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1. 发明申请

WO2011016973A2 HIGH STIFFNESS SHAPE MEMORY ALLOY ACTUATED AEROSTRUCTURE 审中-公开
标题翻译：高刚度形状记忆合金致动航空结构
公开(公告)号：WO2011016973A2
公开(公告)日：2011-02-10
申请号：PCT/US2010/042331
申请日：2010-07-16
申请人： THE BOEING COMPANY , WIDDLE JR., Richard D. , GRIMSHAW, Matthew T. , CROSSON-ELTURAN, Kava S. , MABE, James Henry , CALKINS, Frederick T. , GRAVATT, Lynn Marie , SHOME, Moushumi
发明人： WIDDLE JR., Richard D. , GRIMSHAW, Matthew T. , CROSSON-ELTURAN, Kava S. , MABE, James Henry , CALKINS, Frederick T. , GRAVATT, Lynn Marie , SHOME, Moushumi
IPC分类号： F02K1/00 , B05B12/00
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.
摘要翻译：公开了形状记忆合金（SMA）致动的飞行结构，其可操作以根据飞行条件动态地改变形状。可变形结构由连接到可变形结构的面板的SMA致动器致动。启动SMA致动器通过激活SMA致动器的形状变化而产生可变形结构的复杂形状变化。 SMA执行器通过基于工作条件的主动或被动温度变化来启动。 SMA驱动的航空结构可用于可变形喷嘴，例如喷气发动机的可变面积风扇喷嘴和/或可变几何形状V形臂，以在起飞期间降低发动机噪音而不降低巡航期间的燃料燃烧。

2. 发明申请

WO2015050599A1 SMART SUSCEPTOR FOR A SHAPE MEMORY ALLOY (SMA) ACTUATOR INDUCTIVE HEATING SYSTEM 审中-公开
标题翻译：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：WO2015050599A1
公开(公告)日：2015-04-09
申请号：PCT/US2014/043589
申请日：2014-06-23
申请人： THE BOEING COMPANY
发明人： SHOME, Moushumi , CALKINS, Frederick T. , AMOROSI, Stephen R. , JAMISON, Flint M. , APDALHALIEM, Sahrudine , MILLER, Robert James
IPC分类号： F03G7/06
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。

3. 发明申请

WO2016018477A1 SHAPE MEMORY ALLOY ACTUATOR SYSTEM FOR COMPOSITE AIRCRAFT STRUCTURES 审中-公开
标题翻译：用于复合飞机结构的形状记忆合金致动器系统
公开(公告)号：WO2016018477A1
公开(公告)日：2016-02-04
申请号：PCT/US2015/024070
申请日：2015-04-02
申请人： THE BOEING COMPANY
发明人： DILLIGAN, Matthew A. , CALKINS, Frederick T. , ZIMMERMAN, Tyler J. , MABE, James H. , BLOHOWIAK, Kay Y.
IPC分类号： B64C3/48 , B64C3/44 , B64C9/02 , B64C9/16 , B64C13/50
CPC分类号： B64C3/48 , B64C9/02 , B64C9/16 , B64C13/50 , B64C2003/445 , F03G7/065 , Y02T50/14 , Y02T50/32
摘要： Method and apparatus for controlling a shape of a composite structure. A shape memory structure associated with the composite structure is activated. The shape memory structure changes from a buckled shape to an original shape and causes the composite structure to change from an undeployed shape to a deployed shape. The shape memory structure is deactivated. The shape memory structure changes from the original shape to the buckled shape in response to a load from the composite structure and causes the composite structure to change from the deployed shape to the undeployed shape.
摘要翻译：用于控制复合结构的形状的方法和装置。与复合结构相关联的形状记忆结构被激活。形状记忆结构从弯曲形状变为原始形状，并且使得复合结构从未部署形状变化为展开形状。形状记忆结构被禁用。形状记忆结构响应于来自复合结构的载荷而从原始形状变化到弯曲形状，并且使得复合结构从展开形状变为未部署形状。

4. 发明申请

WO2015053840A1 RATCHETING SHAPE MEMORY ALLOY ACTUATORS AND SYSTEMS AND METHODS INCLUDING THE SAME 审中-公开
标题翻译：冲击形状记忆合金执行机构及系统及其相关方法
公开(公告)号：WO2015053840A1
公开(公告)日：2015-04-16
申请号：PCT/US2014/048367
申请日：2014-07-28
申请人： THE BOEING COMPANY
发明人： MARTIG, Thomas , CALKINS, Frederick T. , KOUNG, Tony
IPC分类号： F03G7/00
CPC分类号： F16H25/14 , F03G7/00 , F03G7/065 , Y10T74/18888
摘要： Ratcheting shape memory alloy actuators (100) and systems and methods including the same are disclosed herein. The ratcheting shape memory alloy actuators (100) include a ratcheting assembly (110) that is operatively coupled to a first bracket (62) and a shape memory alloy element (150) that is operatively coupled to the ratcheting assembly (110) and to a second bracket (72). The first bracket (62) is configured to be operatively coupled to a first structure (60), while the second bracket (72) is configured to be operatively coupled to a second structure (70). The shape memory alloy element (150) is configured to apply a motive force to the ratcheting assembly (110) upon deformation between a first conformation and a second conformation. The ratcheting assembly (110) is configured to utilize the motive force to selectively adjust an orientation of the first structure (60) relative to the second structure (70).
摘要翻译：棘轮形状记忆合金致动器（100）及其系统和方法在此公开。棘轮状记忆合金致动器（100）包括可操作地联接到第一支架（62）的棘轮组件（110）和可操作地联接到棘轮组件（110）的形状记忆合金元件（150）第二支架（72）。第一支架（62）构造成可操作地联接到第一结构（60），而第二支架（72）构造成可操作地联接到第二结构（70）。形状记忆合金元件（150）构造成在第一构象和第二构象之间的变形时向棘轮组件（110）施加动力。棘轮组件（110）构造成利用所述动力来选择性地调节所述第一结构（60）相对于所述第二结构（70）的取向。

5. 发明申请

WO2008134193A1 DEPLOYABLE FLAP EDGE FENCE 审中-公开
标题翻译：可配合的翼瓣边缘
公开(公告)号：WO2008134193A1
公开(公告)日：2008-11-06
申请号：PCT/US2008/059322
申请日：2008-04-03
申请人： THE BOEING COMPANY , LARSSEN, Jon V. , CALKINS, Frederick T.
发明人： LARSSEN, Jon V. , CALKINS, Frederick T.
IPC分类号： B64C9/18 , B64C9/24 , B64C23/06 , B64C7/00
CPC分类号： B64C9/18 , B64C7/00 , B64C9/24 , B64C23/06 , Y02T50/162 , Y02T50/32
摘要： A method and systems are disclosed for reducing fluid flow noise. The method and systems use a thermal mechanism to deploy a flap edge fence (406) during landing and/or other operating conditions, and stow the flap edge fence during other operational conditions such as cruise. The flap edge fence is controlled passively. by ambient temperature or actively by a controller based on temperature changes corresponding to various operating conditions.
摘要翻译：公开了用于减少流体流动噪声的方法和系统。该方法和系统使用热机构在着陆和/或其他操作条件期间部署翼片边缘（406），并且在诸如巡航的其它操作条件期间收起翼片边缘围栏。皮瓣边缘被动被动地控制。通过环境温度或由控制器主动地基于对应于各种操作条件的温度变化。

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