Abstract
Transonic aeroelasticity of wings with active control surfaces is studied by using the unsteady-small disturbance transonic aerodynamic equations coupled with modal structural equations of motion. The aerodynamic and structural equations of motion are simultaneously integrated by a time-accurate numerical scheme. A procedure of synthesizing active controls with unsteady transonics is presented. Flutter suppression in the transonic regime using active controls is demonstrated for a rectangular wing. Characteristics of a selected control law in the transonic regime are studied. The results from this study are useful in the design of active control systems in the transonic regime.
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