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 laser distance sensor disposed inside the first actuator 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 laser distance sensor disposed inside the second actuator 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 :

    LASER REFLECTION AERODYNAMIC CONTROL SURFACE MOVEMENT MONITORING SYSTEM


    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 :

    04.10.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / G01S RADIO DIRECTION-FINDING , Funkpeilung



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