To cope with misalignment of positions of holes formed in a main structural member and a leading edge member.SOLUTION: A wing includes a main structural member, a leading edge member formed of a material that has a linear thermal expansion coefficient different from that of the material of the main structural member, cylindrical eccentric bushings each having a circular through hole formed therein, and fastening members. First holes each having a long shape in a specific direction are formed in the leading edge member. Second holes are formed in the main structural member. The central axis of the eccentric bushing and the central axis of the through hole are parallel to each other and are offset from each other. The eccentric bushing is inserted into the first hole. The fastening member is inserted into the through hole and the second hole to connect the main structural member and the leading edge member.SELECTED DRAWING: Figure 4

    【課題】主構造部材と前縁部材とに形成される穴の位置の不整合に対応する。【解決手段】翼が、主構造部材と、主構造部材の材料と異なる線熱膨張係数を有する材料で形成された前縁部材と、円形の貫通穴が形成された、円柱状の偏心ブッシングと、締結部材とを備えている。前縁部材には、特定方向に長い形状を有する第1穴が形成されている。主構造部材には、第2穴が形成されている。偏心ブッシングの中心軸と貫通穴の中心軸とは、平行であり、且つ、ずれて位置している。偏心ブッシングは、第1穴に挿入されている。締結部材は、貫通穴及び第2穴に挿入されて主構造部材と前縁部材とを結合する。【選択図】図4


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    Title :

    WING, MISSILE, AND MANUFACTURING METHOD FOR WING


    Additional title:

    翼、飛翔体及び翼の製造方法


    Contributors:

    Publication date :

    2021-12-13


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Japanese


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge / B64F GROUND OR AIRCRAFT-CARRIER-DECK INSTALLATIONS SPECIALLY ADAPTED FOR USE IN CONNECTION WITH AIRCRAFT , Boden- oder Flugzeugträgerdeckeinrichtungen besonders ausgebildet für die Verwendung in Verbindung mit Luftfahrzeugen / F42B EXPLOSIVE CHARGES, e.g. FOR BLASTING , Explosive Ladungen, z.B. für Sprengungen



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