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    Method of making composite panels for a fuselage
    5.
    发明授权
    Method of making composite panels for a fuselage 有权
    制作机身复合板的方法

    公开(公告)号：US07935289B2

    公开(公告)日：2011-05-03

    申请号：US11695561

    申请日：2007-04-02

    Applicant: Donald A. Anderson ,  Brice A. Johnson ,  Stephen S. Spoon

    Inventor： Donald A. Anderson ,  Brice A. Johnson ,  Stephen S. Spoon

    IPC: B32B37/00

    CPC classification number: B29C70/543 ,  B29C33/68 ,  B29C37/0003 ,  B29C53/60 ,  B29C53/68 ,  B29C70/30 ,  B29C70/446 ,  Y02T50/43 ,  Y10T29/49867 ,  Y10T29/49879 ,  Y10T29/49895 ,  Y10T29/49998

    Abstract: A method is provided for making a composite laminate aircraft skin for a fuselage in multiple composite panels. A resin-impregnated composite tape is placed on a lay-up surface of a mandrel tool to form the composite laminate aircraft skin as a barrel that is substantially the shape of a fuselage section. The barrel is cut into a plurality of panels on the mandrel tool, and at least one panel of the plurality of panels is transferred, individually and independently of all other of the plurality of panels, from the lay-up surface of the mandrel tool to a first cure tool of a plurality of cure tools having an aero surface tooled to an outer mold line. The at least one of the panels is cured on the first cure tool to form a cured composite panel. The first cure tool defines and controls the outer mold line of the at least one panel. The cured composite panel is removed from the first cure tool.

    Abstract translation: 提供了一种用于制造用于多个复合板中的机身的复合层压飞机皮肤的方法。 将树脂浸渍的复合带放置在心轴工具的叠置表面上，以形成基本上为机身部分形状的复合层压飞机皮肤。 将筒体切割成心轴工具上的多个面板，并且多个面板中的至少一个面板独立地且独立于多个面板中的所有其他面板从芯棒工具的叠置表面传递到 多个固化工具的第一固化工具，其具有加工到外模线的航空表面。 所述至少一个所述面板在所述第一固化工具上固化以形成固化的复合板。 第一固化工具定义和控制至少一个面板的外模线。 固化的复合板从第一固化工具移除。

    MULTIPLE HEAD AUTOMATED COMPOSITE LAMINATING MACHINE FOR THE FABRICATION OF LARGE BARREL SECTION COMPONENTS
    7.
    发明申请
    MULTIPLE HEAD AUTOMATED COMPOSITE LAMINATING MACHINE FOR THE FABRICATION OF LARGE BARREL SECTION COMPONENTS 审中-公开
    多头自动化复合层压机用于制造大型钢筋部件

    公开(公告)号：US20080156436A1

    公开(公告)日：2008-07-03

    申请号：US11866308

    申请日：2007-10-02

    Applicant: Brice A. Johnson ,  Stephen S. Spoon ,  Randal S. Darras

    Inventor： Brice A. Johnson ,  Stephen S. Spoon ,  Randal S. Darras

    IPC: B32B37/00

    CPC classification number: B29C70/386 ,  B29C53/62 ,  B29C53/70 ,  B29C53/8016 ,  B29C70/32 ,  B29C70/545 ,  B29L2031/3076 ,  Y10T156/17

    Abstract: An aircraft part manufacturing device for automated composite lamination on a mandrel surface of a tool having a rotational axis includes a mechanical supporting structure that supports multiple material delivery heads. The tool is moveable and rotatable relative to the mechanical supporting structure. The mechanical supporting structure provides for axial translation of the material delivery heads relative to the mandrel surface while the mandrel surface is rotated for laying down courses of composite material over the entire mandrel surface of the tool. The position and movement of each of the plurality of material delivery heads is individually adjustable. Arm mechanisms provide motion of each material delivery head in a direction normal to the mandrel surface; rotation about an axis normal to the mandrel surface; circumferential position adjustment in a hoop direction relative to the mandrel surface; and axial position adjustment relative to the other material delivery heads.

    Abstract translation: 用于在具有旋转轴线的工具的心轴表面上的用于自动复合层压的飞行器部件制造装置包括支撑多个材料输送头的机械支撑结构。 该工具相对于机械支撑结构是可移动的和可旋转的。 机械支撑结构提供了材料输送头相对于心轴表面的轴向平移，同时心轴表面旋转以在复合材料的整个心轴表面上放置层叠的过程。 多个材料输送头中的每一个的位置和运动是单独调节的。 臂机构提供每个材料输送头沿与心轴表面垂直的方向的运动; 围绕与心轴表面垂直的轴旋转; 相对于心轴表面在环向方向上的周向位置调整; 和相对于其他材料输送头的轴向位置调节。

    SYSTEMS AND METHODS FOR DYNAMIC CONTROL OF TASK ASSIGNMENTS IN A FABRICATION PROCESS
    8.
    发明申请
    SYSTEMS AND METHODS FOR DYNAMIC CONTROL OF TASK ASSIGNMENTS IN A FABRICATION PROCESS 审中-公开
    用于制造过程中任务分配的动态控制的系统和方法

    公开(公告)号：US20140067108A1

    公开(公告)日：2014-03-06

    申请号：US13600686

    申请日：2012-08-31

    Applicant: SAMUEL F. PEDIGO ,  Julie A. Shah ,  Brice A. Johnson

    Inventor： SAMUEL F. PEDIGO ,  Julie A. Shah ,  Brice A. Johnson

    IPC: G06F19/00

    CPC classification number: G05B19/41865 ,  G05B2219/32085 ,  G05B2219/32423 ,  Y02P90/20 ,  Y02P90/24

    Abstract: Systems and methods for the dynamic control of task assignments in a fabrication process that employs a plurality of machines to fabricate a manufactured component. These systems and methods may include executing a plurality of task assignments with an available portion of the plurality of machines, monitoring a process variable that defines the available portion of the plurality of machines, and adjusting the plurality of task assignments to create a plurality of adjusted task assignments based upon the monitoring. The plurality of task assignments may include a plurality of tasks that are to be completed during fabrication of the manufactured component, and the executing may include initiating a respective task assignment of the plurality of task assignments with each machine in the available portion of the plurality of machines, thereby fabricating at least a portion of the manufactured component.

    Abstract translation: 用于动态控制制造过程中的任务分配的系统和方法，其使用多个机器来制造制造的部件。 这些系统和方法可以包括利用多个机器的可用部分执行多个任务分配，监视定义多个机器的可用部分的过程变量，以及调整多个任务分配以创建多个调整的 基于监控的任务分配。 多个任务分配可以包括要在制造的部件的制造期间完成的多个任务，并且执行可以包括：在多个任务分配的可用部分中的每个机器启动多个任务分配的相应任务分配 机器，从而制造制造的部件的至少一部分。

    COMPOSITE MATERIAL PLACEMENT METHOD AND SYSTEM
    10.
    发明申请
    COMPOSITE MATERIAL PLACEMENT METHOD AND SYSTEM 审中-公开
    复合材料放置方法与系统

    公开(公告)号：US20110073238A1

    公开(公告)日：2011-03-31

    申请号：US12961066

    申请日：2010-12-06

    Applicant: Brice A. Johnson ,  David J. Carbery

    Inventor： Brice A. Johnson ,  David J. Carbery

    IPC: B32B37/02

    CPC classification number: B29C70/386 ,  B29C70/32 ,  B29C70/545 ,  B29C2793/0027 ,  B29C2793/0081 ,  Y10T156/10 ,  Y10T156/1052 ,  Y10T156/1062 ,  Y10T156/1077 ,  Y10T156/17

    Abstract: To apply a course on a layup mold, a ply boundary that defines a ply area on the layup mold is determined and a tape of composite material is applied on the ply area at an oblique angle relative to the ply boundary. In addition, a leading edge of the tape is butt cut and the leading edge, and the ply boundary essentially converge. Furthermore, a trailing edge is generated. The trailing edge is a butt cut and the trailing edge and the ply boundary essentially converge.

    Abstract translation: 为了在上层模具上施加路线，确定了在铺层模具上限定层叠区域的层边界，并且复合材料带以相对于帘布层边界的倾斜角度施加在帘布层区域上。 另外，带子的前缘是对接的，并且前缘，并且帘布层边界基本上会聚。 此外，产生后沿。 后缘是对接切割，后缘和帘布层边界基本上会聚。

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