A rotor blade fold system for an aircraft includes one or more actuators operably connected to one or more blade components of one or more rotor blades of the aircraft. One or more sensors are located at the one or more rotor blades and are configured to sense operation of the one or more blade components. A fold control system is configured to monitor output from the one or more sensors and is capable of stopping operation of the blade fold system, via communication with the one or more actuators, if the one or more blade components are not operating within predetermined limits.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    Blade fold system monitoring


    Beteiligte:
    HOOVER ERIC D (Autor:in)

    Erscheinungsdatum :

    18.08.2015


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



    Blade fold mechanism

    SCHANK TROY CYRIL / MARESH ANDREW RYAN / TZENG CHYAU-SONG | Europäisches Patentamt | 2022

    Freier Zugriff

    BLADE FOLD MECHANISM

    SCHANK TROY CYRIL / MARESH ANDREW RYAN / TZENG CHYAU-SONG | Europäisches Patentamt | 2019

    Freier Zugriff

    Blade fold system using flap hinge

    BASKIN BRYAN KENNETH / D'ANNA FRANK P / ALBER MARK R | Europäisches Patentamt | 2021

    Freier Zugriff

    BLADE FOLD SYSTEM USING FLAP HINGE

    BASKIN BRYAN KENNETH / D'ANNA FRANK P / ALBER MARK R | Europäisches Patentamt | 2017

    Freier Zugriff

    SINGLE ACTUATOR BLADE FOLD LINKAGE

    D' ANNA FRANK P | Europäisches Patentamt | 2017

    Freier Zugriff