A reconfigurable flight controller is presented using an adaptive sliding mode control scheme for actuator fault case. Sliding mode controller, which has good performance for the systems with various uncertainties, is used to deal with the actuator faults. Actuator fault can be considered as a disturbance or an unexpected parameter change, which degrades the system performance and may destabilize the system. The adaptive sliding mode control technique is adopted to compensate the effects of the disturbance generated by actuator faults. Lyapunov stability theory is used to derive the adaptive rule, and the closed-loop system stability analysis is performed. To demonstrate the effectiveness of the proposed controller, numerical simulation is performed for aircraft having redundant control surfaces.


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    Title :

    Design of reconfigurable flight control system using adaptive sliding mode control: Actuator fault


    Additional title:

    Entwurf einer rekonfigurierbaren Flugregelung mittels adaptiver Gleitmodusregelung: Aktorfehler


    Contributors:
    Shin, D. (author) / Moon, G. (author) / Kim, Y. (author)


    Publication date :

    2005


    Size :

    8 Seiten, 15 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English