A novel method of exoatmospheric guidance law design is proposed in this paper. By analyzing the nonlinear kinematic equations, a class of nominal motions that requires no maneuver effort can be derived for a nose jet control missile. A unique time to go can be solved online from the equations derived from the property of the nominal motion to guarantee a perfect interception. With the time to go determined, the nominal heading angle and heading angular rate can be obtained to impose an impact angle constraint. A backstepping-based continuous three-order finite-time guidance law is designed such that the heading angle tracking is guaranteed. The superiority of the guidance law is demonstrated by a series of simulation results.


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    Titel :

    A Backstepping-Based Guidance Law for an Exoatmospheric Missile With Impact Angle Constraint


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


    Erscheinungsdatum :

    01.04.2019


    Format / Umfang :

    1657644 byte




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch