A Plane and Thin Panel with Representative Simply Supported Boundary Conditions for Laboratory Vibroacoustic Tests

Abstract

At echnique to setup as imply supported rectangular plane panel for laboratory vibroacoustic tests is described and validated. Forag iven panel fixed to thin vertical supports, ad imensionless parameter is proposed to size these supports following adesired frequencyprecision compared to theoretical eigenfrequencies of apanel with such boundary conditions. An umerical study confirms the potential of this design parameter.D etailed instructions for assembling apanel with adequate thin vertical supports on arigid frame are then given. Finally,three laboratory cases are described which illustrate possible experimental vibroacoustic applications using ap anel assembled following previous guidelines. The design parameter viability is experimentally confirmed, and all obtained results depicted good agreement with analytical solutions and numerical predictions.

Time‐resolved identification of mechanical loadings on plates using the virtual fields method and deflectometry measurements

“…[] Simply supported conditions are achieved along all the plate boundaries using a dedicated method. []…”

“…[27,28] Simply supported conditions are achieved along all the plate boundaries using a dedicated method. [37] There are several methods for producing a mirror-like finish on the plate. The process used to apply a gel coat composed of epoxy resin and graphite powder on a composite plate, including an investigation of its effects on structural stiffness, is given in Devivier.…”

Reproducing Acceleration Power Spectral Density from an Aircraft Fuselage Panel Excited by Turbulent Boundary Layer Using Piezoelectric Actuators

“…Some have attempted to reproduce a panel with simply supported boundary conditions, which allows the equations for the acceleration PSD response to be simplified [43][44][45][46][47]. However, these experimental setups are either very difficult to manufacture or are structurally weak for a thin aircraft panel.…”

“…The front and rear views of the constructed test setup can be found in Figure 11 and Figure 12 respectively. [47]. Figure 13 contains their summarized diagrams of different experimental approaches.…”

“…Robin's [47] summarized diagram of experimental setups that represent simply supported boundary conditions by: (a) Ochs [43] (b) Champoux [44] (c) Hoppmann [45] and Barnard [46] The proposed test setups are very difficult to construct due to the thickness of the aircraft panel being replicated. The panel to be analyzed is 0.04 inches representing a thick aircraft panel, which makes Och's and Champoux's setups difficult because they require a hole to be drilled on the side and the panel is too thin for such a method of construction.…”