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1. 发明申请

US20160003280A1 ASSEMBLIES INCLUDING SHAPE MEMORY ALLOY FITTINGS AND COMPOSITE STRUCTURAL MEMBERS 有权
标题翻译：包括形状记忆合金配件和复合结构件的组装
公开(公告)号：US20160003280A1
公开(公告)日：2016-01-07
申请号：US14323529
申请日：2014-07-03
申请人： The Boeing Company
发明人： Waeil M. Ashmawi , Jaime C. Garcia , Sahrudine Apdalhaliem , Jeffery L. Marcoe , Moushumi Shome
IPC分类号： F16B17/00
CPC分类号： F16B1/0014
摘要： 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.
摘要翻译：提供了具有与形状记忆合金结构互锁的复合结构的组件和制造这种组件的方法。联锁可以包括将形状记忆合金结构的互锁突起插入到复合结构的互锁开口中，并且加热形状记忆合金结构的至少该突起以激活合金并改变突起的形状。这种形状变化与开口中的突起接合，使得突起不能从开口移除。在使用热循环和变形的组合形成组件以实现特定的预激活和后激活形状之后，形状记忆合金结构可以被特别地训练。预激活形状允许将互锁突起插入开口中，而后激活形状与开口内的互锁突起接合。因此，形状记忆合金的激活将两个结构互锁。

2. 发明申请

US20140360654A1 Stabilizer Torque Box Assembly and Method 有权
标题翻译：稳定器扭矩箱装配和方法
公开(公告)号：US20140360654A1
公开(公告)日：2014-12-11
申请号：US14469575
申请日：2014-08-26
申请人： The Boeing Company
发明人： Jeffery L. Marcoe
IPC分类号： B32B37/02 , B32B38/00
CPC分类号： B29C70/30 , B32B1/08 , B32B5/02 , B32B15/08 , B32B27/12 , B32B37/02 , B32B38/004 , B32B2262/10 , B32B2307/202 , B32B2307/544 , B32B2307/558 , B32B2311/18 , B32B2311/24 , B32B2311/30 , B32B2313/04 , B32B2605/00 , B32B2605/18 , B64C3/00 , B64C3/18 , Y02T50/43 , Y10T29/49826
摘要： In an embodiment of the disclosure, there is provided a method of fabricating a thermoplastic torque box assembly. The method includes providing a plurality of braided thermoplastic tubular spar caps, connecting one or more connector elements to one or more of the braided thermoplastic tubular spar caps, and laying up an inner thermoplastic facesheet in a continuous manner around the one or more braided thermoplastic tubular spar caps. The method further includes attaching a plurality of skin panel stabilization elements to the inner thermoplastic facesheet to define four torque box side portions, laying up and attaching an outer thermoplastic facesheet in a continuous manner around the plurality of skin panel stabilization elements, and heating at an effective temperature and an effective pressure the thermoplastic torque box assembly.
摘要翻译：在本公开的一个实施例中，提供了一种制造热塑性扭矩箱组件的方法。该方法包括提供多个编织的热塑性管状翼梁帽，将一个或多个连接器元件连接到一个或多个编织热塑性管状翼梁帽，以及连续地围绕一个或多个编织热塑管翼梁帽该方法还包括将多个皮肤稳定元件附接到内部热塑性面板以限定四个扭矩箱侧部分，以连续的方式围绕多个皮肤面板稳定元件放置和附接外部热塑性面板，并且在有效温度和有效压力的热塑性扭矩箱组件。

3. 发明申请

US20140102578A1 Thermoplastic Composite Tubular Structures and Methods of Fabricating the Same 有权
标题翻译：热塑性复合管状结构及其制造方法
公开(公告)号：US20140102578A1
公开(公告)日：2014-04-17
申请号：US13650139
申请日：2012-10-12
申请人： The Boeing Company
发明人： Aaron W. Bartel , Brett I. Lyons , Jeffery L. Marcoe
IPC分类号： B29C70/30 , F16L11/04
CPC分类号： B29C70/205 , B29C33/52 , B29C70/462 , B29C2035/0811 , F16L9/128
摘要： 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.
摘要翻译：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。

4. 发明授权

US10774858B2 Assemblies including shape memory alloy fittings and composite structural members 有权
公开(公告)号：US10774858B2
公开(公告)日：2020-09-15
申请号：US15630745
申请日：2017-06-22
申请人： The Boeing Company
发明人： Waeil M. Ashmawi , Jaime C. Garcia , Sahrudine Apdalhaliem , Jeffery L. Marcoe , Moushumi Shome
IPC分类号： F16B1/00
摘要： 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.

5. 发明申请

US20180290402A1 High Rate Production Fiber Placement System and Method 审中-公开
公开(公告)号：US20180290402A1
公开(公告)日：2018-10-11
申请号：US16008660
申请日：2018-06-14
申请人： The Boeing Company
发明人： Marc R. Matsen , Mark A. Negley , Jeffery L. Marcoe , Stephen G. Moore , Brice A. Johnson , Alexandra K. Dillon , Megan M. Petersen
IPC分类号： B29C70/38 , B29C65/16 , B29C65/00 , B29C65/32
CPC分类号： B29C70/382 , B29C65/02 , B29C65/08 , B29C65/1416 , B29C65/1419 , B29C65/1432 , B29C65/16 , B29C65/1616 , B29C65/1619 , B29C65/1622 , B29C65/1632 , B29C65/18 , B29C65/22 , B29C65/30 , B29C65/32 , B29C66/1122 , B29C66/45 , B29C66/723 , B29C66/7392 , B29C66/8322 , B29C66/8362 , B29C66/87 , B29C70/38 , B29K2101/12
摘要： A fiber placement system including a fiber placement station at a first location, the fiber placement station including a tool and a fiber placement assembly configured to construct a reinforcement layup on the tool, the first fiber placement assembly including a compaction roller rotatable about an axis of rotation, the compaction roller at least partially defining a nip, a thermoplastic composite ply extending through the nip and a heating unit positioned to heat the thermoplastic composite ply proximate the nip, and a consolidation station at a consolidation location, the consolidation location being different from the first location, the consolidation station including a consolidation tool and a consolidation system configured to consolidate a reinforcement layup assembly that includes the reinforcement layup.

6. 发明申请

US20180243972A1 Adaptive Composite Structure Using Shape Memory Alloys 审中-公开
公开(公告)号：US20180243972A1
公开(公告)日：2018-08-30
申请号：US15963890
申请日：2018-04-26
申请人： The Boeing Company
发明人： Jeffery L. Marcoe , Sahrudine Apdalhaliem , Moushumi Shome
IPC分类号： B29C61/06 , B64C3/48 , B29C70/30 , B29C70/88 , B64C3/52 , F03G7/06 , H05K1/16 , B32B15/08 , B29B11/16 , H05K1/05 , B29K267/00 , B29K71/00 , B29C53/82 , B29L31/30 , B64C3/44 , B64C3/54 , B64C27/72
CPC分类号： B29C61/0625 , B29B11/16 , B29C53/822 , B29C70/222 , B29C70/30 , B29C70/32 , B29C70/88 , B29K2071/00 , B29K2267/00 , B29L2031/3085 , B32B15/08 , B32B2250/02 , B32B2605/18 , B64C3/48 , B64C3/52 , B64C2003/445 , B64C2003/543 , B64C2027/7288 , F03G7/065 , H05K1/056 , H05K1/165 , H05K2201/0129 , H05K2201/0308 , Y02T50/34 , Y02T50/43
摘要： 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.

7. 发明授权

US10016947B2 High rate production fiber placement system and method 有权
公开(公告)号：US10016947B2
公开(公告)日：2018-07-10
申请号：US14718893
申请日：2015-05-21
申请人： The Boeing Company
发明人： Marc R. Matsen , Mark A. Negley , Jeffery L. Marcoe , Stephen G. Moore , Brice A. Johnson , Alexandra K. Dillon , Megan M. Petersen
IPC分类号： B29C70/38 , B29C65/16 , B29C65/00 , B29C65/32 , B29K101/12
CPC分类号： B29C70/382 , B29C65/02 , B29C65/08 , B29C65/1416 , B29C65/1419 , B29C65/1432 , B29C65/16 , B29C65/1616 , B29C65/1619 , B29C65/1622 , B29C65/1632 , B29C65/18 , B29C65/22 , B29C65/30 , B29C65/32 , B29C66/1122 , B29C66/45 , B29C66/723 , B29C66/7392 , B29C66/8322 , B29C66/8362 , B29C66/87 , B29C70/38 , B29K2101/12
摘要： A fiber placement system including a fiber placement station at a first location, the fiber placement station including a tool and a fiber placement assembly configured to construct a reinforcement layup on the tool, the first fiber placement assembly including a compaction roller rotatable about an axis of rotation, the compaction roller at least partially defining a nip, a thermoplastic composite ply extending through the nip and a heating unit positioned to heat the thermoplastic composite ply proximate the nip, and a consolidation station at a consolidation location, the consolidation location being different from the first location, the consolidation station including a consolidation tool and a consolidation system configured to consolidate a reinforcement layup assembly that includes the reinforcement layup.

8. 发明授权

US09827710B2 Radius filler and method of manufacturing same 有权
公开(公告)号：US09827710B2
公开(公告)日：2017-11-28
申请号：US14171779
申请日：2014-02-04
申请人： The Boeing Company
发明人： Angelo Rossi , Jeffery L. Marcoe , Marc R. Matsen , Aaron W. Bartel
IPC分类号： B29C33/52 , B29C70/40 , B29C65/72 , B29C33/44 , B29C65/62 , B29D99/00 , D04C1/06 , B29C70/50 , B29C70/24 , B32B27/00 , B29B11/16
CPC分类号： B29C65/72 , B29B11/16 , B29C33/448 , B29C65/62 , B29C70/24 , B29C70/504 , B29D99/0003 , B29D99/0007 , B29D99/0014 , D04C1/06 , Y02T50/43
摘要： 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.

9. 发明授权

US10828847B2 High rate production fiber placement system and method 有权
公开(公告)号：US10828847B2
公开(公告)日：2020-11-10
申请号：US16008660
申请日：2018-06-14
申请人： The Boeing Company
发明人： Marc R. Matsen , Mark A. Negley , Jeffery L. Marcoe , Stephen G. Moore , Brice A. Johnson , Alexandra K. Dillon , Megan M. Petersen
IPC分类号： B29C70/38 , B29C65/00 , B29C65/32 , B29C65/16 , B29C65/14 , B29C65/02 , B29C65/18 , B29K101/12 , B29C65/08 , B29C65/30 , B29C65/22
摘要： A fiber placement system including a fiber placement station at a first location, the fiber placement station including a tool and a fiber placement assembly configured to construct a reinforcement layup on the tool, the first fiber placement assembly including a compaction roller rotatable about an axis of rotation, the compaction roller at least partially defining a nip, a thermoplastic composite ply extending through the nip and a heating unit positioned to heat the thermoplastic composite ply proximate the nip, and a consolidation station at a consolidation location, the consolidation location being different from the first location, the consolidation station including a consolidation tool and a consolidation system configured to consolidate a reinforcement layup assembly that includes the reinforcement layup.

10. 发明申请

US20160339647A1 High Rate Production Fiber Placement System and Method 有权
标题翻译：高速生产光纤放置系统及方法
公开(公告)号：US20160339647A1
公开(公告)日：2016-11-24
申请号：US14718893
申请日：2015-05-21
申请人： The Boeing Company
发明人： Marc R. Matsen , Mark A. Negley , Jeffery L. Marcoe , Stephen G. Moore , Brice A. Johnson , Alexandra K. Dillon , Megan M. Petersen
IPC分类号： B29C70/38 , B29C65/00 , B29C65/32 , B29C65/16
CPC分类号： B29C70/382 , B29C65/02 , B29C65/08 , B29C65/1416 , B29C65/1419 , B29C65/1432 , B29C65/1616 , B29C65/1619 , B29C65/1622 , B29C65/1632 , B29C65/18 , B29C65/22 , B29C65/30 , B29C65/32 , B29C66/1122 , B29C66/45 , B29C66/723 , B29C66/7392 , B29C66/8322 , B29C66/8362 , B29C70/38 , B29K2101/12
摘要： A fiber placement system including a fiber placement station at a first location, the fiber placement station including a tool and a fiber placement assembly configured to construct a reinforcement layup on the tool, the first fiber placement assembly including a compaction roller rotatable about an axis of rotation, the compaction roller at least partially defining a nip, a thermoplastic composite ply extending through the nip and a heating unit positioned to heat the thermoplastic composite ply proximate the nip, and a consolidation station at a consolidation location, the consolidation location being different from the first location, the consolidation station including a consolidation tool and a consolidation system configured to consolidate a reinforcement layup assembly that includes the reinforcement layup.
摘要翻译：一种光纤放置系统，包括在第一位置处的光纤放置台，所述光纤放置台包括工具和配置成在所述工具上构造加强层的光纤放置组件，所述第一光纤放置组件包括压缩辊，至少部分地限定压区的压实辊，延伸穿过压区的热塑性复合层，以及定位成加热邻近压区的热塑性复合层的加热单元，以及固结位置处的固结位置，所述第一位置，所述合并工位包括固结工具和被配置为整合包括所述加固层的加强层叠组件的合并系统。

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