Eigenvalue Analysis of Thin Plate with Complicated Shapes By a Novel Infinite Element Method

Deshin Liu and Yuwei Chen,

1 Department of Mechanical Engineering and Advanced Institute of Manufacturing with High-Tech Innovations,National Chung-Cheng University,Minhsiung,Chiayi 62102,Taiwan.

Abstract:A novel infinite element method (IEM) is presented for solving plate vibration problems in this paper.In the proposed IEM,the substructure domain is partitioned into multiple layers of geometrically similar finite elements which use only the data of the boundary nodes.A convergence criterion based on the trace of the mass matrix is used to determine the number of layers in the IE model partitioning process.Furthermore,in implementing the Craig-Bampton (CB) reduction method,the inversion of the global stiffness matrix is calculated using only the stiffness matrix of the first element layer.The validity and performance of the proposed method are investigated by means of four illustrative problems.The first example considers the case of a simple clamped rectangular plate.It is observed that the IEM results are consistent with the theoretical results for first six natural frequencies.The second example considers the frequency response of a clamped rectangular plate with a crack.The main feature of IEM is that a very fine and good quality virtual mesh can be created around the crack tip.The third and fourth examples consider the natural frequency of a multiple point supported plate and a perforated plate,respectively.The results are obtained just need to adjust the reference point or boundary nodes.The parametric analyses for various geometric profiles are easy to be conducted using these numerical techniques.In general,the results presented in this study have shown that the proposed method provides a direct,convenient and accurate tool for eigenvalue analysis of thin plate structure with complicated shapes.

Keywords:Infinite element method,Craig-Bampton method,plate vibration,eigenvalue problem.

1 Introduction

The classical finite element method solving large structural or singularity problems usually requires the construction of a large number of elements,resulting in insufficient computer memory or slow computation.Therefore,many scholars have proposed methods to reduce the degree of freedom of the model (such as Irons-Guyan reduction method,modal synthesis method,etc.) or other numerical methods (such as boundary element method,meshless method,etc.) to solve the above problems.The similarity of elements is also one of the numerical methods.

Thatcher [Thatcher (1975)] combines the concepts of finite element methods and similarity to create many refined triangle elements near a singularity to approximate the solution.For the problem of cracked structural,Ying [Ying (1978)] produces a number of similar triangular elements near the crack tip and combines them into a single element,was called infinite similar element method (ISEM).Han et al.[Han and Ying (1979);Han and Ying (1982)] continue to study the derivation and application of the ISEM,the many elements are reduced into a super-element using elemental similarity,and consider the inertial effect,was called infinite element method (IEM).Ying [Ying (1992)] proved that there exists a transformation matrix to relate the nodal displacement vector between the inner and outer layers,therefore the total stiffness matrix could reduce to form a combined stiffness matrix related only to boundary nodes.Notably,it was shown that the combined stiffness matrix could converge to a certain constant quantity as the number of layers approached to infinity.Liu has been working on the study of the IEM since the 2000s.Liu et al.[Liu and Chiou (2003a);Liu and Chiou (2003b)] proposed a hybrid IE-FE model to analyze elastic problems with multiple cracks.Liu et al.[Liu,Zhuang and Chung (2009)] extended the IEFE formalism to model and analyze moisture diffusion in a heterogeneous epoxy resin containing multiple randomly distributed particles.In a later study,Liu et al.[Liu,Tu and Chung (2013)] proposed a Plate IEM (PIEM) algorithm based on Mindlin-Reissner theory to investigate the bending strength of plates with through-thickness holes.According to the above literature,most scholars use the similarity of elements to degrade IEM to the boundary nodes.Although the amount of computing can be greatly reduced in these methods,the accuracy of the higher natural frequency is somewhat inadequate.

In earlier works,Guyan [Guyan (1965)],Irons [Irons (1965)] and Kidder [Kidder (1973)] proposed the reduction procedures to degenerate the mass/stiffness matrix of the FE domain,respectively.However,the accuracy decreased because of the neglect of the inertial effect in the reduction procedures for dynamic analysis.Component mode synthesis (CMS) is a dynamic matrix reduction method.Hurty [Hurty (1965)] first proposed a component mode synthesis that used rigid-body modes,redundant-interface modes and fixed-interface normal modes to form a structural modal matrix.Craig and Bampton [Craig and Bampton (1968)] simplified Hurty’s method,proposed the constraint modes and fixedinterface normal modes to form a structural modal matrix,this scheme is called Craig-Bampton method (CBM).Saito et al.[Saito,Castanier and Pierre (2006)],Gupta et al.[Gupta,Hussein,Degrande et al.(2007)] and Kim et al.[Kim,Kim and Yoo (2010)] used CBM reduction techniques to simplify complex models,respectively.Liu and Lin [Liu and Lin (2016)] integrated Craig-Bampton method with a dynamic infinite element (DIE) formulation to analyze the membrane vibration problem.Liu et al.[Liu and Chen (2018)] improved the efficiency of the CBM reduction for DIE model.The efficiency of the CBM reduction process is improved by using a numerically recursive procedure to calculate the inversion of stiffness matrix.

Based on the Liu et al.[Liu and Chen (2018)] proposed scheme,eigenvalue analysis of thin plate with complicated shapes are investigated in this paper.First,an infinite element model of the Mindlin-Reissner plate is created,and then the model is reduced adopting the Craig-Bampton method.In Mindlin-Reissner plate theory,the conventional IEM algorithm cannot be applied.The stiffness matrix needs to be disassembled and recombined to obtain the similarity between the element layers.The validity and performance of the proposed method are studied by means of four familiar thin plate structures with complicated shape,involve a rectangular plate,a side cracked plate,a multiple point supported plate,and a perforated plate.

2 Infinite element method

2.1 Finite element formulation of mindlin-reissner plate

Mindlin-Reissner plate theory [Mindlin (1951)] is an extension of Kirchhoff-Love plate theory [Love (1888)] which takes into account shear deformations through the thickness of the plate.The equation of motion of the plate is established as:

with mass matrix [M],stiffness matrix [K] and the displacement vector{δ}.From Mindlin-Reissner plate theory,the displacement {δ} = {u,v,w}Thave the form given in Eq.(2).

wherexandyare in-plane axes located at the mid-plane of the plate,andzis along the direction of plate thickness as seen in Fig.1.

Figure 1:Coordinate frame of the plate element.

Theθxandθyare the rotations of the mid-plane about theyandxaxes,respectively;andγis the angle caused by the transverse shear deformation.Mapping from the physical coordinates to the natural coordinates,the rotate and transverse displacements can be expressed as:

whereHiare the 4-node plate finite element shape functions,and (ζ,η) is represented as natural coordinates.From that the element matrices are established as:

[Bb],[Bs] and [N] consist of the shape functions as listed in Eqs.(6)-(8),respectively.In addition,[Db],[Ds] and [I] are related to dimension or material properties of model as listed in Eqs.(9)-(11),respectively.

2.2 Infinite element model

The basic concept of IE model as shown in Fig.2,the computational domain is partitioned into multiple layers of geometrically-similar elements.For elementI,the local nodesiare numbered 1,2,3,and 4 in the counterclockwise direction,and (,) denotes the global coordinate value of nodei.By taking the global originOandcas the center of the similarity and the proportionality ratio,respectively,the elementIIis created.The global coordinates of elementsIandIIare related as shown in Eq.(12).From Eq.(12),and recalling Eq.(5),the determinants of the Jacobian matrices of the elementIandIIare related as shown in Eq.(13).Similarly,from Eq.(12),and recalling Eq.(6),the relation of [Bb] of the elementIandIIcan be shown in Eq.(14) [Liu and Chiou (2003a)].

Figure 2:Schematic representation of geometrically-similar 2D elements in IE formulation

Therefore,as shown in Eq.(15),the mass matrix [M] and bending stiffness matrix [Kb] of the first and second element layers are related.The matrices of the first element layer have the forms shown in Eq.(16),where the mass matrix is transformed as a diagonal matrix by a lumped-mass formulation.

From Eq.(15),the four-node elementsIandIIcan both be mapped using the same squareshaped master element.In other words,these elements are designated as similar elements when the coordinate of an element is similar to other elements.Combining the matrices from first ton-thelement layer,the mass and bending stiffness matrices can be established as in Eq.(17) and Eq.(18).

whereR=L1+c2L2andQ=K1+K2.For shear stiffness,let the matrix [Bs] be partitioned into two submatrices:

Substituting Eq.(19) into Eq.(4),the shear stiffness is re-represented as follow:

where

According to geometric similarity,the relationship of the shear stiffness matrix between the first and second element layers is:

where the submatrices of the first element layer are shown as:

Similarly,combining the shear stiffness matrices from first ton-thelement layer,can be established as:

where

Recalling Eq.(1),the eigenvalue formulation can be obtained by assembling the aforementioned equations follows:

where

The convergence analysis of element number is necessary before the numerical analysis.In practice,the convergence of the mass matrix depends on the number of element layers in the IE model.For dynamic problems,the trace of the mass matrix will converge to a constant [Liu and Chen (2018)]:

ifc＜1,then

wherendenotes the number of chosen element layers,andTr[M]IEconverges to a constant as the number of element layers approaches infinity.

2.3 Model reduction

In this study,the Craig-Bampton reduction procedure [Craig and Bampton (1968)] is adopted to reduce the infinite element model.The mass and stiffness matrices and displacement vector in the Eq.(26) can be partitioned respectively as:

where the vectorsuBanduIdenote physical displacements of boundary and interior points,respectively.In the Craig-Bampton reduction procedure,the coordinate transformation relating the modal coordinate to the physical coordinates is:

where the constraint modes [φC] are defined as the mode shapes of the interior freedoms due to successive unit displacements of the boundary points,with all other boundary points being totally constrained:

And the normal modes [φN] are defined as the normal modes with totally constrained boundary.Thus,they are the eigenvectors of the eigenvalue problem:

where matrices [Ui] and [Vi] are computed as follow:

Denoting the diagonal blocks ofasDi,that can be obtained recursively as follow [Jain,Li,Cauley et al.(2007)]:

where matrices [Si] are defined as follow:

And [Si] are computed using the following numerically recursive procedure:

The inversion of [KII] can be rewritten as follow:

where the [KII]-1is calculated using only the stiffness matrix of the first element layer.Substituting Eq.(34) into Eq.(26),the eigenequation can be obtained by substituting the coordinate transformation relation:

3 Case studies

3.1 Rectangular plate

Consider a rectangular plate shown in Fig.3(a).Let the plate geometric conditions and material properties be given as follows:a=1.2 m,b=1.0 m,thicknessh=0.01 m,mass densityρ=7800 kg/m3,Young’s modulusE=200 GPa,and Poisson’s ratioν=0.3.Furthermore,assume that the plate is clamped on all four sides,the natural frequencyωm,nare estimated respectively as:

In implementing the IE model,88 nodes are deployed at the boundary,and the virtual mesh pattern is shown in Fig.3(b).For an ideal element,the aspect ratio should have a value of 1.0,so the ratio should be equal to 0.875 in this case.A number of requiredcelement layers=40 is obtained by the convergence criterion Eq.(30).The convergence process is shown in Fig.4.Based on the above results,for more accurate results,the number of layers,s,is 40 and the proportionality ratio,c,is 0.875 with respect to the related similar partition centers.The first six mode shapes of the rectangular plate are depicted in Fig.5.The results for the six lowest natural frequencies are shown in Tab.1 with the theoretical results,where the relative difference is less than 0.5%.Comparing the sets of natural frequencies reveals,the IEM results are in satisfactory agreement with the theoretical results.

Table 1:First six natural frequencies of clamped rectangular plate (Hz)

Figure 3:Schematic illustration and virtual mesh configuration of the clamped rectangular plate

Figure 4:The convergence process of the required virtual element layer

Figure 5:First six mode shapes of clamped rectangular plate

3.2 Cracked plate

Considering a rectangular plate with a side through-thickness crack,and the crack has a lengthl,is shown in Fig.6(a).The plate is assumed be clamped on all the sides.The geometric conditions of the plate are assigned as follows:a=0.5 m,b=1.0 m,thicknessh=0.01 m.The same material properties are assigned as previous example:mass densityρ=7800 kg/m3,Young’s modulusE=200 GPa,and Poisson’s ratioν=0.3.In this study,the crack lengthis assigned various values in the range ofl=0.1～0.4 m.The proportionality ratio is set asc=0.875,and number of virtual element layers=40 as in the previous example.Fig.6(b) shows the virtual mesh configuration and virtual node arrangement of the IE model.Given various crack lengths,the results obtained from the proposed IEM for the six lowest natural frequencies as shown in Fig.7.The results show that the fourth and fifth frequencies are highly sensitive to the crack length.Fig.8 shows the first six mode shapes given crack lengths ofl=0.1,0.2,0.3,and 0.4 m,respectively.

Using these efficient numerical techniques,a very fine and good quality grid pattern can be created around each crack tip without many freedoms.Furthermore,the results of obtaining IEM only need to adjust the reference point,that is easily allowed to conduct parametric analysis for various crack lengths.

Figure 6:Schematic illustration and virtual mesh configuration of the cracked plate

Figure 7:First six natural frequencies of cracked plate (Hz)

Figure 8:First six mode shapes of cracked plate

3.3 Multiple point supported plate

Considering a multiple point supported plate is shown in Fig.9(a),a square plate is locked on the four symmetrically point supports.The dimensions of the plate are assigned as follows:a=1 m and thicknessh=0.01 m,and the same material properties as first example.Fig.9(b) shows the virtual mesh configuration and virtual node arrangement of the corresponding model.The model consists of four subdomains,each of which is an IE model.As shown,the reference points are set at the support points,respectively.The proportionality ratiocand number of virtual element layersare same as the first example.Fig.10 shows the six lowest natural frequencies obtained from IEM,and consider the support position is shifted formx0=0.1 m tox0=0.4 m.The maximum fundamental frequency is achieved in the range aroundx0=0.175～0.275 m.Li et al.[Li,Tian,Wang et al.(2016)] have confirmed this finding.Fig.11 shows the first six mode shapes given support positions ofx0=0.1,0.2,0.3,and 0.4 m,respectively.The results show that the rectangular plate begins to weaken significantly when the support positionx0is shifted over 0.25 m.In addition,the sixth natural frequency is decreased but not apparent when the support positionx0is shifted over 0.25 m.That mainly due to the supports are closed enough to the center of the thin plate,so that has little effect for the natural frequencies and mode shapes of sixth mode.As in the second example,the results of obtaining IEM only need to adjust the reference point.It is easily allowed to conduct parametric analysis for various support position.Furthermore,this example demonstrates the feasibility of combining IEM subdomains.

Figure 9:Schematic illustration and virtual mesh configuration of the multiple supported plate

Figure 10:First six natural frequencies of the multiple point supported plate (Hz)

Figure 11:First six mode shapes of the multiple point supported plate

3.4 Perforated plate

Considering a perforated plate is shown in Fig.12(a),where the dimensions of the plate are assigned as follows:a=0.8 m and thicknessh=0.01 m,and the same material properties as first example.The plate is assumed be clamped on all four sides and the circle holes have a radiusr.The circle hole radiusris assigned various values in the range ofr=0.03～0.07 m in this study.Fig.12(b) shows the virtual mesh configuration and virtual node arrangement of the corresponding model.The model consists of sixteen subdomains,each of which is the same IE model.The proportionality ratiocand number of virtual element layersare same as the first example.Fig.13 shows the six lowest natural frequencies given various circle hole sizes.Fig.14 shows the first six mode shapes given hole radius ofr=0.03,0.04,0.05,0.06,and 0.07 m,respectively.

This is another case to show the advantage of IEM.The results are obtained just need to adjust the boundary nodes of one subdomain.The parametric analyses for various circle hole radius are easy to be conducted.Furthermore,this example not only demonstrates the feasibility of combining IEM subdomains,but also copying.

Figure 12:Schematic illustration and virtual mesh configuration of the perforated plate

Figure 13:First six natural frequencies of the perforated plate (Hz)

Figure 14:First six mode shapes of the perforated plate

4 Conclusions

A novel infinite element method is presented for solving Mindlin-Reissner plate vibration problems in this study.In the proposed method,the substructure domain is partitioned into multiple layers of geometrically similar finite elements,which use only the data of the boundary nodes,and the degree of freedom of the model is reduced using Craig-Bampton (CB) method.The convergence analysis of element layers involves only the mass matrix of the first element layer.Furthermore,in Craig-Bampton (CB) reduction process,the inversion of the symmetric block-tridiagonal global stiffness matrix has been determined only using the stiffness matrix of the first element layer.The validity of the proposed IEM has been demonstrated by means of four familiar examples involving a rectangular plate,a side cracked plate,a multiple point supported plate,and a perforated plate.The first example has demonstrated the general feasibility and accuracy of the proposed method.The second example considers a rectangular plate containing a through-thickness crack.The results show that the fourth and fifth frequencies are highly sensitive to the crack length.The third example considers a four point supported plate.The results show that the rectangular plate begins to weaken apparently when the support positionx0is shifted over 0.25 m.The fourth example considers a perforated plate.The results show that the plate starts to weaken but is not apparent when the hole becomes larger.The above examples show the advantages of IEM for singularity problems and geometric parametric analysis.In general,the results presented in this study have shown that the proposed method provides a direct,convenient and accurate tool for eigenvalue analysis of thin plate structure with complicated shapes.

Acknowledgement:This work was partially supported by the Advanced Institute of Manufacturing with High-tech Innovations (AIM-HI) from The Featured Areas Research Center Program within the framework of the Higher Education Sprout Project by the Ministry of Education (MOE) in Taiwan.This research was also supported by R.O.C.MOST Foundation Contract No.MOST108-3017-F-194 -001.