A flow body for an aircraft includes a skin having a first flow surface, having a flow influencing section with at least one first layer, at least one separator layer, at least one third layer, and at least one base layer. The first layer includes lithiated carbon fibers embedded into a matrix to form a negative electrode. The third layer includes carbon fibers with an electrode active material coating to form a positive electrode. The separator layer includes a non-conductive material for electrically isolating the first layer and the third layer from each other. The flow influencing section is configured for selectively raising a region of the arrangement of first layer, separator layer and third layer from the base layer upon application of a voltage between the first and third layers to form a bump on the flow body.


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    Titel :

    FLOW BODY FOR AN AIRCRAFT WITH A SELECTIVELY ACTIVATABLE SHOCK BUMP


    Weitere Titelangaben:

    FLUGZEUFSTRÖMUNGSKÖRPER MIT SELEKTIV ANSTEUERBARER STOSSERZEUGENDEN KONTURAUSBEULUNGEN
    STRUCTURE AÉRODYNAMIQUE MUNIE DE PROTUBÉRANCES GÉNÉRATRICES DE CHOCS SÉLECTIVEMENT ACTIVABLES


    Beteiligte:
    LINDE PETER (Autor:in) / MACHUNZE WOLFGANG (Autor:in)

    Erscheinungsdatum :

    2024-06-26


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F03G Feder-, Gewichts-, Trägheits- oder ähnliche Kraftmaschinen , SPRING, WEIGHT, INERTIA, OR LIKE MOTORS



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