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公开(公告)号：US10425997B2
公开(公告)日：2019-09-24
申请号：US15012843
申请日：2016-02-01
申请人： The Boeing Company
IPC分类号： H05B6/06 , H05B6/10 , B29C73/10 , B29C73/30 , B29C73/34 , B29C35/00 , H05B6/36 , B29C35/08 , B29K63/00 , B29K105/12 , B29K105/00 , B29K307/04
摘要： A composite part is cured out-of-autoclave using an inductively heated, stand-alone tooling. The part in placed on a tool and is covered by a heating blanket. One side of the part is heated by inductive coil circuits in the tool, and the other side of the part is heated by inductive coil circuits in the blanket.
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公开(公告)号：US10018175B2
公开(公告)日：2018-07-10
申请号：US14873684
申请日：2015-10-02
申请人： The Boeing Company
CPC分类号： F03D1/0675 , B29C35/0805 , B29C64/129 , B29C70/446 , B29C2035/0811 , B29D99/0028 , B29L2031/08 , Y02E10/721 , Y02P70/523
摘要： A method of fabricating a thermoplastic composite tubular structure for use as a wind turbine blade is presented using a combination of induction heating with smart susceptors to consolidate a wrapped mandrel. The method can include overbraiding the mandrel with a continuous fiber thermoplastic composite material to form an overbraided mandrel that is then installed in a ceramic induction oven where the mandrel is pressurized internally to consolidate the thermoplastic overbraid during heating.
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公开(公告)号：US09718248B2
公开(公告)日：2017-08-01
申请号：US14465911
申请日：2014-08-22
申请人： The Boeing Company
发明人： Jeffery Lee Marcoe , Marc Rollo Matsen , Waeil M. Ashmawi , Jaime C. Garcia , Sahrudine Apdalhaliem , John B. Moser , Brett I. Lyons , Moushumi Shome , Kay Y. Blohowiak
CPC分类号： B32B1/08 , B29C33/52 , B29C70/205 , B29C70/462 , B29C2035/0811 , B32B5/024 , B32B2262/106 , B32B2605/08 , B32B2605/12 , B32B2605/18 , D04C1/06
摘要： Manufacturing a thermoplastic composite tubular structure embedded with a first load fitting comprising the steps of braiding a first plurality of inner layers of thermoplastic composite material around a soluble, expandable mandrel. A first load fitting is positioned on the first plurality of inner layers of thermoplastic composite material. A second plurality of outer layers of thermoplastic composite material is braided around the first load fitting and the mandrel so as to form an overbraided mandrel embedded with the first load fitting. The overbraided mandrel is installed into a matched tooling assembly and heated at a specified heating profile in order to consolidate the first plurality of inner layers of thermoplastic composite material and the second plurality of outer layers of thermoplastic composite material with the first load fitting so as to form a thermoplastic composite tubular structure embedded with the first load fitting. A second load fitting may be positioned on the first plurality of inner layers of thermoplastic composite material.
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公开(公告)号：US20160262216A1
公开(公告)日：2016-09-08
申请号：US14640227
申请日：2015-03-06
申请人： The Boeing Company
发明人： James M. Kestner , Robert James Miller , Marc Rollo Matsen , Cameron Kai-Ming Chen , Leah Gillian Glauber , Christopher John Hottes
CPC分类号： H05B6/105 , H05B6/40 , H05B2206/023
摘要： A susceptor wire array. The array includes a first susceptor wire comprising an alloy having a first Curie temperature point and a second susceptor wire comprising an alloy having a second Curie temperature point, the second Curie temperature point is different than the first Curie temperature point of the first susceptor wire. In one susceptor wire arrangement, the second Curie temperature point of the second susceptor wire is lower than the first Curie temperature point of the first susceptor wire. In another susceptor wire arrangement, the array further comprises a third susceptor wire, the third susceptor wire comprising an alloy having a third Curie temperature point. The third Curie temperature point of the third susceptor wire may be different than the first Curie temperature point of the first susceptor wire.
摘要翻译： 感受器线阵列。 阵列包括第一基座线，其包括具有第一居里温度点的合金和包括具有第二居里温度点的合金的第二基座线，第二居里温度点不同于第一基座线的第一居里温度点。 在一个基座线布置中，第二基座线的第二居里温度点低于第一基座线的第一居里温度点。 在另一基座线布置中，阵列还包括第三基座线，第三基座线包括具有第三居里温度点的合金。 第三基座线的第三居里温度点可以不同于第一基座线的第一居里温度点。
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公开(公告)号：US20160143092A1
公开(公告)日：2016-05-19
申请号：US14548045
申请日：2014-11-19
申请人： The Boeing Company
发明人： Robert James Miller , Marc Rollo Matsen , Cameron Kai-Ming Chen , Leah Gillian Glauber , James M. Kestner , Christopher John Hottes
CPC分类号： H05B6/105 , C22C38/08 , H05B6/06 , H05B6/14 , H05B6/40 , H05B2206/023 , Y02P10/253
摘要： A coaxially arranged smart susceptor conductor, comprising a smart susceptor core comprising an alloy having a first Curie temperature point and a first smart susceptor shell coaxially arranged around the smart susceptor core. The first smart susceptor shell comprising a second Curie temperature point that is different than the first Curie temperature point of the smart susceptor core. In one arrangement, the second Curie temperature point of the first smart susceptor shell is lower than the first Curie temperature point of the smart susceptor core. In another arrangement, the smart susceptor conductor further comprises a second smart susceptor shell disposed about the first smart susceptor shell. The second smart susceptor shell comprising a third Curie temperature point.
摘要翻译： 一种同轴布置的智能基座导体，包括智能基座芯，其包括具有第一居里温度点的合金和位于智能基座芯周围同轴布置的第一智能基座壳。 第一智能基座壳包括不同于智能感受体芯的第一居里温度点的第二居里温度点。 在一种布置中，第一智能基座壳的第二居里温度点低于智能感受体芯的第一居里温度点。 在另一种布置中，智能感受体导体还包括围绕第一智能基座壳布置的第二智能基座壳。 第二智能感受器壳包括第三居里温度点。
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公开(公告)号：US20150013888A1
公开(公告)日：2015-01-15
申请号：US13937253
申请日：2013-07-09
申请人： The Boeing Company
IPC分类号： B29C65/70
CPC分类号： B29C70/446 , B29C35/0272 , B29C35/0805 , B29C2035/0811 , B29K2101/12 , B29L2031/3076 , Y10T156/1002
摘要： A method of forming a consolidated structure. The method comprises placing a thermoplastic material onto a forming tool to form a structure; positioning the structure within a tool; and consolidating the structure to form the consolidated structure. The tool has a number of die liners configured to generate heat in response to a magnetic field. Consolidating comprises applying a magnetic field to the number of die liners to heat the structure to a consolidation temperature.
摘要翻译： 形成固结结构的方法。 该方法包括将热塑性材料放置在成形工具上以形成结构; 将结构定位在工具内; 巩固结构，形成综合结构。 该工具具有多个管芯衬套，其配置成响应于磁场产生热量。 整合包括将磁场施加到模具衬套的数量以将结构加热到固结温度。
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公开(公告)号：US20150013883A1
公开(公告)日：2015-01-15
申请号：US13937269
申请日：2013-07-09
申请人： The Boeing Company
IPC分类号： B29C70/02
CPC分类号： B29C35/0805 , B29C70/446 , B29C2035/0811 , B29D24/004 , B29D99/0014 , B29K2101/12 , B29L2031/3085 , Y02T50/43
摘要： An apparatus and method are presented. An apparatus comprises a composite structure, a plurality of cavities extending into the composite structure, and a plurality of mandrels located within the plurality of cavities. The composite structure comprises a thermoplastic material that is consolidated. The plurality of mandrels comprises a first material that is configured to generate heat in response to a magnetic field.
摘要翻译： 提出了一种装置和方法。 一种装置包括复合结构，延伸到复合结构中的多个空腔和位于多个空腔内的多个心轴。 复合结构包括被固结的热塑性材料。 多个心轴包括被配置为响应于磁场产生热量的第一材料。
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公开(公告)号：US10377084B2
公开(公告)日：2019-08-13
申请号：US15477723
申请日：2017-04-03
申请人： The Boeing Company
IPC分类号： H05B6/10 , B23K28/00 , B29C65/02 , B23K13/04 , B29C65/00 , B29C65/36 , B64C3/26 , B29L31/00 , B29L31/30
摘要： A method and apparatus for joining parts. A plurality of conformable induction coils embedded in a number of elastomeric sheets is positioned relative to a first composite part of the parts and a second composite part of the parts. A magnetic field is generated with the plurality of conformable induction coils. The magnetic field is configured to generate heat in a magnetically permeable material at a joint location. The heat joins the first composite part and the second composite part to each other.
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公开(公告)号：US10322564B2
公开(公告)日：2019-06-18
申请号：US15292089
申请日：2016-10-12
申请人： The Boeing Company
发明人： Marc Rollo Matsen , Jeffery Lee Marcoe , Max U. Kismarton , Paul Stevenson Gregg , Lee Charles Firth
IPC分类号： B32B15/08 , B29D99/00 , B29C70/44 , B29C33/06 , B29C35/02 , B29C35/08 , B32B3/12 , B29L31/30 , B29K101/12
摘要： A method and apparatus for forming a sandwich structure is presented. A sandwich structure comprises a metallic core layer and a thermoplastic layer on a first side of the metallic core layer. The thermoplastic layer is consolidated against the first side of the metallic core layer.
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公开(公告)号：US10059054B2
公开(公告)日：2018-08-28
申请号：US14753538
申请日：2015-06-29
申请人： The Boeing Company
IPC分类号： B29C65/36 , B29C65/04 , B29C65/00 , B29C70/30 , B64C1/00 , B29L31/30 , B29K101/12 , B29K105/08
CPC分类号： B29C65/04 , B29C65/3632 , B29C65/3636 , B29C65/364 , B29C65/3668 , B29C65/3676 , B29C65/3684 , B29C66/112 , B29C66/131 , B29C66/524 , B29C66/532 , B29C66/61 , B29C66/63 , B29C66/7212 , B29C66/72141 , B29C66/73921 , B29C66/81422 , B29C66/81423 , B29C66/843 , B29C66/8432 , B29C70/30 , B29C70/46 , B29K2101/12 , B29K2105/0881 , B29L2031/3076 , B29L2031/3085 , B64C1/00 , B64F5/10 , B29K2307/04
摘要： A method and apparatus for welding a thermoplastic structure. The apparatus comprises a base, a cover, and a channel. The base is formed of a material that is magnetically opaque to a frequency in a range of 30 KHz to 350 KHz. The cover is formed of the material. The channel extends between the base and the cover.
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