The hinge moment acting on the actuator will cause an out-of-plane moment, which is a destabilizing factor to the angular motion of spinning missiles. A new tuning criterion for the actuator controller is proposed to decrease the out-of-plane moment. It is noted that the integral element does not decrease the out-of-plane moment. A carefully designed proportional–derivative controller with some compromises can ensure the stability of the missile and provide good performance for the actuator.


    Zugriff

    Zugriff über TIB

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Retuning the actuator proportional–integral–derivative controller of spinning missiles




    Erscheinungsdatum :

    2017




    Medientyp :

    Aufsatz (Zeitschrift)


    Format :

    Print


    Sprache :

    Englisch



    Klassifikation :

    BKL:    55.50 Luftfahrzeugtechnik / 55.60 Raumfahrttechnik
    Lokalklassifikation TIB:    275/7040



    Retuning the actuator proportional–integral–derivative controller of spinning missiles

    Zhou, Wei / Yang, Shuxing / Zhao, Liangyu | SAGE Publications | 2017


    An Adaptive, Optimal Proportional-Integral Guidance For Missiles

    Evcimen, Çagdas / Leblebicioglu, Kemal | AIAA | 2013



    An Adaptive, Optimal Proportional-Integral Guidance For Missiles (AIAA 2013-4784)

    Evcimen, C. / Leblebicioglu, K. / American Institute of Aeronautics and Astronautics | British Library Conference Proceedings | 2013


    Autonomous Lane Change Control Using Proportional-Integral-Derivative Controller and Bicycle Model

    Joshi, Ajinkya A. / Peters, Diane L. / Bastiaan, Jennifer M. | SAE Technical Papers | 2020