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Equipment panels, solar panels and reflectors of spacecraft are made-up laminated sandwich composite with a honeycomb core between the composite fiber reinforced plastic (CFRP) or aluminum face sheets. Such structures have large area to mass ratio and low inherent damping due to which large resonance responses are observed when subjected to acoustic loads, which occur during the spacecraft launch. In this paper, we present an experimental assessment of the response attenuation of honeycomb sandwich plate under diffused acoustic excitation in a reverberation chamber. The honeycomb cells are filled with viscoelastic damping particles in strategically selected areas. The insertion of damping particle is reported to improve the damping behavior of the panel as the damping particles dissipate vibration energy of host structure by collision and friction. The vibration attenuation trend has been studied experimentally for varying sound pressure level (SPL). The attenuation has been quantified in terms of power spectral density (PSD) of the vibration responses. Vibration reduction by this method can be used advantageously in the design of damping devices for acoustic vulnerable structures.
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