This paper considers the control of coupled aeroelastic aircraft model which is configured with Variable Camber Continuous Trailing Edge Flap (VCCTEF) system. The relative deflection between two adjacent flaps is constrained and this actuation constraint is accounted for when designing an effective control law for suppressing the wing vibration. A simple tuned-mass damper mechanism with two attached masses is used as an example to demonstrate the effectiveness of vibration suppression with confined motion of tuned masses. In this paper, a dynamic inversion based pseudo-control hedging (PCH) and bounded control approach is investigated, and for illustration, it is applied to the NASA Generic Transport Model (GTM) configured with VCCTEF system.


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    Title :

    Aeroelastic Wing Shaping Control Subject to Actuation Constraints


    Contributors:
    S. S. M. Swei (author) / N. Nguyen (author)

    Publication date :

    2014


    Size :

    15 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




    Aeroelastic Wing Shaping Control Subject to Actuation Constraints.

    Swei, Sean Shan-Min / Nguyen, Nhan | NTRS | 2014


    Aeroelastic Wing Shaping Control Subject to Actuation Constraints (AIAA 2014-1041)

    Swei, S.S.-M. / Nguyen, N.T. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2014


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    Nguyen, Nhan T. / Reynolds, Kevin Wayne / Ting, Eric B. | NTRS | 2017


    Aeroelastic wing shaping using distributed propulsion

    NGUYEN NHAN T / REYNOLDS KEVIN WAYNE / TING ERIC B | European Patent Office | 2017

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