Aiming at the related problems of discrete guidance law, the design of the dynamic delay characteristic of missile autopilots is considered as discrete finite time convergent sliding mode guidance law for the first-order inertial link. Firstly, the discrete guidance equation considering the dynamic characteristics of autopilot was derived; secondly, the discrete sliding mode variable structure guidance law was analyzed; thirdly, the finite time convergence characteristic of the designed guidance law was analyzed and proved. The simulation results show that the designed discrete sliding mode guidance law is convergent in finite time, which ensures the stability of guidance and improves the precision of guidance.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Discrete sliding mode guidance law considering dynamic characteristics for autopilot


    Beteiligte:
    Zhang, Yunxi (Autor:in) / Liu, Jia (Autor:in) / Lian, Wenyu (Autor:in) / Yang, Li (Autor:in)


    Erscheinungsdatum :

    01.05.2018


    Format / Umfang :

    535071 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Adaptive Fuzzy Sliding Mode Guidance Law considering Available Acceleration and Autopilot Dynamics

    Yulin Wang / Shengjing Tang / Wei Shang et al. | DOAJ | 2018

    Freier Zugriff

    Sliding-Mode Control for Integrated Missile Autopilot Guidance

    Tal Shima / Moshe Idan / Oded Golan | AIAA | 2006



    Sliding Mode Control for Integrated Missile Autopilot-Guidance

    Shima, Tal / Idan, Moshe / Golan, Oded | AIAA | 2004