구조 패널 어셈블리는, 적어도 하나의 탭이 제1 패널의 메이팅 에지로부터 확대되고 제2 복합 패널의 내부 표면의 대응하는 부분과 대면 정합하고 있는 외부 표면을 포함하되 에지방향 정렬로 배치된 제1 및 제2 복합 패널을 포함한다. 대응하는 부분은 탭과 인터핏하거나 그렇지 않으면 탭을 수용하도록 구성된 오목한 영역을 포함하고 있다. 탭의 외부 표면은 복합 패널을 접합하기 위해 그들 사이에 접합 재료를 수용하도록 대응하는 부분으로부터 이격되어 있다.

    An aircraft fuselage assembly (100) comprising: first (112) and second (114) skin sections each further comprising a plurality of plies of composite materials and having a mating edge, with the mating edges (116, 118) disposed in edgewise alignment with each other; anda plurality of tabs (120) each extending longitudinally from the mating edge (116) of the first skin (112) section along an interior surface of the second skin (114) section, each tab (120) including an exterior surface (124) in facing registration with a corresponding portion of the interior surface (132) of the second skin (114) section, each of said tabs (120) further including at least one injection hole (142) formed therethrough for injection of bonding material (140) between said exterior surface (124) and said corresponding portion for attaching the first (112) and second (114) skin sections.


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    Title :

    COMPOSITE STRUCTURAL PANELS AND AIRCRAFT FUSELAGES


    Additional title:

    복합 구조 패널 및 항공기 동체


    Publication date :

    2019-09-18


    Type of media :

    Patent


    Type of material :

    Electronic Resource


    Language :

    Korean


    Classification :

    IPC:    B64C AEROPLANES , Flugzeuge



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