Application is made in the present paper of the recently developed relaxed aerodynamic energy concept and synthesis techniques to the definition of appropriate active control systems for the low-speed flutter model of the B-2707-300 supersonic cruise airplane. The effectiveness of the resulting activated systems is analytically tested for flutter suppression, wing root bending moment alleviation, and ride control (fuselage accelerations). The results obtained indicate that considerable increase in flutter speeds can be obtained by the various control systems, using a single trailing-edge control. In all cases, the flutter suppression control system led to a substantial reduction in both wing root bending moments and in fuselage and wing accelerations.


    Access

    Access via TIB

    Check availability in my library


    Export, share and cite



    Title :

    Active controls for flutter suppression and gust alleviation in supersonic aircraft


    Contributors:
    Nissim, E. (author) / Lottati, I. (author)

    Publication date :

    1980-08-01


    Type of media :

    Miscellaneous


    Type of material :

    No indication


    Language :

    English