A vibration control system 200 for a rotorcraft 100 includes at least one of an integrated actuator 208 and an intermediate actuator 210 associated with a first source of vibration, a sensor configured to sense vibration from the first source of vibration, a dedicated actuator 212 configured for association with a fuselage 106, and a controller 204 configured to receive information from the sensor and configured to control the dedicated actuator and the at least one of the integrated actuator and the intermediate actuator.


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    Titel :

    UNIFIED CONTROL OF MULTIPLE ACTIVE SYSTEMS FOR HELICOPTER VIBRATION SUPRESSION


    Weitere Titelangaben:

    VEREINHEITLICHTE STEUERUNG VON MEHREREN AKTIVEN SYSTEMEN ZUR UNTERDRÜCKUNG VON HUBSCHRAUBERSCHWINGUNGEN
    COMMANDE UNIFIÉE DE MULTIPLES SYSTÈMES ACTIFS DE SUPPRESSION DES VIBRATIONS D'UN HÉLICOPTÈRE


    Beteiligte:
    HEVERLY DAVID E (Autor:in) / SINGH RUPINDER (Autor:in) / LEE TAEOH (Autor:in) / SMITH MICHAEL (Autor:in)

    Erscheinungsdatum :

    16.06.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



    UNIFIED CONTROL OF MULTIPLE ACTIVE SYSTEMS FOR HELICOPTER VIBRATION SUPPRESSION

    HEVERLY II DAVID E / SINGH RUPINDER / LEE TAEOH et al. | Europäisches Patentamt | 2017

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