A leading edge structure 1, for an aircraft wing aerofoil, has a skin 10 forming an external aerodynamic surface of the aerofoil in which there are first regions 11 interleaved with second regions 12. Each first region has holes 13 extending through the skin, which may be used in a hybrid laminar flow control (HLFC) system in controlling the boundary layer through suction or negative pressure. Each second region has an electrical heating system 14 to increase the temperature of the skin, for a wing ice protection system. Preferably each of the regions are formed in strips which may either be parallel to the span of the leading edge (fig.1b), or parallel to a profile direction (fig.2). Each first region may form a wall of an enclosed chamber 15, or stringer duct, within the leading edge, where the holes provide an air flow path between the chamber interior and the leading edge exterior; the chambers may be connected to a suction pump. At least one chamber may have a wall formed by at least two first regions (fig.4,41) and at least one second region (fig.4,42), these first and/or second regions being smaller than other regions of that type.


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    Title :

    Aerofoil leading edge structures


    Contributors:

    Publication date :

    2020-09-09


    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



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