公开(公告)号：US08272118B2

公开(公告)日：2012-09-25

申请号：US12789308

申请日：2010-05-27

申请人： Pierre Alvez

发明人： Pierre Alvez

IPC分类号： B23P17/00 ,  B23Q3/00

CPC分类号： B21J15/14 ,  B21J15/142 ,  B23B35/00 ,  B23B2215/04 ,  B23P2700/01 ,  B64C1/069 ,  B64C2001/0081 ,  B64F5/10 ,  Y10T29/49895 ,  Y10T29/49956 ,  Y10T29/4998 ,  Y10T408/08

摘要： A method is provided for connecting two fuselage sections. A less complicated and time consuming method was found by using High-Speed-Drilling (HSD) for a group of final bore holes through the outer skin of at least one fuselage section and/or the coupling using one drilling template preferably without any pilot drilling.

摘要翻译： 提供一种用于连接两个机身部分的方法。 通过使用高速钻孔（HSD）通过至少一个机身部分的外皮和/或联接器使用高速钻孔（HSD），优选地不使用任何先导钻孔来实现较不复杂和耗时的方法 。

公开(公告)号：US20120213955A1

公开(公告)日：2012-08-23

申请号：US13212832

申请日：2011-08-18

申请人： Steffen Biesek ,  Robert Alexander Goehlich ,  Cihangir Sayilgan

发明人： Steffen Biesek ,  Robert Alexander Goehlich ,  Cihangir Sayilgan

IPC分类号： B32B1/04 ,  B64C1/06 ,  B32B38/00

CPC分类号： B29C70/86 ,  B23K2101/04 ,  B29C65/56 ,  B29C66/54 ,  B29C66/543 ,  B29C66/721 ,  B29C66/7212 ,  B29C66/72141 ,  B29C66/742 ,  B29K2105/06 ,  B29K2305/00 ,  B29K2307/00 ,  B29L2031/3082 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T156/1043 ,  Y10T428/13 ,  B29K2307/04

摘要： In a method for manufacturing a shell, at least two shell sections are fabricated out of a composite fiber material, at least one compensation body of a plastically deformable material is secured to at least one limiting edge of at least one shell section, the shell sections are overlapped to form the shell, yielding flat seams between respectively adjacent shell sections. The at least one compensation body is arranged on at least one of the seams. In order to compensate for dimensional deviations in each overlap, the shape of the corresponding compensation bodies is changed, and the shells sections are joined together at the seams.

摘要翻译： 在制造壳体的方法中，由复合纤维材料制成至少两个壳体部分，至少一个可塑性变形材料的补偿体固定到至少一个壳体部分的至少一个限制边缘，壳体部分 重叠形成壳体，在相邻的壳体部分之间产生平坦的接缝。 所述至少一个补偿体设置在所述接缝中的至少一个上。 为了补偿每个重叠中的尺寸偏差，相应的补偿体的形状改变，并且壳部分在接缝处连接在一起。

公开(公告)号：US20110042519A1

公开(公告)日：2011-02-24

申请号：US12868101

申请日：2010-08-25

申请人： Stefan Tacke ,  Andre Stuebs

发明人： Stefan Tacke ,  Andre Stuebs

IPC分类号： B64C1/06 ,  B64C1/12

CPC分类号： B64C1/064 ,  B64C1/069 ,  B64C2001/0072 ,  B64C2001/0081 ,  Y02T50/43

摘要： The present invention provides an interconnection, in particular in the field of aerospace. The interconnection has a T-stringer, an Ω-stringer and a connecting arrangement. The connecting arrangement connects base sections of the T-stringer and of the Ω-stringer to one another. This provides a coupling of an Ω-stringer to a T-stringer which is comparatively insensitive with respect to tolerances relating to the orientation of the Ω-stringer in relation to the T-stringer.

摘要翻译： 本发明提供了一种互连，特别是在航天领域。 互连具有一个T形纵梁，一个“纵向”和“连接”。 连接装置将T型纵梁的基部和“OHgr”型的压头彼此连接起来。 这提供了一个与一个T-纵梁的耦合，该T型纵梁相对于相对于T型纵梁的方向的公差相对不敏感。

公开(公告)号：US07857258B2

公开(公告)日：2010-12-28

申请号：US12108642

申请日：2008-04-24

申请人： Mathieu Normand ,  Marc Cazzola ,  Sandrine Deilhes

发明人： Mathieu Normand ,  Marc Cazzola ,  Sandrine Deilhes

IPC分类号： B64C1/00

CPC分类号： B64C1/12 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43

摘要： An aircraft fuselage including at least two sections kept assembled at a circumferential join, each section having at least one panel. The circumferential join includes at least one inner ring, situated on one face, called the inner face, of the fuselage. The inner ring has a width li, partially overlaps each of the two panels and is fixed to the two panels by fasteners. The fuselage also includes an outer ring, situated on one face, called the outer face, of the fuselage, opposite to the inner face. The outer ring has a width le, partially overlaps the two panels, and is fixed to the two panels and to the inner ring by some or all of the fasteners fixing the inner ring to the two panels.

摘要翻译： 包括至少两个部分的飞机机身保持组装在圆周连接处，每个部分具有至少一个面板。 圆周连接件包括位于机身的一个表面（称为内表面）上的至少一个内圈。 内圈具有宽度li，与两个面板中的每一个部分重叠，并通过紧固件固定到两个面板上。 机身还包括一个外环，位于机身的一个面，称为外表面，与内表面相对。 外圈具有宽度le，与两个面板部分重叠，并且通过将内圈固定到两个面板上的部分或全部紧固件固定到两个面板和内圈。

公开(公告)号：US20100320322A1

公开(公告)日：2010-12-23

申请号：US12735799

申请日：2009-02-16

申请人： Volker Reye ,  Stefan Tacke ,  Stephan Mischereit

发明人： Volker Reye ,  Stefan Tacke ,  Stephan Mischereit

IPC分类号： B64C1/00 ,  B23P11/00

CPC分类号： B64C1/069 ,  B64C1/06 ,  B64C2001/0072 ,  B64C2211/00 ,  Y02T50/43 ,  Y10T29/49826

摘要： The invention relates to a transverse butt connection (1, 24) between two fuselage sections (2, 3, 25, 26), more particularly for creating a fuselage cell for an aircraft, with a number of stringers (41, 42) arranged spaced out uniformly parallel to one another inside on an outer skin (4, 5, 27, 28).In order to enable a universal tolerance compensation with standardised compensating means within a predetermined tolerance band between two fuselage sections which are to be joined together, it is proposed according to the invention that both end areas (6, 7, 29, 30) of the fuselage sections (2, 3, 25, 26) have on the inside oppositely inclined skin wedge faces (8, 9) and the connection of the two end areas (6, 7, 29, 30) is carried out by a circumferential transverse butt strap (10, 31) which is provided with two oppositely inclined transverse butt strap wedge faces (12, 13) in the underneath area (11) wherein a wedge (14, 15, 33, 34) can be pushed in between each one transverse butt strap wedge face (12, 130) and a skin wedge face (8, 9) for tolerance compensation between the fuselage sections (2, 3, 25, 26).

摘要翻译： 本发明涉及两个机身部分（2,3,25,26）之间的横向对接连接（1,24），更特别地涉及用于产生用于飞行器的机身单元，其中多个桁条（41,42）间隔布置 在外皮（4,5,27,28）上彼此均匀地平行地排列。 为了能够在要连接在一起的两个机身部分之间的预定公差带内的标准化补偿装置实现通用公差补偿，根据本发明提出了两个端部区域（6,7,29,30） 机身部分（2,3,25,26）在内侧相对倾斜的皮肤楔形面（8,9）上，并且两个端部区域（6,7,29,30）的连接通过圆周横向对接 带子（10,31），其在下部区域（11）中设置有两个相对倾斜的横向对接带楔面（12,13），其中楔形物（14,15,33,34）可以推入每个横向 对接带楔面（12,130）和皮肤楔面（8,9），用于机身部分（2,3,25,26）之间的公差补偿。

公开(公告)号：US07823362B2

公开(公告)日：2010-11-02

申请号：US11855197

申请日：2007-09-14

申请人： Cedric Meyer

发明人： Cedric Meyer

IPC分类号： E04B1/38

CPC分类号： B64C1/064 ,  B64C1/069 ,  B64C2001/0081

摘要： A splice plate for stringers designed to connect two adjacent stringers at least three independent pieces, a connection rod being designed to be fixed by two opposite extremities to two adjacent stringers, and at least two connecting plates, each connecting plate being designed to be fixedly joined to a first extremity of one of the two stringers, and by a second extremity of a cross bar disposed between the two stringers. The disclosed embodiment also relate to a device for orbital fixation including at least one stringer splice plate splice bar.

摘要翻译： 用于桁条的拼接板，设计用于将两个相邻的桁条连接至少三个独立的部件，连接杆被设计成由两个相对的末端固定到两个相邻的桁条，以及至少两个连接板，每个连接板被设计成固定连接 到两个桁条之一的第一末端，以及设置在两个桁条之间的横杆的第二末端。 所公开的实施例还涉及用于轨道固定的装置，包括至少一个桁条拼接板拼接条。

公开(公告)号：US20100264272A1

公开(公告)日：2010-10-21

申请号：US12738600

申请日：2008-09-12

申请人： Helene Cazeneuve ,  Bruno Cacciaguerra ,  Jean-Claude Lacombe ,  David Andissac

发明人： Helene Cazeneuve ,  Bruno Cacciaguerra ,  Jean-Claude Lacombe ,  David Andissac

IPC分类号： B64C1/06

CPC分类号： B64C1/064 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43

摘要： An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area.

摘要翻译： 一种飞机结构，包括在接合处组装的加强板，不加强筋的连续性。 多个面板用于形成飞机的机身，尾翼和机翼。 这些面板包括在每个面板连接处中断的加强件。 然而，尽管有这些中断，加强件经受的应力必须被传送。 已知的解决方案需要使用每个加强筋至少一个附加部件和每个中断。 为了解决这个问题，所公开的实施例包括对于该区域中的所有被中断的加强件，每个面板接合面积最多需要一个附加部件的倍增器。

公开(公告)号：US20090020646A1

公开(公告)日：2009-01-22

申请号：US12108642

申请日：2008-04-24

申请人： Mathieu Normand ,  Marc Cazzola ,  Sandrine Deilhes

发明人： Mathieu Normand ,  Marc Cazzola ,  Sandrine Deilhes

IPC分类号： B64C1/00

CPC分类号： B64C1/12 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43

摘要： An aircraft fuselage including at least two sections kept assembled at a circumferential join, each section having at least one panel. The circumferential join includes at least one inner ring, situated on one face, called the inner face, of the fuselage. The inner ring has a width li, partially overlaps each of the two panels and is fixed to the two panels by fasteners. The fuselage also includes an outer ring, situated on one face, called the outer face, of the fuselage, opposite to the inner face. The outer ring has a width le, partially overlaps the two panels, and is fixed to the two panels and to the inner ring by some or all of the fasteners fixing the inner ring to the two panels.

摘要翻译： 包括至少两个部分的飞机机身保持组装在圆周连接处，每个部分具有至少一个面板。 圆周连接件包括位于机身的一个表面（称为内表面）上的至少一个内圈。 内圈具有宽度li，与两个面板中的每一个部分重叠，并通过紧固件固定到两个面板上。 机身还包括一个外环，位于机身的一个面，称为外表面，与内表面相对。 外圈具有宽度le，与两个面板部分重叠，并且通过将内圈固定到两个面板上的部分或全部紧固件固定到两个面板和内圈。

公开(公告)号：US20080111026A1

公开(公告)日：2008-05-15

申请号：US12016258

申请日：2008-01-18

申请人： Jeffrey Stulc ,  Wallace Chan ,  Brian Clapp ,  Neal Rolfes

发明人： Jeffrey Stulc ,  Wallace Chan ,  Brian Clapp ,  Neal Rolfes

IPC分类号： B64C1/12

CPC分类号： B64C1/069 ,  B64C1/068 ,  B64C1/12 ,  B64C1/1492 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49616 ,  Y10T29/49622 ,  Y10T29/49826 ,  Y10T428/19 ,  Y10T428/24331 ,  Y10T428/24612 ,  Y10T428/24628 ,  Y10T428/24661

摘要： Structures and methods for joining composite fuselage sections and other panel assemblies together are disclosed herein. In one embodiment, a shell structure configured in accordance with the present invention includes a first panel portion positioned adjacent to a second panel portion. The first panel portion can include a first stiffener attached to a first composite skin, and the second panel portion can include a second stiffener attached to a second composite skin. The shell structure can further include a fitting extending across a first edge region of the first panel portion and a second edge region of the second panel portion. A first end portion of the fitting can be attached to the first stiffener and the first composite skin, and a second end portion of the fitting can be attached to a second stiffener and a second composite skin, to join the first panel portion to the second panel portion.

摘要翻译： 本文公开了将复合机身部分和其它面板组件连接在一起的结构和方法。 在一个实施例中，根据本发明构造的壳结构包括邻近第二面板部分定位的第一面板部分。 第一面板部分可以包括附接到第一复合皮肤的第一加强件，并且第二面板部分可以包括附接到第二复合皮肤的第二加强件。 外壳结构还可以包括跨过第一面板部分的第一边缘区域延伸的配件和第二面板部分的第二边缘区域。 配件的第一端部可以附接到第一加强件和第一复合表皮，并且配件的第二端部可以附接到第二加强件和第二复合表皮，以将第一面板部分连接到第二加强件 面板部分。

公开(公告)号：US20080067289A1

公开(公告)日：2008-03-20

申请号：US11855197

申请日：2007-09-14

申请人： Cedric Meyer

发明人： Cedric Meyer

IPC分类号： B64C1/06 ,  E01B9/02

CPC分类号： B64C1/064 ,  B64C1/069 ,  B64C2001/0081

摘要： A splice plate for stringers designed to connect two adjacent stringers at least three independent pieces, a connection rod being designed to be fixed by two opposite extremities to two adjacent stringers, and at least two connecting plates, each connecting plate being designed to be fixedly joined to a first extremity of one of the two stringers, and by a second extremity of a cross bar disposed between the two stringers. The disclosed embodiment also relate to a device for orbital fixation including at least one stringer splice plate splice bar.

摘要翻译： 用于桁条的拼接板，设计用于将两个相邻的桁条连接至少三个独立的部件，连接杆被设计成由两个相对的末端固定到两个相邻的桁条，以及至少两个连接板，每个连接板被设计成固定连接 到两个桁条之一的第一末端，以及设置在两个桁条之间的横杆的第二末端。 所公开的实施例还涉及用于轨道固定的装置，包括至少一个桁条拼接板拼接条。