Flutter Suppression for a Two Degree of Freedom Aeroelastic Wing Section: a Structured H-infinity-Based Gain-Scheduling Approach with Explicit Hidden Coupling Terms Handling
Résumé
This paper tackles the active limit cycle oscillations and flutter suppression of a two degree of freedom prototypical aeroelastic wing section actuated by a single control surface. To avoid the possible unstable internal dynamics due to partial feedback linearization, which is indeed the most popular approach considered in the literature, we apply in this paper gain-scheduling control based on the Jacobian linearization of the system. Since flutter involves large pitch angle oscillations, an appropriate limit cycle oscillations suppression requires to schedule the controller gains with this system variable. The main concern with this approach lies in the fact that using endogenous signals as scheduling parameters will introduce hidden coupling terms in the linearized gain-scheduled controller dynamics, which may result in performance degradation and instability of the closed-loop system. The procedure adopted in this paper handles these hidden coupling terms via a structured H-infinity design. Specifically, this approach guarantees that the resulting nonlinear closed-loop system fully complies with the controller design in the sense that the linearization of the closed-loop nonlinear model coincides at each operating point with the closed-loop linear system used in the design. The validity of this approach applied to the flutter suppression of a two degree of freedom prototypical aeroelastic wing section is demonstrated based on
nonlinear simulations.