Adaptive boundary control of store induced oscillations in a flexible aircraft wing

An adaptive boundary control strategy is developed for the suppression of store induced oscillations in the bending and twisting deflections of an uncertain flexible aircraft wing. A Lyapunov-based stability analysis is used to show that the total energy in the system, and hence the distributed states of the system, remains bounded and decays asymptotically to zero. Simulation results illustrate the performance of the developed controller.