Feedback control of limit cycle oscillations and transonic buzz, using the nonlinear transonic small disturbance aerodynamics

In this paper, a systematic method to suppress transonic buzz with feedback is presented. A trailing edge control surface in the form of part-span flap was used only modify and unsteady aerodynamic loading on wing. The rotation provide feedback, which consisted weighted linear combination amplitudes principal modes structure, referred as law. linear, optimal law, that synthesized systematically based pseudo-spectral time domain analysis, may be principle, assess its capacity actively flow by using servo-controlled unsteady, nonlinear loads Thus, it essential set feasible laws are first constructed. done applying doublet-lattice method. Restrictions, such near-zero structural damping mode, were imposed aeroelastic model facilitate occurrence buzz. then assessed small disturbance theory an optimum selected differences behaviour closed-loop system flow, when compared applications potential presented discussed.