This paper considers an aeroelastic two-dimensional wing-flap system with uncertainty and external disturbance. Nonlinear stiffness in pitch is expressed as the second-order polynomial form. In the uncontrolled aeroelastic model, limit cycle oscillation (LCO) appears at postflutter speed. By utilizing leading-edge and trailing-edge control surfaces as the control input, a sliding mode control scheme using varying boundary layers based on backstepping design is developed to suppress aeroelastic vibration. The proposed control strategy combines the advantages of both sliding mode control with varying boundary layers and backstepping technique. In contrast to the conventional sliding mode control design, the proposed method not only avoids chattering but also obtains stronger robustness. The results of numerical simulation clearly demonstrate the effectiveness of the proposed control strategy for aeroelastic vibration suppression under saturated controller input.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Sliding Mode Control for a Nonlinear Aeroelastic System through Backstepping


    Beteiligte:
    Xu, Xing-zhi (Autor:in) / Wu, Wan-xiang (Autor:in) / Zhang, Wei-guo (Autor:in)

    Erschienen in:

    Erscheinungsdatum :

    2017-09-20




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Unbekannt




    Backstepping Sliding Mode Control for Missile Attitude System

    Zi-rui, Huang / Yun-jie, Wu / Jing-xing, Zuo et al. | IEEE | 2018


    Incremental Backstepping Sliding Mode Fault-Tolerant Flight Control

    Wang, Xuerui / Van Kampen, Erik-Jan | AIAA | 2019


    Backstepping sliding mode control for formation flying spacecraft

    Guo, Yong / Song, Shen-Min / Li, Xue-Hui | Emerald Group Publishing | 2018