A sideslip velocity autopilot is designed for the model of a tactical missile and robust stability of the closed-loop system investigated. The tail-controlled missile in the cruciform fin configuration is modelled as a six-order quasi-linear parameter-varying system. This nonlinear model is obtained from the Taylor linearised model of the lateral and longitudinal motions by including explicit dependence of the aerodynamic derivatives on a state and external parameters. The autopilot design is based on input-output pseudo-linearisation, which is the restriction of input-output feedback linearisation to the set of equilibria of the nonlinear model. The design makes Taylor linearisation of the closed-loop system independent of the choice of equilibria. Simulations for constant lateral acceleration demands show good tracking with fast response time. Parametric stability margins for uncertainty in the controller parameters and aerodynamic derivatives are analysed using quadratic Lyapunov approach.


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    Title :

    Pseudolinearing autopilot for a 6-DOF quasi-linear parameter varying missile model


    Contributors:
    Tsourdos, A. (author) / White, B.A. (author)


    Publication date :

    2000


    Size :

    6 Seiten, 9 Quellen




    Type of media :

    Conference paper


    Type of material :

    Print


    Language :

    English




    Robust Autopilot for a Quasi-Linear Parameter-Varying Missile Model

    Antonios Tsourdos / Rafal Zbikowski / Brian A. White | AIAA | 2001



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