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公开(公告)号：US10265923B2
公开(公告)日：2019-04-23
申请号：US15465029
申请日：2017-03-21
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
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：US10202939B2
公开(公告)日：2019-02-12
申请号：US13855721
申请日：2013-04-03
申请人： The Boeing Company
发明人： Richard D. Widdle , Matthew T. Grimshaw , Kava S. Crosson-Eltruan , James Henry Mabe , Frederick T. Calkins , Lynn Marie Gravatt , Moushumi Shome
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：US20150328877A1
公开(公告)日：2015-11-19
申请号：US14276918
申请日：2014-05-13
申请人： The Boeing Company
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.
摘要翻译： 接合材料的方法可以包括在物体表面上的固化区中限定两种材料之间的键合界面，并且非导电地加热接合界面而不直接加热固化区外部的表面。 非导电加热接合界面可能涉及向接合界面施加微波辐射。
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4.发明申请SMART SUSCEPTOR FOR A SHAPE MEMORY ALLOY (SMA) ACTUATOR INDUCTIVE HEATING SYSTEM 有权形状记忆合金（SMA）执行器感应加热系统的智能断路器公开(公告)号：US20150096293A1
公开(公告)日：2015-04-09
申请号：US14045121
申请日：2013-10-03
申请人： The Boeing Company
发明人： Moushumi Shome , Frederick T. Calkins , Stephen R. Amorosi , Flint M. Jamison , Sahrudine Apdalhaliem , Robert James Miller
CPC分类号： F03G7/065 , H01F41/02 , Y10T29/4902
摘要： A system for heating a shape memory alloy (SMA) actuator may include an SMA actuator, a smart susceptor, a plurality of induction coils, and a control module. The SMA actuator may have at least one layup. The SMA actuator may be selectively heated to a transition temperature. The smart susceptor may be in thermal contact with the at least one layup of the SMA actuator. The induction heating coils may be configured to receive an alternating current and generate a magnetic field based on the alternating current. The magnetic field may create an eddy current in at least one of the SMA actuator and the smart susceptor to heat the SMA actuator to the transition temperature. The control module may be configured to drive the alternating current supplied to the induction heating coils.
摘要翻译： 用于加热形状记忆合金（SMA）致动器的系统可以包括SMA致动器，智能基座，多个感应线圈和控制模块。 SMA致动器可以具有至少一个叠层。 可以将SMA致动器选择性地加热到转变温度。 智能基座可以与SMA致动器的至少一个叠层热接触。 感应加热线圈可以被配置为接收交流电流并且基于交流电产生磁场。 磁场可以在SMA致动器和智能基座中的至少一个中产生涡流，以将SMA致动器加热到转变温度。 控制模块可以被配置为驱动提供给感应加热线圈的交流电。
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公开(公告)号：US09919505B2
公开(公告)日：2018-03-20
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
IPC分类号： B29C70/34 , B29C70/54 , B32B37/00 , B32B37/10 , B32B37/18 , B29C33/38 , B29C33/48 , B29C70/44 , B29L31/30
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.
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6.发明申请公开(公告)号：US20170190137A1
公开(公告)日：2017-07-06
申请号：US15465029
申请日：2017-03-21
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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7.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
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。
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公开(公告)号：US20150240793A1
公开(公告)日：2015-08-27
申请号：US14186915
申请日：2014-02-21
申请人： THE BOEING COMPANY
发明人： Morteza Safai , Kimberly D. Meredith , Sahrudine Apdalhaliem , Moushumi Shome , Frederick T. Calkins
IPC分类号： F03G7/06
CPC分类号： F03G7/065
摘要： Described herein is an apparatus for controlling an actuator made from a shape-memory alloy includes a first layer made from a thermally conductive material and a second layer. The second layer is made from a thermally conductive material. The apparatus also includes at least one thermoelectric heater positioned between the first and second layers. Additionally, the apparatus includes at least one thermoelectric cooler positioned between the first and second layers.
摘要翻译： 这里描述了一种用于控制由形状记忆合金制成的致动器的装置，包括由导热材料制成的第一层和第二层。 第二层由导热材料制成。 该装置还包括位于第一和第二层之间的至少一个热电加热器。 另外，该设备包括位于第一和第二层之间的至少一个热电冷却器。
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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
申请人： The Boeing Company
IPC分类号： 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
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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10.发明授权公开(公告)号：US10300634B2
公开(公告)日：2019-05-28
申请号：US14941998
申请日：2015-11-16
申请人： The Boeing Company
发明人： Moushumi Shome , Aloke K. Pal
IPC分类号： B29C35/02 , F26B23/06 , F26B3/18 , F26B3/30 , B29C70/54 , B29C70/34 , B29C73/34 , B29K105/08 , B29K307/04
摘要： A composite structure curing system employs a plurality of heaters mounted in at least one array in spaced proximity to a composite structure to be cured. A plurality of temperature sensors are mounted to sense temperature at selected locations on the structure. A control system receives an input from each of the plurality of temperature sensors and is adapted to control each of the plurality of heaters responsive to each input to establish a predetermined temperature profile on the structure during cure.
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