Vibrations of point-supported rectangular plates with variable thickness using a set of static tapered beam functions

Free vibration of thick, layered rectangular plates with point supports by finite layer method

Free and forced flexural vibration analysis of cantilever plates with attached point mass

An analytical-type solution based on the superposition method is developed. The supports are of the type realized by means of bolts or spot welds. While the analysis is general in nature, it will be highly applicable to the study of vibration of electronic circuit boards and solar panels

Analytical and experimental study of vibrating rectangular plates onrigid point supports

Accurate analytical-type solutions are obtained for the free vibration of thin rectangular orthotropic plates resting on point supports symmetrically distributed about the plate central axis. Solutions are obtained by the method of superposition. Convergence is found to be rapid. It is pointed out that the same method permits the obtaining of solutions regardless of the number of supports and even when the support points are not symmetrically distributed. Highly accurate eigenvalues are tabulated for the first four modes of the three families of free-vibration modes characteristic of square plates with four symmetrically distributed point supports located on the plate diagonals. These are modes fully symmetrical, and fully antisymmetric, about the plate central axis, as well as modes symmetrical about one axis and antisymmetric about the other. Dimensionless distances from the center of the plate to the support points are allowed to vary from 0.2 to 0.9. Parameters that characterize the orthotropic properties of the plate are permitted to vary within a limited range.

Free-Vibration Analysis of Point-Supported Orthotropic Plates

Effects of attached masses on free vibration of rigid point supported rectangular plates

Modal momentum coefficients and modal identity parameters can, in principle, be identified experimentally using a procedure that entails obtaining estimates of modal momentum coefficients x scale factor for each mode from driven-base test data, then obtaining modal scale factors from tests with a portable exciter, and, finally, calculating the modal momentum coefficients from the various estimates. The estimated modal momenta can further be used with modal identities to assess the relative importance of modes and the completeness of the set of identified modes. The results of laboratory tests aimed at assessing the practicality of the procedure in the case of a complex structure are presented. The test structure, called FLECS, is representativ e of a typical modular spacecraft in terms of mass properties and modal density. The results demonstrate that the procedure successfully identifies the modal parameters.

R. K. Singal

Papers

Analytical and experimental study of vibrating rectangular plates onrigid point supports

Effects of attached masses on free vibration of rigid point supported rectangular plates

Experimental identification of modal identity-related parameters of a spacecraft representative structure