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    Identification and assessment of a nonlinear dynamic actuator model for controlling an experimental flexible wing

    Identification and assessment of a nonlinear dynamic actuator model for controlling an experimental flexible wing

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    In this paper, the effect of nonlinear actuator dynamics on the performance of an active load alleviation system for an experimental flexible wing is studied. Common nonlinearities such as backlash or rate limits are considered for the control surface actuator. An aeroelastic simulation model of a flexible wing with control surface is being used. With this, a parameter study is carried out to quantify the impact of the individual nonlinearities on the overall closed-loop performance by means of describing functions. Finally, the nonlinear actuator model with parameters identified from dedicated tests is experimentally validated allowing for an accurate prediction of the expected gust load alleviation performance.

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    Titel :

    Identification and assessment of a nonlinear dynamic actuator model for controlling an experimental flexible wing

    Weitere Titelangaben:

    CEAS Aeronaut J

    Beteiligte:
    Tang, Martin (Autor:in) / Böswald, Marc (Autor:in) / Govers, Yves (Autor:in) / Pusch, Manuel (Autor:in)
    Erschienen in:

    CEAS Aeronautical Journal ; 12 , 2 ; 413-426

    Erscheinungsdatum :

    2021-04-01

    Format / Umfang :

    14 pages

    ISSN :

    1869-5590 , 1869-5582

    DOI :

    https://doi.org/10.1007/s13272-021-00504-y

    Medientyp :

    Aufsatz (Zeitschrift)

    Format :

    Elektronische Ressource

    Sprache :

    Englisch

    Schlagwörter :

    System identification , Active load alleviation , Wind tunnel experiment , Actuator modeling , Nonlinear dynamics , Aeroservoelasticity Engineering , Aerospace Technology and Astronautics

    Lizenzbestimmungen :

    http://creativecommons.org/licenses/by/4.0/

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