The problem of designing flight control system for high performance anti-air missiles is discussed in this report. The research addresses three areas of missile autopilot design. The first area investigates the application of nonlinear H-infinity optimal control for an integrated aerodynamic/thrust vector controlled missile. The second area investigates the design of autopilots for missiles using on-off reaction control valve actuators. A sliding mode control law is developed using H-infinity design methods. The third area focused on developing nonconservative robustness analysis algorithms for gain scheduled missile autopilots.


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    Title :

    Nonlinear Control of Missiles


    Contributors:

    Publication date :

    1995


    Size :

    196 pages


    Type of media :

    Report


    Type of material :

    No indication


    Language :

    English




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