Flutter suppression for the active flexible wing - A classical design

The synthesis and experimental validation of a control law for an active flutter suppression system for the active flexible wing wind-tunnel model is presented. The design was accomplished with traditional root locus methods making extensive use of interactive computer graphics tools and simulation-based analysis. The design approach relied on a fundamental understanding of the flutter mechanism to formulate a very simple control law structure resulting in a filter with a "inverted notch" characteristic. This unusual filter characteristic was required to compensate for adverse zero locations in the frequency range near flutter. Wind-tunnel tests of the flutter suppression controller demonstrated simultaneous suppression of two flutter modes, significantly increasing the flutter dynamic pressure. The flutter suppression controller was also successfully operated in combination with a rolling maneuver controller to perform flutter suppression during rapid rolling maneuvers.

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