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    METHOD AND APPARATUS FOR INSTALLING FASTENERS
    1.
    发明申请
    METHOD AND APPARATUS FOR INSTALLING FASTENERS 审中-公开
    用于安装紧固件的方法和装置

    公开(公告)号：WO2008124353A1

    公开(公告)日：2008-10-16

    申请号：PCT/US2008/058801

    申请日：2008-03-29

    Applicant: THE BOEING COMPANY ,  SARH, Branko

    Inventor： SARH, Branko

    IPC: B23Q9/00 ,  B21J15/14 ,  B23P19/06

    CPC classification number: B23P19/003 ,  B21J15/14 ,  B21J15/142 ,  B21J15/32 ,  B21J15/323 ,  B23P19/001 ,  B23P19/007 ,  B23P2700/01 ,  Y10T29/49718 ,  Y10T29/49947 ,  Y10T29/53 ,  Y10T29/53004 ,  Y10T29/53478

    Abstract: Apparatus for installing fasteners in a workpiece is mounted for computer controlled movement over the workpiece surface. The apparatus includes all of the tools, fasteners, drives and controls on-board that are needed to operate autonomously, without external connections. The apparatus may also include an on-board power supply for powering the tools, drives and controls. A supply of fasteners is held in an on-board replaceable cassette. An on-board fastener transferring device transfers individual fasteners from the cassette to the tools.

    Abstract translation: 用于在工件中安装紧固件的装置被安装用于在工件表面上的计算机控制的移动。 该装置包括在没有外部连接的情况下自主操作所需的所有工具，紧固件，驱动器和板上控制。 该装置还可以包括用于为工具，驱动器和控制器供电的车载电源。 紧固件供应装在板上可更换盒中。 板上紧固件传送装置将各个紧固件从盒子传送到工具。

    DEBRIS REMOVAL SYSTEM FOR CUTTING TOOLS
    3.
    发明申请
    DEBRIS REMOVAL SYSTEM FOR CUTTING TOOLS 审中-公开
    用于切割工具的DEBRIS拆卸系统

    公开(公告)号：WO2008027266A1

    公开(公告)日：2008-03-06

    申请号：PCT/US2007/018610

    申请日：2007-08-22

    Applicant: THE BOEING COMPANY ,  GAMBOA, Darryl ,  ERICKSON, Chris, J. ,  SARH, Branko

    Inventor： GAMBOA, Darryl ,  ERICKSON, Chris, J. ,  SARH, Branko

    IPC: B23Q11/00

    CPC classification number: B23Q11/0046 ,  Y10T408/03 ,  Y10T408/46 ,  Y10T408/50 ,  Y10T408/554 ,  Y10T408/56245 ,  Y10T409/304088

    Abstract: A system for removing debris generated by a cutting tool draws the debris into a mixing chamber formed in a workpiece clamp where the debris is combined with a high velocity airflow. A vacuum source draws the debris-air mixture into a cyclonic airflow extraction chamber where the mixture is accelerated before being extracted from the clamp through an exhaust channel. A clamping ring seals the area surrounding the cutting site so that air velocity in the mixing chamber is increased and debris is accelerated into the extraction chamber.

    Abstract translation: 用于去除由切割工具产生的碎屑的系统将碎屑吸入形成在工件夹具中的混合室中，其中碎片与高速气流结合。 真空源将碎屑 - 空气混合物吸入旋风气流提取室，在该气室中，混合物通过排气通道从夹具中提取之前被加速。 夹紧环密封切割部位周围的区域，使得混合室中的空气速度增加，碎片加速到提取室中。

    MULTI-RING SYSTEM FOR FUSELAGE BARREL FORMATION
    4.
    发明申请
    MULTI-RING SYSTEM FOR FUSELAGE BARREL FORMATION 审中-公开
    用于熔融条形成的多环系统

    公开(公告)号：WO2006113041A3

    公开(公告)日：2007-04-05

    申请号：PCT/US2006010705

    申请日：2006-03-22

    Applicant: BOEING CO ,  SARH BRANKO

    Inventor： SARH BRANKO

    IPC: B64C1/12 ,  B64C1/00

    CPC classification number: B64C1/068 ,  B29C70/32 ,  B64C1/061 ,  B64C1/064 ,  B64C1/12 ,  B64C2001/0072 ,  B64C2211/00 ,  B64F5/10 ,  Y02T50/433

    Abstract: An aircraft fuselage barrel (10) includes a skin (12) and a shear tie (18). The shear tie (18) resides within and is integrally formed with the skin (12). The shear tie (18) is separate from and configured for frame attachment thereon. A multi-ring system (79) for fuselage barrel formation includes a mold (68) with a ring (50). The ring (50) has width (W2) approximately equal to a separation distance (D) between two adjacent fuselage frames (22) and includes a module (52) that has a circumferential length (L1) that is greater than a circumferential distance between two fuselage longerons (14). A support structure (80) is coupled to and supports the mold (68). A method of forming the aircraft fuselage barrel (10) includes constructing the support structure (80). Rings (86) of the mold (68) are attached to and over the support structure (80). The mold (68) is constructed. Material is laid-up onto the mold (68) to integrally form the one-piece fuselage barrel (10) including a Hat-configured longeron (14).

    Abstract translation: 飞机机身枪管（10）包括皮肤（12）和剪切带（18）。 剪切带（18）位于皮肤（12）内并与皮肤（12）一体形成。 剪切带（18）与其上的框架附接分离并构造成用于框架附接。 用于机身桶形成的多环系统（79）包括具有环（50）的模具（68）。 环（50）具有大致等于两个相邻的机身框架（22）之间的间隔距离（D）的宽度（W2），并且包括具有大于圆周长度（L1）的周向长度（L1）的模块（52） 两个机身长度（14）。 支撑结构（80）联接到并支撑模具（68）。 形成飞行器机身筒（10）的方法包括构造支撑结构（80）。 模具（68）的环（86）附接到支撑结构（80）上和上方。 构造模具（68）。 将材料放置在模具（68）上以整体形成包括帽构造的龙门（14）的单件机身筒体（10）。

    MULTI-RING SYSTEM FOR FUSELAGE BARREL FORMATION
    7.
    发明申请
    MULTI-RING SYSTEM FOR FUSELAGE BARREL FORMATION 审中-公开
    用于熔融条形成的多环系统

    公开(公告)号：WO2006113041A2

    公开(公告)日：2006-10-26

    申请号：PCT/US2006/010705

    申请日：2006-03-22

    Applicant: THE BOEING COMPANY ,  SARH, Branko

    Inventor： SARH, Branko

    IPC: B64C1/12 ,  B64C1/00

    CPC classification number: B64C1/068 ,  B29C70/32 ,  B64C1/061 ,  B64C1/064 ,  B64C1/12 ,  B64C2001/0072 ,  B64C2211/00 ,  B64F5/10 ,  Y02T50/43

    Abstract: An aircraft fuselage barrel (10) includes a skin (12) and a shear tie (18). The shear tie (18) resides within and is integrally formed with the skin (12). The shear tie (18) is separate from and configured for frame attachment thereon. A multi-ring system (79) for fuselage barrel formation includes a mold (68) with a ring (50). The ring (50) has width (W2) approximately equal to a separation distance (D) between two adjacent fuselage frames (22) and includes a module (52) that has a circumferential length (L1) that is greater than a circumferential distance between two fuselage longerons (14). A support structure (80) is coupled to and supports the mold (68). A method of forming the aircraft fuselage barrel (10) includes constructing the support structure (80). Rings (86) of the mold (68) are attached to and over the support structure (80). The mold (68) is constructed. Material is laid-up onto the mold (68) to integrally form the one-piece fuselage barrel (10) including a Hat-configured longeron (14).

    Abstract translation: 飞机机身枪管（10）包括皮肤（12）和剪线（18）。 剪切带（18）位于皮肤（12）内并与皮肤（12）一体形成。 剪切带（18）与其上的框架附接分离并构造成用于框架附接。 用于机身筒形的多环系统（79）包括具有环（50）的模具（68）。 环（50）具有大致等于两个相邻的机身框架（22）之间的间隔距离（D）的宽度（W2），并且包括具有大于圆周长度（L1）的圆周长度（L1）的模块（52） 两个机身长度（14）。 支撑结构（80）联接到并支撑模具（68）。 一种形成飞机机身筒（10）的方法包括构造支撑结构（80）。 模具（68）的环（86）附接到支撑结构（80）上并在其上方。 构造模具（68）。 将材料放置在模具（68）上以整体形成包括帽构造的龙门（14）的单件机身筒（10）。

    AIRFOIL BOX AND ASSOCIATED METHOD
    8.
    发明申请
    AIRFOIL BOX AND ASSOCIATED METHOD 审中-公开
    AIRFOIL BOX及相关方法

    公开(公告)号：WO2005110842A3

    公开(公告)日：2006-02-16

    申请号：PCT/US2005014329

    申请日：2005-04-26

    Applicant: BOEING CO ,  SARH BRANKO

    Inventor： SARH BRANKO

    IPC: B64C1/00 ,  B64C3/00 ,  B64F5/00

    CPC classification number: B64C3/18 ,  B64C3/00 ,  B64F5/10

    Abstract: An airfoil box and associated method are provided. The airfoil box (10) includes two or more half-shell structures (30, 50). Each half-shell structure (30, 50) is an integral or unitary member that includes at least a portion of the outer skin (16) of the airfoil as well as stiffener members (34, 54) and connection members (38, 58). For example, the half-shell structures (30, 50) can be integrally formed of composite materials. The half-shell structures (30, 50) can be assembled by connecting the connection members (38, 58) with fasteners (70) such as rivets to form the airfoil box (10).

    Abstract translation: 提供了一种翼型箱和相关方法。 翼型箱（10）包括两个或更多个半壳结构（30,50）。 每个半壳结构（30,50）是包括翼型件的外皮（16）的至少一部分以及加强件（34,54）和连接构件（38,58）的整体或整体构件， 。 例如，半壳结构（30,50）可以由复合材料一体形成。 半壳结构（30,50）可以通过将连接构件（38,58）与诸如铆钉之类的紧固件（70）连接而形成翼型箱（10）来组装。

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