Provided is a composite material structure that enables weight reduction, with consideration given to stress concentrations in areas around holes. A wing (1), which is the composite material structure, is a composite material made of fiber reinforced plastic extending in one direction and in which access holes (5) are formed. A lower outer plate (3) on the wing (1) is subjected to a tensile load in the longitudinal direction. The longitudinal tensile stiffness of peripheral regions (3a) of the access holes (5) is smaller than the longitudinal tensile stiffness of other regions (3b) surrounding the peripheral regions (3a).


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    Titel :

    COMPOSITE MATERIAL STRUCTURE, AND AIRCRAFT WING AND FUSELAGE PROVIDED THEREWITH


    Weitere Titelangaben:

    VERBUNDWERKSTOFFSTRUKTUR SOWIE FLUGZEUGFLÜGEL UND -RUMPF DAMIT
    STRUCTURE EN MATÉRIAU COMPOSITE, ET AILE ET FUSELAGE D'AVION COMPRENANT CELLE-CI


    Beteiligte:
    TANAKA YUYA (Autor:in) / YOSHIDA SHINICHI (Autor:in) / TANAKA HIDEAKI (Autor:in) / SUZUKI HIDEYUKI (Autor:in) / ABE TOSHIO (Autor:in) / KASHIWAGI MASAHIRO (Autor:in)

    Erscheinungsdatum :

    2018-01-03


    Medientyp :

    Patent


    Format :

    Elektronische Ressource


    Sprache :

    Englisch


    Klassifikation :

    IPC:    B64C AEROPLANES , Flugzeuge / B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS / B32B LAYERED PRODUCTS, i.e. PRODUCTS BUILT-UP OF STRATA OF FLAT OR NON-FLAT, e.g. CELLULAR OR HONEYCOMB, FORM , Schichtkörper, d.h. aus Ebenen oder gewölbten Schichten, z.B. mit zell- oder wabenförmiger Form, aufgebaute Erzeugnisse



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