公开(公告)号：US20130181092A1

公开(公告)日：2013-07-18

申请号：US13533266

申请日：2012-06-26

申请人： Bruno Cacciaguerra ,  Alain Depeige ,  Jean-Claude Lacombe ,  Helene Cazeneuve ,  Marc-Antoine Castanet

发明人： Bruno Cacciaguerra ,  Alain Depeige ,  Jean-Claude Lacombe ,  Helene Cazeneuve ,  Marc-Antoine Castanet

IPC分类号： B64C1/06 ,  B64F5/00

CPC分类号： B64C1/069 ,  B64C1/068 ,  B64C2001/0081 ,  B64F5/10 ,  Y10T29/49622

摘要： Device for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces.Set of fuselage sections assembled by means of a device of the type described above.Method of assembling two fuselage sections by means of a device of the type described above.

摘要翻译： 用于组装两个飞行器机身部分的装置，每个飞行器机身部分各自包括皮肤和纵向加强件，该装置包括分别属于所述部分的相互对齐的纵向加强件的鱼板钓鱼钩，每个鱼板包括两个鱼板块，每个鱼板包括至少一个用于固定的纵向底板 纵向加强件和横向支撑头以及能够相互夹紧所述鱼板片的相应支撑头的至少一个可拆卸连接件，以允许在这些鱼片之间传递纵向力。 通过上述类型的装置组装的机身部分组。 通过上述类型的装置组装两个机身部分的方法。

公开(公告)号：US20130117983A1

公开(公告)日：2013-05-16

申请号：US13518984

申请日：2010-12-21

申请人： Toshikazu Sana ,  Naoki Tamura ,  Tomoya Takahashi ,  Toshiaki Takechi

发明人： Toshikazu Sana ,  Naoki Tamura ,  Tomoya Takahashi ,  Toshiaki Takechi

IPC分类号： B64C1/06

CPC分类号： B64F5/0009 ,  B29C33/38 ,  B29C33/485 ,  B29L2031/3082 ,  B64C1/069 ,  B64F5/10 ,  Y02T50/43 ,  Y10T29/4978 ,  Y10T29/49828 ,  Y10T29/53539

摘要： A technique which can assemble a mandrel having a substantially cylindrical shape and being dividable into plurality of segments, which is used for manufacturing, for example, a fuselage of an aircraft, with high position accuracy and an easy manner. In a segment fastening step, a segment which is a fastened target is fastened to a specified fastening portion which is one of a plurality of fastening portions set along a pair of support rings placed to face each other. In a rotation step, before the segment fastening step, the support rings are rotated so that the specified fastening portion is located at an uppermost portion of the support rings. In the segment fastening step, the segment which is the fastened target is placed between the support rings and lifted vertically up to a height corresponding to the specified fastening portion and then fastened to the support rings.

公开(公告)号：US08353479B2

公开(公告)日：2013-01-15

申请号：US12742206

申请日：2008-11-13

申请人： Stefan Tacke ,  Thorsten Roming ,  Klaus Edelmann

发明人： Stefan Tacke ,  Thorsten Roming ,  Klaus Edelmann

IPC分类号： B64C1/00

CPC分类号： B64C1/061 ,  B64C1/069 ,  B64C2001/0081

摘要： A coupling element for connecting stringers in the process of joining two fuselage sections by means of at least one transverse splicing plate, wherein in each case the fuselage sections on the inside comprise a multitude of stringers arranged on fuselage skins, as well as annular frame elements, wherein the coupling element comprises a base flange and a frame element flange, and by way of the coupling element in each case a connection between the opposing stringers, the annular frame element and the fuselage skins or the transverse splicing plate takes place so that the coupling element beyond a connection of the stringer base also supports the connection of stringers on the flank side.

摘要翻译： 一种用于在通过至少一个横向拼接板连接两个机身部分的过程中连接桁条的联接元件，其中在每种情况下，内侧的机身部分包括布置在机身外壳上的多个桁条以及环形框架元件 ，其中所述联接元件包括底部凸缘和框架元件凸缘，并且通过所述联接元件，在每种情况下，相对的纵梁之间的连接，所述环形框架元件和机身外壳或横向拼接板发生，使得 连接元件超过桁条基座的连接，也支撑在侧面上的桁条的连接。

公开(公告)号：US08302909B2

公开(公告)日：2012-11-06

申请号：US12738594

申请日：2008-10-15

申请人： Helene Cazeneuve ,  Bruno Cacciaguerra

发明人： Helene Cazeneuve ,  Bruno Cacciaguerra

IPC分类号： B64C1/00

CPC分类号： B64C1/06 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43

摘要： An aircraft fuselage produced by assembling, at a circumferential joint, at least two sections, each section including a coating and at least one element of at least one stiffener, the aforementioned two elements having a closed cross section and being assembled by a splicing piece. The elements of the stiffener and the splicing piece are made of composite. The aforementioned splicing piece, which has two flanges, is fixed to the coatings and to the stiffener elements by working fastenings positioned only on the flanges of the aforementioned splicing piece.

摘要翻译： 通过在周向接头处组装至少两个部分，每个部分包括涂层和至少一个加强件的至少一个元件而制造的飞行器机身，上述两个元件具有闭合的横截面并且由拼接件组装。 加强件和拼接件的元件由复合材料制成。 具有两个凸缘的上述拼接片通过仅位于上述拼接件的凸缘上的工作紧固件固定到涂层和加强件上。

公开(公告)号：US20120104167A1

公开(公告)日：2012-05-03

申请号：US13381579

申请日：2010-07-02

申请人： Dominique Moreau ,  Cedric Meyer ,  Jocelyn Gaudin

发明人： Dominique Moreau ,  Cedric Meyer ,  Jocelyn Gaudin

IPC分类号： B64C1/12 ,  B64C1/06

CPC分类号： B64C1/064 ,  B64C1/069 ,  B64C1/12 ,  B64C2001/0081

摘要： The invention relates to a fuselage element (1) comprising a first fuselage segment (2a) comprising a skin (3a), and junction means (4) for connecting the first segment (2a) to a second adjacent fuselage segment (2b), the first segment (2a) extending along the longitudinal axis (X) of the fuselage, wherein the fuselage element (1) includes stiffening elements (5a) extending along the axis (X). The end (5a1) of at least one stiffening element (5a) extends beyond a free edge (7) of the skin (3a) by a predetermined length (L).

摘要翻译： 本发明涉及一种机身元件（1），其包括包括皮肤（3a）的第一机身段（2a）和用于将第一段（2a）连接到第二相邻机身段（2b）的接合装置（4） 第一段（2a）沿着机身的纵向轴线（X）延伸，其中机身元件（1）包括沿轴线（X）延伸的加强元件（5a）。 至少一个加强元件（5a）的端部（5a1）延伸超出皮肤（3a）的自由边缘（7）预定长度（L）。

公开(公告)号：US08061035B2

公开(公告)日：2011-11-22

申请号：US12016258

申请日：2008-01-18

申请人： Jeffrey F. Stulc ,  Wallace C. Chan ,  Brian C. Clapp ,  Neal G. Rolfes

发明人： Jeffrey F. Stulc ,  Wallace C. Chan ,  Brian C. Clapp ,  Neal G. Rolfes

IPC分类号： B21D53/88

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：US20100258676A1

公开(公告)日：2010-10-14

申请号：US12738612

申请日：2008-09-12

申请人： Laurent Gauthie ,  Philippe Bernadet

发明人： Laurent Gauthie ,  Philippe Bernadet

IPC分类号： B64C1/06 ,  B21D53/88

CPC分类号： B64C1/064 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43 ,  Y10T29/49826

摘要： A system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections.

摘要翻译： 用于在机身中的加强框架和加强件之间的交叉处传递应力的系统以及用于生产一个这样的系统的方法。 飞机机身包括由加强框架中断的扶强材。 在上述中断过程中，尽管存在加强框架，但是加强件经受的应力必须被传递。 已知的解决方案难以制造和安装，并且当仅由复合材料制造时，不提供简单的应力传递路径。 为了解决这个问题，所公开的实施例包括创建覆盖加强件的连续部分的端部和机身的皮肤的延伸部分，以加强上述两个连续的部分。

公开(公告)号：US20100181428A1

公开(公告)日：2010-07-22

申请号：US12669956

申请日：2008-07-09

申请人： Torsten Noebel ,  Arne Paulukuhn

发明人： Torsten Noebel ,  Arne Paulukuhn

IPC分类号： B64C1/06 ,  B64C1/00

CPC分类号： B64C1/064 ,  B64C1/065 ,  B64C1/069 ,  B64C2001/0072 ,  Y02T50/43

摘要： The present invention provides a profiled part, for use, in particular, within an aircraft or spacecraft, the profiled part comprising at least one hollow profiled part portion and a T-shaped and/or L-shaped profiled part portion.

摘要翻译： 本发明提供一种用于特别是在飞行器或航天器内使用的成形部件，所述成形部件包括至少一个中空型材部分部分和T形和/或L形型材部分部分。

公开(公告)号：US20100044514A1

公开(公告)日：2010-02-25

申请号：US12418153

申请日：2009-04-03

申请人： Stefan Tacke

发明人： Stefan Tacke

IPC分类号： B64C1/06

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

摘要： A connection arrangement for connecting a first and second reinforcing element of an aircraft or spacecraft, the reinforcing elements each have profiled cross-sections comprising at least one foot portion and at least one web portion. They are spaced from one another at their end connection faces by a strap element. The connection arrangement comprises at least one foot portion connection element, which can be adjusted and firmly joined on one side to the geometrical shape of the foot portion of the first reinforcing element, on the other side to the geometrical shape of the foot portion of the second reinforcing element and to the interposed strip element, and comprising at least one web coupling element, which can be adjusted and firmly joined on one side to the geometrical shape of the web portion of the first reinforcing element, and on the other side to the strap element. A shell component of an aircraft or spacecraft comprises at least two shell elements connected to a strap element at a transverse seam, which shell elements each comprise at least a first and second reinforcing element which, in turn, are connected to a connection arrangement.

摘要翻译： 用于连接飞行器或航天器的第一和第二加强元件的连接装置，所述加强元件各自具有包括至少一个脚部分和至少一个腹板部分的成型横截面。 它们在其端部连接面处由带元件彼此间隔开。 连接装置包括至少一个脚部连接元件，该连接元件可以在另一侧被调节并牢固地连接在第一加强元件的脚部的几何形状的一侧上，与第一加强元件的脚部的几何形状相一致 第二增强元件和插入的带状元件，并且包括至少一个腹板联接元件，其可以在一侧被调节并牢固地连接到第一增强元件的腹板部分的几何形状，并且在另一侧到 表带元素。 飞行器或航天器的壳体部件包括在横向接缝处连接到带元件的至少两个壳体元件，所述壳体元件各自包括至少第一和第二加强元件，所述第一和第二加强元件又连接到连接装置。

公开(公告)号：US10046845B2

公开(公告)日：2018-08-14

申请号：US14725551

申请日：2015-05-29

申请人： Airbus Operations (S.A.S.)

发明人： Francis Dazet ,  Jérome Antypas ,  Laurent Bel ,  Philippe Delorme ,  Raphaël Brisbart

IPC分类号： B64C1/18 ,  B64C1/06 ,  F16G11/06 ,  F16G11/12

CPC分类号： B64C1/069 ,  B64C1/062 ,  B64C1/18 ,  F16G11/06 ,  F16G11/12

摘要： The disclosure herein relates to a part of an aircraft structure including a portion of a floor structure and a portion of a hull structure, connected to one another by a connecting element. In accordance with, the disclosure herein the connecting element includes a flexible cable fixed at one of the ends thereof to the portion of a floor structure and fixed at the other, second of the ends thereof to the portion of a hull structure. When the connection between the portion of a floor structure and the portion of a hull structure is subjected to tensile load, the flexible cable makes it possible to meet the standards of resistance to forward accelerations of the aircraft. When the connection is subjected to compressive load, the flexible cable relaxes and bends, which limits the requirements of withstanding compressive stresses and therefore the weight of the connecting element.