Abstract
A well-known problem in civil aeronautic engineering is the reduction of vibrations of all the parts of the fuselage, e.g. frames, skin panels, trim panels, caused by the external airflow and by the airplane engines, which affect both comfort and safety of the flight. Currently, special passive devices are adopted to reduce these vibrations, namely Dynamic Vibration Absorbers (DVA), but their performance are quite limited, especially for rejection of broadband disturbances. In this work the possibility to adopt active dynamic absorbers is explored, by resorting to an actuator based on a magnetostrictive material, with the aim of increasing the reduction of undesired vibrations. First, a mathematical model of the flexible structure, i.e. a fuselage panel of a civil airplane, is deduced by means of a new modal analysis algorithm aimed at identifying the modal parameters of the mechanical system. Then, a number of different control strategies are designed and experimentally compared in two case studies, showing the feasibility of the proposed approach.
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