An aircraft comprises a wing having at least a first pressure sensor 15a and a second pressure sensor 15b, wherein each pressure sensor 15 is configured to measure pressure of a liquid within the wing and has a known position (s1, s2) within the wing. A processing system is configured to receive first and second pressure data from the first and second pressure sensors respectively and determine a bending state of the wing based on the pressure data and the known positions of the first and second pressure sensors within the wing. Reference pressure sensors 16a, 16b may determine the density of the liquid, and the liquid may be fuel.


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    Titel :

    Determining bending state of aircraft wing


    Beteiligte:
    DYLAN VIGNOLA (Autor:in)

    Erscheinungsdatum :

    05.06.2024


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    G01M TESTING STATIC OR DYNAMIC BALANCE OF MACHINES OR STRUCTURES , Prüfen der statischen oder dynamischen Massenverteilung rotierender Teile von Maschinen oder Konstruktionen / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen



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