Abstract
This paper presents the work that has been performed on a wind-tunnel aeroelastic wing model to implement a multisurface modal control system. Wing model realization, the control system, and experimental setup were described briefly here, together with a methodology used to numerically tune the simple control system. Usage of a multiple wind-tunnel test session has been adopted first to perform numerical-experimental correlations and then to optimize control parameters. The entire control system demonstrates the capability to damp the wing bending and torsion modes while still remaining stable within the flight envelope.
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