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11.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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公开(公告)号：US08973871B2
公开(公告)日：2015-03-10
申请号：US13751086
申请日：2013-01-26
Applicant: The Boeing Company
Inventor： Jeffery L. Marcoe , Paul S. Nordman , Stephen T. Brown , William G. Roeseler , Terry K. Isomura , Willard N. Westre
CPC classification number: B64C3/185 , B29C70/30 , B29D99/0014 , B32B3/12 , B32B5/022 , B32B5/024 , B32B5/12 , B32B5/18 , B32B2260/023 , B32B2260/046 , B32B2262/0261 , B32B2262/0269 , B32B2262/101 , B32B2262/106 , B32B2266/08 , B32B2307/54 , B32B2307/542 , B32B2307/718 , B32B2605/18 , B64C3/20 , Y02T50/43
Abstract: There is provided a box structure for carrying load having upper and lower composite integrated sandwich panels. The panels have facesheets sandwiching one or more core portions and adjacent dense packs oriented in an axial direction. The box structure further has a plurality of spars. Each spar has a web and web attachments and has a spar length in the axial direction. The plurality of spars are connected to the panels with the web attachments located at the dense packs. The facesheets are configured to carry primarily torsion and pressure loads in shear and no significant axial loads. The dense packs are configured to carry all significant box bending in axial tension and compression loads.
Abstract translation: 提供了一种用于承载具有上部和下部复合一体夹芯板的箱结构。 这些面板具有夹着一个或多个芯部分和沿轴向方向定向的相邻致密包装的面板。 盒结构还具有多个翼梁。 每个翼梁具有腹板和腹板附件，并且在轴向具有翼梁长度。 多个翼梁连接到面板，网片附件位于密集的包装上。 这些面板被配置为主要承受剪切中的扭转和压力载荷，并且没有显着的轴向载荷。 致密包装被配置为承受所有重要的箱体在轴向张力和压缩载荷下弯曲。
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公开(公告)号：US11110647B2
公开(公告)日：2021-09-07
申请号：US15963890
申请日：2018-04-26
Applicant: The Boeing Company
Inventor： Jeffery L. Marcoe , Sahrudine Apdalhaliem , Moushumi Shome
IPC: B29C61/06 , B64C3/48 , B64C3/52 , B29C70/88 , B29B11/16 , B29C70/32 , B29C70/22 , B29C70/30 , B32B15/08 , F03G7/06 , H05K1/05 , H05K1/16 , B64C3/44 , B64C27/72 , B64C3/54 , B29C53/82 , B29K71/00 , B29K267/00 , B29L31/30
Abstract: Systems and processes that integrate thermoplastic and shape memory alloy materials to form an adaptive composite structure capable of changing its shape. For example, the adaptive composite structure may be designed to serve as a multifunctional adaptive wing flight control surface. Other applications for such adaptive composite structures include in variable area fan nozzles, winglets, fairings, elevators, rudders, or other aircraft components having an aerodynamic surface whose shape is preferably controllable. The material systems can be integrated by means of overbraiding (interwoven) with tows of both thermoplastic and shape memory alloy materials or separate layers of each material can be consolidated (e.g., using induction heating) to make a flight control surface that does not require separate actuation.
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公开(公告)号：US10744722B2
公开(公告)日：2020-08-18
申请号：US15797314
申请日：2017-10-30
Applicant: The Boeing Company
Inventor： Angelo Rossi , Jeffery L. Marcoe , Marc R. Matsen , Aaron W. Bartel , Waeil M. Ashmawi , Sahrudine Apdalhaliem , Adriana Willempje Blom-Schieber , David Reusch
Abstract: A radius filler includes a plurality of fibers encapsulated in resin and braided into a braided radius filler. The braided radius filler has a substantially triangular shape with concave radius filler side surfaces and a substantially planar radius filler base surface.
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Patent Agency Ranking
公开(公告)号：US20180065314A1
公开(公告)日：2018-03-08
申请号：US15797314
申请日：2017-10-30
Applicant: The Boeing Company
Inventor： Angelo Rossi , Jeffery L. Marcoe , Marc R. Matsen , Aaron W. Bartel , Waeil M. Ashmawi , Sahrudine Apdalhaliem , Adriana Willempje Blom-Schieber , David Reusch
Abstract: A radius filler includes a plurality of fibers encapsulated in resin and braided into a braided radius filler. The braided radius filler has a substantially triangular shape with concave radius filler side surfaces and a substantially planar radius filler base surface.
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公开(公告)号：US20170292547A1
公开(公告)日：2017-10-12
申请号：US15630745
申请日：2017-06-22
Applicant: The Boeing Company
Inventor： Waeil M. Ashmawi , Jaime C. Garcia , Sahrudine Apdalhaliem , Jeffery L. Marcoe , Moushumi Shome
IPC: F16B1/00
CPC classification number: F16B1/0014
Abstract: Provided are assemblies having composite structures interlocked with shape memory alloy structures and methods of fabricating such assemblies. Interlocking may involve inserting an interlocking protrusion of a shape memory alloy structure into an interlocking opening of a composite structure and heating at least this protrusion of the shape memory alloy structure to activate the alloy and change the shape of the protrusion. This shape change engages the protrusion in the opening such that the protrusion cannot be removed from the opening. The shape memory alloy structure may be specifically trained prior to forming an assembly using a combination of thermal cycling and deformation to achieve specific pre-activation and post-activation shapes. The pre-activation shape allows inserting the interlocking protrusion into the opening, while the post-activation shape engages the interlocking protrusion within the opening. As such, activation of the shape memory alloy interlocks the two structures.
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公开(公告)号：US09719536B2
公开(公告)日：2017-08-01
申请号：US14323529
申请日：2014-07-03
Applicant: The Boeing Company
Inventor： Waeil M. Ashmawi , Jaime C. Garcia , Sahrudine Apdalhaliem , Jeffery L. Marcoe , Moushumi Shome
IPC: F16B1/00
CPC classification number: F16B1/0014
Abstract: Provided are assemblies having composite structures interlocked with shape memory alloy structures and methods of fabricating such assemblies. Interlocking may involve inserting an interlocking protrusion of a shape memory alloy structure into an interlocking opening of a composite structure and heating at least this protrusion of the shape memory alloy structure to activate the alloy and change the shape of the protrusion. This shape change engages the protrusion in the opening such that the protrusion cannot be removed from the opening. The shape memory alloy structure may be specifically trained prior to forming an assembly using a combination of thermal cycling and deformation to achieve specific pre-activation and post-activation shapes. The pre-activation shape allows inserting the interlocking protrusion into the opening, while the post-activation shape engages the interlocking protrusion within the opening. As such, activation of the shape memory alloy interlocks the two structures.
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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：US09981444B2
公开(公告)日：2018-05-29
申请号：US13928760
申请日：2013-06-27
Applicant: The Boeing Company
Inventor： Lyle R. Deobald , John D. Morris , Karl B. Lee , Jeffery L. Marcoe , Mark C. Iden , Christopher G. Harris
CPC classification number: B32B3/08 , B29C70/865 , B29D99/0003 , B32B3/04 , B64C1/064 , B64C1/065 , B64C3/182 , B64C3/185 , B64C2001/0072 , Y02T50/43 , Y10T428/197 , Y10T428/24174 , Y10T428/24182
Abstract: A composite stiffener is fabricated using preforms of laminated, unidirectional composite tape. The stiffener includes a void that is reinforced by a filler wrapped with a structural adhesive. The surfaces of the preforms surrounding the void include a layer of composite fabric which is bonded to the filler by the adhesive, thereby increasing the toughness of stiffeners around the void and improving pull-off strength of the stiffener.
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