| Aeroelastic phenomena have been studied for many years and their effects on flexible structures are well documented. These phenomena are investigated in the following research in a two-fold investigation. The first investigation examines the static characteristics of a wing section with a full span, leading edge-trailing edge control surface configuration. A linear configuration is used in the investigation of control surface reversal and the prevention thereof, with reversal behavior described in terms of roll performance as well as lift effectiveness. Using leading edge control, it is possible to delay reversal, and is accomplished by an appropriate choice of control surface deflections, given in terms of a deflection ratio or gearing ratio. The second investigation examines nonlinear behavior, namely, the occurrence of limit cycle oscillations, in which the nonlinearities occur in the pitch motion. It has been recognized that a multiple control surface configuration provides guarantees on the control capabilities of the aeroelastic system. The use of the multiple control surface configurations, namely, the leading edge-trailing edge control surface configuration, is used herein to suppress limit cycle oscillations. Adaptive control strategies are developed and implemented in wind tunnel experiments. |
