An actuator system for controlling a flight surface of an aircraft includes a first actuator having a first actuator input and a first linear translation element that moves based on rotational motion received at the first actuator input and a first sensor coupled to the first linear translation element that generates a first output based on a displacement of the first linear translation element. The system also includes a second actuator having a second actuator input and a second linear translation element that moves based on rotational motion received at the second actuator input and a second sensor coupled to the second linear translation element that generates a second output based on a displacement of the second linear translation element. The system also includes a control unit that receives the first and second outputs and determines if an error condition exists for the system based on first and second output.


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    Titel :

    AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM


    Beteiligte:
    BAINES ANDREW N (Autor:in) / CRANDALL-SEIBERT CORY M (Autor:in) / BARGER VICTOR (Autor:in) / LEDEN WILLIAM E (Autor:in) / BOE DAVID K (Autor:in)

    Erscheinungsdatum :

    17.08.2017


    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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