抄録
The present paper treats the flutter suppression of composite plate wings with segmented piezoelectric sensors and actuators. In the first report of this paper, fundamental mechanism of flutter suppression based on the measurement and control of specific vibration modes is examined for composite plate wings. Aeroelastic analysis of composite plates is based on the finite element method and the subsonic unsteady lifting surface theory. The minimum state method is applied to approximate the unsteady aerodynamic forces as the transfer functions of the Laplace variable. PVDF sensors are used as a modal sensor for measurement of specific modal displacements, and PZT actuators are used as actuators of flutter suppression, which generate the modal forces for specific modes. The importance of the measurement and control of the first torsional vibration mode for the flutter suppression is clarified through the numerical examples.
