A method of a SMC (sliding mode control)-based guidance law design is proposed for an exoatmospheric missile with constant positive acceleration. By analyzing the nonlinear kinematic equations of the missile, a class of nominal motions that requires no maneuver effort can be defined. The unique time-to-go, the corresponding nominal heading angle and the nominal heading angular rate can be solved from the equations that are derived from the properties of the nominal motions to guarantee a perfect interception with a desired impact angle. A nonsingular SMC-based guidance law is designed for the disturbed heading angle tracking system such that the tracking is guaranteed in finite time.


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    Titel :

    A nonsingular SMC-based guidance law for an accelerating exoatmospheric missile


    Beteiligte:
    Ye, Qing (Autor:in) / Liu, Chunsheng (Autor:in)


    Erscheinungsdatum :

    2016-08-01


    Format / Umfang :

    214548 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch






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