The pitch rate control of a missile is analyzed by an Hinfinity controller. The system dynamics governing the aerodynamic stability derivatives and airframe structure vibration is formulated in a generalized state space realization form. This formulation facilitates the gamma -iteration method in solving the associated Ricatti equation of the 4-block Hinfinity control problem. It is shown that the Hinfinity controller, because of its loop shaping capabilities, can provide improved tracking performance and stability robustness compared with H2 (linear-quadratic-Gaussian (LQG)) and classical proportional-integral-derivative (PID) controller in the rigid airframe model. When airframe flexibility effect is considered, the Hinfinity controller is also shown to be robust under structure natural frequency variations.


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    Title :

    Application of Hinfinity control to pitch autopilot of missiles


    Additional title:

    Die Anwendung eines H<sup>unendlich</sup>-Reglers beim Autopiloten von Raketen


    Contributors:
    Yang, S.M. (author) / Huang, N.H. (author)


    Publication date :

    1996


    Size :

    8 Seiten, 15 Quellen




    Type of media :

    Article (Journal)


    Type of material :

    Print


    Language :

    English