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    Device for joining composite structure elements with metallic structure elements
    1.
    发明申请
    Device for joining composite structure elements with metallic structure elements 有权
    用于将复合结构元件与金属结构元件连接的装置

    公开(公告)号：US20060018710A1

    公开(公告)日：2006-01-26

    申请号：US11187283

    申请日：2005-07-22

    申请人： Jean-Marc Durand ,  Bruno Sarpy ,  Gilles Bazerque

    发明人： Jean-Marc Durand ,  Bruno Sarpy ,  Gilles Bazerque

    IPC分类号： F16D1/00

    CPC分类号： B64C1/26 ,  Y10T403/44 ,  Y10T403/75

    摘要： A device for joining, in particular, composite structure elements with metallic structure elements of an aircraft, comprising a junction element, provided with a first longitudinal partition wall fastened to a metallic panel, integral with a stiffener comprising a vertical core and at least one baseplate, with a second longitudinal partition wall, fastened to a composite panel, and with a lower branch to which are connected the proximal extremities of the said first and second longitudinal partition walls, the device comprising, moreover, a first fitting element, provided with a first pick-up fitting body on the said stiffener and with a first heel and a second fitting element, provided with a second pick-up fitting body on the composite panel, and with a second heel, the heels of the fitting elements being fastened to the lower branch, on both sides of the lower branch, opposite each other.

    摘要翻译： 一种用于连接特别是具有飞行器的金属结构元件的复合结构元件的装置，包括接合元件，该接合元件设置有紧固到金属板的第一纵向间隔壁，该加强件与包括垂直芯部的至少一个基板 ，具有紧固到复合板的第二纵向分隔壁，并且具有连接所述第一和第二纵向间隔壁的近端的下部分支，所述装置还包括第一装配元件，所述第一装配元件设置有 第一拾取配件本体在所述加强件上，并具有第一跟部和第二装配元件，在复合板上设置有第二拾取配件主体，并且具有第二脚跟，配件元件的脚跟被紧固到 下分支在下分支的两侧相对。

    Device for joining composite structure elements with metallic structure elements
    2.
    发明授权
    Device for joining composite structure elements with metallic structure elements 有权
    用于将复合结构元件与金属结构元件连接的装置

    公开(公告)号：US07195418B2

    公开(公告)日：2007-03-27

    申请号：US11187283

    申请日：2005-07-22

    申请人： Jean-Marc Durand ,  Bruno Sarpy ,  Gilles Bazerque

    发明人： Jean-Marc Durand ,  Bruno Sarpy ,  Gilles Bazerque

    IPC分类号： B64C1/06 ,  E04B1/18

    CPC分类号： B64C1/26 ,  Y10T403/44 ,  Y10T403/75

    摘要： A device for joining, in particular, composite structure elements with metallic structure elements of an aircraft. The device includes a junction element, provided with a first longitudinal partition wall fastened to a metallic panel, integral with a stiffener comprising a vertical core and at least one baseplate, with a second longitudinal partition wall, fastened to a composite panel, and with a lower branch to which are connected the proximal extremities of the said first and second longitudinal partition walls. The device further includes a first fitting element, provided with a first pick-up fitting body on the said stiffener and with a first heel and a second fitting element, provided with a second pick-up fitting body on the composite panel, and with a second heel, the heels of the fitting elements being fastened to the lower branch, on both sides of the lower branch, opposite each other.

    摘要翻译： 一种用于将具有飞机的金属结构元件的复合结构元件特别地结合的装置。 该装置包括连接元件，该连接元件设置有固定到金属面板的第一纵向分隔壁，该加强件与包括垂直芯部和至少一个基板的加强件成一体，其具有固定到复合板上的第二纵向间隔壁， 下分支连接到所述第一和第二纵向分隔壁的近端。 该装置还包括第一装配元件，在所述加强件上设置有第一拾取配件主体，并具有第一跟部和第二装配元件，在复合板上设置有第二拾取配件主体，并且具有 第二脚跟，配合元件的后跟紧固到下分支，在下分支的两侧彼此相对。

    Fuselage spar for aircraft and central sparbox provided with such a spar
    3.
    发明申请
    Fuselage spar for aircraft and central sparbox provided with such a spar 有权
    飞机和中央翼型架的机身翼梁提供了这样的翼梁

    公开(公告)号：US20050230538A1

    公开(公告)日：2005-10-20

    申请号：US11070648

    申请日：2005-03-02

    申请人： Bruno Sarpy

    发明人： Bruno Sarpy

    IPC分类号： B64C1/06 ,  B64C1/26 ,  B64C1/00

    CPC分类号： B64C1/26

    摘要： A fuselage spar for aircraft is vertically mounted between an upper surface panel and a lower surface panel of the fuselage at the junction between a first wing structure spar and a second wing structure spar symmetrical with the first wing structure spar relative to the fuselage, and comprises peripheral zones and a central zone. This fuselage spar comprises a hollowed-out portion in the central zone, the peripheral zones of the spar providing for a draining of the normal loads conveyed by the wing structure spars. Also disclosed is a central spar box comprising such a spar.

    摘要翻译： 用于飞机的机身翼梁垂直地安装在机身的上表面面板和下表面面板之间的第一翼结构翼梁和与第一翼结构翼梁相对于机身对称的第二翼结构翼梁之间的接合处，并且包括 周边区域和中心区域。 该机身翼梁包括在中心区域中的中空部分，翼梁的周边区域用于排出由机翼结构翼梁输送的正常载荷。 还公开了包括这种翼梁的中心翼梁箱。

    Fuselage spar for aircraft and central sparbox provided with such a spar
    5.
    发明授权
    Fuselage spar for aircraft and central sparbox provided with such a spar 有权
    飞机和中央翼型架的机身翼梁提供了这样的翼梁

    公开(公告)号：US07316372B2

    公开(公告)日：2008-01-08

    申请号：US11070648

    申请日：2005-03-02

    申请人： Bruno Sarpy

    发明人： Bruno Sarpy

    IPC分类号： B64C1/00

    CPC分类号： B64C1/26

    摘要： A fuselage spar for aircraft is vertically mounted between an upper surface panel and a lower surface panel of the fuselage at the junction between a first wing structure spar and a second wing structure spar symmetrical with the first wing structure spar relative to the fuselage, and comprises peripheral zones and a central zone. This fuselage spar comprises a hollowed-out portion in the central zone, the peripheral zones of the spar providing for a draining of the normal loads conveyed by the wing structure spars. Also disclosed is a central spar box comprising such a spar.

    摘要翻译： 用于飞机的机身翼梁垂直地安装在机身的上表面面板和下表面面板之间的第一翼结构翼梁和与第一翼结构翼梁相对于机身对称的第二翼结构翼梁之间的接合处，并且包括 周边区域和中心区域。 该机身翼梁包括在中心区域中的中空部分，翼梁的周边区域用于排出由机翼结构翼梁输送的正常载荷。 还公开了包括这种翼梁的中心翼梁箱。