Research Article  Open Access
Coupling between Transverse Vibrations and Instability Phenomena of Plates Subjected to InPlane Loading
Abstract
As it is known, the problems of free transverse vibrations and instability under inplane loads of a plate are two different technological situations that have similarities in their approach to elastic solution. In fact, they are two eigenvalue problems in which we analyze the equilibrium situation of the plate in configurations which differ very slightly from the original, undeformed configuration. They are coupled in the event where inplane forces are applied to the edges of the transversely vibrating plate. The presence of forces can have a significant effect on structural and mechanical performance and should be taken into account in the formulation of the dynamic problem. In this study, distributed forces of linear variation are considered and their influence on the natural frequencies and corresponding normal modes of transverse vibration is analyzed. It also analyzes their impact for the case of vibration control. The forces' magnitude is varied and the first natural frequencies of transverse vibration of rectangular thin plates with different combinations of edge conditions are obtained. The critical values of the forces which cause instability are also obtained. Due to the analytical complexity of the problem under study, the Ritz method is employed. Some numerical examples are presented.
1. Introduction
The transversefree vibrations and buckling of plates which are subjected to edge loads acting in their middle planes are areas of research which have received a great deal of attention in the past century.
As it was stated experimentally by Hearmon [1] for the case of a beam, bifurcation buckling may be regarded as a special case of the vibration problem, that is, determining the inplane stresses which cause vibration frequencies to reduce to zero.
Most of the work has dealt with rectangular plates having uniformly distributed inplane edge loads. In that case, the governing differential equations of motion and equilibrium have constant coefficients, yielding exact solutions for frequencies and buckling loads straightforwardly when two opposite edges of the plates are simply supported.
Many researchers have analyzed both the buckling and vibration of rectangular plates subjected to inplane stress field. Among them, one can mention Kang and Leissa [2]; Leissa and Kang [3]; Bassily and Dickinson [4]; Dickinson [5]; Kielb and Han [6]; Kaldas and Dickinson [7].
For the linearly varying loading, the governing differential equations have variable coefficients.
Leissa and Kang [3] found exact solutions for the free vibration and buckling problems of the SSCSSC isotropic plate loaded at its simply supported edges by linearly varying inplane stresses.
They also found the exact solution [8] for the buckling of rectangular plates having linearly varying inplane loading on two opposite simply supported edges, with different boundary conditions at the other opposite edges.
Within the realm of the classical theory of plates, the case of buckling and vibrations problems for all the possibilities of boundary conditions and linearly varying inplane forces offers considerable difficulty. This is the reason why it is quite common to make use of the Ritz variational method.
2. Approximate Analytical Solution
In the case of a transversely vibrating, thin, isotropic plate subjected to inplane forces , , and , (Figure 1 and (5)), the maximum value of the potential energy due to bending deformation is where is the deflection amplitude of the middle plane of the plate, is the well known flexural rigidity , is the Young modulus, and is the Poisson coefficient.
While the maximum of the kinetic energy is where is the density of the plate material, is the circular frequency, and is the thickness of the plate.
And the maximum potential energy of the internal stresses caused by the inplane loading is
The lengths of the sides of the rectangular plate are in the direction and in the direction. The coordinates are written in the dimensionless form as follows:
And the inplane forces are expressed as (Bambill et al. [9]):
Then, the governing functional of the system is
Equation (6) satisfies, if is the exact solution, the condition:
Following the Ritz method, the expression of the deflection of the plate is approximated in the form of a truncated series: where and are the characteristic functions for the normal modes of vibration of beams with end conditions nominally similar to those of the opposite edges of the plate in each coordinate direction [10]. Consequently, they satisfy the essential boundary conditions, as the method requires.
The variational equation (7) is replaced by the homogeneous linear system of equations: and using nondimensional variables, becomes
Finally, one obtains a homogeneous linear system of equations in terms of the ’s parameters.
The nontriviality condition of the system (10) requires the determinant to be zero: where are the frequency coefficients.
The elements of the matrices involved in (11) are given by where is the aspect ratio where is a factor that indicates the magnitude of the inplane loading system, regarding the relative value of the forces. Consider
As it is known, the condition in (11) yields the critical value of the inplane loading.
3. Numerical Evaluations
Hearmon [1] has experimented on a fixedfree strip. Admittedly, the problem is analytically simpler in the case of onedimensional domains. As an example, let us try with a pinnedpinned transversely vibrating beam, subjected to an axial compressive force . The expression of the frequency coefficient is where is the density of the material, is the crosssection, is the length, and the flexural rigidity of the beam.
All the Euler buckling loads are determined making zero expression (15). For , the critical buckling load of the beam, , is obtained.
Plotting the values of the first three frequency coefficients depending upon the ratio yield regular curves as is shown in Figure 2. The presence of the compressive axial load does not alter the order of the modal shapes of the beam.
In the case of a plate, in general, and due to the bidimensional behavior induced by the torsional rigidity, the compressive inplane load may alter both the order and shape of the modal shapes associated to each natural frequency.
This situation has an important technological signification from the point of view of vibration control.
Certainly, the modal shape of a natural resonant frequency must be known in order to suppress it. In the case of inplane loading, this shape can be different from the expected one.
Due to the quantity and variability of the parameters involved in the description of the behaviour of these kinds of structures, just a few representative cases will be considered to demonstrate the convenience of the procedure and the importance of the situation.
All the values are determined taking in (8).
Table 1 shows the values of the first natural frequency coefficients for a CCFF plate subjected to a general inplane loading: linear load in direction ()—bending moment, constant load in y direction (), and constant shear force .

In order to show the influence of the inplane loading, the next two examples are presented.
Table 2 shows the natural frequency coefficients for a CCSSSS square plate under uniform compression in the direction (, , and ).

Figure 3 shows that a minimal presence of inplane loading (10% of the critical value) dramatically modifies the mode shapes, while changes in the values of frequencies may not be noticed (0.3% in the sixth frequency). It is important to point out that the small load can be originated by thermal variations and restrictions on plane displacements imposed by the external supports.
Finally, Table 3 shows the results for a rectangular CCSSSS plate subjected to shear inplane forces.

Figure 4 shows that the third and fourth natural frequencies interchange their normal modes as increases. This situation is noticeable from Figure 5.
This means that for a given value of , between 0.25 and 0.4 of the critical value, there are two normal modes for the same natural frequency (repeated frequency). This is an important point in vibration control, since when repeated frequencies arise in a system, the related vibration mode shape cannot be uniquely determined. Any linear combination of the modes is still valid for the repeated frequency.
In order to evaluate the accuracy of the expounded procedure, comparison is made with the results obtained in [3] for a SSCSSC plate loaded at its simply supported edges by linearly varying inplane stresses (Tables 4 and 5).
 
A: present approach with different and B: [3]. 
 
[A]: present approach and [B]: [3]. 
In Table 4, values of are compared for three different cases of the direction load: constant (), linear with null value at one extreme (), and bending moment (), and different aspect radii of the plate. A convergence study is also made. As it can be seen, taking provides an excellent accuracy from an engineering viewpoint.
4. Conclusions
The classical, variational method of Ritz has been successfully used in the present study to obtain an approximate, yet quite accurate, solution to a difficult elastodynamics problem.
Natural frequencies and mode shapes of transverse vibration are obtained for a meaningful combination of the boundary conditions of a thin plate subjected to general inplane loads. The critical values of the inplane forces which cause instability of the plates are also obtained.
The obtained values are the outcome of an algorithm, relatively simple to implement, [11] which allows studying these with only the assistance of a PC.
Additional complexities like orthotropic material characteristics can be taken into account [12].
The agreement with results available in the literature is excellent. Nevertheless, it is also possible to increase the number of terms in the summation on (8) to increase the accuracy.
No claim of originality is made, but it is hoped that the present work draws the attention to the effect that the presence of plane stress state may have on the effectiveness of vibration control on plates.
Acknowledgments
The present work has been sponsored by the Secretaría General de Ciencia y Tecnología of Universidad Nacional del Sur, UNS, at the Department of Engineering and by Consejo Nacional de Investigaciones Científicas y Técnicas, CONICET. The authors wish to thank Dr. D. H. Felix from Universidad Nacional del Sur.
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Copyright
Copyright © 2013 D. V. Bambill and C. A. Rossit. This is an open access article distributed under the Creative Commons Attribution License, which permits unrestricted use, distribution, and reproduction in any medium, provided the original work is properly cited.