# Generalized Differential Quadrature Method for Free Vibration Analysis of a Rotating Composite Thin-Walled Shaft

Authors: Weiyan Zhong; Feng Gao; Yongsheng Ren
Journal: Mathematical Problems in Engineering
 (2019)

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## Abstract

A refined variational asymptotic method (VAM) and Hamilton’s principle were used to establish the free vibration differential equations of a rotating composite thin-walled shaft with circumferential uniform stiffness (CUS) configuration. The generalized differential quadrature method (GDQM) was adopted to discretize and solve the governing equations. The accuracy and efficiency of the GDQM were validated in analyzing the frequency of a rotating composite shaft. Compared to the available results in literature, the computational results by the GDQM are accurate. In addition, effects of boundary conditions, rotating speed, ply angle, ratio of radius over thickness, and ratio of length over radius on the frequency characteristics were also investigated.


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## Body

## 1. Introduction

A rotating shaft, as an important structure, is commonly used in many applications. Composite materials have been widely applied in shaft structural designs owing to their advantages of strength, specific modulus, corrosion resistance, wear resistance, fatigue life, light weight, high specific stiffness, and design ability.In the past decades, great effort has been made in developing more accurate and appropriate models and methods to analyze dynamic characteristics of shaft structures. Zinberg and Symonds [1] determined the critical speeds of rotating anisotropic cylindrical shafts simply supported at the ends using equivalent modulus beam theory (EMBT). Dos Reis et al. [2] evaluated the rotordynamic performance of shaft configuration of Zinberg and Symmonds [1] using the finite element method. Kim and Bert [3] derived the motion equations of the rotating composite thin-walled shafts by means of the thin- and thick-shell theories of first-order approximation. They investigated the critical speeds of composite shafts including the effect of bending-twisting coupling. Bert and Kim [4] studied the dynamic instability of drive shafts subjected to fluctuating torque and/or rotational speed by means of various thin shell theories. The theories included the combined effects of torsion and rotation. Singh and Gupta [5] developed two composite spinning shaft models by using EMBT and layerwise beam theory (LBT), respectively. It was indicated that a discrepancy existed between the critical speeds obtained from the two theories for the unsymmetric laminated composite shaft. Chen and Peng [6, 7] analyzed the stability of a rotating shaft subjected to axial periodic forces using the finite element method. In their study, each node contains 5 degrees of freedom. Based on a first-order shear deformable beam theory, Chang et al. [8] presented a simple spinning composite shaft model. They found the approximate solution of the system using the finite element model with three-node one-dimensional line elements that have 6 degrees of freedom in each node. Lagrangian interpolation functions were used to approximate the displacement fields of the shaft. Chang et al. [9] studied the vibration behaviors of the rotating composite shafts containing randomly oriented reinforcements. The finite element model of the composite shaft [8] was extended to the case that contains the fiber inclusions by taking effective elastic moduli into account. Gubran and Gupta [10] modified EMBT with shear deformation, rotary inertia, and gyroscopic effects and analysed the natural frequencies of composite tubular shafts. Song et al. [11] investigated the vibrational and stability behavior of spinning circular shafts modeled as thin-walled beams considering the effects of transverse shear, rotatory inertias, the axial compressive load, and boundary conditions. Sino et al. [12] developed a simplified homogenized beam theory (SHBT) to analyse the sensitivity of the frequencies and instability thresholds regarding shear effect, stacking order, and fiber orientation. Boukhalfa et al. [13] performed free vibration analysis of rotating composite shafts using the p-version hierarchical finite element method with trigonometric shape functions. Boukhalfa and Hadjoui [14] also studied the vibratory behavior of rotating composite shafts. The study incorporated the rotary inertia, gyroscopic effects, transverse shear deformation, and the coupling effect due to the lamination of composite layers. Alwan et al. [15] analyzed solid shafts and composite tube shafts using ANSYS. Boukhalfa [16] considered the dynamic behavior of the spinning Functionally Graded Material (FGM) shaft on rigid bearings. A p-version hierarchical finite element was employed to define the model. Considering the effects of stacking sequences and shear-normal coupling on rotating composite shafts, Arab et al. [17] developed a finite element based on Equivalent Single Layer Theory (ESLT) to model the rotating composite shaft using the Timoshenko beam theory. More recently, Layerwise Shaft Theory (LST) is developed based on shaft finite element theory by Arab et al. [18]. They investigated the dynamic analysis of rotating laminated shafts including t the influences of stacking sequence, fiber orientation, and shear-normal coupling.Many studies have been done on the vibration analysis of composite shafts using Galerkin methods. Kim et al. [19] investigated the free vibration of a rotating tapered composite Timoshenko shaft. The spatial solutions to the equations of motion were obtained by the general Galerkin method. Oh et al. [20] studied vibration and instability of functionally graded cylindrical spinning thin-walled beams also using the Galerkin method. Na et al. [21] evaluated the vibration and stability of a cylindrical shaft modeled as a tapered thin-walled composite beam and adopted the extended Galerkin method to solve the eigenvalue problem. Ren et al. [22] conducted structural modeling and dynamic analysis of a rotating composite shaft and also used the Galerkin method to discretize and solve the governing equations. Furthermore, Ren et al. [23] studied the dynamic behavior of an internally damped rotating composite shaft considered as an anisotropic thin-walled Timoshenko beam. The Galerkin method was also employed to discretize and solve the equations of motion.The generalized differential quadrature method (GDQM) is a well-organized numerical technique originating from the differential quadrature method (DQM) proposed by Bellman and Casti [24]. The DQM has been promoted as a potential alternative to conventional numerical solution techniques such as the Galerkin method and finite element method.So far, no publications have reported on using the GDQM to conduct the free vibration analysis of rotating composite thin-walled shaft. In this paper, the equations of motion of the rotating shaft were established by a refined variational asymptotic method and Hamilton’s principle. The motion governing equations are partial differential equations. With the aid of the GDQM, the partial differential governing equations were transformed approximately into a set of linear algebraic governing equations. Imposing the given boundary conditions, the numerical eigenvalue equations for the free vibration of the shaft were derived and then solved. The dynamic characteristics of the rotating shaft were then analyzed. The computational results using the GDQM were compared to those available in literature, and it was validated that the GDQM is accurate and efficient for the frequency analysis of a rotating composite shaft. Effects of boundary conditions, rotating speed, ply angle, ratio of radius over thickness, and ratio of length over radius on the frequency characteristics were also investigated.


## 2. Model of Rotating Composite Thin-Walled Shaft

The model of the composite thin-walled rotating shaft is shown in Figure1, where L, r, and h denote the length, the radius of curvature of the middle surface, and the thickness, respectively, satisfying r≪L and h≪r. The following coordinate systems are defined to describe the motion of the rotating shaft: (1)  (X,Y,Z) represents the inertial coordinate system whose origin is at the geometric center, and the corresponding unit vector is (I, J,K); (2) (x,y,z) is a rotating reference system and the corresponding unit vector is (i, j, k); (3)  (x,s,ξ) is a local coordinate system, where s and ξ represent the directions, tangent, and normal to the middle surface of the shaft, respectively. Inertial (X,Y,Z) and rotating (x,y,z) coordinate systems are shown in Figure 2. The shaft rotates along its longitudinal x-axis at a constant rate Ω. θ represents the ply angle measured by the s-axis positive coordinate.Figure 1
Composite thin-walled rotating shaft of a circular cross section.Figure 2
InertialX,Y,Z and rotating x,y,z coordinate systems.


### 2.1. Stress-Strain Formulae

The stress-strain relations of a lamina shown in Figure3 [13] in the principle material directions are as follows [25]:(1)σ11σ22σ33τ12τ13τ23=Q11Q12Q13000Q12Q22Q23000Q13Q23Q33000000Q66000000Q55000000Q44ε11ε22ε33γ12γ13γ23Figure 3
A typical composite lamina.The above formula can be abbreviated as(2)σ=Qεwhere [Q] is the stiffness matrix and the material constants Qij can be determined according to the material properties of orthogonal anisotropic laminates [25].(3)Q11=E111-v23v32Δ,Q22=E221-v31v13ΔQ33=E331-v12v21Δ,Q44=κG23,Q55=κG13,Q66=κG12Q12=E11v21+v31v23Δ=E22v12+v32v13ΔQ13=E11v31+v21v32Δ=E22v13+v12v23ΔQ23=E22v32+v12v31Δ=E33v23+v21v13ΔΔ=1-v12v21-v23v32-v31v13-2v21v32v13where Eij are the elastic moduli, Gij are the shear moduli, vij are Poisson’s ratios, and κ is the Timoshenko shear coefficient [26].Consider an arbitrary layer of the laminate whose fiber direction makes an angleη with respect to the x-axis of the cylindrical coordinate system (x,s,ξ) as shown in Figure 4 [13]. The stress-strain relationship can be written as [25](4)σxxσssσξξτξsτxξτxs=Q¯11Q¯12Q¯1300Q¯16Q¯12Q¯22Q¯2300Q¯26Q¯13Q¯23Q¯3300Q¯36000Q¯44Q¯450000Q¯45Q¯550Q¯16Q¯26Q¯3600Q¯66εxxεssεξξγξsγxξγxsFigure 4
Definitions of the principal material coordinate axes on an arbitrary layer of the composite shaft.The above equation can be abbreviated as(5)σ=Q¯εwhere Q¯ is the transformed stiffness matrix of the layer, which can be obtained by transformation matrix [T]:(6)Q¯=T-1QT-Tin which(7)T=c2s20002css2c2000-2cs001000000c-s0000sc0-cscs000c2-s2,c=cos⁡η,s=sin⁡ηThe displacement field of the shaft based on the refined VAM thin-walled beam theory is assumed in the form [22]:(8)ux,y,z,t=Ux,t-ysψyx,t-zsψzx,t+gs,x,tvx,y,z,t=Vx,t-zsϕx,twx,y,z,t=Wx,t+ysϕx,twhere Ux,t, Vx,t, and Wx,t denote the rigid body displacements in the x,y,z directions, while ϕx,t, ψyx,t, and ψzx,t are the rotation angles of the cross-section about x-, y-, and z-axis, respectively. gs,x,t is the warping function, which is modified as(9)gs,x,t=Gsϕ′x,t+g1sU′x,t+g2sψy′x,t+g3sψz′x,twhere Gs,g1s,g2s, and g3(s) are related to physical behavior of the torsion twist rate, the axial strain, and the bending curvatures, respectively.In the (x,y,z) frame,ψyx,t and ψzx,tcan be expressed as(10)ψyx,t=V′x,t-2γzxψzx,t=W′x,t-2γyxwhere γzx and γyx are the transverse shear strains in the planes of xz and xy, respectively.According to the displacement representations (8), (9), and (10), the strains of the composite shaft are obtained by(11)εxx=U′x,t-ysψy′x,t-zsψz′x,t2γxs=dgds+rnϕ′x,t+V′x,t-ψyx,tdyds+W′x,t-ψzx,tdzds2γxξ=V′x,t-ψyx,tdzds+W′x,t-ψzx,tdydswhere rn denotes the normal projection of r of an arbitrary point on the cross section of the deformed shaft in the normal direction:(12)rn=ysdzsds-zsdysds


### 2.2. Strain Energy of Composite Shaft

The strain energy of the composite shaft is(13)U=12∫0L∬Aσxxεxx+τxsγxs+τxξγxξdAdxwhere σxx, τxs, and τxξ are the engineering stresses associated with the engineering strains εxx, γxs, and γxξ.Taking variation of the above strain energy expression, (14) is obtained:(14)δU=∫0L∬Aσxxδεxx+τxsδγxs+τxξδγxξdAdx=∫0LFx′δU+Qy′δV+QZ′δW+Mx′δϕ+Mz′+Qyδψy+My′+QzδψzdxDefine the stress resultantsFx,Qy,Qz and stress couples Mx,My,Mz as(15)Fx=∮NxxdsMx=∮NxsrndsMy=-∮NxxzsdsMz=-∮NxxysdsQy=∮Nxsdysds+NxξdzsdsdsQz=∮Nxsdzsds+Nxξdysdsdswhere Nxx, Nxs, and Nxξ are shell stress resultants, which are defined according to the following expressions:(16)NxxNxsNxξ=AsBs20Bs2Cs4000κDsεxx2γxsγxξin which(17)As=A11-A122A22,Bs=2A16-A12A26A22,Cs=4A66-A262A22,Ds=A44-A452A55,Aij=∫-h/2h/2Q¯ijdξ=∑k=1NQ¯ijkzk-zk-1i,j=1,2,6;i,j=4,5Combining (11) and (16), (15) can be expressed in the following form:(18)Fx=C11U′+C12ϕ′+C13ψz′+C14ψy′+C15V′-ψy+C16W′-ψZMx=C12U′+C22ϕ′+C23ψz′+C24ψy′+C25V′-ψy+C26W′-ψZMy=C13U′+C23ϕ′+C33ψz′+C34ψy′+C35V′-ψy+C36W′-ψZMz=C14U′+C24ϕ′+C34ψz′+C44ψy′+C45V′-ψy+C46W′-ψZQy=C15U′+C25ϕ′+C35ψz′+C45ψy′+C55V′-ψy+C56W′-ψZQz=C16U′+C26ϕ′+C36ψz′+C46ψy′+C56V′-ψy+C66W′-ψZwhere Cij=Cji(i,j=1,⋯,6) are the stiffness coefficients of the composite shaft, which can be expressed according to the cross section geometry and material properties as follows:(19)C11=∮ΓA-B2Cds+∮ΓB/Cds2∮Γ1/Cds,C12=∮ΓB/Cds∮Γ1/CdsAe,C13=-∮ΓA-B2Czds-∮ΓB/Cds∮ΓB/Czds∮Γ1/Cds,C14=-∮ΓA-B2Cyds-∮ΓB/Cds∮ΓB/Cyds∮Γ1/Cds,C15=12∮ΓBdydsds,C16=12∮ΓBdzdsds,C22=1∮Γ1/CdsAe2,C23=-∮ΓB/Czds∮Γ1/CdsAe,C24=-∮ΓB/Cyds∮Γ1/CdsAe,C25=14∮ΓrnCdydsds,C26=14∮ΓrnCdzdsds,C33=∮ΓA-B2Cz2ds+∮ΓB/Czds2∮Γ1/Cds,C34=∮ΓA-B2Cyzds+∮ΓB/Cyds∮ΓB/Czds∮Γ1/Cds,C35=-12∮ΓBzdydsds,C36=-12∮ΓBzdzdsds,C44=κ∮ΓA-B2Cy2ds+∮ΓB/Cyds2∮Γ1/Cds,C45=-12κ∮ΓBydydsds,C46=-12κ∮ΓBydzdsds,C55=κ∮Γ14Cdyds2+Ddzds2ds,C56=κ∮Γ14C-Ddydsdzdsds,C66=κ∮Γ14Cdzds2+Ddyds2ds,Ae=12κ∮Γydzds-zdydsdswhere ∮Γ∙ds denotes the integral around the loop of the midline cross section; Ae is the surrounded area of the midline of the section.


### 2.3. Kinetic Energy of Composite Shaft

The position vector of an arbitrary point on the composite shaft can be written as(20)r=y+vi+z+wj+x+ukFrom the above equation, the velocity of an arbitrary point can be given by(21)V=r˙=v˙-Ωz+wi+w˙+Ωy+vj+u˙kThe kinetic energy of the composite spinning shaft can be written as(22)T=12∫0L∬AρV∙VdAdxThe variation of kinetic energy can be written as(23)δT=-∫0LI1δU+I2δV+I3δW+I4ψy+I5ψz+I6ϕdxin which(24)I1=mcU¨-Szψ¨y-Syψ¨zI2=mcV¨-2ΩW˙-Ω2V-Sz2Ωϕ˙+Ω2-Syϕ¨-Ω2ϕI3=mcW¨-2ΩV˙-Ω2W+Szϕ¨+Ω2ϕ-Sy2Ωϕ˙+Ω2I4=SzU¨-Izψ¨y-Iyzψ¨zI5=SyW¨-Iyzψ¨y-Iyψ¨zI6=SzW¨+2ΩU˙-Ω2W+Iy+Izϕ¨-Ω2ϕ-SyV¨-2ΩW˙-Ω2Vmc=∬AρdA,Sz=∬AρydA,Sy=∬AρzdA,Iz=∬Aρy2dA,Iy=∬Aρz2dA,Iyz=∬AρyzdAwhere Iii=1,⋯,6 are equivalent cross section mass coefficients.


### 2.4. Governing Equations

To derive the vibration equation of the composite thin-walled shaft, Hamilton's principle was applied:(25)∫t0t1δU-δTdt=0Combining (14), (23), and (25), the governing equations of the composite shaft are obtained:(26)-Fx′+I1=0-Qy′+I2=0-Qz′+I3=0-Mz′-Qy+I4=0-My′-Qz+I5=0-Mx′+I6=0Substituting internal forces into (26), the free vibration equations can be derived. The special properties of the circular cross section shaft with CUS configuration cause some of stiffness coefficients to be zero. The equations of motion involving variables in terms of displacements can be reduced as(27a)f1U,ϕ=-C11U′′-C12ϕ′′+mcU¨=0(27b)f2U,ϕ=-C12U′′-C22ϕ′′+Iy+Izϕ¨-Ω2ϕ=0(27c)f3V,W,ψy,ψz=-C35ψz′′-C55V′′-ψy′+mcV¨-2ΩW˙-Ω2V=0(27d)f4V,W,ψy,ψz=-C46ψy′′-C66W′′-ψz′+mcW¨+2ΩV˙-Ω2W=0(27e)f5V,W,ψy,ψz=-C44ψy′′-C46W′′-ψz′-C35ψz′-C55V′-ψy-Izψ¨y=0(27f)f6V,W,ψy,ψz=-C33ψz′′-C35V′′-ψy′-C46ψy′-C66W′-ψz-Iyψ¨z=0The vibration equations are decoupled as the tensile-torsion coupling system ((27a) and (27b)) and bending-transverse shear coupling system ( (27c)~(27f)). This paper only studies the latter.


## 2.1. Stress-Strain Formulae

The stress-strain relations of a lamina shown in Figure3 [13] in the principle material directions are as follows [25]:(1)σ11σ22σ33τ12τ13τ23=Q11Q12Q13000Q12Q22Q23000Q13Q23Q33000000Q66000000Q55000000Q44ε11ε22ε33γ12γ13γ23Figure 3
A typical composite lamina.The above formula can be abbreviated as(2)σ=Qεwhere [Q] is the stiffness matrix and the material constants Qij can be determined according to the material properties of orthogonal anisotropic laminates [25].(3)Q11=E111-v23v32Δ,Q22=E221-v31v13ΔQ33=E331-v12v21Δ,Q44=κG23,Q55=κG13,Q66=κG12Q12=E11v21+v31v23Δ=E22v12+v32v13ΔQ13=E11v31+v21v32Δ=E22v13+v12v23ΔQ23=E22v32+v12v31Δ=E33v23+v21v13ΔΔ=1-v12v21-v23v32-v31v13-2v21v32v13where Eij are the elastic moduli, Gij are the shear moduli, vij are Poisson’s ratios, and κ is the Timoshenko shear coefficient [26].Consider an arbitrary layer of the laminate whose fiber direction makes an angleη with respect to the x-axis of the cylindrical coordinate system (x,s,ξ) as shown in Figure 4 [13]. The stress-strain relationship can be written as [25](4)σxxσssσξξτξsτxξτxs=Q¯11Q¯12Q¯1300Q¯16Q¯12Q¯22Q¯2300Q¯26Q¯13Q¯23Q¯3300Q¯36000Q¯44Q¯450000Q¯45Q¯550Q¯16Q¯26Q¯3600Q¯66εxxεssεξξγξsγxξγxsFigure 4
Definitions of the principal material coordinate axes on an arbitrary layer of the composite shaft.The above equation can be abbreviated as(5)σ=Q¯εwhere Q¯ is the transformed stiffness matrix of the layer, which can be obtained by transformation matrix [T]:(6)Q¯=T-1QT-Tin which(7)T=c2s20002css2c2000-2cs001000000c-s0000sc0-cscs000c2-s2,c=cos⁡η,s=sin⁡ηThe displacement field of the shaft based on the refined VAM thin-walled beam theory is assumed in the form [22]:(8)ux,y,z,t=Ux,t-ysψyx,t-zsψzx,t+gs,x,tvx,y,z,t=Vx,t-zsϕx,twx,y,z,t=Wx,t+ysϕx,twhere Ux,t, Vx,t, and Wx,t denote the rigid body displacements in the x,y,z directions, while ϕx,t, ψyx,t, and ψzx,t are the rotation angles of the cross-section about x-, y-, and z-axis, respectively. gs,x,t is the warping function, which is modified as(9)gs,x,t=Gsϕ′x,t+g1sU′x,t+g2sψy′x,t+g3sψz′x,twhere Gs,g1s,g2s, and g3(s) are related to physical behavior of the torsion twist rate, the axial strain, and the bending curvatures, respectively.In the (x,y,z) frame,ψyx,t and ψzx,tcan be expressed as(10)ψyx,t=V′x,t-2γzxψzx,t=W′x,t-2γyxwhere γzx and γyx are the transverse shear strains in the planes of xz and xy, respectively.According to the displacement representations (8), (9), and (10), the strains of the composite shaft are obtained by(11)εxx=U′x,t-ysψy′x,t-zsψz′x,t2γxs=dgds+rnϕ′x,t+V′x,t-ψyx,tdyds+W′x,t-ψzx,tdzds2γxξ=V′x,t-ψyx,tdzds+W′x,t-ψzx,tdydswhere rn denotes the normal projection of r of an arbitrary point on the cross section of the deformed shaft in the normal direction:(12)rn=ysdzsds-zsdysds


## 2.2. Strain Energy of Composite Shaft

The strain energy of the composite shaft is(13)U=12∫0L∬Aσxxεxx+τxsγxs+τxξγxξdAdxwhere σxx, τxs, and τxξ are the engineering stresses associated with the engineering strains εxx, γxs, and γxξ.Taking variation of the above strain energy expression, (14) is obtained:(14)δU=∫0L∬Aσxxδεxx+τxsδγxs+τxξδγxξdAdx=∫0LFx′δU+Qy′δV+QZ′δW+Mx′δϕ+Mz′+Qyδψy+My′+QzδψzdxDefine the stress resultantsFx,Qy,Qz and stress couples Mx,My,Mz as(15)Fx=∮NxxdsMx=∮NxsrndsMy=-∮NxxzsdsMz=-∮NxxysdsQy=∮Nxsdysds+NxξdzsdsdsQz=∮Nxsdzsds+Nxξdysdsdswhere Nxx, Nxs, and Nxξ are shell stress resultants, which are defined according to the following expressions:(16)NxxNxsNxξ=AsBs20Bs2Cs4000κDsεxx2γxsγxξin which(17)As=A11-A122A22,Bs=2A16-A12A26A22,Cs=4A66-A262A22,Ds=A44-A452A55,Aij=∫-h/2h/2Q¯ijdξ=∑k=1NQ¯ijkzk-zk-1i,j=1,2,6;i,j=4,5Combining (11) and (16), (15) can be expressed in the following form:(18)Fx=C11U′+C12ϕ′+C13ψz′+C14ψy′+C15V′-ψy+C16W′-ψZMx=C12U′+C22ϕ′+C23ψz′+C24ψy′+C25V′-ψy+C26W′-ψZMy=C13U′+C23ϕ′+C33ψz′+C34ψy′+C35V′-ψy+C36W′-ψZMz=C14U′+C24ϕ′+C34ψz′+C44ψy′+C45V′-ψy+C46W′-ψZQy=C15U′+C25ϕ′+C35ψz′+C45ψy′+C55V′-ψy+C56W′-ψZQz=C16U′+C26ϕ′+C36ψz′+C46ψy′+C56V′-ψy+C66W′-ψZwhere Cij=Cji(i,j=1,⋯,6) are the stiffness coefficients of the composite shaft, which can be expressed according to the cross section geometry and material properties as follows:(19)C11=∮ΓA-B2Cds+∮ΓB/Cds2∮Γ1/Cds,C12=∮ΓB/Cds∮Γ1/CdsAe,C13=-∮ΓA-B2Czds-∮ΓB/Cds∮ΓB/Czds∮Γ1/Cds,C14=-∮ΓA-B2Cyds-∮ΓB/Cds∮ΓB/Cyds∮Γ1/Cds,C15=12∮ΓBdydsds,C16=12∮ΓBdzdsds,C22=1∮Γ1/CdsAe2,C23=-∮ΓB/Czds∮Γ1/CdsAe,C24=-∮ΓB/Cyds∮Γ1/CdsAe,C25=14∮ΓrnCdydsds,C26=14∮ΓrnCdzdsds,C33=∮ΓA-B2Cz2ds+∮ΓB/Czds2∮Γ1/Cds,C34=∮ΓA-B2Cyzds+∮ΓB/Cyds∮ΓB/Czds∮Γ1/Cds,C35=-12∮ΓBzdydsds,C36=-12∮ΓBzdzdsds,C44=κ∮ΓA-B2Cy2ds+∮ΓB/Cyds2∮Γ1/Cds,C45=-12κ∮ΓBydydsds,C46=-12κ∮ΓBydzdsds,C55=κ∮Γ14Cdyds2+Ddzds2ds,C56=κ∮Γ14C-Ddydsdzdsds,C66=κ∮Γ14Cdzds2+Ddyds2ds,Ae=12κ∮Γydzds-zdydsdswhere ∮Γ∙ds denotes the integral around the loop of the midline cross section; Ae is the surrounded area of the midline of the section.


## 2.3. Kinetic Energy of Composite Shaft

The position vector of an arbitrary point on the composite shaft can be written as(20)r=y+vi+z+wj+x+ukFrom the above equation, the velocity of an arbitrary point can be given by(21)V=r˙=v˙-Ωz+wi+w˙+Ωy+vj+u˙kThe kinetic energy of the composite spinning shaft can be written as(22)T=12∫0L∬AρV∙VdAdxThe variation of kinetic energy can be written as(23)δT=-∫0LI1δU+I2δV+I3δW+I4ψy+I5ψz+I6ϕdxin which(24)I1=mcU¨-Szψ¨y-Syψ¨zI2=mcV¨-2ΩW˙-Ω2V-Sz2Ωϕ˙+Ω2-Syϕ¨-Ω2ϕI3=mcW¨-2ΩV˙-Ω2W+Szϕ¨+Ω2ϕ-Sy2Ωϕ˙+Ω2I4=SzU¨-Izψ¨y-Iyzψ¨zI5=SyW¨-Iyzψ¨y-Iyψ¨zI6=SzW¨+2ΩU˙-Ω2W+Iy+Izϕ¨-Ω2ϕ-SyV¨-2ΩW˙-Ω2Vmc=∬AρdA,Sz=∬AρydA,Sy=∬AρzdA,Iz=∬Aρy2dA,Iy=∬Aρz2dA,Iyz=∬AρyzdAwhere Iii=1,⋯,6 are equivalent cross section mass coefficients.


## 2.4. Governing Equations

To derive the vibration equation of the composite thin-walled shaft, Hamilton's principle was applied:(25)∫t0t1δU-δTdt=0Combining (14), (23), and (25), the governing equations of the composite shaft are obtained:(26)-Fx′+I1=0-Qy′+I2=0-Qz′+I3=0-Mz′-Qy+I4=0-My′-Qz+I5=0-Mx′+I6=0Substituting internal forces into (26), the free vibration equations can be derived. The special properties of the circular cross section shaft with CUS configuration cause some of stiffness coefficients to be zero. The equations of motion involving variables in terms of displacements can be reduced as(27a)f1U,ϕ=-C11U′′-C12ϕ′′+mcU¨=0(27b)f2U,ϕ=-C12U′′-C22ϕ′′+Iy+Izϕ¨-Ω2ϕ=0(27c)f3V,W,ψy,ψz=-C35ψz′′-C55V′′-ψy′+mcV¨-2ΩW˙-Ω2V=0(27d)f4V,W,ψy,ψz=-C46ψy′′-C66W′′-ψz′+mcW¨+2ΩV˙-Ω2W=0(27e)f5V,W,ψy,ψz=-C44ψy′′-C46W′′-ψz′-C35ψz′-C55V′-ψy-Izψ¨y=0(27f)f6V,W,ψy,ψz=-C33ψz′′-C35V′′-ψy′-C46ψy′-C66W′-ψz-Iyψ¨z=0The vibration equations are decoupled as the tensile-torsion coupling system ((27a) and (27b)) and bending-transverse shear coupling system ( (27c)~(27f)). This paper only studies the latter.


## 3. GDQM Solution to Governing Equations

The GDQM was used to solve the governing equations. In the GDQM, derivative of any order of a function is approximated by a weighted linear sum of the function values at all the discrete points. Taking a functionf(x,t) as an example, the mathematic description of the GDQM is given by [27](28)∂pfx,t∂xpx=xj=∑k=1NCjkpfxk,t,j=1,2,⋯,Nwhere N is the number of total discrete grid points in the x direction. Cjkp is the weighting coefficient related to the pth-order derivative, and the weighting coefficenct is obtained by the following.If p= 1, then(29)Ajk1=M1xjxj-xkM1xk,j≠k,j,k=1,2,…,NAjj1=-∑k=1k≠jNAjk1,j=1,2,⋯,Nwhere M1x is the first derivative of M(x) and they can be defined as(30)Mx=∏k=1Nx-xk,M1xk=∏j=1j≠kNxk-xjIf p>1, namely, for the second and higher order derivatives, the weighting coefficients are obtained by using the following simple recurrence relationship:(31)Ajkn=pAjk1∙Ajjn-1-Ajkn-1xj-xk,j≠k,j,k=1,2,…,N,n≥2Ajjn=-∑k=1k≠jNAjkn,j=1,2,⋯,NTo get denser population near boundaries, the sampling points are selected based on the Chebyshev–Gauss–Lobatto grid distribution.(32)xj=L21-cos⁡j-1N-1π,j=1,2,⋯,NTo find the approximate solution of the composite shaft, assume that bending deformation and bending angle are of the following form:(33)vx,t=Vxeiωt,wx,t=Wxeiωt,ψyx,t=Ψyxeiωt,ψzx,t=Ψzxeiωtwhere Vx,Wx,Ψyx, and Ψzx denote mode functions of the composite shaft; ω is the natural frequency; i=-1.Substituting (33) into the governing Equations (27c), (27d), (27e), and (27f), a group of ordinary differential equations with the coefficients varying toward thex-direction is produced:(34)L∗U∗=0where U∗T=Vx,Wx,Ψyx,Ψzx and L∗=Lij∗i,j=1,⋯,4 is a 4×4 matrix which includes the differential operative of U∗ defined as(35)L∗=-ω2M+iωG+Kwhere(36)M=mc0000mc0000-Iz0000-IyG=0-2Ωmc002Ωmc00000000000K=-C55∂2∂x2-mcΩ20C55∂∂x-C35∂2∂x20-C66∂2∂x2-mcΩ2-C46∂2∂x2C66∂∂x-C55∂∂x-C46∂2∂x2-C44∂2∂x2+C55C46-C35∂∂x-C35∂2∂x2-C66∂∂xC35-C46∂∂x-C33∂2∂x2+C66Considering (28), the differential quadrature discrete expression of the governing equations of the composite shaft can be obtained:(37a)-C55∑j=1NPij2Vxj-mcΩ2Vxi+C55∑j=1NPij1Ψyxj-C35∑j=1NPij2Ψzxj-iω2ΩmcWxi-ω2mcVxi=0(37b)-C66∑j=1NPij2Wxj-mcΩ2Wxi-C46∑j=1NPij2Ψyxj+C66∑j=1NPij1Ψzxj+iω2ΩmcVxi-ω2mcVxi=0(37c)-C55∑j=1NPij1Vxj-C46∑j=1NPij2Wxj-C44∑j=1NPij2Ψyxj+C55Ψyxi+C46-C35∑j=1NPij1Ψzxj+ω2IzΨyxi=0(37d)-C35∑j=1NPij2Vxj-C66∑j=1NPij1Wxj+C35-C46∑j=1NPij1Ψyxj-C33∑j=1NPij2Ψzxj+C66Ψzxi+ω2IyΨzxi=0where i=2,⋯,N-1.The differential quadrature discrete expression can be simplified as(38)Mω2d+Giωd+Kddd+Kdbb=0In the above equations, the dimensions ofM, G, and Kdd are 4N-2×4N-2; the dimension of Kdb is 4N-2×8; the dimensions of vectors d and b are 4N-2 and 8, respectively, which can be expressed as(39)dT=Vx2,⋯,VxN-1,Wx2,⋯,WxN-1,Ψyx2,⋯,ΨyxN-1,Ψzx2,⋯,ΨzxN-1bT=Vx1,⋯,VxN,Wx1,⋯,WxN,Ψyx1,⋯,ΨyxN,Ψzx1,⋯,ΨzxNSimilarly, the discretized form of the boundary conditions becomes(40)Kbdd+Kbbb=0In the current application of the GDQM, three boundary conditions considered for shafts are(a)
clamped at both edges (clamped-clamped, C-C)(41)V=0,W=0,Ψy=0,Ψz=0x=0,L(b)
simply supported at both edges (simply supported-simply supported, S-S)(42)V=0,W=0,My=0,Mz=0x=0,L(c)
cantilever shaft (clamped-free, C-F)(43)V=0,W=0,Ψy=0,Ψz=0x=0Qy=0,Qz=0,My=0,Mz=0x=LCombine (40) and (38) to remove vector b, and then (44) is obtained:(44)Mω2d+Giωd+Kdd-KdbKbb-1Kbdd=0Equation (44) can be abbreviated as(45)Mω2d+Giωd+Kd=0Equation (45) is a nonstandard eigenvalue equation that can be equivalently converted into a standard formula for a certain frequency [28]:(46)0I-K-G-ωI00Mdωd=0where I is an identity matrix and its dimension is 4(N − 2) × 4(N − 2).By a mainstream method, the eigenvalue equation (46) can be solved, and the natural frequencies are achieved.


## 4. Numerical Results Analysis and Discussion

### 4.1. Convergence Analysis and Accuracy Verification

To validate the approximate calculation method in this paper, the composite hollow shafts made of the boron/epoxy composite material, which are considered by Bert and Kim [30], were investigated.The properties of the material areE11=211 GPa, E22=24.1 GPa, G12=G13=G23=6.9 GPa, v12=0.36, and ρ = 1967 kg/m3. The dimensions of the shaft are L=2.47 m, r=0.06345 m, and h=1.321 mm. The stacking sequence of the composite shaft is [90°/45°/45°/0°6/90°].The effects of the number of grid points on the first five natural frequencies of the rotating composite shafts with various boundary conditions are shown in Figures5–7, respectively. It can be seen from the figures that the first five natural frequencies converge quickly. When the number of grid points is larger than 12, the first five natural frequencies almost do not vary. This indicates that the convergence of the GDQM is good. Therefore, in later calculations, 12 uniform grid points are used.Figure 5
Effect of grid points N on natural frequencies of the simply-supported shaft.Figure 6
Effect of grid points N on natural frequencies of the clamped shaft.Figure 7
Effect of grid points N on natural frequencies of the cantilever shaft.Table1 presents the natural frequencies of cantilever composite shafts without shear deformation obtained from both present model and [29] at different rotating speeds. Ω∗ and ωi∗ denote the nondimensional rotating speed and natural frequency, respectively. As shown in the Table, the numerical results agree well with those in [29].Table 1
Natural frequencies of cantilever composite shafts.
Ω ∗ ω 1 ∗ ω 2 ∗ ω 3 ∗ ω 4 ∗ ω 5 ∗ ω 6 ∗ 0 3.5160 3.5160 22.0345 22.0345 61.6975 61.6975 Ref [29] 3.5160 3.5160 22.0340 22.0340 61.6970 61.6970 2 1.5160 5.5160 20.0345 24.0345 59.6975 63.6975 Ref [29] 1.5160 5.5160 20.0340 24.0340 59.6970 63.6970 3.5 0.0160 7.0160 18.5345 25.5345 58.1975 65.1975 Ref [29] - 7.0160 18.5340 25.5340 58.1970 65.1970 4 0.4840 7.5160 18.0345 26.0345 57.6975 65.6975 Ref [29] - 7.5160 18.0340 26.0340 57.6970 65.6970 8 4.4839 11.5160 14.0345 30.0345 53.6975 69.6975 Ref [29] - 11.5160 14.0340 30.0340 53.6970 69.6970


### 4.2. Stability and Free Vibration Analysis

In the following example, the shaft is made of the graphite-epoxy composite material with parameters as follows:E 11 = 206.8 GPa, E22 = E33 = 5.17 GPa, G12=3.1 GPa, G23=G13 = 2.55 GPa, v21=v31=0.00625, v32=0.25, and ρ=1528.15 kg/m3.The dimensions of the shaft areL=2.023 m, r=0.127 m, and h=0.381 mm. The stacking sequence of the shaft is ±θ3.Figure8 shows the first natural frequencies of the rotating composite shaft, which considers the shear deformation versus rotating speed for selected ply angles. When the rotating speed is zero, each ply angle corresponds to a single fundamental frequency because the bending mode frequencies in horizontal and vertical directions are the same for a circular cross section shaft. As soon as the rotation starts, a bifurcation of natural frequencies occurs because of the gyroscopic effect. Hence, a natural frequency curve splits into an upper one and a lower one. With the increase of rotational speed, the upper curve goes up corresponding to the forward feed (F), while the lower curve goes down corresponding to the backward feed (B).Figure 8
The first natural frequencies of the rotating composite shaft versus rotating speed for different ply angles.
(a)
C-C (b)
S-S (c)
C-FThe shaft spinning speed at zero natural frequency is called the critical speed, which corresponds to the instability. When the spinning speed exceeds the critical speed, the natural frequency increases with the rotating speed. It also can be seen that both natural frequencies and critical spinning speed of the shaft with the clamped boundary condition are higher than those with simply supported and cantilever boundary conditions.The numerical results of the Figure8 are given in Table 2 to show the influence of the gyroscopic effect.Table 2
The first natural frequencies of the shaft for different boundary conditions and various rotating speed (θ=60°).
Rotating  SpeedΩ [rpm] Frequencyω [Hz] 1B(C-C) 1F(C-C) 1B(S-S) 1F(S-S) 1B(C-F) 1F(C-F) 0 289.3935 289.3935 207.0878 207.0878 49.0284 49.0284 100 287.7097 291.0775 205.4020 208.7737 47.3530 50.7041 200 286.0260 292.7615 203.7163 210.4598 45.6779 52.3801 300 284.3423 294.4457 202.0308 212.1461 44.0031 54.0564 400 282.6588 296.1299 200.3455 213.8326 42.3286 55.7330 500 280.9753 297.8142 198.6603 215.5191 40.6544 57.4099 600 279.2920 299.4987 196.9752 217.2059 38.9806 59.0871 700 277.6087 301.1832 195.2904 218.8928 37.3070 60.7646 800 275.9256 302.8678 193.6057 220.5798 35.6337 62.4424 900 274.2425 304.5526 191.9211 222.2670 33.9607 64.1205 1000 272.5596 306.2374 190.2367 223.9544 32.2881 65.7990Figure9 reveals the first three natural frequencies of the rotating composite thin-walled shaft with different boundary conditions versus the ply angle when rotation speed is 800 rpm. Figure 9(a) represents the clamped boundary condition. As shown in the figure, the maximum values of the first- and second-order natural frequencies occur at θ=70°, while the maximum values of the third order natural frequencies occur at θ=65°. Figure 9(b) represents the simply supported shaft. The figure shows the maximum values of the first order natural frequencies occur at θ=75°, while the second- and third-order natural frequencies occur at θ=70°. Figure 9(c) represents the cantilever composite shaft. The figure indicates that the maximum values of the first-order natural frequencies occur at θ=80°, and the maximum values of the second-order ones occur at θ=75°, while those of the third order occur at θ=70°. It also can be seen from Figure 9 that the higher the mode, the lager the variation amplitude for the three aforementioned boundary conditions. The numerical results of the figure are given in Table 3 to show the influence of the boundary conditions and ply angles.Table 3
The first three natural frequencies of the shaft for different boundary conditions and ply angles (Ω = 800rpm).
Boundary conditions Ply angleθ [°] Frequencyω [Hz] 1B 1F 2B 2F 3B 3F C-C 0° 89.5956 116.5424 250.1030 277.5957 462.3860 490.3354 30° 109.5489 136.5861 325.5890 353.6101 653.8300 683.2888 60° 275.9256 302.8678 724.3444 751.8162 1314.0023 1341.9065 75° 356.2460 382.9658 765.3613 792.1977 1233.6654 1260.4888 S-S 0° 60.1498 87.1267 211.7786 239.3596 423.3616 451.4875 30° 71.8321 98.8569 263.8645 291.8418 569.8837 599.3474 60° 193.2056 220.5798 618.5663 646.1292 1207.7548 1235.8342 75° 288.0808 314.8729 730.6617 757.5166 1214.6430 1241.4759 C-F 0° 4.0188 30.8277 91.7179 119.2882 266.1023 294.4848 30° 6.1303 32.9436 109.4554 137.1525 334.9323 364.0539 60° 35.6337 62.4424 282.7588 310.3222 771.1312 799.4811 75° 75.0446 101.8206 402.6232 429.7342 895.0152 922.1036Figure 9
The first three natural frequencies of the rotating composite thin-walled shaft versus ply angle (Ω = 800rpm).
(a)
C-C (b)
S-S (c)
C-FFigure10 shows the first three natural frequencies of the rotating composite thin-walled shaft versus the ratio of mean radius to thickness. The natural frequencies increase with the ratio of radius to thickness, and this tendency becomes more obvious when the mode is higher.Figure 10
The first three natural frequencies of the composite thin-walled rotating shaft versus mean radius to thickness ratios (Ω= 800rpm, θ=60°).
(a)
C-C (b)
S-S (c)
C-FFigure11 shows the first three frequencies of the rotating composite thin-walled shaft versus the ratio of length to mean radius. The figure demonstrates that the natural frequencies decrease with the increase of the ratio of length to mean radius. In addition, the higher the mode, the faster the natural frequencies decrease.Figure 11
The first three natural frequencies of the rotating composite thin-walled shaft versus length to mean radius ratio (Ω=800rpm, θ=60°).
(a)
C-C (b)
S-S (c)
C-F


## 4.1. Convergence Analysis and Accuracy Verification

To validate the approximate calculation method in this paper, the composite hollow shafts made of the boron/epoxy composite material, which are considered by Bert and Kim [30], were investigated.The properties of the material areE11=211 GPa, E22=24.1 GPa, G12=G13=G23=6.9 GPa, v12=0.36, and ρ = 1967 kg/m3. The dimensions of the shaft are L=2.47 m, r=0.06345 m, and h=1.321 mm. The stacking sequence of the composite shaft is [90°/45°/45°/0°6/90°].The effects of the number of grid points on the first five natural frequencies of the rotating composite shafts with various boundary conditions are shown in Figures5–7, respectively. It can be seen from the figures that the first five natural frequencies converge quickly. When the number of grid points is larger than 12, the first five natural frequencies almost do not vary. This indicates that the convergence of the GDQM is good. Therefore, in later calculations, 12 uniform grid points are used.Figure 5
Effect of grid points N on natural frequencies of the simply-supported shaft.Figure 6
Effect of grid points N on natural frequencies of the clamped shaft.Figure 7
Effect of grid points N on natural frequencies of the cantilever shaft.Table1 presents the natural frequencies of cantilever composite shafts without shear deformation obtained from both present model and [29] at different rotating speeds. Ω∗ and ωi∗ denote the nondimensional rotating speed and natural frequency, respectively. As shown in the Table, the numerical results agree well with those in [29].Table 1
Natural frequencies of cantilever composite shafts.
Ω ∗ ω 1 ∗ ω 2 ∗ ω 3 ∗ ω 4 ∗ ω 5 ∗ ω 6 ∗ 0 3.5160 3.5160 22.0345 22.0345 61.6975 61.6975 Ref [29] 3.5160 3.5160 22.0340 22.0340 61.6970 61.6970 2 1.5160 5.5160 20.0345 24.0345 59.6975 63.6975 Ref [29] 1.5160 5.5160 20.0340 24.0340 59.6970 63.6970 3.5 0.0160 7.0160 18.5345 25.5345 58.1975 65.1975 Ref [29] - 7.0160 18.5340 25.5340 58.1970 65.1970 4 0.4840 7.5160 18.0345 26.0345 57.6975 65.6975 Ref [29] - 7.5160 18.0340 26.0340 57.6970 65.6970 8 4.4839 11.5160 14.0345 30.0345 53.6975 69.6975 Ref [29] - 11.5160 14.0340 30.0340 53.6970 69.6970


## 4.2. Stability and Free Vibration Analysis

In the following example, the shaft is made of the graphite-epoxy composite material with parameters as follows:E 11 = 206.8 GPa, E22 = E33 = 5.17 GPa, G12=3.1 GPa, G23=G13 = 2.55 GPa, v21=v31=0.00625, v32=0.25, and ρ=1528.15 kg/m3.The dimensions of the shaft areL=2.023 m, r=0.127 m, and h=0.381 mm. The stacking sequence of the shaft is ±θ3.Figure8 shows the first natural frequencies of the rotating composite shaft, which considers the shear deformation versus rotating speed for selected ply angles. When the rotating speed is zero, each ply angle corresponds to a single fundamental frequency because the bending mode frequencies in horizontal and vertical directions are the same for a circular cross section shaft. As soon as the rotation starts, a bifurcation of natural frequencies occurs because of the gyroscopic effect. Hence, a natural frequency curve splits into an upper one and a lower one. With the increase of rotational speed, the upper curve goes up corresponding to the forward feed (F), while the lower curve goes down corresponding to the backward feed (B).Figure 8
The first natural frequencies of the rotating composite shaft versus rotating speed for different ply angles.
(a)
C-C (b)
S-S (c)
C-FThe shaft spinning speed at zero natural frequency is called the critical speed, which corresponds to the instability. When the spinning speed exceeds the critical speed, the natural frequency increases with the rotating speed. It also can be seen that both natural frequencies and critical spinning speed of the shaft with the clamped boundary condition are higher than those with simply supported and cantilever boundary conditions.The numerical results of the Figure8 are given in Table 2 to show the influence of the gyroscopic effect.Table 2
The first natural frequencies of the shaft for different boundary conditions and various rotating speed (θ=60°).
Rotating  SpeedΩ [rpm] Frequencyω [Hz] 1B(C-C) 1F(C-C) 1B(S-S) 1F(S-S) 1B(C-F) 1F(C-F) 0 289.3935 289.3935 207.0878 207.0878 49.0284 49.0284 100 287.7097 291.0775 205.4020 208.7737 47.3530 50.7041 200 286.0260 292.7615 203.7163 210.4598 45.6779 52.3801 300 284.3423 294.4457 202.0308 212.1461 44.0031 54.0564 400 282.6588 296.1299 200.3455 213.8326 42.3286 55.7330 500 280.9753 297.8142 198.6603 215.5191 40.6544 57.4099 600 279.2920 299.4987 196.9752 217.2059 38.9806 59.0871 700 277.6087 301.1832 195.2904 218.8928 37.3070 60.7646 800 275.9256 302.8678 193.6057 220.5798 35.6337 62.4424 900 274.2425 304.5526 191.9211 222.2670 33.9607 64.1205 1000 272.5596 306.2374 190.2367 223.9544 32.2881 65.7990Figure9 reveals the first three natural frequencies of the rotating composite thin-walled shaft with different boundary conditions versus the ply angle when rotation speed is 800 rpm. Figure 9(a) represents the clamped boundary condition. As shown in the figure, the maximum values of the first- and second-order natural frequencies occur at θ=70°, while the maximum values of the third order natural frequencies occur at θ=65°. Figure 9(b) represents the simply supported shaft. The figure shows the maximum values of the first order natural frequencies occur at θ=75°, while the second- and third-order natural frequencies occur at θ=70°. Figure 9(c) represents the cantilever composite shaft. The figure indicates that the maximum values of the first-order natural frequencies occur at θ=80°, and the maximum values of the second-order ones occur at θ=75°, while those of the third order occur at θ=70°. It also can be seen from Figure 9 that the higher the mode, the lager the variation amplitude for the three aforementioned boundary conditions. The numerical results of the figure are given in Table 3 to show the influence of the boundary conditions and ply angles.Table 3
The first three natural frequencies of the shaft for different boundary conditions and ply angles (Ω = 800rpm).
Boundary conditions Ply angleθ [°] Frequencyω [Hz] 1B 1F 2B 2F 3B 3F C-C 0° 89.5956 116.5424 250.1030 277.5957 462.3860 490.3354 30° 109.5489 136.5861 325.5890 353.6101 653.8300 683.2888 60° 275.9256 302.8678 724.3444 751.8162 1314.0023 1341.9065 75° 356.2460 382.9658 765.3613 792.1977 1233.6654 1260.4888 S-S 0° 60.1498 87.1267 211.7786 239.3596 423.3616 451.4875 30° 71.8321 98.8569 263.8645 291.8418 569.8837 599.3474 60° 193.2056 220.5798 618.5663 646.1292 1207.7548 1235.8342 75° 288.0808 314.8729 730.6617 757.5166 1214.6430 1241.4759 C-F 0° 4.0188 30.8277 91.7179 119.2882 266.1023 294.4848 30° 6.1303 32.9436 109.4554 137.1525 334.9323 364.0539 60° 35.6337 62.4424 282.7588 310.3222 771.1312 799.4811 75° 75.0446 101.8206 402.6232 429.7342 895.0152 922.1036Figure 9
The first three natural frequencies of the rotating composite thin-walled shaft versus ply angle (Ω = 800rpm).
(a)
C-C (b)
S-S (c)
C-FFigure10 shows the first three natural frequencies of the rotating composite thin-walled shaft versus the ratio of mean radius to thickness. The natural frequencies increase with the ratio of radius to thickness, and this tendency becomes more obvious when the mode is higher.Figure 10
The first three natural frequencies of the composite thin-walled rotating shaft versus mean radius to thickness ratios (Ω= 800rpm, θ=60°).
(a)
C-C (b)
S-S (c)
C-FFigure11 shows the first three frequencies of the rotating composite thin-walled shaft versus the ratio of length to mean radius. The figure demonstrates that the natural frequencies decrease with the increase of the ratio of length to mean radius. In addition, the higher the mode, the faster the natural frequencies decrease.Figure 11
The first three natural frequencies of the rotating composite thin-walled shaft versus length to mean radius ratio (Ω=800rpm, θ=60°).
(a)
C-C (b)
S-S (c)
C-F


## 5. Conclusions

A refined VAM and Hamilton’s principle were used to establish the vibration differential equation of the rotating composite thin-walled shaft, and the equation was solved by the GDQM. The computational results by this method were compared with those available in literature, and it was validated that the GDQM is accurate and efficient for the frequency analysis of the rotating composite shaft. The influences of the boundary conditions, rotating speed, ply angle, ratio of radius over thickness, and ratio of length over radius on the frequency characteristics were discussed.Compared with the numerical solution methods such as the Galerkin method and finite element method, the GDQM has the advantages of simple mathematical principle, fast convergence speed, high calculation accuracy, small calculation amount and less memory demand, etc. According to the results obtained in this work, the main conclusions are followed as below:(1) When the composite shaft rotates, a bifurcation of natural frequencies appears due to the effects of gyroscopic forces. With the increase of spinning speed, the forward whirling frequencies increase, while the backward whirling frequencies decrease.(2) For the same ply angle, with the clamped boundary condition, the composite thin-walled shaft has higher natural frequencies and critical spinning speed; on the other hand, with simply supported and cantilever boundary conditions, both natural frequencies and critical spinning speed are lower.(3) The natural frequencies of the rotating composite thin-walled shaft increase with the ratio of diameter over thickness and decrease with the increasing ratio of length to diameter. The natural frequencies of higher-order mode vary faster than those of lower order mode.



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*Source: 1538329-2019-03-20.xml*