A method and device for precise control of and controller design for aircrafts consisting of at least one spinning part and at least one non-spinning part is provided. The required torques for control of the spinning parts and for the non-spinning parts are continuously and individually calculated. All torques are combined to get the correct torque for the complete aircraft. Doing this, it's possible to continuously apply the correct torque, both correctly distributed among the roll and pitch axes (correct angle), and correct magnitude. The result is a decoupling of the roll and pitch axes, simplifying controller design to a design of two single input single output controllers, one for each axe.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    ATTITUDE REGULATOR


    Weitere Titelangaben:

    FLUGLAGEREGELUNG
    RÉGULATEUR D'ATTITUDE


    Beteiligte:

    Erscheinungsdatum :

    13.03.2019


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / B64C AEROPLANES , Flugzeuge



    A globally stable linear attitude regulator

    Mortensen, R.E. | Tema Archiv | 1968


    Underwater helicopter with attitude regulator and attitude control method thereof

    HUANG HAOCAI / FENG RENDONG / WANG ZHANGLIN et al. | Europäisches Patentamt | 2024

    Freier Zugriff