which ccos(i) is the ith-order weighting coefficient matrix and Rcos(i) is the ith-order derivative of Rcos. By using this type of weighting coefficients, natural frequency parameters are derived again to compare with the results obtained before. Table 2 shows the frequency comparison between the results derived by these two types of weighting coefficients. The number of grid points is chosen as N=35. It is clear that the introduction of auxiliary functions will improve the accuracy of this method.Table 2
Natural frequency parameters under different boundary conditions obtained by two types of weighting coefficients (n=0, m=0).
F-S
S-S
F-C
With auxiliary functions
0.1435
0.2234
0.8696
Without auxiliary functions
0.8442
0.8772
0.8403
Irie et al. [6]
0.1441
0.2233
0.8696


## 4.4. Relation between the Numbers of Truncated Fourier Series and Grid Points

For the study above, the numbers of truncated Fourier series and grid points follow the relation thatN=M+5 to ensure that R is a square matrix. It is well known that pseudoinverse of R could also be adopted to derive weighting coefficients even when N≠M+5. Figure 6 shows the natural frequency parameters when M is set to M=30 and N=10–100. It is clear that only if N=35, that is, N=M+5, the accurate results could be obtained. To implement this method, the relation between the numbers of truncated Fourier series and grid points should be strictly set to N=M+5.Figure 6
Natural frequency parameters derived by different numbers of grid points whenM=30 ((a) C-C, (b) F-S).
(a)
C-C
(b)
F-S


## 4.5. The Centrosymmetric Properties of the Weighting Coefficients

When DQ method was developed, the centrosymmetric and skew centrosymmetric properties were observed shown as [21](25)ci=ci-1∗c1.Equation (25) shows that the DQ weighting coefficient matrix is skew centrosymmetric for odd derivatives (i is odd) and centrosymmetric for even order derivatives (i is even) when the grid distribution is symmetric with respect to the center point. This conclusion is true for both uniform and nonuniform grids.In this proposed method, the centrosymmetric properties are also validated. Two types of weighting coefficients calculated in different ways are employed to study the eigenvalue problems; those are(26)ci=Ri∗R-1,(27)ci=ci-1∗c1.To implement (27), c(1) is first derived based on (26). Table 3 shows the natural frequency parameters obtained by these two types of weighting coefficients. The small discrepancies between these two results show a good agreement. It is concluded that the weighting coefficient matrix derived by this proposed method also obeys the centrosymmetric property.Table 3
Natural frequency parameters obtained by employing (26) and (27) (n=0, m=0).
F-C
C-C
F-S
By employing (27)
0.8689
0.8730
0.1440
By employing (26)
0.8689
0.8731
0.1435
Irie et al. [6]
0.8689
0.8731
0.1441


## 4.6. Effects of Geometric Parameters

The geometric parameters play an important role in affecting the natural frequencies of a conical shell. In this part, two parameters are studied to study their effects on the free vibration behavior of the conical shells. Figure7 shows the natural frequency parameters changing with variable ratio of length to radius of the conical shell under C-C and F-C boundary conditions. The geometric parameters are chosen as a=45°, h/R2=0.01, and variable Lsin⁡a/R0=0.5–0.9. The frequency parameters nearly keep constant when n=0 as increasing the ratio of length to radius. The frequency parameters decrease when n=1,2, except for the case of n=2 for F-C boundary conditions. Next, the effect of semivertex angle is studied with the geometric parameters h/R0=0.01, Lsin⁡a/R0=0.5, and variable semivertex angle a = 30°–90°. Figure 8 shows the natural frequency parameters of different circumferential wave numbers. As semivertex angle increasing to 90°, the frequencies converge to one value. This phenomenon can be explained by the fact that the conical shell degenerates to a circular plate when semivertex angle is 90°.Figure 7
Natural frequency parameters for the conical shell with variation of length to radius (a=45°, h/R2=0.01; (a) C-C, (b) F-C).
(a)
(b)Figure 8
Natural frequency parameters of the conical shell with the variation of semivertex angle (h/R2=0.01, Lsin⁡a/R2=0.5; (a) S-S, (b) S-C).
(a)
(b)


## 5. Conclusions

In this paper, a new method is proposed to generate the weighting coefficients of the DQ method. The functions in the DQ method are expressed as the Fourier cosine series combined with close-form auxiliary functions. The weighting coefficients are directly derived by the inverse of the constant matrix which presents a much easier way. The boundary conditions and differential governing equations are discretized to form the numerical eigenvalue equations. The results obtained by this method are compared with those available in the literature and a good agreement is observed. The centrosymmetric properties of these newly proposed weighting coefficients are also validated. By increasing the number of grid points, the efficiency and high stability are presented in this method. The effect of those parameters which may affect the dynamic characteristics of the shell is also studied.This method gives a much easier way to generate weighting coefficients in DQ algorithm. It can also be extended to study higher-order partial differential equations just by adding more corresponding supplementary functions to the Fourier cosine series.



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*Source: 9617957-2015-12-24.xml*