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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    Title :

    F-16 nonlinear Hinfinity control


    Contributors:


    Publication date :

    2002


    Size :

    6 Seiten, 8 Quellen




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




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