A system for an aircraft (12) that includes a plurality of zones including:a first fiber optic cable (26A, 26E, 26) routed through a zone of the plurality of zones. The first fiber optic cable (26A, 26E, 26) is attached to a landing gear (42A) of the aircraft (12) in the zone of the plurality of zones;and a first controller configured to provide a first optical signal to the first fiber optic cable (26A, 26E, 26) and obtain a first optical response signal from the first fiber optic cable (26A, 26E, 26). The first controller is further configured to determine at least one temperature within the zone of the plurality of zones based on the first optical response signal, the first optical signal, and coherent optical frequency domain reflectometry (COFDR).


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    Title :

    INTEGRATED LANDING GEAR FIRE DETECTION AND FATIGUE MONITORING SYSTEM


    Additional title:

    INTEGRIERTES FAHRWERKSBRANDMELDE- UND -ERMÜDUNGSÜBERWACHUNGSSYSTEM
    SYSTÈME INTÉGRÉ DE SURVEILLANCE DE LA FATIGUE ET DE DÉTECTION D'INCENDIE DE TRAIN D'ATTERRISSAGE


    Contributors:

    Publication date :

    2023-07-19


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    G01K MEASURING TEMPERATURE , Messen der Temperatur / B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G01L Messen von Kraft, mechanischer Spannung, Drehmoment, Arbeit, mechanischer Leistung, mechanischem Wirkungsgrad oder des Drucks von Fluiden , MEASURING FORCE, STRESS, TORQUE, WORK, MECHANICAL POWER, MECHANICAL EFFICIENCY, OR FLUID PRESSURE / G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen



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