Design and synthesis of a nonlinear supersonic missile longitudinal dynamics control for angle-of-attack output tracking are presented. In addition a sliding mode observer is designed to estimate the angle-of-attack which is difficult to measure in practice. The employed method is simple to implement in practical applications and enables the sliding mode control design to exhibit the desired dynamic properties during the entire output-tracking process independent of perturbations. Results of simulations are presented to demonstrate the performance, robustness, and stability of the considered autopilot.


    Zugriff

    Zugriff prüfen

    Verfügbarkeit in meiner Bibliothek prüfen

    Bestellung bei Subito €


    Exportieren, teilen und zitieren



    Titel :

    Sliding mode autopilot and observer design for a supersonic flight vehicle


    Beteiligte:
    Bahrami, M. (Autor:in) / Ebrahimi, B. (Autor:in) / Ansarifar, G. R. (Autor:in) / Roshanian, J. (Autor:in)


    Erscheinungsdatum :

    01.12.2008


    Format / Umfang :

    568694 byte




    Medientyp :

    Aufsatz (Konferenz)


    Format :

    Elektronische Ressource


    Sprache :

    Englisch




    FLIGHT VEHICLE AUTOPILOT

    WISE KEVIN A / LAVRETSKY EUGENE / ROBERTS BRIAN C et al. | Europäisches Patentamt | 2018

    Freier Zugriff

    FLIGHT VEHICLE AUTOPILOT

    WISE KEVIN A / LAVRETSKY EUGENE / ROBERTS BRIAN C et al. | Europäisches Patentamt | 2019

    Freier Zugriff

    Flight vehicle autopilot

    WISE KEVIN A / LAVRETSKY EUGENE / ROBERTS BRIAN C et al. | Europäisches Patentamt | 2017

    Freier Zugriff

    Sliding Mode Control with Optimal Sliding Surfaces for Missile Autopilot Design

    Metin U. Salamci / M. Kemal -Oslash / zg-ograve, ren et al. | AIAA | 2000