This paper is aimed at the active damping of vibrations of a cantilever beam, as an aircraft wing, using piezo-actuators. The actuators used for active control are assumed to be embedded in and/or bonded to wing structure. The steady-state response of the beam loaded by a harmonic distributed force, caused by aerodynamics effects (e.g. flutter phenomenon) on the wing system, is obtained from the solution of boundary value problem. The boundary problem is formulated by the beam equations of motion, the boundary conditions at the ends of the beam, continuity conditions between sections and the free stress conditions at the piezo-actuator edges. The formulation is applied to an example beam and the numerical results are presented diagrammatically.
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