Research Article  Open Access
Nonlinear Dynamic Modeling and Model Reduction Strategy for Rotating Thin Cylindrical Shells
Abstract
Nonlinear dynamic modeling and model reduction strategy are studied in this paper for a rotating thin cylindrical shell. The nonlinear dynamic model is first established in terms of ordinary differential equations, in which the effects of Coriolis and centrifugal forces are considered, as well as the initial hoop tension due to rotation. This model describes both the inplane vibrations and the flexural vibration and reflects the coupling effects of those deformations. Based on this original model, a novel model reduction strategy is proposed to reduce the degrees of freedom by neglecting vibration modes predominated by inplane vibrations. Meanwhile, for the reducedorder model, the inplane vibrations’ contributions to the rotating shell’s response are still preserved. To validate the dynamic model and the model reduction strategy, comparisons and simulations are carried out. Subsequently, nonlinear dynamic behaviors are investigated preliminarily by analyzing the rotating cylindrical shell’s amplitudefrequency responses under different excitation levels.
1. Introduction
Rotating thin cylindrical shells have been widely used in engineering applications, such as rotors of aircraft engines, rotating satellite structures, and highspeed centrifugal separators. Their large vibration amplitudes can be easily excited in engineering. Hence the nonlinear shell theory instead of linear one should be applied, and it is of practical importance to carry out nonlinear dynamic studies on thin rotating cylindrical shells.
Saito et al. [1], Zohar et al. [2], and Huang et al. [3] conducted the early studies for the rotating cylinders. The travellingmodes phenomenon was reported in those researches. Also they systematically analyzed the effects of centrifugal and Coriolis forces. Subsequently, some researchers proposed several analytical and numerical methods to study the dynamic characteristics of rotating shells, such as Fourier series expansion approach [4], wave propagation method [5], discrete singular convolution method [6, 7], harmonic reproducing kernel particle approach [8], Rayleigh–Ritz technique [9], and finite element method [10]. In recent years, due to the wide application of composite materials in lots of engineering fields, the dynamic behaviors of rotating composite shells are studied in numerous published articles [11, 12]. Mehrparvar et al. [13] and Malekzadeh et al. [14] studied functional graded rotating cylindrical shells’ vibration behaviors. Liu et al. [15] analyzed the dynamic characteristics of rotating shells with ringers. Song et al. [16] carried out studies on rotating crossply laminated cylindrical shells. The knowledge of rotating cylindrical shells has been steadily improved by those researches.
A monograph has been published by Amabili et al. [17] to investigate both theoretical and experimental aspects of nonlinear vibrations of cylindrical shells. As summarized in this monograph, Chu [18] and Evensen [19] conducted early studies related to the cylindrical shell’s largeamplitude vibration. After that, many extensive studies have been carried out which are about the classic thin cylindrical shell’s general theories. And now the research interests of many scholars are developing theories and approaches to study the nonlinear vibration of laminated cylindrical shells [20–25], nanotubereinforced composite material [26], and functionally graded material [27–33]. Moreover, some studies have been carried out on modeling and simulation. In particular, Hasrati et al. [34] developed a numerical solution strategy (variational differential quadrature, VDQ) to solve nonlinear free and forced vibration problems of cylindrical shells. They also systematically studied the nonlinear dynamic characteristics of FGCNTRC shells and plates with this method [35–39]. Based on the perturbation procedure and proper orthogonal decomposition, Goncalves et al. [40] proposed lowdimensional modes for the nonlinear vibration analysis of cylindrical shells.
Recently, the nonlinear vibration of rotating cylindrical shells has attracted the researchers’ attentions. Wang et al. [41, 42] studied rotating cylindrical shells’ nonlinear dynamic characteristics and the nonlinear vibrations of a rotating laminated composite cylindrical shell [43]. Liu et al. [44] analyzed the influences of damping, excitation, and nonlinearity on rotating shells’ frequency responses. Han et al. [45] studied the thin cylinder’s parametric instability whose rotating speed is periodically timevarying. Nevertheless, researches related to rotating cylindrical shells’ nonlinear vibrations are still extremely limited. To the authors’ knowledge, none of the previous studies have given the nonlinear dynamic model which could reflect the coupling of flexural vibration and the vibrations in plane (i.e., the longitudinal and torsional vibrations). In [46], the authors derived a nonlinear model containing those three vibrations of a rotating shell and investigated the nonlinear travelling wave vibrations. However, this model may have defects in some cases because the quadratic nonlinear terms are not contained in the dynamic equations. Moreover, in order to facilitate the investigations of rotating cylindrical shells’ nonlinearities, most scholars neglected all inertia terms along inplane directions to derive simplified governing equations, which means the contributions of inplane vibrations to the dynamic response are discarded directly. However, it is a question whether the system described by this simplified governing equations can retain the characteristics of nonlinear vibration, especially the lowfrequency characteristics.
In this paper, the nonlinear dynamic modeling and model reduction strategy are studied for a rotating cylindrical shell. Considering the quadratic nonlinear terms neglected in authors’ previous study [46], the nonlinear dynamic model for the shell with simply supported conditions is first derived in terms of ordinary differential equations. This model can reflect the coupling of three deformation directions and describe both the flexural and the inplane vibrations. The model derived is accurate because no simplification is applied during the modeling procedure. Then, based on the original model derived, a novel model reduction strategy is proposed to reduce the degrees of freedom (DOFs) by neglecting vibration modes predominated by inplane vibrations, which is different from the previous studies neglecting inplane vibrations directly. Finally, comparisons and simulations are conducted to validate the original nonlinear dynamic model and model reduction strategy, and nonlinear dynamic behaviors are investigated preliminarily.
2. Nonlinear Dynamic Modeling
Figure 1 shows a simply supported thin cylindrical shell rotating on its symmetrical and horizontal axis with an angular velocity . The shell’s thickness, mean radius, and length are , , and . , , and represent the shell’s deformations in , , and directions in the orthogonal coordinate system () fixed on the shell’s middle surface. The material of this shell is assumed to be isotropic and has mass density , Young’s modulus , and Poisson’s ratio .
2.1. Energy Equations
The kinetic energy of the rotating cylindrical shell is expressed aswhere , and is the velocity vector of an arbitrary point of the cylindrical shell that can be expressed as follows:The position vector is given bywhere i, , and are unit vectors in , , and directions. Considering (2) and (3), the rotating shell’s kinetic energy can be expressed as follows:
The material of the shell studied in this paper is elastic, isotropic, and homogeneous. The thickness of this shell is small. Therefore, Donnell’s nonlinear shell theory which is suitable for thin shells is selected and used in the paper. According to Donnell’s nonlinear theory [21], the straindisplacement relations are given bywhereThe stressstrain relationship can be expressed as follows:whereThen the shell’s strain energy due to stretching and bending can be written asAnd the potential energy of the rotating cylindrical shell due to the initial hoop tension induced by rotation is expressed as follows:where is the initial hoop tension due to the centrifugal force that can be expressed as follows:
2.2. Displacement Field
The cylindrical shell is assumed to be simply supported and corresponding boundary conditions areHere, and are the boundary force and boundary moment, respectively.
The displacements , , and , satisfying the simply supported boundary conditions, can be expressed in Fourier serieswhere is the modal participation factor. The displacements (, , and ) are expressed by infinite series of (, ) combinations. Here and are numbers of axial halfwaves and circumferential waves, respectively.
Rewrite expression (16) asLetThen, the displacements , , and expressed in (17) are rewritten aswhereand
2.3. Governing Equations of Original Model
The viscoustype damping force is used and expressed with the Rayleigh dissipation functionwhere the value of is related to the mode expansion terms. Considering expression (19), expression (22) can be expanded as follows:The damping coefficients and in this expression are relevant to the modal damping ratio obtained from experiments. Simple calculations of and are given byHere and are the stationary cylindrical shell’s damping coefficient and circular frequencies with mode , respectively.
The transverse excitation imposed on the rotating cylindrical shell is written aswhere , , and denote the amplitude, frequency, and position of the excitation. Symbol represents the Dirac function.
Using Lagrange equations, the nonlinear governing equations of the rotating cylindrical shell are derived and expressed aswhereHere, the expressions of symbols in (27)(29) are shown in Appendixes A and B.
Equation (26) gives the nonlinear dynamic model of rotating cylindrical shells. The model derived is accurate, because no simplification is applied during the modeling procedure and both the quadratic and cubic nonlinear terms are contained. For every vibration mode (m, n), is a 6×1 vector. To guarantee good accuracy for the calculation of the dynamic response, enough vibration modes must be taken into account, and the scale of DOFs of the overall system increases dramatically. Therefore, it is necessary to derive a reduced model which can retain the main characteristics of the original model.
3. Model Reduction
3.1. Frequencies and Modes of the Corresponding Linear Cylindrical Shell
The frequencies and modes of the corresponding linear cylindrical shell are obtained first for the purpose of the model reduction in the following formulation. For the travelling wave vibration mode with number (, , ), the displacement field expressed in (16) can be rewritten in general formwhere , , and are the displacement amplitudes in the , , and directions, respectively. represents the natural frequency.
The energy function of the rotating cylindrical shell isSubstituting (5)(8) into (9) and (10) (the expressions of strain energy and ), one can express and with shell displacements , , and . Subsequently, substituting the displacement expression (30) into the expressions of kinetic energy (, Eq. (4)) and strain energy ( and ), the energy function can be written asHere, denotes the high order terms of , , and , which are related to the nonlinear vibration. and represent the dimensionless frequency and the rotating speed, and they are expressed aswhere
To obtain the eigenvalue equation associated with the cylindrical shell’s linear vibration, high order terms denoted by are neglected, and the following expressions can be derived by Rayleigh–Ritz procedureEquation (34) leads toHere,where and
According to the nonzero solution identification theorem of homogeneous linear equations, the nondimensional frequency parameters can be obtained by solving the equation expressed aswhich can be expanded aswhere
Six distinct natural frequencies () can be obtained from (38) and the corresponding natural modes are given by
For a stationary cylindrical shell, the lowest frequency is related to the flexural vibration [17]. When the shell rotates on its axis, rotation induces Coriolis accelerations. The Coriolis acceleration bifurcates the shells’ natural frequencies. Therefore, there are two frequencies related to the flexural vibration for a rotating cylindrical shell, and they are the lowest two which can be identified. Therefore, the lowest two (i.e., and ) among those six frequencies () are related to the shell’s flexural vibrations, and the other four frequencies are associated with inplane vibrations (i.e., the longitudinal and torsional vibrations). Moreover, both the literature and the author’s validation show that the displacement amplitude ratios satisfy
For the travelling wave vibration mode (m, n=0), the displacement field expressed in (16) can be rewritten in general form
Similar to the formulations for the mode with circumferential wave number (), one can obtain the characteristic equation aswhere
From (43), four natural frequencies () are derived and the corresponding natural modes are given by
Among the four frequencies derived from (43), the lowest two (i.e., and ) are relevant to the shell’s flexural vibrations. It should be noted that equals because of the axial symmetry of the mode (n=0), which is different from the modes with circumferential wave number (). Correspondingly, the displacement amplitude ratios also satisfy (41).
3.2. ReducedOrder Model
The previous studies of Amabili [17] found that the flexural vibrations predominate the dynamic response of cylindrical shells, and, for every mode (m, n; both and ), the frequencies associated with the flexural vibrations are much lower than the other frequencies. This characteristics show us a viable path to reduce the model by neglecting the contributions of the vibration mode predominated by inplane vibrations which are associated with the higher frequencies. Considering (40), (41), and (45), expression (18) can be written aswhereThen, the displacements , , and are rewritten aswhere
Similarly, using Lagrange equations, the nonlinear rotating cylindrical shell’s reduced model can be obtained as follows:whereHere, symbols in are shown in Appendix C.
From (51), one can obtain the nonlinear reduced model of the rotating cylindrical shell for vibration mode (). It is given byHere, the subscript and time variable of and are neglected for brevity. And symbols used in (55) are expressed as
The reduced model given by (55) is actually a 2DOF gyroscopic system with cubic nonlinearities. The information related to inplane vibrations ( and ) is still included in the reduced model, because the present model reduction only neglects vibration mode predominated by inplane vibrations. However, the previous studies in the model simplification directly neglect inplane vibrations ( and ) to obtain the 2DOF system. Equation (55) preserves the rotating cylindrical shell’s main vibration characteristics which could reflect the coupling of three deformation directions (, , and ). The approximate solution for (55), a gyroscopic system, can be derived by using some analytical approaches, such as LP method, multiple scales method, harmonic balance method, and averaging method. Then, one can perform qualitative analysis to find the complex nonlinear dynamic phenomena on rotating thin cylindrical shell. Moreover, applying the model reduction procedure, the scale of DOFs of the overall system reduces to onethird of what it has been. Thus, the efficiency of numerical calculation for quantitative analysis can be improved as expected.
4. Numerical Results and Discussions
To validate the nonlinear dynamic model shown in (26), a comparison is conducted between the frequencies calculated by the corresponding linear system and those available in open literature, as shown in Table 1. Between the lowest two nondimensional frequencies (i.e., and ), (1) is the lower one and corresponding to the forward wave frequency and (2) is the higher one and corresponding to the backward wave frequency, as shown in literature [5]. It can be seen from Table 1 that good agreement is achieved.

Table 2 shows the simulation parameters for a rotating cylindrical shell considered in this paper. To validate the model reduction strategy, the first five nondimensional frequency parameters, computed by using the corresponding linear system of reducedorder model, are compared with those obtained from original model, as shown in Tables 3 and 4. Excellent agreement is shown in this comparison for a wide variety of modes with different rotating speeds. It may indicate that the model reduction strategy proposed in this paper is available to some extent.



Figures 2(a) and 2(b) illustrate the variation of the natural frequencies with respect to with m=1 for different rotating speeds =0.005 and =0.01. It can be observed that, for a specific , two frequencies exist, i.e., the forward and backward wave frequencies. For this two rotating speeds, the fundamental frequencies of them are both corresponding to the mode (m=1, n=4), which is also shown in Table 3. However, the second order modes are mode (m=1, n=5) and mode (m=1, n=3) for =0.005 and =0.01, respectively. Figure 3 shows the variation of the natural frequencies with respect to nondimensional rotating speed for fundamental mode (m=1, n=4). It can be observed that there is only one natural frequency at rotating speed =0. As the rotating speed increases, this frequency bifurcates.
(a)
(b)
Without loss of generality, further investigation is carried out for the rotating speed =0.005 by using RungeKutta method, and the cylindrical shell’s first two modes at this rotating speed, i.e., mode (m=1, n=4) and mode (m=1, n=5), are considered.
Figures 4–6 give comparisons of the amplitudefrequency responses between original model and reduced model, under different levels of excitation. Here, the excitation is located at the center of shell, which is (, ). The damping ratio is =0.01. The symbol is used to denote the corresponding stationary cylindrical shell’s flexural vibration circular frequency. It can be observed that the lowfrequency responses of original model can be preserved by the reduced model perfectly. It may indicate that the model reduction strategy is effective, and the reduced model is available to investigate the nonlinear dynamic behaviors of thin rotating cylindrical shells.
The amplitudefrequency responses for modes (m=1, n=4) and (m=1, n=5) under excitation level =500N are given by Figures 4 and 5, respectively. The system shows linear behavior, as depicted in the two figures. In each figure, two resonance peaks exist and are respectively corresponding to forward and backward waves. They are all offset upward from the one corresponding to a stationary shell (). This phenomenon is induced by the effects of Coriolis and centrifugal forces, as well as the initial hoop tension due to rotation. The existing of two resonance peaks is consistent with the characteristics of rotating cylindrical shells, which can prove the models’ correctness in some extent. It should be noted that two resonance peaks do not appear in the amplitudefrequency response curve of as expected. It may be led by the special location of excitation. One can see that, at the position (, ) considered in the simulation, symbol in (55) equals 0.
As depicted in Figure 6, when the excitation amplitude increases to 1000N, the jump phenomenon appears, which is a typical characteristic of nonlinearity system. As depicted in Figure 7, if the excitation amplitude increases furtherly, more complex nonlinear behaviors of the rotating shell will appear, such as the ultraharmonic resonance. Figures 8–11 give the closeup views of amplitudefrequency curves for the first mode (m=1, n=4) and the second mode (m=1, n=5) under different excitation levels. The variation of the amplitudefrequency curves with respect to excitation level is well illustrated. The jump phenomenon and ultraharmonic resonance are clearly shown in those figures, especially in Figures 10 and 11. Further, one can conclude that the amplitudefrequency responses for the second mode (m=1, n=5) are more complex than those for the first mode (m=1, n=4).