The three-loop autopilot is employed by spinning missiles as well as by many high-performance command or homing guidance missiles currently because it performs well in stabilizing airframe and implementing guidance commands. However, for spinning missiles, the closed-loop system may be dynamically unstable in the form of a divergent coning motion due to the existence of cross-coupling effects. And the stability criteria of the autopilot applicable to the nonspinning missile are no longer valid in the event of the spinning. To address this issue, the structure of a three-loop autopilot of spinning missiles is introduced in this study, for which the sufficient and necessary condition of coning motion stability is analytically derived from the equations in the form of complex summation. The stability criteria are further illustrated by numerical simulation. It is noticed that spinning shrinks the stable region of the design parameters significantly. And the higher the spinning rate, the smaller the stable region becomes.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Three-loop autopilot of spinning missiles


    Beteiligte:
    Li, Keyong (Autor:in) / Yang, Shuxing (Autor:in) / Zhao, Liangyu (Autor:in)


    Erscheinungsdatum :

    01.06.2014


    Format / Umfang :

    7 pages




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    Three-loop autopilot of spinning missiles

    Li, Keyong | Online Contents | 2014


    Stability of Spinning Missiles with an Acceleration Autopilot

    Li, Keyong / Yang, Shuxing / Zhao, Liangyu | AIAA | 2012



    Stability Limits of Spinning Missiles with Attitude Autopilot

    Yan, Xiaoyong / Yang, Shuxing / Xiong, Fenfen | AIAA | 2011