会员体验
专利管家(专利管理)
工作空间(专利管理)
风险监控(情报监控)
数据分析(专利分析)
侵权分析(诉讼无效)
联系我们
交流群
官方交流:
QQ群: 891211   
微信请扫码    >>>
现在联系顾问~
热词
    • 6. 发明公开
    • Composite structural panels and aircraft fuselages
    • 复合结构面板和飞机机身
    • EP2676877A3
    • 2017-11-01
    • EP13171397.6
    • 2013-06-11
    • The Boeing Company
    • Cardin, Rachel
    • B64C1/00B64C1/06B64C1/12
    • B64C1/12B29D99/001B32B3/06B64C1/069B64C2001/0072Y02T50/43Y10T29/49622Y10T428/192
    • 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.
    • 1。一种飞机机身组件(100),包括:第一表皮部分(112)和第二表皮部分(114),每个表皮部分还包括多层复合材料并具有配合边缘,配合边缘(116,118)布置成与 彼此; 以及多个突片(120),每个突片沿着第二表皮(114)部分的内表面从第一表皮(112)部分的配合边缘(116)纵向延伸,每个突片(120)包括外表面(124) 在与第二表皮(114)部分的内表面(132)的相应部分面对准时,每个所述凸片(120)还包括至少一个穿过其中形成的用于注入粘结材料(140)的注入孔(142) 在所述外表面(124)和所述相应部分之间用于连接所述第一(112)和第二(114)蒙皮部分。