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Latin American Journal of Solids and Structures
versão Online ISSN 16797825
Lat. Am. j. solids struct. vol.9 no.1 Rio de Janeiro 2012
http://dx.doi.org/10.1590/S167978252012000100001
ARTICLES
Vibration analysis of stiffened plates using finite element method
Shahed Jafarpour Hamedani^{I}; Mohammad Reza Khedmati^{II,} ^{*}; Saeed Azkat^{III}
^{I}M.Sc. Student, Faculty of Marine Technology, Amirkabir University of Technology, Tehran 15914 – Iran
^{II}Associate Professor, Faculty of Marine Technology, Amirkabir University of Technology, Tehran 15914 – Iran
^{III}Head of Maintenance and Planning Department, Iranian Offshore Oil Company, Tehran 1966664791 – Iran
ABSTRACT
This paper presents the vibration analysis of stiffened plates, using both conventional and super finite element methods. Mindlin plate and Timoshenko beam theories are utilized so as to formulate the plate and stiffeners, respectively. Eccentricity of the stiffeners is considered and they are not limited to be placed on nodal lines. Therefore, any configuration of plate and stiffeners can be modeled. Numerical examples are proposed to study the accuracy and convergence characteristics of the super elements. Effects of various parameters such as the boundary conditions of the plate, along with orientation, eccentricity, dimensions and number of the stiffeners on free vibration characteristics of stiffened panels are studied.
Keywords: vibration, stiffened plates, Finite Element Method, super element.
1 INTRODUCTION
Noise and vibration control is an increasingly important area in the most fields of engineering. There are many vibrating parts in structures of ships, aircrafts and offshore platforms. The amplitude of their motions can be large due to the inherently low damping characteristics of these structures. Such noise is commonly eradicated by use of heavy viscoelastic damping materials which lead to increase in cost and weight. Vibration isolators between pieces of equipment and their supporting structures can be another solution. Clearly, isolating large structures can be difficult, expensive and in some cases, such as the wings of an aircraft, almost impossible. In recent years, much attention has been focused on active noise control of structures. However, their installation and maintenance can be expensive, so possible passive solutions would be preferable [20].
In the case of plates/shells, one common and cost effective approach in order to improve their NVH^{1} performance is to add stiffeners. Stiffened plates are lightweight, highstrength structural elements, commonly used in ships, aircrafts, submarines, offshore drilling rigs, pressure vessels, bridges, and roofing units [19, 21]. Most of these structures are required to operate in dynamic environments. Therefore, a thorough study of their dynamic behavior and characteristics is essential in order to develop a perfect strategy for modal vibration control [8]. The stiffeners enhance the rigidity of base structures by increasing their cross sectional second moment of inertia. The configuration of the stiffeners should be consistent with the natural modes likely to be excited by the service loads, so as to arrive at a design with a high strengthtoweight ratio [4]. In general, the stiffening of the structures is applied, because of two main reasons: Increasing load carrying capacity and preventing buckling, especially in the case of inplane loading [6].
Different geometries of stiffened shells have been studied in the literature which can be categorized into three groups including plates, single curved shells, and double curved shells. The Superimposition of the stiffeners with respect to the plate midplane, i.e. eccentric or concentric is also a matter of concern for the structural analysts. The stiffener of which, centroid is coincident with the plate/shell midsurface, is called concentric, otherwise eccentric stiffener [16].
The analysis of stiffened plate vibration has been the purpose of numerous investigations. Among the known solution techniques, the finite element method is certainly the most favourable. Olson and Hazell [14] predicted and measured the first 24 eigenfrequencies of stiffened plates using FEM and realtime laser holography. Mustafa and Ali [12] developed an eightnoded orthogonally stiffened super finite element to study the free vibration of a stiffened cylindrical shell with diaphragm ends. Experimental measurements of natural frequencies and mode shapes of an orthogonally stiffened shell were also carried out to substantiate theoretical predictions. A plate with centrally placed stiffener has been studied by Mukherjee and Mukhopadhyay [11]. An isoparametric stiffened plate element has been utilized in their analysis considering shear deformation in order to analyse thick as well as thin plates. In the proposed formulation, the stiffeners can be placed anywhere within the plate element and they are not required to necessarily follow the nodal lines. Koko and olson [9] have developed another super element to model the free vibration of stiffened plates. This super element allows a coarser mesh (at the expense of more complex interpolation functions), so that only a single element per bay or span is needed. Sinha and Mukhopadhyay [18] investigated stiffened shells utilizing a highprecision triangular shallow shell element in which stiffeners can be anywhere within the plate element. The vibration analysis of stiffened plates has been investigated by Barrette and Beslin [3] using hierarchical finite elements with a set of local trigonometric interpolation functions. Nayak and Bandyopadhyay [13] presented a finite element analysis for free vibration behaviour of doubly curved stiffened shallow shells. The eight/ninenode doubly curved isoparametric thin shallow shell elements along with the threenode curved isoparametric beam element has been used in this study. Their Formulation suffers from the limitation, that stiffeners can only be placed along nodal lines in x or y directions. Two years later Samanta and Mukhopadhyay [17] developed a new 3 noded stiffened shell element and applied it in determining natural frequencies and mode shapes of the different stiffened structures. Another Stiffened element with seven degrees of freedom per node has been presented by voros [21]. Torsionflexural coupling, torsional warping effect and the second order terms of finite rotations have been considered in this investigation.
In the present work, four different elements including two conventional and two super elements [2] have been used so as to predict the dynamic characteristics of stiffened panels. The formulation of the plate and stiffeners are both based on the first order shear deformation theories so it can be applicable to both thin and thick plates. In the proposed formulation, the stiffeners are modeled in such a way that they can be placed anywhere within the plate element. This may be considered as a prominent advantage over most of approximate analyses, since this method can be applied to any plate and stiffeners configuration. It is worth to mention that, the shape function of the plate is also used to express the displacement of the stiffener at any generic point along it. In this way, displacement compatibility between the plate and the stiffeners is ensured automatically in the whole continuum and no additional node is utilized for the stiffeners.
After studying the accuracy and convergence of super elements, they have been utilized to investigate different problems. Because of significantly less time and fewer global DOFs needed for super elements, they are useful for preliminary designs and parametric studies; where, repeated calculations are often required. Effects of various parameters such as the orientation, eccentricity and number of stiffeners on free vibration characteristics have been studied. These examples demonstrate the strength of the developed formulation, and it is hoped that the results presented will prove useful to other researchers. Up to authors' knowledge, such results have not been published before.
2 FORMULATION
The equation of motion for free vibration of elastic bodies, with infinitesimal displacements is:
Where [M] and [K] is overall mass and stiffness matrix, respectively. {d} is the displacement vector and dots denote derivatives with respect to time. Overall matrices in equation (1) are obtained by assembling matrices corresponding to each element, and applying appropriate boundary condition. In this paper, the following hypotheses are made:

The material of the plate and the stiffeners is isotropic, linear elastic and Hookian.

Inplane displacements are neglected in order to reduce the computational time. If the plate edges are immovable in the plane, the inplane displacements will be much smaller than outofplane ones. Therefore, in such cases this can be a rational assumption.

Stresses in the direction normal to the plate middle surface are negligible.

Normal to the undeformed midplane remains straight and unstretched in length, but not necessarily normal to the deformed midplane. This assumption implies the consideration of shear deformation, but it also leads to the nonzero shear stresses at the free surface, because of constant shear stress through the plate thickness.

Rotary inertia effect is included.

The magnitude of transverse deflection (w) is small in comparison to the plate thickness (h).
Stiffness and mass matrices corresponding to each element are the summation of the plate stiffness and mass matrices, and the contributions of stiffeners to this element as
in which plate and stiffener are denoted by subscripts p and s, respectively [5, 7, 10].
2.1 Plate element
A flat, thin/thick plate of uniform thickness is considered. As it was assumed, constitutive material is homogeneous, linear elastic and Hookian. For the purpose of finite element modeling 4 types of element are used, including eight/ninenode conventional elements and eight/twelvenode super elements. Each node has 3 degrees of freedom. They consist of one displacement in transverse direction, and two rotations about xaxis and yaxis. Displacement at each point within the element is related to nodal values by
where i and n are the corresponding node and total number of nodes in a the plate element, and N_{i} is the shape function of the i^{th} node. In the isoparametric formulation the above functions are used for defining the displacement as well as the location of any point within the element in terms of nodal coordinates.
Implementing Mindlin plate theory, displacement filed can be expressed as follow (figure 1)
in which z is measured from the neutral surface of whole structure consists of the plate and one or more stiffeners. Based on linear elasticity the strain component are given by
Where ε_{x} and ε_{y} are normal strains, and ε_{xy}, ε_{xz} and ε_{yz} are shear strains. For isotropic, linear elastic, Hookian Materials
Where σ_{x} and σ_{y} are normal strains, τ_{xy}, τ_{xz} and τ_{yz} are shear strains, E is the elasticity modulus, G is the shear modulus, ν is the poison's ratio and κ is the shear correction factor to compensate the error due to the assumption of constant shear strains within the plate thickness. In this stage, strain energy functional of the plate element can be obtained
In which V is the volume of the plate element. The kinetic energy of vibrating plate element is also given by
In which t denotes time and ρ is the plate mass density. The integrations are calculated using gauss quadrate scheme. Special considerations are applied so as to avoid shear locking effect [5, 7, 10, 15, 22].
2.2 Stiffener
In this section, the matrices corresponding to the stiffener which can be placed everywhere within the plate element are extracted. The proposed method releases the formulation from the limitation of stiffeners to be lied along nodal lines. Hence, oblique stiffeners can be analysed. For this purpose, by use of same shape function for both the plate and the stiffeners, displacement compatibility is guaranteed and no additional node is introduced for the stiffeners. The stiffener specifications are calculated at the Gauss points along it. Therefore a transformed coordinate system is implemented (Figure 2). Based on Timoshenko beam theory, displacement field of the stiffener is given by
where θ_{x'} and θ_{y'} are rotations about x' and y', respectively. As mentioned before, z is measured from the reference surface of whole structure. Displacement functions can be expressed in terms of nodal values of plate element using a transformation matrix (Eq. 15) and aforementioned shape functions.
Again, by applying linear elasticity
Similar to the plate element, for an isotropic material
In which σ_{x'} is the normal stress along the longitudinal axis of the stiffener, τ_{x'z'} is shear strain and τ_{x'y'} is torsional strain. So energy functional of the stiffener are obtained as follow
in which V' is the volume of the part stiffener, confined within the plate element. The governing equation of vibration of stiffened plates is derived by use of Hamilton's principle which requires
where d is the variational operator. Now stiffness and mass matrices of the stiffened element can be calculated. By assembling matrices corresponding to each element in a suitable manner, overall stiffness and mass matrices are obtained. Finally, boundary conditions are applied and governing eigenvalue equation for undamped free vibration of stiffened plates takes the form
where ω is the natural frequency in radian per second, and {d} represents eigenvector [5, 7, 10, 15, 22].
2.3 Super element
The super element is a compound one, which is composed of a number of conventional finite elements. In this regard, each super element is divided into a number of conventional elements and corresponding matrices to each subdivided element are constructed (Figure 3).
Subdivided elements' matrices are assembled, as in general finite element procedure. Degrees of freedom related to servant nodes, defined later, are then condensed out while the effect of them on super element matrices is taken into account. This procedure is named as dynamic condensation, which is described in the following. The dynamic equilibrium equation neglecting damping effect is given by,
Where index s denotes the terms related to the DOFs of super nodes that will remain after condensation, and c represents the terms related to other DOFs which will condensed out through the this procedure. They are sometimes called as master and servant nodes, respectively. Using appropriate transformation matrix the following equation is obtained,
In this way, the effect of servant node is also embedded in the condensed super element. Aforementioned element has remarkable ability to reduce the size of problem.
3 NUMERICAL EXAMPLES
3.1 Vibration of a Mindlin plate with different boundary conditions
In order to assess the vibration behaviour of the super plate elements, free vibration of a square Mindlin plate with different boundary conditions is first investigated. This problem has been studied by several investigators using exact or other approximate methods. The natural frequencies are presented in terms of the nondimensional eigenvalue λ, given by
where D is the plate flexural rigidity, h is the plate thickness, and a the side length of the plate. The eigenvalues for the various combinations of edge conditions are shown in Table 1.
The comparison between present and other numerical results shows a good agreement in all ten cases considered. It should be noted that, unlike super element developed by Koko and Olson [9] the present super elements result in accurate values for second and higher modes. It is also indicated that, implementing super elements leads to reduction in computational time with no significant change in results accuracy, which is expected because of the significantly fewer number of global DOFs, used in the super elements.
3.2 Clamped square plate with a central stiffener
To validate the present formulations and study the characteristics of super elements, a stiffened clamped square plate with central stiffener (Figure 4) is analyzed. (E = 6.87 × 10^{10}, ν = 0.3, ρ = 2823 )
The first ten natural frequencies from the super elements are compared with the finite element and experimental results in Table 2. A fundamental modeling difference between the super element developed by Koko and Olson [9] and present elements, is that they allow for inplane displacements of the plate, whereas the present theory assumes pure bending deformation of the plate. However, such effects are expected to be small for thin plates.
All frequencies from the present approach are very close to the experimental and conventional finite element results. The agreement between the super elements and the experimental results reported by Olson and Hazell is wonderful. Although deviation of the eigenfrequencies computed employing S12 from mentioned results is negligible, based on authors' point of view results obtained by S8 are more accurate. Because Due to the finite stiffness of any clamped structure, exact edge conditions are not possible in practice. Consequently numerical results must be on the stiff side of experimental ones.
Moreover, it can be seen from the table that there is a significant reduction in the global DOFs and consequently in computational time by utilizing super elements, compared to the conventional finite elements. As another conclusion, effect of neglecting inplane deflections on natural frequencies isn't considerable in this case.
3.3 Clamped square plate with two parallel stiffeners
This configuration has first been studied by Olson and Hazell [14] using experimental and conventional finite element method (Figure 5). Boundary conditions and material properties are same as the previous example.
Eigenfrequencies obtained from the present analysis are presented in Table 3 along with the previous numerical and experimental results.
Again, there are significantly fewer global DOFs used in the super element models than the conventional finite element models, which leads to considerable reduction in computational time. Present super elements predictions are almost in agreement with the results obtained from previous super element results [14]. But there is relatively remarkable difference with the experimental results. The reason may be
1. Perfectly clamped edges are impossible in practice, so experimental results are lower than the numerical ones, as said.
2. Inplane deflections are neglected in this investigation. With increase in number of stiffeners these displacements play more important role. Although this simplification leads to less computational time, can affect results when number of stiffeners increases. Because in this case deviation of reference surface of whole structure from plate midplane and consequently first moment of inertia gets more considerable.
Eigenfrequencies from present conventional elements are always on the stiff side of experimental values except for two modes, contrary to what is expected of a displacement based theory. It is possible that the experimental procedure have not measured the frequencies of those modes accurately. In the case of super elements, again S8 leads to more acceptable results, especially for the first three modes. Therefore, the viability of the super element formulation is clearly exhibited in that most of the super element solutions are close to the experimental and conventional finite element results, even though this method uses significantly fewer DOFS.
3.4 Convergence study
The accuracy of numerical calculations depends on the number of the divisions. Convergence characteristics of the elements used with respect to number of divisions is studied in this section. The Analysis is performed on a clamped square plate with central stiffener (Figure 4). Results are shown in Figure 6.
It can be seen obviously from the Figure 6 that the conventional elements have faster rate of convergence compared to super elements. In fact, super elements do not converge necessarily. Although these elements lead to acceptable results with low number of elements, recedes from the exact eigenfrequencies with an increase in number of divisions. The reason may be eliminating internal nodes and making the super element softer. As another conclusion, 2 and 3 elements per bay is needed for analyzing a stiffened plate using the S12 and S8 elements, respectively, but in other cases 5 elements should be employed in each bay. The rest of present calculations are based on mentioned division numbers.
3.5 Effect of eccentricity
To investigate the effect of eccentricity on the free vibration of stiffened plates, a clamped square plate with one, two and three stiffeners has been analysed for both concentric and eccentric types (Figure 7). (E = 2.06×10^{11}, ν = 0.3, ρ = 7650 )
The results obtained from such case are presented in Table 4. The effect of eccentricity on eigenfrequencies has been observed.
It is interesting to note that the inclusion of eccentricity does not affect the values of natural frequencies of the clamped plate with merely one stiffener. As the number of stiffeners increases, effect of eccentricity is more insignificant. Deviation of neutral surface of whole structure, with respect to which second moments of inertia, should be calculated from mid plane of the plate may be the reason. It is worth to mention that in the case of concentric stiffeners the neutral surface is same as the mid plane of the plate.
From the preceding discussion it can be concluded that the consideration of eccentricity affects the natural frequencies of stiffened clamped plates. But when there is just one stiffener, the effect of eccentricity can be neglected without any significant loss of accuracy. Whether this conclusion is true for other boundary conditions or not, needs more investigations.
3.6 Number of stiffeners
The objective of the present example is to study the influence of the number of stiffeners on natural frequencies of square clamped plates. Dimensions and material properties are the same as previous section. Number of stiffeners is changed from 0 to 11 and results are summarized in Figure 8 for the first five modes.
Figure 8 clearly shows that the fundamental frequency is increasing with the increase in the number of stiffeners, which was expected before. However this increase gradually becomes insignificant after a critical value of the number of stiffeners, as generally observed for all 5 modes. This critical value is 4 or 5 stiffeners. Based on authors' point of view the reason is that, utilizing stiffeners leads to eliminating some mode shapes, so the fundamental frequency increases. But after this critical value, no mode shape elimination occurs and stiffened plate acts as a plate with larger thickness. Therefore providing more than four stiffeners is not recommended based on economical point of view.
3.7 Inclination angle
Improving the vibration or noise characteristics of structures by changing its configuration has been a subject that has fascinated the minds of engineers and scientists during last decades [1]. In this section, the orientation angle of the stiffener arranged over a clamped square plate is selected to optimize the dynamic characteristics of these plates/stiffener assemblies (Figure 9).
The objective is to find the inclination angle (ϕ) for the stiffener arrangement that maximizes the fundamental frequency of the stiffened plate structure. The first natural frequency as a function of the stiffener inclination angle is calculated and plotted in Figure 10.
With due attention to Figure 10 an optimum value for inclination angle of 80º was found to maximize the fundamental frequency. The presented approach can be invaluable in the design of stiffened plates for various vibration and noise control applications.
3.8 Practical configurations in ship
Two practical configurations which are used practically in the body of ships are analysed. These two cases are square clamped plates with one stiffener (Case 1) and with two orthogonal stiffeners (Case 2) shown in figure 11. The dimensions of the plate and the stiffeners are the same in both cases. The material properties are similar to the previous example.
Calculations have been performed for different thicknesses. Results are presented in Tables 5 and 6.
Figure 6 and 7 show that adding stiffener to the plate can increase its natural frequency significantly, which was predictable. Moreover, form obtained results it seems that natural frequencies vary linearly with the thickness of the plate.
4 CONCLUSION
The vibration analysis of stiffened plates using both conventional and super elements has been presented. The capability of placing stiffeners anywhere within the plate element has enabled the proposed formulation to encounter any configuration of stiffened plates. The efficiency of the super elements has been examined with different types of problems. The comparison of the present approach with the existing numerical and experimental results shows remarkable agreement. Although super elements yield acceptable results in significantly short time, conventional elements are superior to them according to their convergence characteristics. As a result, these elements are attractive for preliminary designs and parametric studies, where repeated calculations are often needed. It is also observed that the fundamental frequency of stiffened plates is increasing with the increase in the number of stiffeners up to a specific number after which there is no appreciable increase in frequency. Moreover, the effect of neglecting the eccentricity of the stiffeners has been studied in details. It is understood that for a clamped plate with only one stiffener eccentricity can be neglected with no considerable change in results. However, effect of eccentricity for more stiffeners should be included. This paper has also presented a rational design approach to optimize the dynamic characteristics of stiffened plates. In order to maximize the fundamental frequency, the optimal orientation angle is found to be equal to 80º. Further works can be undertaken to study hydroelastic analysis of stiffened panels, which may be important in practical point of view for marine structures.
Acknowledgement The authors would like to acknowledge the financial support received from Iranian Offshore Oil Company.
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Received 12 Mar 2011;
In revised form 08 Feb 2012
* Author email: khedmati@aut.ac.ir
1 Noise Vibration Harshness