Optimal wing design for flutter suppression with pzt actuators including power requirement

In this paper, the integrated aeroservoelastic wing design is conducted using optimization technique. An active flutter suppression system for a composite wing model is designed using piezoelectric materials. The self-sensing piezoelectric actuators are used for feedback control of aeroelastic responses. A way of predicting the electric power requirement of the piezoelectric materials for control is proposed and the defined total power is used as a part of the objective functions. The analysis for a laminated composite wing with segmented piezoelectric pairs is conducted by Ritz solution technique. Unsteady aerodynamic forces calculated by the doublet lattice method are approximated as the transfer functions of the Laplace variable by minimum state method. The linear quadratic regulator theory with output feedback is applied to design the control system. Using a simple swept wing model, the performance of the controlled system is investigated. The electric power requirement for aeroelastic control is also predicted. The geometry of self-sensing piezoelectric actuators, i.e., the size, thickness, and location are determined using the optimization technique. Design objectives are to minimize the control performance index and the electric power consumption required for the control. Numerical results show a substantial saving in control effort as well as the electric power compared with the initial model.