This paper investigates the implementation of nonlinear Hinfinity control theory for F-16 flight control system. The complete six degree-of-freedom nonlinear equations of motion for F-16 are considered directly for the design of the nonlinear Hinfinity flight controller by treating the longitudinal and lateral motions as a whole. The associated Hamilton-Jacobi partial differential inequality is solved analytically, resulting in a nonlinear Hinfinity controller with simple proportional feedback structure. Real aerodynamic data and engine data of F-16 are employed to determine the angles of control surface deflection from the nonlinear Hinfinity control command. Feasibility of tracking nonlinear Hinfinity control command by using F-16 actuator system is discussed in detail and the guaranteed stability and robustness or nonlinear Hinfinity flight control system implemented by F-16 actuators are confirmed over large flight envelope in a six degree-of-freedom flight simulator.


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    Titel :

    F-16 nonlinear Hinfinity control


    Beteiligte:


    Erscheinungsdatum :

    2002


    Format / Umfang :

    6 Seiten, 8 Quellen




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Print


    Sprache :

    Englisch




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