Abstract
The flutter characteristics of a wing with morphing flap are analyzed based on computational fluid dynamics (CFD) method. The unsteady aerodynamic reduced order model (ROM) is constructed to model the morphing flap with high accuracy, and the effect of flap camber on the wing flutter boundary is investigated. Active suppression of aeroelastic response by controlling the flap deflection is validated through numerical simulations. A Linear Quadratic Gaussian (LQG) compensator is designed to explore the potential of suppressing wing flutter by deflecting the flap actively. The simulation results show that the order of morphing flap camber may change the critical flutter speed and flutter frequency of the wing. Compared with the conventional plain flap, the morphing flap shows higher control efficiency with fewer deflection demands.
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