An aircraft fuselage structure comprising a skin element having an inner surface, a support structure connected to the inner surface for supporting the skin element, and a door opening provided in the skin element, wherein the support structure comprises an upper longitudinal element, a lower longitudinal element, a first circumferential element and a second circumferential element provided at the door opening. The object to provide an aircraft fuselage structure, wherein the support structure around the door opening is optimized for a minimum weight, is achieved in that the support structure comprises a first upper angled element extending from an upper first corner to an upper center point, and a second upper angled element extending from an upper second corner to the upper center point, such that the upper longitudinal element, the first upper angled element, and the second upper angled element together form a central upper triangle.


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    Titel :

    AIRCRAFT FUSELAGE STRUCTURE


    Beteiligte:
    ELBRACHT DIRK (Autor:in) / HAACK CORD (Autor:in)

    Erscheinungsdatum :

    2017-05-11


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS / B33Y ADDITIVE MANUFACTURING, i.e. MANUFACTURING OF THREE-DIMENSIONAL [3D] OBJECTS BY ADDITIVE DEPOSITION, ADDITIVE AGGLOMERATION OR ADDITIVE LAYERING, e.g. BY 3D PRINTING, STEREOLITHOGRAPHY OR SELECTIVE LASER SINTERING , Additive (generative) Fertigung, d. h. die Herstellung von dreidimensionalen [3D] Bauteilen durch additive Abscheidung, additive Agglomeration oder additive Schichtung, z. B. durch 3D- Drucken, Stereolithografie oder selektives Lasersintern



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