Evaluation of vibro-acoustic behavior of composite fuselage panel with embedded damping treatment

Structures subjected to dynamic loads, generally show structural damping values which are just slightly capable of reducing oscillations amplitude. In aerospace field, low structural damping, or high oscillations amplitudes, may impact negatively on structural stability and emitted noise. This is much evident if composite structures are referred to. In force of their stiffness-over-weight ratio, composite materials are deeply used in large assemblies and subassemblies belonging to fuselage and/or lifting surfaces (wing, tail empennages, control surfaces); on the other hand, structural ad-vantages related to composite solutions are accompanied by drawbacks mainly due to materials’ high vibration and noise permeability.