In this article, a method to make the normal acceleration of medium angle of attack missile to track some desired trajectories is presented. The dynamics which describe a missile acceleration are known to be non-minimum phase, which makes it difficult to use a straightforward feedback linearization technique. This article aims at showing that this problem may be overcome by employing cascaded regulations in the non-linear area. First, inner loop controller by dynamical sliding mode control (SMC) method based on asymptotic output tracking is designed for angle of attack control which has a minimum phase characteristics. Also then, the problem that is addressed here is the completion of the global loop by designing an additional outer loop proportional-integral (PI) controller and angle of attack estimator. The performance and stability of proposed method are illustrated via computer simulations.


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    Titel :

    Missile acceleration controller design using proportional-integral and non-linear dynamic control design method


    Weitere Titelangaben:

    Entwurf eines Raketen-Beschleunigungs-Controllers mit Hilfe einer proportional-integralen und nichtlinear-dynamischen Steuerungsdesignmethode


    Beteiligte:
    Kim, S.H. (Autor:in) / Tahk, M.J. (Autor:in)


    Erscheinungsdatum :

    2012


    Format / Umfang :

    16 Seiten, 15 Bilder, 17 Quellen




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch