ABSTRACT
This chapter is concerned with designing a state variable feedback controller and observer-based output feedback controller for the prototypical aeroelastic wing section with structural nonlinearity [Bar06b], [Bar06a] using the tensor product (TP) model-based approach proposed in this book. The same control problem extended with friction compensation is given in [TBnt]. The wing section problem has traditionally been used for theoretical as well as experimental analysis of twodimensional aeroelastic behavior, and shown to exhibit limit-cycle oscillation without control effort. The main advantage of applying the TP approach here is that asymptotic stability via single trailing-edge control surface can be guaranteed. Moreover, in contrast with the previous solutions, a variety of different design specifications, such as decay rate optimization and input constraint, can be readily incorporated. The TP approach further shows that the prototypical aeroelastic wing section can be described exactly by the time-varying convex combination of six linear timeinvariant (LTI) models, that is, by a six-element convex polytopic model. Such model representation is the result of the TP model transformation, which has not been investigated in previous studies of areroelastic models. The advantage of this new representation is that it allows application of various recent linear matrix inequality (LMI)-based designs of the wing section for control.
