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公开(公告)号：US20140183784A1
公开(公告)日：2014-07-03
申请号：US13732624
申请日：2013-01-02
Applicant: The Boeing Company
Inventor： Aaron W. Bartel , David E. Gideon , Michael H. Larson
IPC: B29C51/02
CPC classification number: B29C51/02 , B29C70/50 , B29D99/0003
Abstract: A method of fabricating a reinforced thermoplastic composite part comprises moving a laminate of reinforcing fibers embedded in a thermoplastic matrix for sequential operations through a heating station and then a forming station. The heating station is used to soften the thermoplastic matrix in a portion of the laminate while the forming station is used to impart a geometry to a portion of the laminate whose thermoplastic matrix had just been softened. The softening and the forming are performed simultaneously on different portions of the laminate.
Abstract translation: 制造增强热塑性复合材料部件的方法包括将嵌入热塑性基质中的增强纤维的层压体移动通过加热站然后成形站进行顺序操作。 加热站用于软化层压体的一部分中的热塑性基质，同时使用成形工位将几何形状赋予热塑性基体刚刚软化的层压体的一部分。 在层压体的不同部分上同时进行软化和成形。
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2.发明申请公开(公告)号：US20140102578A1
公开(公告)日：2014-04-17
申请号：US13650139
申请日：2012-10-12
Applicant: The Boeing Company
Inventor： Aaron W. Bartel , Brett I. Lyons , Jeffery L. Marcoe
CPC classification number: B29C70/205 , B29C33/52 , B29C70/462 , B29C2035/0811 , F16L9/128
Abstract: A method of fabricating a thermoplastic composite tubular structure provides a mandrel of a soluble, expandable material. The method overbraids the mandrel with a continuous fiber thermoplastic composite material to form an overbraided mandrel. The method installs the overbraided mandrel into a matched tooling assembly. The method heats in a heating apparatus the matched tooling assembly with the installed overbraided mandrel at a specified heating profile in order to consolidate the thermoplastic composite material and form a thermoplastic composite tubular structure. The method cools the matched tooling assembly with the formed thermoplastic composite tubular structure at a specified cooling profile. The method removes the formed thermoplastic composite tubular structure from the matched tooling assembly. The method solubilizes the mandrel to permanently remove the mandrel from the formed thermoplastic composite tubular structure.
Abstract translation: 一种制造热塑性复合管状结构的方法提供了可溶的可膨胀材料的心轴。 该方法用连续的纤维热塑性复合材料超过心轴以形成一个超支撑的心轴。 该方法将过量的心轴安装到匹配的工具组件中。 该方法在加热装置中加热匹配的加工组件，其中安装的包覆心轴处于规定的加热轮廓，以便固化热塑性复合材料并形成热塑性复合管状结构。 该方法以所规定的冷却曲线冷却具有成形的热塑性复合管状结构的匹配的加工组件。 该方法从匹配的模具组件移除形成的热塑性复合管状结构。 该方法使心轴溶解以从形成的热塑性复合管状结构永久地移除心轴。
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公开(公告)号：US10058950B1
公开(公告)日：2018-08-28
申请号：US13660376
申请日：2012-10-25
Applicant: THE BOEING COMPANY
Inventor： Noel T. Gerken , Robert James Miller , Jeffery L. Marcoe , John B. Moser , Aaron W. Bartel , Marc R. Matsen
CPC classification number: B23K13/015 , B23K13/01 , B23K13/04 , B23K35/001
Abstract: An induction welding system is provided. The system includes at least one induction coil configured to generate an alternating magnetic field, and a smart susceptor film sized to be positioned between a first component and a second component to be welded to the first component. The smart susceptor film includes a thermoplastic resin, and a plurality of metal alloy wires disposed in the thermoplastic resin such that the plurality of metal alloy wires are oriented substantially parallel to the generated alternating magnetic field.
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公开(公告)号：US20150291283A1
公开(公告)日：2015-10-15
申请号：US14252816
申请日：2014-04-15
Applicant: The Boeing Company
Inventor： Brett I. Lyons , Aaron W. Bartel , Trevor E. Tucker
CPC classification number: B29C64/135 , B22F3/1055 , B29C64/118 , B29C64/124 , B29C64/129 , B29C64/153 , B29C67/0062 , B29C67/0066 , B29C67/0077 , B29K2995/0016 , B29K2995/0091 , B29L2031/3076 , B32B1/08 , B32B3/263 , B32B3/266 , B32B3/30 , B32B2605/18 , B33Y10/00 , B33Y80/00 , F16L9/006 , F16L9/21
Abstract: One example of the present disclosure relates to a monolithic part including an exterior wall and a first cavity. The first cavity includes a first aperture in communication with the exterior wall and a first inner surface defining a first shape. The first shape prevents extraction from the first cavity, via the first aperture, of a first virtual object having the first shape.
Abstract translation: 本公开的一个实例涉及包括外壁和第一腔的整体部件。 第一腔包括与外壁连通的第一孔和限定第一形状的第一内表面。 第一形状防止具有第一形状的第一虚拟物体从第一孔经由第一孔提取。
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公开(公告)号：US10065370B2
公开(公告)日：2018-09-04
申请号：US15215978
申请日：2016-07-21
Applicant: The Boeing Company
Inventor： Brett I. Lyons , Aaron W. Bartel , Trevor E. Tucker
IPC: B29C41/22 , B29C67/00 , B33Y10/00 , F16L9/00 , B32B3/26 , B32B1/08 , B29C64/124 , B29C64/118 , B22F3/105 , B29C64/135 , B29C64/129 , B29C64/153 , B33Y80/00 , B32B3/30 , B29L31/30 , F16L9/21
CPC classification number: B29C64/135 , B22F3/1055 , B29C64/118 , B29C64/124 , B29C64/129 , B29C64/153 , B29K2995/0016 , B29K2995/0091 , B29L2031/3076 , B32B1/08 , B32B3/263 , B32B3/266 , B32B3/30 , B32B2605/18 , B33Y10/00 , B33Y80/00 , F16L9/006 , F16L9/21
Abstract: A method of forming a monolithic aircraft part includes additively forming a first cavity, defined by a first wall of the part, additively forming a second cavity, defined by a second wall of the part, so that the first cavity and the second cavity are not in communication with each other and share a common wall portion so that the second cavity is partially contained within the first cavity. Additively forming the first cavity includes forming a first aperture, extending through the first wall, forming a second aperture, extending through the first wall, and forming a first inner surface of the first wall, defining a first shape, wherein a first object, permanently having the first shape, would not be able to be mechanically extracted from the first cavity via the first aperture or the second aperture.
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Patent Agency Ranking
公开(公告)号：US09827710B2
公开(公告)日：2017-11-28
申请号：US14171779
申请日：2014-02-04
Applicant: The Boeing Company
Inventor： Angelo Rossi , Jeffery L. Marcoe , Marc R. Matsen , Aaron W. Bartel
IPC: B29C33/52 , B29C70/40 , B29C65/72 , B29C33/44 , B29C65/62 , B29D99/00 , D04C1/06 , B29C70/50 , B29C70/24 , B32B27/00 , B29B11/16
CPC classification number: B29C65/72 , B29B11/16 , B29C33/448 , B29C65/62 , B29C70/24 , B29C70/504 , B29D99/0003 , B29D99/0007 , B29D99/0014 , D04C1/06 , Y02T50/43
Abstract: A method of manufacturing a radius filler may include providing a plurality of fibers, braiding the plurality of fibers into a braided preform, shaping the braided preform into a braided radius filler, and cutting the braided radius filler to a desired length.
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公开(公告)号：US20160325494A1
公开(公告)日：2016-11-10
申请号：US15215978
申请日：2016-07-21
Applicant: The Boeing Company
Inventor： Brett I. Lyons , Aaron W. Bartel , Trevor E. Tucker
CPC classification number: B29C64/135 , B22F3/1055 , B29C64/118 , B29C64/124 , B29C64/129 , B29C64/153 , B29C67/0062 , B29C67/0066 , B29C67/0077 , B29K2995/0016 , B29K2995/0091 , B29L2031/3076 , B32B1/08 , B32B3/263 , B32B3/266 , B32B3/30 , B32B2605/18 , B33Y10/00 , B33Y80/00 , F16L9/006 , F16L9/21
Abstract: One example of the present disclosure relates to a monolithic part including an exterior wall and a first cavity. The first cavity includes a first aperture in communication with the exterior wall and a first inner surface defining a first shape. The first Shape prevents extraction from the first cavity, via the first aperture, of a first virtual object having the first shape.
Abstract translation: 本公开的一个实例涉及包括外壁和第一腔的整体部件。 第一腔包括与外壁连通的第一孔和限定第一形状的第一内表面。 第一形状防止通过第一孔径从具有第一形状的第一虚拟物体的第一腔中提取。
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公开(公告)号：US09956718B2
公开(公告)日：2018-05-01
申请号：US13621991
申请日：2012-09-18
Applicant: The Boeing Company
Inventor： Aaron W. Bartel , John B. Moser
IPC: B29C53/04 , B29C53/42 , B29L31/30 , B29C65/08 , B29C65/36 , B29C65/50 , B29C65/56 , B29L23/00 , B29C65/00 , B29K79/00 , B29C53/38 , B29C53/84 , B29K101/12 , B29L9/00 , B29C65/48
CPC classification number: B29C53/04 , B29C53/385 , B29C53/42 , B29C53/84 , B29C65/08 , B29C65/36 , B29C65/48 , B29C65/5071 , B29C65/5085 , B29C65/56 , B29C66/1142 , B29C66/1222 , B29C66/1224 , B29C66/1226 , B29C66/4322 , B29C66/49 , B29C66/53243 , B29C66/547 , B29C66/71 , B29C66/721 , B29C66/723 , B29C66/72523 , B29C66/72525 , B29C66/727 , B29C66/73921 , B29C66/81455 , B29C2791/006 , B29K2079/085 , B29K2101/12 , B29L2009/00 , B29L2023/22 , B29L2031/3076 , Y10T156/1038
Abstract: A method of forming a structural tube may include urging a substantially flat thermoplastic sandwich sheet against a mandrel and heating the thermoplastic sandwich sheet to a temperature below a glass transition temperature. The method may further include allowing the thermoplastic sandwich sheet to cool and removing the mandrel, thereby forming a tube portion.
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9.发明授权公开(公告)号：US09174393B2
公开(公告)日：2015-11-03
申请号：US13650139
申请日：2012-10-12
Applicant: The Boeing Company
Inventor： Aaron W. Bartel , Brett I. Lyons , Jeffery L. Marcoe
CPC classification number: B29C70/205 , B29C33/52 , B29C70/462 , B29C2035/0811 , F16L9/128
Abstract: A method of fabricating a thermoplastic composite tubular structure provides a mandrel of a soluble, expandable material. The method overbraids the mandrel with a continuous fiber thermoplastic composite material to form an overbraided mandrel. The method installs the overbraided mandrel into a matched tooling assembly. The method heats in a heating apparatus the matched tooling assembly with the installed overbraided mandrel at a specified heating profile in order to consolidate the thermoplastic composite material and form a thermoplastic composite tubular structure. The method cools the matched tooling assembly with the formed thermoplastic composite tubular structure at a specified cooling profile. The method removes the formed thermoplastic composite tubular structure from the matched tooling assembly. The method solubilizes the mandrel to permanently remove the mandrel from the formed thermoplastic composite tubular structure.
Abstract translation: 一种制造热塑性复合管状结构的方法提供了可溶的可膨胀材料的心轴。 该方法用连续的纤维热塑性复合材料超过心轴以形成一个超支撑的心轴。 该方法将过量的心轴安装到匹配的工具组件中。 该方法在加热装置中加热匹配的加工组件，其中安装的包覆心轴处于规定的加热轮廓，以便固化热塑性复合材料并形成热塑性复合管状结构。 该方法以所规定的冷却曲线冷却具有成形的热塑性复合管状结构的匹配的加工组件。 该方法从匹配的模具组件移除形成的热塑性复合管状结构。 该方法使心轴溶解以从形成的热塑性复合管状结构永久地移除心轴。
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公开(公告)号：US20150217508A1
公开(公告)日：2015-08-06
申请号：US14171779
申请日：2014-02-04
Applicant: The Boeing Company
Inventor： Angelo Rossi , Waeil M. Ashmawi , Sahrudine Apdalhaliem , Jeffery L. Marcoe , Marc R. Matsen , Aaron W. Bartel , Adriana Willempje Blom , David Reusch
CPC classification number: B29C65/72 , B29B11/16 , B29C33/448 , B29C65/62 , B29C70/24 , B29C70/504 , B29D99/0003 , B29D99/0007 , B29D99/0014 , D04C1/06 , Y02T50/43
Abstract: A method of manufacturing a radius filler may include providing a plurality of fibers, braiding the plurality of fibers into a braided preform, shaping the braided preform into a braided radius filler, and cutting the braided radius filler to a desired length.
Abstract translation: 制造半径填料的方法可以包括提供多根纤维，将多根纤维编织到编织预成型件中，将编织的预制件成形为编织半径填料，并将编织的半径填料切割成所需的长度。
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