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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    Title :

    UNIFIED CONTROL OF MULTIPLE ACTIVE SYSTEMS FOR HELICOPTER VIBRATION SUPRESSION


    Additional title:

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


    Contributors:

    Publication date :

    2021-06-16


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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