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    Saddle bracket assemblies
    21.
    发明授权
    Saddle bracket assemblies 有权
    鞍座支架组件

    公开(公告)号：US09097003B1

    公开(公告)日：2015-08-04

    申请号：US14281125

    申请日：2014-05-19

    申请人： The Boeing Company

    发明人： Saif Sultan ,  Bogdan M. Popescu ,  Ramanlal A. Patel

    IPC分类号： E04B1/38 ,  E04B1/41 ,  E04B1/61 ,  F16B5/00 ,  B64C1/06

    CPC分类号： B64C1/069 ,  E04B2/828 ,  E04B2001/6195 ,  F16B5/01

    摘要： Saddle bracket assemblies and corresponding methods of assembly and/or use are disclosed. Saddle brackets comprise two bracket members, a male bracket member and a female bracket member. The bracket members are configured to mate to a panel, such as a sandwich panel, through one or more panel passages through the panel. The bracket members generally have an L-shaped profile with two arms. The male bracket member includes one or more standoffs affixed to one arm, the standoff(s) being configured to fit the panel passage(s). The saddle bracket is assembled by inserting the standoff(s) through the panel passage(s), aligning the female bracket member to the standoff(s) and/or the panel passage(s), and securing the bracket members together with one or more panel connectors coupling the standoff(s) of the male bracket member, though the panel passage(s), to the female bracket member.

    摘要翻译： 公开了鞍形支架组件和相应的组装和/或使用方法。 鞍形支架包括两个支架构件，一个阳托架构件和一个阴托架构件。 支架构件被配置成通过穿过面板的一个或多个面板通道与诸如夹心板的面板配合。 托架构件通常具有两个臂的L形轮廓。 阳托架构件包括固定到一个臂的一个或多个支座，所述支架构造成适合所述面板通道。 鞍座支架通过将支座插入通过面板通道而组装，将阴托架构件对准支架和/或面板通道，并将支架构件与一个或多个 更多的面板连接器将阳托架构件的支座（通过面板通道）连接到阴托架构件。

    Composite fuselage system with composite fuselage sections
    23.
    发明授权
    Composite fuselage system with composite fuselage sections 有权
    具有复合机身部分的复合机身系统

    公开(公告)号：US08960604B1

    公开(公告)日：2015-02-24

    申请号：US13226971

    申请日：2011-09-07

    申请人： Eugene A. Dan-Jumbo

    发明人： Eugene A. Dan-Jumbo

    IPC分类号： B64C1/00 ,  B64C1/06

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

    摘要： A method and apparatus comprising a composite section. The composite section has a cylindrical shape. The composite section also has an outer wall configured to be bonded to a first inner wall of a first composite cylindrical fuselage section and a second inner wall of a second composite cylindrical fuselage section for an aircraft.

    摘要翻译： 一种包括复合部分的方法和装置。 复合截面具有圆柱形。 复合部分还具有被配置为结合到第一复合圆柱形机身部分的第一内壁和用于飞行器的第二复合圆柱形机身部分的第二内壁的外壁。

    Splice joints for composite aircraft fuselages and other structures
    24.
    发明授权
    Splice joints for composite aircraft fuselages and other structures 有权
    复合飞机机身和其他结构的接头

    公开(公告)号：US08869403B2

    公开(公告)日：2014-10-28

    申请号：US13225057

    申请日：2011-09-02

    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 disclosure 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 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，根据本公开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。 外壳结构可以包括穿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。

    METHOD FOR OPTIMIZING THE TOLERANCING OF A SET OF FLEXIBLE PARTS SUBJECTED TO FORCES
    25.
    发明申请
    METHOD FOR OPTIMIZING THE TOLERANCING OF A SET OF FLEXIBLE PARTS SUBJECTED TO FORCES 审中-公开
    用于优化一组受到力的柔性部件的限制的方法

    公开(公告)号：US20140288895A1

    公开(公告)日：2014-09-25

    申请号：US14350067

    申请日：2012-10-04

    申请人： EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCE ,  ECOLE NORMALE SUPERIEURE DE CACHAN

    发明人： Benoit Fricero ,  Francois Thiebaut ,  Alain Stricher ,  Laurent Champaney

    IPC分类号： G06F17/50

    CPC分类号： G06F17/50 ,  B64C1/069 ,  B64C2001/0072 ,  B64C2001/0081 ,  B64F5/10 ,  G05B19/4097 ,  G05B2219/31068 ,  G05B2219/35017 ,  G05B2219/35117 ,  G05B2219/35223 ,  G05B2219/45055 ,  Y02P90/04 ,  Y02P90/265 ,  Y02T50/43

    摘要： A method for optimizing the tolerancing of a set of flexible parts subjected to forces. At the design phase, an optimum tolerancing for flexible parts is defined according to the assembly process plan and the desired functional requirements. The structural digital models are considered as parts to be assembled and composed of a plurality of assembly points, a plurality of structural points, and mathematical relations or mechanical stiffness, such as a non-null relative displacement of a structural/assembly point in relation to the other structural/assembly points in a single digital model, modify tensor in each structural/assembly point. From a mechanical point of view, these mathematical relations express the existence of an elastic recovery property between the points that make up the digital model. The issue of optimization is simplified by: the definition of influence factors; the simulation of parts deviating from the nominal by a distortion vector.

    摘要翻译： 一种用于优化受到力的一组柔性部件的公差的方法。 在设计阶段，根据组装过程计划和所需的功能要求，定义柔性部件的最佳公差。 结构数字模型被认为是组装的部件，并且由多个组装点，多个结构点，数学关系或机械刚度组成，例如结构/装配点相对于 单个数字模型中的其他结构/汇编点在每个结构/汇编点修改张量。 从机械的角度来看，这些数学关系表示组成数字模型的点之间存在弹性恢复特性。 优化问题简化为：影响因素的定义; 通过失真向量模拟偏离标称的部分。

    Splice Joints for Composite Aircraft Fuselages and Other Structures
    27.
    发明申请
    Splice Joints for Composite Aircraft Fuselages and Other Structures 有权
    复合飞机机身和其他结构的接头接头

    公开(公告)号：US20140165361A1

    公开(公告)日：2014-06-19

    申请号：US13225057

    申请日：2011-09-02

    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： B64C1/06

    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 disclosure 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 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，根据本公开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。 外壳结构可以包括穿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。

    Access Door Assembly and Method of Making the Same
    30.
    发明申请
    Access Door Assembly and Method of Making the Same 有权
    进出门组件及其制作方法

    公开(公告)号：US20130082143A1

    公开(公告)日：2013-04-04

    申请号：US13251221

    申请日：2011-10-01

    申请人： Marc Storozuk

    发明人： Marc Storozuk

    IPC分类号： B64C1/14 ,  B60J5/00 ,  E06B3/00

    CPC分类号： B64C1/1446 ,  B64C1/069 ,  B64C1/12 ,  B64C2001/0081 ,  Y02T50/42

    摘要： In another embodiment of the disclosure, there is provided an access door assembly for joining to a structure. The access door assembly has an access door with at least one access door nonlinear edge. The access door assembly further has a support structure with at least one support structure nonlinear edge. The access door assembly further has a doubler element attached to an interior side of the support structure. The support structure nonlinear edge is designed to interlace with the access door nonlinear edge to form an access door assembly for joining to a structure, the access door assembly having an interlaced nonlinear edge interface. A diameter of the doubler element of the access door assembly is preferably reduced as compared to a diameter of a doubler element of an access door assembly having a linear or circular edge, such that the reduced diameter preferably results in an overall reduced weight of the access door assembly and the structure to which the access door assembly is joined.

    摘要翻译： 在本公开的另一个实施例中，提供了一种用于接合到结构的通道门组件。 检修门组件具有至少一个入口门非线性边缘的检修门。 进出门组件还具有至少一个支撑结构非线性边缘的支撑结构。 进出门组件还具有附接到支撑结构的内侧的倍增元件。 支撑结构非线性边缘被设计成与进入门非线性边缘交织以形成用于结合到结构的检修门组件，门禁组件具有隔行非线性边缘接口。 与具有线性或圆形边缘的进出门组件的倍增元件的直径相比，访问门组件的倍增元件的直径优选地减小，使得减小的直径优选地导致通道的整体减小的重量 门组件和接入门组件所连接的结构。