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公开(公告)号：US20170120512A1
公开(公告)日：2017-05-04
申请号：US15407216
申请日：2017-01-16
申请人： The Boeing Company
IPC分类号： B29C65/00 , B32B37/00 , B29C65/48 , B29C65/50 , B32B37/06 , B29C65/14 , B29C73/10 , B29C73/12 , B29C73/34 , B32B41/00 , B29C35/08
CPC分类号： B29C66/9141 , B29C35/08 , B29C35/0805 , B29C65/1425 , B29C65/1467 , B29C65/1496 , B29C65/4835 , B29C65/5021 , B29C65/5028 , B29C65/5057 , B29C65/5078 , B29C66/0342 , B29C66/12463 , B29C66/5326 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/72323 , B29C66/73941 , B29C66/843 , B29C66/8742 , B29C66/91216 , B29C66/91221 , B29C66/91411 , B29C66/91443 , B29C66/9161 , B29C66/919 , B29C66/91951 , B29C66/949 , B29C66/961 , B29C66/9672 , B29C66/9674 , B29C73/10 , B29C73/12 , B29C73/34 , B29C2035/0855 , B29K2063/00 , B29K2101/10 , B29K2105/0097 , B29L2031/30 , B29L2031/3076 , B29L2031/3082 , B29L2031/3085 , B29L2031/3091 , B29L2031/5254 , B29L2031/7692 , B32B37/0046 , B32B37/06 , B32B37/18 , B32B38/0008 , B32B41/00 , B32B43/00 , Y10T156/10 , B29K2307/04
摘要： A method of bonding materials may comprise defining a bond interface between two materials in a cure zone on a surface of an object, and non-conductively heating the bond interface without directly heating the surface outside of the cure zone. Non-conductively heating the bond interface may involve applying microwave radiation to the bond interface.
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公开(公告)号：US20160023406A1
公开(公告)日：2016-01-28
申请号：US14340914
申请日：2014-07-25
申请人： THE BOEING COMPANY
发明人： Moushumi Shome , Sahrudine Apdalhaliem , Frederick T. Calkins , Waeil M. Ashmawi , Kimberly Meredith
CPC分类号： B32B37/1036 , B29C33/38 , B29C33/485 , B29C70/446 , B29C70/54 , B29K2905/00 , B29L2031/3076 , B32B37/0046 , B32B37/18 , B32B2605/18 , Y02T50/43
摘要： In one or more aspects of the present disclosure, a mandrel is disclosed. The mandrel having a shape memory alloy (SMA) shell having a longitudinal axis, an interior extending along the longitudinal axis and an exterior contour, the SMA shell being configured to interface with a structure to be cured, and at least one SMA actuation member disposed within the interior and connected to the SMA shell, where the at least one SMA actuation member is configured to exert pressure against the SMA shell effecting an interface pressure between the exterior contour of the SMA shell and the structure to be cured where the exterior contour has a predetermined actuated shape that corresponds to a predetermined cured shape of the structure to be cured.
摘要翻译： 在本公开的一个或多个方面，公开了一种心轴。 心轴具有具有纵向轴线的形状记忆合金（SMA）壳体，沿着纵向轴线延伸的内部和外部轮廓，SMA壳体被配置为与要固化的结构相接触，并且至少一个SMA致动构件设置在 在内部并且连接到SMA壳体，其中至少一个SMA致动构件构造成对SMA壳施加压力，从而影响SMA外壳的外部轮廓与外部轮廓具有的待固化结构之间的界面压力 对应于要固化的结构的预定固化形状的预定的致动形状。
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23.发明申请THERMOPLASTIC COMPOSITE STRUCTURES EMBEDDED WITH AT LEAST ONE LOAD FITTING AND METHODS OF MANUFACTURING SAME 有权具有至少一个负载配件的热塑复合结构及其制造方法公开(公告)号：US20150321441A1
公开(公告)日：2015-11-12
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.
摘要翻译： 制造嵌入有第一负载配件的热塑性复合管状结构，其包括在可溶性可扩张心轴周围编织第一组多个热塑性复合材料内层的步骤。 第一负载配件位于热塑性复合材料的第一多个内层上。 围绕第一负载配件和心轴编织第二多个热塑性复合材料外层，以便形成嵌入第一负载配件的外包芯。 将所覆盖的心轴安装到匹配的模具组件中并以特定的加热轮廓加热，以便将第一多个热塑性复合材料的内层和第二多个热塑性复合材料的外层与第一负载配件固结，以便 形成嵌入第一负载配件的热塑性复合管状结构。 第二负载配件可以被定位在热塑性复合材料的第一多个内层上。
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公开(公告)号：US09145198B1
公开(公告)日：2015-09-29
申请号：US13734421
申请日：2013-01-04
申请人： The Boeing Company
CPC分类号： B64C3/48 , B64C3/14 , B64C2003/142 , Y02T50/14
摘要： A system for varying a camber of an airfoil may include an airfoil having an upper surface and a lower surface meeting to form a leading edge and a trailing edge, the lower surface having a first actuator including shape memory alloy sheet, a controller including a plurality of heating elements attached to the shape memory alloy sheet for selectively heating the sheet to a temperature above ambient to deform the upper and lower surfaces to morph a geometry of a camber of the airfoil thereby, a computer control connected to selectively control individual activation of the heating elements to heat the shape memory alloy sheet to a selected temperature to effect a selected deflection, and a cooling device to allow ambient air to enter the wing and exit over the actuator to resume a non-morphed state.
摘要翻译： 用于改变翼型的弯度的系统可以包括具有上表面和下表面的翼面，以形成前缘和后缘，所述下表面具有包括形状记忆合金薄片的第一致动器，包括多个 附接到形状记忆合金薄片的加热元件，用于选择性地将薄片加热到高于环境温度的温度，以使上表面和下表面变形，从而变形翼型件的曲面的几何形状，计算机控制器连接以选择性地控制 加热元件以将形状记忆合金薄片加热到所选择的温度以实现所选择的偏转;以及冷却装置，以允许环境空气进入机翼并离开致动器以恢复非变形状态。
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公开(公告)号：US09981421B2
公开(公告)日：2018-05-29
申请号：US14332412
申请日：2014-07-16
申请人： The Boeing Company
IPC分类号： H01B17/20 , H01B17/38 , H01B7/08 , B29C61/06 , B64C3/48 , B64C3/52 , B29C70/30 , B32B15/08 , F03G7/06 , H05K1/05 , H05K1/16 , B29C70/88 , B29B11/16 , B64C3/44 , B64C27/72 , B64C3/54 , B29K71/00 , B29K267/00 , B29L31/30 , B29C53/82
CPC分类号： B29C61/0625 , B29B11/16 , B29C53/822 , B29C70/30 , 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.
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公开(公告)号：US20180094622A1
公开(公告)日：2018-04-05
申请号：US13855721
申请日：2013-04-03
申请人： The Boeing Company
发明人： Richard D. Widdle, JR. , Matthew T. Grimshaw , Kava S. CROSSON-ELTURAN , James H. Mabe , Frederick T. Calkins , Lynn M. Gravatt , Moushumi Shome
IPC分类号： F03G7/06
CPC分类号： F02K1/10 , B64C2027/7288 , F02K1/386 , F03G7/065 , F05D2250/184 , F05D2300/505 , Y02T50/34 , Y02T50/672
摘要： A shape memory alloy (SMA) actuated aerostructure operable to dynamically change shape according to flight conditions is disclosed. Deformable structures are actuated by SMA actuators that are coupled to face sheets of the deformable structures. Actuating the SMA actuators produces complex shape changes of the deformable structures by activating shape changes of the SMA actuators. The SMA actuators are actuated via an active or passive temperature change based on operating conditions. The SMA actuated aerostructure can be used for morphable nozzles such as a variable area fan nozzle and/or a variable geometry chevron of a jet engine to reduce engine noise during takeoff without degrading fuel burn during cruise.
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公开(公告)号：US09908634B2
公开(公告)日：2018-03-06
申请号：US15138377
申请日：2016-04-26
申请人： The Boeing Company
发明人： Moushumi Shome
CPC分类号： B64D37/005 , B32B1/00 , B64F5/0009 , B64F5/10 , F16L9/006 , F16L9/12 , F16L9/128 , F16L9/14
摘要： A fluid line adapted to contain a pressurized fluid imposing loads on the line that vary along its length comprises a tube formed of a fiber reinforced plastic, wherein the fibers are locally tailored along the length of the tube to meet local load requirements. The tube is consolidated within a volumetric chamber having separate, individually controlled chamber compartments for respectively consolidating different segments of the tube.
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公开(公告)号：US09744719B2
公开(公告)日：2017-08-29
申请号：US15407216
申请日：2017-01-16
申请人： The Boeing Company
IPC分类号： B29C65/48 , B29C65/00 , B32B41/00 , B32B37/00 , B29C65/50 , B29C35/08 , B29C65/14 , B29C73/10 , B29C73/12 , B29C73/34 , B32B37/06 , B29K101/10 , B29K63/00 , B29K105/00 , B29L31/30
CPC分类号： B29C66/9141 , B29C35/08 , B29C35/0805 , B29C65/1425 , B29C65/1467 , B29C65/1496 , B29C65/4835 , B29C65/5021 , B29C65/5028 , B29C65/5057 , B29C65/5078 , B29C66/0342 , B29C66/12463 , B29C66/5326 , B29C66/71 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/72323 , B29C66/73941 , B29C66/843 , B29C66/8742 , B29C66/91216 , B29C66/91221 , B29C66/91411 , B29C66/91443 , B29C66/9161 , B29C66/919 , B29C66/91951 , B29C66/949 , B29C66/961 , B29C66/9672 , B29C66/9674 , B29C73/10 , B29C73/12 , B29C73/34 , B29C2035/0855 , B29K2063/00 , B29K2101/10 , B29K2105/0097 , B29L2031/30 , B29L2031/3076 , B29L2031/3082 , B29L2031/3085 , B29L2031/3091 , B29L2031/5254 , B29L2031/7692 , B32B37/0046 , B32B37/06 , B32B37/18 , B32B38/0008 , B32B41/00 , B32B43/00 , Y10T156/10 , B29K2307/04
摘要： A method of bonding materials may comprise defining a bond interface between two materials in a cure zone on a surface of an object, and non-conductively heating the bond interface without directly heating the surface outside of the cure zone. Non-conductively heating the bond interface may involve applying microwave radiation to the bond interface.
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29.发明授权公开(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：US20170211552A1
公开(公告)日：2017-07-27
申请号：US15006187
申请日：2016-01-26
申请人： The Boeing Company
发明人： Moushumi Shome
摘要： An actuator includes a shape-memory alloy (SMA), a power supply that transmits electrical current, a heat source positioned proximate to the SMA, a heat sink positioned proximate to the SMA, and a control module. The control module causes the power supply to transmit the electrical current to the heat source in response to receiving a first signal, thereby causing the heat source to heat the SMA via induction heating. The control module also causes the power supply to cease transmitting the electrical current to the heat source in response to receiving a second signal, thereby causing the heat source to stop heating the SMA. The control module also causes the power supply to transmit the electrical current to the heat sink in response to receiving the second signal, thereby causing the heat sink to cool the SMA via magneto-thermal convection cooling.
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