Multi-input/multi-output adaptive output feedback control design for aeroelastic vibration suppression

Via the use of leading- and trailing-edge control surface actuation, an adaptive output feedback controller is designed for suppressing aeroelastic vibrations on a nonlinear wing section. Although a single flap under adaptive control can suppress vibrations, the response rate is limited by the system zero dynamics. Under the restriction that only pitching and plunging variables are available for measurement but their rates are not, the proposed algorithm addresses the problem of designing a singularity-free adaptive output feedback controller when the control inputs are coupled via an input gain matrix for which the parameters are uncertain. The stability result achieved is global asymptotic tracking. Simulation results demonstrate the efficacy of the multi-input/multi-output control toward suppressing flutter and limit-cycle oscillations, as well as reducing the vibrational level in the subcritical flight-speed range. Pertinent conclusions are outlined