A wake produced by a leader aircraft and experienced by a follower aircraft is sensed in the following manner. Measurements carried out by the follower aircraft are estimated (311) based on a simulated response of the follower aircraft to an estimated aerodynamic context (309). The estimated aerodynamic context (309) includes a model of the wake and an estimated position of the follower aircraft with respect to the model of the wake. The estimated aerodynamic context (309) is adjusted (308) based on a comparison between the measurements that have been estimated (311) and actual measurements (312) carried out by the follower aircraft. The aforementioned estimation and adjustment operations are carried out iteratively. Information (313) on the wake is then extracted from the estimated aerodynamic context (309).


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    Title :

    AIRCRAFT WAKE SENSING


    Additional title:

    ERKENNUNG DES AUFWACHENS EINES FLUGZEUGS
    DÉTECTION DE SILLAGE D'AÉRONEF


    Contributors:

    Publication date :

    2023-06-07


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    G05D SYSTEMS FOR CONTROLLING OR REGULATING NON-ELECTRIC VARIABLES , Systeme zum Steuern oder Regeln nichtelektrischer veränderlicher Größen / B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT / G01C Messen von Entfernungen, Höhen, Neigungen oder Richtungen , MEASURING DISTANCES, LEVELS OR BEARINGS / G08G Anlagen zur Steuerung, Regelung oder Überwachung des Verkehrs , TRAFFIC CONTROL SYSTEMS



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