Abstract
An active control law is synthesized for the suppression of wing flutter for a mathematical model of a flight test vehicle. Eigenvalue placement is used to synthesize a full state controller that satisfies performance specifications on control surf ace activity and that exhibits excellent gain and phase margins. A simple frequency response matching technique is used to design a realizable compensator which approximates the feedback properties of the full state controller. The performance of the control system using this compensator is evaluated at various flight conditions and found to be satisfactory. In addition, eigenvector shaping is used to enhance the gust load alleviation capabilities of the flutter control system.
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