2007
DOI: 10.1117/12.715657
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Test/analysis comparison of piezoelectric patch local behavior for vibroacoustic active control application

Abstract: 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 piezoe… Show more

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“…To represent sensors, the configuration corresponds to cases where the voltage remains very small, and an electrical charge is generated basically because of mechanical deformations. For the actuator configuration, the electrical charge corresponds to the resulting force associated with the voltage, applied through a voltage driven amplifier .…”
Section: Active Smart Structure and Fe Modelmentioning
confidence: 99%
“…To represent sensors, the configuration corresponds to cases where the voltage remains very small, and an electrical charge is generated basically because of mechanical deformations. For the actuator configuration, the electrical charge corresponds to the resulting force associated with the voltage, applied through a voltage driven amplifier .…”
Section: Active Smart Structure and Fe Modelmentioning
confidence: 99%