The design of a control law for simultaneously suppressing the symmetric and antisymmetric flutter modes of a sting mounted fixed-in-roll aeroelastic wind-tunnel model is described. The flutter suppression control law was designed using linear quadratic Gaussian theory, and it also involved control law order reduction, a gain root-locus study, and use of previous experimental results. A 23 percent increase in the open-loop flutter dynamic pressure was demonstrated during the wind-tunnel test. Rapid roll maneuvers at 11 percent above the symmetric flutter boundary were also performed when the model was in a free-to-roll configuration.


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    Title :

    Flutter suppression digital control law design and testing for the AFW wind tunnel model


    Contributors:


    Publication date :

    1994-06-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English