An aircraft anti-icing system (200) is disclosed. A tube (270) having a plurality of outlet ports is disposed within an interior of an outer housing (230) in spaced relation to a closed end (236) of this outer housing. The exterior of the outer housing includes a leading edge (238) at its closed end. The tube is anchored relative to the outer housing by one or more brackets (250) that extend from the tube to the outer housing. An open end of the outer housing may be closed by an aft wall (246) that encloses the tube within an interior compartment (248) of the outer housing.


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    Title :

    AIRCRAFT ANTI-ICING SYSTEM


    Additional title:

    LUFTFAHRZEUGENTEISUNGSSYSTEM
    SYSTÈME ANTIGIVRAGE D'AÉRONEF


    Contributors:

    Publication date :

    2023-08-16


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    English


    Classification :

    IPC:    B64D Ausrüstung für Flugzeuge , EQUIPMENT FOR FITTING IN OR TO AIRCRAFT




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