A numerical control design method for prototypical aeroelastic wing section with structural non-linearity

A comprehensive analysis of aeroelastic systems has shown that these systems exhibit a broad class of pathological response regimes when certain types of non-linearities are included. In this paper, we propose a design method of a state-dependent non-linear controller for aeroelastic systems that includes polynomial structural non-linearities. The method is based on recent numerical methods such as Tensor Product model transformation and Parallel Distributed Compensation. As an example, a controller is derived that ensures the quadratic stability of a prototypical aeroelastic wing section via one control surface. Numerical simulations are used to provide empirical validation of the control results. The effectiveness of the controller design is compared with former approaches.