A landing gear position sensing system 1 comprising a system measuring position of landing gear component(s) 4, e.g. landing gear 7, bay door 12, uplocks 11, 16 or mechanisms 10, 15. An energy receiver(s) 3 (e.g. lidar sensor) receives energy from energy transmitter(s) 2 (e.g. laser or lidar transmitter). Energy characteristic (e.g. wavelength, energy density, travel time from transmission to reception) is indicative of the landing gear component position. Preferably electromagnetic energy spectrum is used, e.g. microwaves, radio waves, infrared, ultraviolet or visible light. Transmitter and receiver may be unitary 6 or mounted separately, moving relative to one another (figure 2). Receiver and transmitter may form a millimetric radar, monitoring positions of all landing gear bay components. Edge detection software may map the undercarriage bay. Leaks, failures, missing components, animals or a person may be detected in the landing gear bay through digital image comparison. Also disclosed an aircraft controller 5 determining first and second statuses of landing gear component(s) based on data received from energy receiver(s), the data indicative of first and second properties of the landing gear component(s). Properties may include position, temperature, structural rigidity and rotational velocity. Statuses may include landing gear position, tyre or brake condition.


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    Title :

    Landing gear position sensing


    Contributors:

    Publication date :

    2021-03-31


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen / G01S RADIO DIRECTION-FINDING , Funkpeilung



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