PROBLEM TO BE SOLVED: To provide a wing structure using a laminate composite, in particular, a reinforcement material for reinforcing wings.SOLUTION: A wing 104 may include a wing skin 120, a laminate composite first stringer 136, a rib 140, and at least one fastener. A majority of the first stringer 136 may be characterized by a stacked plurality of generally planar plies of reinforcement material structurally joined as a stack to an interior surface of the wing skin and extending generally parallel to the interior surface and a span-wise direction D1 of the wing along a substantial portion of the interior surface. The first stringer 136 may have a generally solid trapezoidal cross section when viewed in a plane that is generally perpendicular to the span-wise direction D1. The rib 140 may be positioned adjacent to the interior surface, and may extend generally perpendicularly to the span-wise direction D1. The trapezoidal cross section may be interfaced with a rib flange. The fastener may extend through the wing skin 120, the trapezoidal cross section, and the rib flange.SELECTED DRAWING: Figure 1

    【課題】積層複合材を用いた翼構造に関し、特に翼を補強するための補強材に関する。【解決手段】翼104は、翼外板120、積層複合材の第一のストリンガ136、リブ140、及び少なくとも一つのファスナを含み得る。第一のストリンガ136の大部分が、スタックとして内側表面に構造的に接合され、内側表面の実質的な部分に沿って内側表面及び翼長方向D1と概して平行に伸びる、積層された複数の概して平らな補強材料のプライによって、特徴付けられ得る。第一のストリンガ136は、翼長方向D1と概して垂直な平面内で見たときに、概して中実の台形断面を有し得る。リブ140は、内側表面に隣接して配置され、翼長方向D1と概して垂直に伸び得る。台形断面は、リブフランジとインターフェイス接続され得る。ファスナは、翼外板120、台形断面、及びリブフランジを通って伸び得る。【選択図】図1


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    Title :

    LAMINATE COMPOSITE WING STRUCTURE


    Additional title:

    積層複合材翼構造体



    Publication date :

    2016-07-28


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B29C Formen oder Verbinden von Kunststoffen , SHAPING OR JOINING OF PLASTICS



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