OPTIMAL LOCATIONS OF PIEZOELECTRIC PATCHES FOR VIBRATION CONTROL USING HARMONIC ANALYSIS IN AIRCRAFT WING

Abstract

Aircraft wing structures are obligatory to be lightweight in today's designs. However, this lowers the overall
stiffness of the wing structure and causes low frequency vibration problems. Active vibration control using piezoelectric
patches is an auspicious technology to solve vibration problems of aerospace structures .Many studies were done on aircraft
wing geometries, however studies on beam geometry which is used comprehensively as engineering structure, is relatively
erratic. The main characteristics of this work were amplification of a finite element model for a plate stiffened by wing
surface. Finite element model of the aircraft wing is generated. This study is a postponement of the wing reading with the
toting of determining the harmonic analysis to optimal mode shapes of the wing structure. First eight mode shapes used to
fine the maximum structure deformation with various frequencies by applying the piezoelectric patches in various locations.
From the harmonic analysis we can identifies the exact location of placing the piezoelectric material in the wing structure.