The structural assembly (200) has box (202) having fiber sections (212,214) which are connected to each other at a crossing point (216). The fiber portion (212) has sub portions (218,220) which are connected to sub portions (232,233) of exterior wall (204) of box. The fiber section (214) has inner and outer ribs (222,224) which extend to inner and outer space (208) of box. A load (230) applied on attachment point (226) formed in outer rib is transferred by fiber section (214) to support element while another load (235) is transferred between sub portions (232,233) by fiber section (212). An independent claim is included for method for manufacture of structural assembly.


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    Titel :

    Structural arrangement, aircraft or spacecraft and method


    Weitere Titelangaben:

    Strukturelle Anordnung, Luft- oder Raumfahrzeug und Verfahren
    Agencement structurel, aéronef ou engin spatial et procédé


    Beteiligte:
    SEACK OLIVER (Autor:in) / BRUNS ALEXANDER (Autor:in)

    Erscheinungsdatum :

    27.12.2017


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS / B29L INDEXING SCHEME ASSOCIATED WITH SUBCLASS B29C, RELATING TO PARTICULAR ARTICLES , Index-Schema für besondere Gegenstände in Verbindung mit Unterklasse B29C / B64C AEROPLANES , Flugzeuge / D03D WOVEN FABRICS , Gewebe







    Facing arrangement and aircraft or spacecraft

    BUSCH HEINZ-PETER / SCHOKE BEREND | Europäisches Patentamt | 2016

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