Computational and experimental studies of microvascular void features for passive-adaptation of structural panel dynamic properties
Section snippets
Background and motivation
Harmonic or random excitations of structures can lead to large amplitude oscillations at the modes of vibration, which are significantly magnified when structures are driven around the natural frequencies. For aerospace structures, vibrations at resonance are particularly concerning. In turbine engines for instance, vibration response has been found to be magnified by 1000 times normal levels when driven at resonance [1]. For compressor blades of such turbines, it was found that oscillations at
Finite element model investigations
This section presents the finite element (FE) model investigations that are used to evaluate the ability of voids to tailor the vibration characteristics of structural panels. In all cases considered, the voids are positioned at the mid-plane of the panels. Void shape, number, size, and location are the parameters considered to be available for manipulation. Then, guidelines that enable changes in eigenfrequency via a material transition between voids are presented to direct experimental
Experimental validation
This section describes experimental efforts undertaken to validate the finite element model and explore opportunities for material transitions through internal voids to tailor the structural dynamics of panels. Following a description of fabrication methods for specimens considered, measurements taken with free-free and fixed-free panels are reported and discussed.
Conclusions
In this research, passive adaptation of structural panel dynamic properties is examined via the transmission of material in and out of voids at the mid-plane of the panel. From computational and experimental studies, it is found that, with respect to an unvoided panel, material voids in areas of higher modal displacement lead to an increase in eigenfrequency while material voids positioned in areas of higher stress correspond to a decrease in eigenfrequency. These effects are magnified using
Acknowledgements
The authors acknowledge helpful conversations about the motivations of this research with Dr. Jeff Baur of the Air Force Research Laboratory and Dr. Darren Hartl of the Texas A&M University. The authors also thank Dr. Jason Dreyer of The Ohio State University (OSU) for assistance during the impact hammer experiments. R.L.H. acknowledges start-up funds from the Department of Mechanical and Aerospace Engineering at The Ohio State University (OSU). N.C.S. acknowledges support from the OSU College
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