An actuator system (100) for controlling a flight surface (24, 26) of an aircraft (10) includes a first actuator (200; 300) having a first actuator input (204; 310) and a first linear translation element (208; 304) that moves based on rotational motion received at the first actuator input (204; 310) and a first sensor (212; 308) coupled to the first linear translation element (208; 304) that generates a first output based on a displacement of the first linear translation element (208; 304). The system also includes a second actuator (202; 300) having a second actuator input (206; 310) and a second linear translation element (210; 304) that moves based on rotational motion received at the second actuator input (206; 310) and a second sensor (214; 308) coupled to the second linear translation element (210; 304) that generates a second output based on a displacement of the second linear translation element (210; 304). The system also includes a control unit (102) 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


    Weitere Titelangaben:

    AERODYNAMISCHES STEUERFLÄCHENBEWEGUNGS-ÜBERWACHUNGSSYSTEM
    SYSTÈME DE SURVEILLANCE DE MOUVEMENT DE SURFACE DE COMMANDE AÉRODYNAMIQUE


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

    Erscheinungsdatum :

    12.12.2018


    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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