An actuator system (100) for controlling a flight surface of an aircraft (10) includes a first actuator (200) 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 laser distance sensor (212) disposed inside the first actuator (200) that generates a first output based on a displacement of the first linear translation element. The system also includes a second actuator (202) 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 laser distance sensor (214) disposed inside the second actuator (202) that generates a second output based on a displacement of the second linear translation element. 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 :

    LASER REFLECTION AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM


    Weitere Titelangaben:

    AERODYNAMISCHES LASER-REFLEXIONS-STEUERFLÄCHEN-BEWEGUNGSÜBERWACHUNGSSYSTEM
    SYSTÈME DE SURVEILLANCE DE MOUVEMENT DE SURFACE DE COMMANDE AÉRODYNAMIQUE À RÉFLEXION LASER


    Beteiligte:
    POPOOLA ISRAEL O (Autor:in) / MILLER LARRY (Autor:in) / GRIMES CHUCK (Autor:in) / GALLAGHER RACHEL (Autor:in) / CRANDALL-SEIBERT CORY M (Autor:in) / HILL DAVID G (Autor:in) / BRAIMAH ELIJAH K (Autor:in)

    Erscheinungsdatum :

    26.02.2020


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge



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