An active control law is synthesized to raise the flutter dynamic pressure boundary of an active flexible wing wind tunnel model. The multi-input/multi-output controller has a two-degree-of-freedom structure consisting of: (1) an output dynamic compensator selected to assign system invariant zeros to shape the multivariable root loci, and (2) an output gain feedback controller, based on eigensystem assignment theory, using the compensator augmented system to stabilize the flutter mode and optimize a specified performance index. Evaluation of a digital implementation of a constant gain controller in a general batch simulation of the system reveals that the feedback system is stable over a dynamic pressure range of 50-400 psf, indicating robustness of design to dynamic pressure variations.


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    Title :

    Active flutter suppression using invariant zeros/eigensystem assignment


    Contributors:

    Conference:

    AIAA Guidance, Navigation and Control Conference ; 1989 ; Boston, MA, United States


    Publication date :

    1989-01-01


    Type of media :

    Conference paper


    Type of material :

    No indication


    Language :

    English