The pitch rate control of a missile is analyzed by an H/sup /spl infin// 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 /spl gamma/-iteration method in solving the associated Ricatti equation of the 4-block H/sup /spl infin// control problem. It is shown that the H/sup /spl infin// controller, because of its loop shaping capabilities, can provide improved tracking performance and stability robustness compared with H/sub 2/ (linear-quadratic-Gaussian (LQG)) and classical proportional-integral-derivative (PID) controller in the rigid airframe model. When airframe flexibility effect is considered, the H/sup /spl infin// controller is also shown to be robust under structure natural frequency variations.


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    Title :

    Application of H/sup /spl infin// control to pitch autopilot of missiles


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


    Publication date :

    1996-01-01


    Size :

    2069634 byte




    Type of media :

    Article (Journal)


    Type of material :

    Electronic Resource


    Language :

    English