Considering the impact of the actuator on the aircraft flight performance, this paper proposes a design method for longitudinal damping control law of aircraft based on Ll adaptive control. Firstly, the aircraft adaptive control model is built according to modeling error and external disturbance of flight control system. And then the actuator model was augmented to the system state vector for accurate pitch rate feedback control. Finally, the Ll adaptive law and observer are designed based on the system structure. The Simulation results show that the Ll adaptive control can perform the longitudinal damping control of the aircraft well, and can still effectively control when the actuator failure.


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    Titel :

    L1 adaptive control law design for Aircraft considering actuator influence


    Beteiligte:
    Liu, Xiaoxiong (Autor:in) / Zhao, Hui (Autor:in) / Ma, Qingyuan (Autor:in) / Shen, Jian (Autor:in)


    Erscheinungsdatum :

    2018-08-01


    Format / Umfang :

    132501 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch



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