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1. 发明授权

US08900391B2 Automated resin and fiber deposition for resin infusion 有权
标题翻译：自动树脂和纤维沉积树脂灌注
公开(公告)号：US08900391B2
公开(公告)日：2014-12-02
申请号：US13168990
申请日：2011-06-26
申请人： Michael D. Silcock , Christopher A. Howe , Brice A. Johnson
发明人： Michael D. Silcock , Christopher A. Howe , Brice A. Johnson
IPC分类号： B29C70/38 , B29C70/44
CPC分类号： B29C70/386 , B29C66/9241 , B29C70/388 , B29C70/465 , B29C70/545 , B29C2793/0027 , B29K2105/0872 , Y10T156/1007 , Y10T156/1378 , Y10T156/17
摘要： A composite structure is fabricated by laying up at least one ply of fiber reinforcement and at least one layer of resin on a tool. The resin film layer is formed by laying strips of resin film. The fiber reinforcement is infused with resin from the resin layer.
摘要翻译：通过在工具上铺设至少一层纤维增强材料和至少一层树脂来制造复合结构。树脂膜层通过铺设树脂膜条而形成。纤维增强材料从树脂层注入树脂。

2. 发明申请

US20120325398A1 AUTOMATED RESIN AND FIBER DEPOSITION FOR RESIN INFUSION 有权
标题翻译：用于树脂输注的自动树脂和纤维沉积
公开(公告)号：US20120325398A1
公开(公告)日：2012-12-27
申请号：US13168990
申请日：2011-06-26
申请人： Michael D. Silcock , Christopher A. Howe , Brice A. Johnson
发明人： Michael D. Silcock , Christopher A. Howe , Brice A. Johnson
IPC分类号： B32B38/04 , B32B38/18
CPC分类号： B29C70/386 , B29C66/9241 , B29C70/388 , B29C70/465 , B29C70/545 , B29C2793/0027 , B29K2105/0872 , Y10T156/1007 , Y10T156/1378 , Y10T156/17
摘要： A composite structure is fabricated by laying up at least one ply of fiber reinforcement and at least one layer of resin on a tool. The resin film layer is formed by laying strips of resin film. The fiber reinforcement is infused with resin from the resin layer.
摘要翻译：通过在工具上铺设至少一层纤维增强材料和至少一层树脂来制造复合结构。树脂膜层通过铺设树脂膜条而形成。纤维增强材料从树脂层注入树脂。

3. 发明授权

US07935289B2 Method of making composite panels for a fuselage 有权
标题翻译：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
申请人： Donald A. Anderson , Brice A. Johnson , Stephen S. Spoon
发明人： Donald A. Anderson , Brice A. Johnson , Stephen S. Spoon
IPC分类号： B32B37/00
CPC分类号： B29C70/543 , B29C33/68 , B29C37/0003 , B29C53/60 , B29C53/68 , B29C70/30 , B29C70/446 , Y02T50/43 , Y10T29/49867 , Y10T29/49879 , Y10T29/49895 , Y10T29/49998
摘要： 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.
摘要翻译：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。

4. 发明授权

US07871487B1 Method for fabricating grid-stiffened composite structures 有权
标题翻译：制造网格加强复合结构的方法
公开(公告)号：US07871487B1
公开(公告)日：2011-01-18
申请号：US12332334
申请日：2008-12-10
申请人： Peter M. Wegner , Jeffrey M. Ganley , Brice A. Johnson , Barry P. Van West
发明人： Peter M. Wegner , Jeffrey M. Ganley , Brice A. Johnson , Barry P. Van West
IPC分类号： B29C53/80 , B29C53/58 , B29C70/86 , B29C69/00 , B29C45/14 , B65H81/00 , B29D22/00 , B32B27/00 , B32B37/24 , B28B7/22 , B27N3/10
CPC分类号： B29C70/342 , B29C53/566 , B29C53/587 , B29D22/00 , B29D99/001 , B29D99/0014 , B29L2031/3082 , B32B1/00 , B32B5/26 , B32B2260/021 , B32B2260/046 , B32B2262/106 , B32B2307/726 , B32B2605/18 , B64C1/068 , B64C3/187 , B64C3/22 , B64C2001/0072 , Y02T50/43
摘要： A method for fabricating a grid-stiffened structure from fiber-reinforced composite materials. Ribs are formed on a smooth hard base tool. Expansion blocks are placed in the shallow cavities formed by the ribs and the base tool, and held in place by one of several means while a skin is placed over the ribs, expansion blocks, and base tool. The assembly is then placed in a vacuum bag and autoclave cured. After cooling, the formed structure is separated from the base tool and the expansion blocks are removed from the cavities. This abstract is provided to comply with the rules requiring an abstract, and is intended to allow a searcher or other reader to quickly ascertain the subject matter of the technical disclosure. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.
摘要翻译：一种从纤维增强复合材料制造网格加强结构的方法。肋骨形成在光滑的硬基工具上。膨胀块放置在由肋和基础工具形成的浅空腔中，并且通过几种方式之一保持在适当位置，同时将皮肤放置在肋，膨胀块和基础工具上。然后将组件放置在真空袋中并使高压釜固化。在冷却之后，将形成的结构与基础工具分离，将膨胀块从空腔中移出。提供该摘要以符合要求摘要的规则，并且旨在允许搜索者或其他读者快速确定技术公开内容的主题。提交它的理解是，它不会用于解释或限制权利要求的范围或含义。

5. 发明申请

US20080156436A1 MULTIPLE HEAD AUTOMATED COMPOSITE LAMINATING MACHINE FOR THE FABRICATION OF LARGE BARREL SECTION COMPONENTS 审中-公开
标题翻译：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
申请人： Brice A. Johnson , Stephen S. Spoon , Randal S. Darras
发明人： Brice A. Johnson , Stephen S. Spoon , Randal S. Darras
IPC分类号： B32B37/00
CPC分类号： B29C70/386 , B29C53/62 , B29C53/70 , B29C53/8016 , B29C70/32 , B29C70/545 , B29L2031/3076 , Y10T156/17
摘要： 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.
摘要翻译：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。

6. 发明授权

US08435375B1 Method for fabricating rib-stiffened composite structures 有权
标题翻译：制造肋加强复合结构的方法
公开(公告)号：US08435375B1
公开(公告)日：2013-05-07
申请号：US13559559
申请日：2012-07-26
申请人： Peter M. Wegner , Jeffrey M. Ganley , Brice A. Johnson , Barry P. Van West
发明人： Peter M. Wegner , Jeffrey M. Ganley , Brice A. Johnson , Barry P. Van West
IPC分类号： B29C53/80 , B29C53/58 , B29C70/86 , B29C69/00 , B29C45/14 , B65H81/00 , B29D22/00 , B32B27/00 , B32B37/24 , B28B7/22 , B27N3/10
CPC分类号： B29C70/342 , B29C53/566 , B29C53/587 , B29D22/00 , B29D99/001 , B29D99/0014 , B29L2031/3082 , B32B1/00 , B32B5/26 , B32B2260/021 , B32B2260/046 , B32B2262/106 , B32B2307/726 , B32B2605/18 , B64C1/068 , B64C3/187 , B64C3/22 , B64C2001/0072 , Y02T50/43
摘要： A method for fabricating a grid-stiffened structure from fiber-reinforced composite materials. A skin is applied to a smooth, hard base tool. Ribs comprised of carbon-fiber tows are formed on the skin, and shallow cavities are formed between the ribs and the skin. An expansion block is placed in each of the cavities, and is held in place by an elastomeric contact adhesive having adhesive properties that are substantially diminished when the adhesive is heated to an elevated curing temperature. The assembly is then autoclave cured. After cooling, the formed structure is separated from the base tool and the expansion blocks are removed from the cavities. A grid-stiffened sandwich structure is formed by applying an outer skin over the ribs and expansion blocks, before curing the assembly. After cooling, the outer skin is removed to allow extraction of the blocks, and subsequently bonded to the ribs.
摘要翻译：一种从纤维增强复合材料制造网格加强结构的方法。皮肤应用于光滑，坚硬的基础工具。在皮肤上形成由碳纤维丝束组成的肋，并且在肋和皮肤之间形成浅的腔。膨胀块放置在每个空腔中，并且通过具有粘合性质的弹性体接触粘合剂保持在适当位置，当粘合剂被加热到升高的固化温度时，粘合剂性质基本上减小。然后将组件高压釜固化。在冷却之后，将形成的结构与基础工具分离，将膨胀块从空腔中移出。在固化组件之前，通过在外肋和膨胀块上施加外皮来形成网格加强的夹层结构。冷却后，除去外皮以允许块的提取，随后粘合到肋上。

7. 发明授权

US07479201B1 Method for fabricating rib-stiffened composite structures 失效
标题翻译：制造肋加强复合结构的方法
公开(公告)号：US07479201B1
公开(公告)日：2009-01-20
申请号：US11239453
申请日：2005-09-27
申请人： Peter M. Wegner , Jeffrey M. Ganley , Brice A. Johnson , Barry P. Van West
发明人： Peter M. Wegner , Jeffrey M. Ganley , Brice A. Johnson , Barry P. Van West
IPC分类号： B29D31/00 , B29D22/00 , B32B27/00 , B65C3/26 , B29C53/80 , B29C53/58 , B29C70/86 , B29C69/00 , B29C45/14 , B65H81/00 , B28B7/22 , B27N3/10
CPC分类号： B29C70/342 , B29C53/566 , B29C53/587 , B29D22/00 , B29D99/001 , B29D99/0014 , B29L2031/3082 , B32B1/00 , B32B5/26 , B32B2260/021 , B32B2260/046 , B32B2262/106 , B32B2307/726 , B32B2605/18 , B64C1/068 , B64C3/187 , B64C3/22 , B64C2001/0072 , Y02T50/43
摘要： A method for fabricating a grid-stiffened structure from fiber-reinforced composite materials. Ribs are formed on a smooth hard base tool. Expansion blocks are placed in the shallow cavities formed by the ribs and the base tool, and held in place by a synthetic elastomer-based adhesive while a skin is placed over the ribs, expansion blocks, and base tool. The assembly is then placed in a vacuum bag and autoclave cured. After cooling, the expansion blocks are removed and the formed structure is removed from the hard base tool. This abstract is provided to comply with the rules requiring an abstract, and is intended to allow a searcher or other reader to quickly ascertain the subject matter of the technical disclosure. It is submitted with the understanding that it will not be used to interpret or limit the scope or meaning of the claims.
摘要翻译：一种从纤维增强复合材料制造网格加强结构的方法。肋骨形成在光滑的硬基工具上。膨胀块放置在由肋和基础工具形成的浅空腔中，并且通过合成的基于弹性体的粘合剂保持在适当位置，同时将皮肤放置在肋，膨胀块和基础工具上。然后将组件放置在真空袋中并使高压釜固化。在冷却之后，移除膨胀块并将形成的结构从硬质基础工具上移除。提供该摘要以符合要求摘要的规则，并且旨在允许搜索者或其他读者快速确定技术公开的主题。提交它的理解是，它不会用于解释或限制权利要求的范围或含义。

8. 发明申请

US20140067108A1 SYSTEMS AND METHODS FOR DYNAMIC CONTROL OF TASK ASSIGNMENTS IN A FABRICATION PROCESS 审中-公开
标题翻译：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
申请人： SAMUEL F. PEDIGO , Julie A. Shah , Brice A. Johnson
发明人： SAMUEL F. PEDIGO , Julie A. Shah , Brice A. Johnson
IPC分类号： G06F19/00
CPC分类号： G05B19/41865 , G05B2219/32085 , G05B2219/32423 , Y02P90/20 , Y02P90/24
摘要： 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.
摘要翻译：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。

9. 发明授权

US08236124B1 Method for fabricating grid-stiffened composite structures 有权
标题翻译：制造网格加强复合结构的方法
公开(公告)号：US08236124B1
公开(公告)日：2012-08-07
申请号：US12967366
申请日：2010-12-14
申请人： Peter M. Wegner , Jeffrey M. Ganley , Brice A. Johnson , Barry P. Van West
发明人： Peter M. Wegner , Jeffrey M. Ganley , Brice A. Johnson , Barry P. Van West
IPC分类号： B29C53/80 , B29C53/58 , B29C70/86 , B29C69/00 , B29C45/14 , B65H81/00 , B29D22/00 , B32B27/00 , B32B37/24 , B28B7/22 , B27N3/10
CPC分类号： B29C70/342 , B29C53/566 , B29C53/587 , B29D22/00 , B29D99/001 , B29D99/0014 , B29L2031/3082 , B32B1/00 , B32B5/26 , B32B2260/021 , B32B2260/046 , B32B2262/106 , B32B2307/726 , B32B2605/18 , B64C1/068 , B64C3/187 , B64C3/22 , B64C2001/0072 , Y02T50/43
摘要： A method for fabricating a grid-stiffened structure from fiber-reinforced composite materials. A skin is applied to a smooth, hard base tool. Ribs comprised of carbon-fiber tows are formed on the skin, and shallow cavities are formed between the ribs and the skin. An expansion block is placed in each of the cavities, and is held in place by an elastomeric contact adhesive having adhesive properties that are substantially diminished when the adhesive is heated to an elevated curing temperature. The assembly is then autoclave cured. After cooling, the formed structure is separated from the base tool and the expansion blocks are removed from the cavities. A grid-stiffened sandwich structure is formed by applying an outer skin over the ribs and expansion blocks, before curing the assembly. After cooling, the outer skin is removed to allow extraction of the blocks, and subsequently bonded to the ribs.
摘要翻译：一种从纤维增强复合材料制造网格加强结构的方法。皮肤应用于光滑，坚硬的基础工具。在皮肤上形成由碳纤维丝束组成的肋，并且在肋和皮肤之间形成浅的腔。膨胀块放置在每个空腔中，并且通过具有粘合性质的弹性体接触粘合剂保持在适当位置，当粘合剂被加热到升高的固化温度时，粘合剂性质基本上减小。然后将组件高压釜固化。在冷却之后，将形成的结构与基础工具分离，将膨胀块从空腔中移出。在固化组件之前，通过在外肋和膨胀块上施加外皮来形成网格加强的夹层结构。冷却后，除去外皮以允许块的提取，随后粘合到肋上。

10. 发明申请

US20110073238A1 COMPOSITE MATERIAL PLACEMENT METHOD AND SYSTEM 审中-公开
标题翻译：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
申请人： Brice A. Johnson , David J. Carbery
发明人： Brice A. Johnson , David J. Carbery
IPC分类号： B32B37/02
CPC分类号： B29C70/386 , B29C70/32 , B29C70/545 , B29C2793/0027 , B29C2793/0081 , Y10T156/10 , Y10T156/1052 , Y10T156/1062 , Y10T156/1077 , Y10T156/17
摘要： 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.
摘要翻译：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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