To predict the effect of active control on aircraft or helicopter trim panels, made with honeycomb sandwich
composite, one approach consists in modeling the panel by Finite Element Method. FEM with shell elements
for the laminate and volume elements for the core is classically used in industry; in a previous study the
homogenized modeling approach has been validated. The aim of the present paper is to make a test/analysis
comparison of the dynamic behavior of a honeycomb core sandwich beam actuated by a piezoelectric patch.
More precisely, the behavior in the vicinity of the piezoelectric actuator is characterized, in order to validate
the modeling approach of honeycomb sandwich composite equipped with piezoelectric patches.
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