A high lift system for an aircraft comprises a wing structure and a leading edge slat movably supported relative to a leading edge of the wing structure, the leading edge slat comprises a leading edge and a trailing edge, wherein the trailing edge is configured to take different positions to form a gap between the leading edge slat and the wing structure, a skin and enclosing an interior space of the leading edge slat, the skin having a flexible leading skin section facing away from the wing structure, a flexible trailing skin section facing towards the wing structure, at least one actuation arrangement arranged inside the interior space for selectively introducing a normal force onto at least one of the leading skin section and the trailing skin section.


    Zugriff

    Download


    Exportieren, teilen und zitieren



    Titel :

    High lift system for an aircraft and aircraft having such a high lift system


    Beteiligte:
    HENNING FRIEDER (Autor:in) / ZANTZ TANNO (Autor:in) / BRADY MICHAEL (Autor:in)

    Erscheinungsdatum :

    16.01.2018


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / F03D Windkraftmaschinen , WIND MOTORS



    HIGH LIFT SYSTEM FOR AN AIRCRAFT AND AIRCRAFT HAVING SUCH A HIGH LIFT SYSTEM

    HENNING FRIEDER / ZANTZ TANNO / BRADY MICHAEL | Europäisches Patentamt | 2015

    Freier Zugriff

    High lift system for an aircraft and aircraft having such a high lift system

    HENNING FRIEDER / BRADY MICHAEL / ZANTZ TANNO | Europäisches Patentamt | 2015

    Freier Zugriff

    METHOD FOR DETERMINING STATE OF COMPONENT IN HIGH LIFT SYSTEM OF AIRCRAFT, HIGH LIFT SYSTEM OF AIRCRAFT AND AIRCRAFT HAVING SUCH HIGH LIFT SYSTEM

    EUGEN NEB / JAN-AREND VAN BRUGGEN / MICHAEL BRADY et al. | Europäisches Patentamt | 2016

    Freier Zugriff

    Lift device for aircraft and aircraft having such lift device

    SCHAAL THOMAS / RIESBECK STEFAN | Europäisches Patentamt | 2023

    Freier Zugriff