Actuator systems and methods for controlling aerodynamic control surfaces of aircraft including a first actuator (226) receiving a first input and a first linear translation element (232) that moves based thereon, the first linear translation element operably connected to a first portion of the control surface. A first sensor assembly (238) is disposed relative to the first actuator that generates an output based on a displacement of the first translation element. A second actuator (228) receives a second input and a second linear translation element (236) moves based on the second input, the second linear translation element operably connected to a second portion of the control surface. A second sensor assembly (240) is disposed relative to the second actuator that generates a second sensor output based on a displacement of the second translation element. A controller (218) generates the inputs and receives the sensor outputs to determine if an error condition exists for the system.


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    Titel :

    AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM FOR AIRCRAFT


    Weitere Titelangaben:

    SYSTEM ZUR ÜBERWACHUNG DER AERODYNAMISCHEN STEUERFLÄCHENBEWEGUNG FÜR FLUGZEUGE
    SYSTÈME DE SURVEILLANCE DE MOUVEMENT DE SURFACE DE COMMANDE AÉRODYNAMIQUE D'AÉRONEF


    Beteiligte:
    HARRINGTON ERIK (Autor:in) / MILLER CHRISTIAN (Autor:in) / BISHOP YUNIYA S (Autor:in)

    Erscheinungsdatum :

    29.12.2021


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT



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