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    ASSEMBLIES INCLUDING SHAPE MEMORY ALLOY FITTINGS AND COMPOSITE STRUCTURAL MEMBERS
    1.
    发明申请
    ASSEMBLIES INCLUDING SHAPE MEMORY ALLOY FITTINGS AND COMPOSITE STRUCTURAL MEMBERS 有权
    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

    Applicant: The Boeing Company

    Inventor： Waeil M. Ashmawi ,  Jaime C. Garcia ,  Sahrudine Apdalhaliem ,  Jeffery L. Marcoe ,  Moushumi Shome

    IPC: F16B17/00

    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.

    Abstract translation: 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。

    Stabilizer Torque Box Assembly and Method
    2.
    发明申请
    Stabilizer Torque Box Assembly and Method 有权
    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

    Applicant: The Boeing Company

    Inventor： Jeffery L. Marcoe

    IPC: B32B37/02 ,  B32B38/00

    CPC classification number: 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

    Abstract: 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.

    Abstract translation: 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。

    Thermoplastic Composite Tubular Structures and Methods of Fabricating the Same
    3.
    发明申请
    Thermoplastic Composite Tubular Structures and Methods of Fabricating the Same 有权
    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

    Applicant: The Boeing Company

    Inventor： Aaron W. Bartel ,  Brett I. Lyons ,  Jeffery L. Marcoe

    IPC: B29C70/30 ,  F16L11/04

    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。

    Assemblies including shape memory alloy fittings and composite structural members
    4.
    发明授权
    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

    Applicant: The Boeing Company

    Inventor： Waeil M. Ashmawi ,  Jaime C. Garcia ,  Sahrudine Apdalhaliem ,  Jeffery L. Marcoe ,  Moushumi Shome

    IPC: F16B1/00

    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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