公开(公告)号：US11225339B2

公开(公告)日：2022-01-18

申请号：US16913855

申请日：2020-06-26

Applicant: THE BOEING COMPANY

Inventor： Eric S. Mindock ,  James H. Mabe ,  Frederick Theodore Calkins ,  Abraham Naroll Gissen ,  Miguel A. Estevez

IPC: H05K7/20 ,  B64G1/50 ,  F28D21/00 ,  H01L23/427 ,  H01L23/42 ,  F28F13/00 ,  H01L23/373

Abstract: An apparatus includes a thermally conductive interface assembly including a first component associated with a first interface surface and a second component associated with a second interface surface. The apparatus also includes a shape memory alloy component coupled to the thermally conductive interface assembly and configured to move one or more components of the thermally conductive interface assembly between a first state and a second state based on a temperature of the shape memory alloy component. In the first state, the first interface surface is in physical contact with the second interface surface, and in the second state, a gap is defined between the first interface surface and the second interface surface.

公开(公告)号：US20140023837A1

公开(公告)日：2014-01-23

申请号：US13732270

申请日：2012-12-31

Applicant: THE BOEING COMPANY

Inventor： Robert J. Miller ,  Diane C. Rawlings ,  Kenneth A. Krienke ,  James H. Mabe ,  Robert T. Ruggeri ,  Dan J. Clingman

IPC: B64C7/00

CPC classification number: B64C7/00 ,  B29C65/48 ,  B29C65/4815 ,  B29C65/483 ,  B29C65/4855 ,  B29C65/4865 ,  B29C65/4875 ,  B29C65/8253 ,  B29C65/8284 ,  B29C66/721 ,  B29C70/88 ,  B29K2101/10 ,  B29K2101/12 ,  B29K2105/16 ,  B29K2503/06 ,  B29K2705/00 ,  B29K2705/12 ,  B29K2995/0003 ,  B29K2995/0008 ,  B29L2031/3082 ,  B29L2031/3085 ,  B64C1/06 ,  B64C1/12 ,  B64D2045/0085 ,  B64F5/60 ,  C09J5/00 ,  C09J9/00 ,  C09J11/00 ,  G01L1/12 ,  G01M5/0016 ,  G01M5/0041 ,  G01M5/0091 ,  G01N29/2412 ,  Y02T50/43 ,  Y10T156/10 ,  Y10T428/24851 ,  Y10T428/31529 ,  Y10T442/10

Abstract: First and second aircraft structures are bonded together with an adhesive including strain-sensitive magnetostrictive material. The magnetostrictive material has a magnetomechanical coefficient greater than e−5.

Abstract translation: 第一和第二飞行器结构用包括应变敏感的磁致伸缩材料的粘合剂粘合在一起。 磁致伸缩材料的磁机械系数大于e-5。

公开(公告)号：US10730645B2

公开(公告)日：2020-08-04

申请号：US15494315

申请日：2017-04-21

Applicant: THE BOEING COMPANY

Inventor： Eric S. Mindock ,  James H. Mabe ,  Frederick Theodore Calkins ,  Abraham Naroll Gissen ,  Miguel A. Estevez

IPC: H05K7/20 ,  F28F13/00 ,  F28F21/00 ,  B64G1/50 ,  F28D21/00 ,  H01L23/427 ,  H01L23/42 ,  H01L23/373

Abstract: An apparatus includes a thermally conductive interface assembly including a first component associated with a first interface surface and a second component associated with a second interface surface. The apparatus also includes a shape memory alloy component coupled to the thermally conductive interface assembly and configured to move one or more components of the thermally conductive interface assembly between a first state and a second state based on a temperature of the shape memory alloy component. In the first state, the first interface surface is in physical contact with the second interface surface, and in the second state, a gap is defined between the first interface surface and the second interface surface.

公开(公告)号：US20170066519A1

公开(公告)日：2017-03-09

申请号：US14848393

申请日：2015-09-09

Applicant: The Boeing Company

Inventor： James H. Mabe ,  Ali Yousefiani

IPC: B64C1/12 ,  B32B3/28 ,  B64G1/22 ,  F03G7/06 ,  B64C1/06 ,  B32B15/01 ,  B32B7/04

CPC classification number: B64G1/22 ,  B32B3/28 ,  B32B7/045 ,  B32B15/01 ,  B32B2250/03 ,  B32B2307/302 ,  B32B2307/732 ,  B32B2605/18 ,  B64C1/061 ,  F02K1/06 ,  F02K1/10 ,  F03G7/065 ,  F05D2300/505 ,  Y02T50/672

Abstract: In one or more aspects of the present disclosure, an aerospace vehicle includes a frame, an actuable multifunctional cellular structure connected to the frame, the actuable multifunctional cellular structure including a first face member and a second face member, and a shape memory alloy core coupled to the first face member and the second face member, and wherein, at least one of the first face member and the second face member is a graded thermal structure configured so that heat transferred through the graded thermal structure in a predetermined thermal pattern to the shape memory alloy core effects a predetermined change in a shape of the shape memory alloy core and effects a change in shape of the actuable multifunctional cellular structure.

Abstract translation: 在本公开的一个或多个方面，航空航天车辆包括框架，连接到框架的可致动的多功能蜂窝结构，所述可致动的多功能蜂窝结构包括第一面构件和第二面构件，以及形状记忆合金芯 并且其中，所述第一面构件和所述第二面构件中的至少一个是渐变热结构，其被构造成使得以预定的热图案传递通过所述分级热结构的热量形成为所述形状 记忆合金芯体影响形状记忆合金芯的形状的预定变化并且实现致动多功能蜂窝结构的形状变化。

公开(公告)号：US20160348580A1

公开(公告)日：2016-12-01

申请号：US15233685

申请日：2016-08-10

Applicant: The Boeing Company

Inventor： James H. Mabe ,  Naveed M. Hussain ,  Edward A. Whalen ,  Frederick T. Calkins

IPC: F02C6/04 ,  F03G7/06

CPC classification number: F02C6/04 ,  F03G7/065

Abstract: A thermal energy harvesting system employs a hot flow conduit and a cold flow conduit with a flow routing device interruptibly interconnecting the hot flow conduit and cold flow conduit with a flow casing. At least one shape memory actuator (SMA) tube is in fluid contact with the flow casing and fixed at a first end. The flow routing device sequentially supplies hot flow from the hot flow conduit and cold flow from the cold flow conduit inducing rotation of the at least one SMA tube at a second end. A generator or alternator is operably connected to the second end of the at least one SMA tube.

Abstract translation: 热能收集系统采用热流导管和冷流导管，其中流动路径装置可将热流导管和冷流导管与流动套管中断连接。 至少一个形状记忆致动器（SMA）管与流动套管流体接触并固定在第一端。 流动路径选择装置顺序地从热流管道提供热流，并且来自冷流道的冷流引起至少一个SMA管在第二端的旋转。 发电机或交流发电机可操作地连接到至少一个SMA管的第二端。

公开(公告)号：US10029781B2

公开(公告)日：2018-07-24

申请号：US14816444

申请日：2015-08-03

Applicant: The Boeing Company

Inventor： William J. Bigbee-Hansen ,  Dan J. Clingman ,  James H. Mabe

IPC: B64C11/06 ,  B64C11/20 ,  B64C11/44 ,  B64C11/30 ,  B64C27/72

Abstract: Shape memory alloy-actuated propeller blades and shape memory alloy-actuated propeller assemblies are disclosed. An example propeller blade includes a propeller body, a plate coupled to the propeller body, a torque transfer member, and a shape memory alloy (SMA) actuator. The torque transfer member has a distal end attached to the plate such that the torque transfer member applies to the plate at least a portion of a torque applied to the torque transfer member at a proximal end of the torque transfer member. The SMA actuator has a distal end and a proximal end. The distal end of the SMA actuator is attached to the torque transfer member. The proximal end of the SMA actuator is coupled to the propeller body such that the distal end is mated to the propeller body. The SMA actuator is configured to apply the torque to the proximal end of the torque transfer member in response to an application of heat to the SMA actuator.

公开(公告)号：US10054047B2

公开(公告)日：2018-08-21

申请号：US15233685

申请日：2016-08-10

Applicant: The Boeing Company

Inventor： James H. Mabe ,  Naveed M. Hussain ,  Edward A. Whalen ,  Frederick T. Calkins

IPC: F02C6/04 ,  F03G7/06

CPC classification number: F02C6/04 ,  F03G7/065

Abstract: A thermal energy harvesting system employs a hot flow conduit and a cold flow conduit with a flow routing device interruptibly interconnecting the hot flow conduit and cold flow conduit with a flow casing. At least one shape memory actuator (SMA) tube is in fluid contact with the flow casing and fixed at a first end. The flow routing device sequentially supplies hot flow from the hot flow conduit and cold flow from the cold flow conduit inducing rotation of the at least one SMA tube at a second end. A generator or alternator is operably connected to the second end of the at least one SMA tube.

公开(公告)号：US20180094622A1

公开(公告)日：2018-04-05

申请号：US13855721

申请日：2013-04-03

Applicant: The Boeing Company

Inventor： Richard D. Widdle, JR. ,  Matthew T. Grimshaw ,  Kava S. CROSSON-ELTURAN ,  James H. Mabe ,  Frederick T. Calkins ,  Lynn M. Gravatt ,  Moushumi Shome

IPC: F03G7/06

CPC classification number: F02K1/10 ,  B64C2027/7288 ,  F02K1/386 ,  F03G7/065 ,  F05D2250/184 ,  F05D2300/505 ,  Y02T50/34 ,  Y02T50/672

Abstract: 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.

公开(公告)号：US09885345B2

公开(公告)日：2018-02-06

申请号：US14566376

申请日：2014-12-10

Applicant: The Boeing Company

Inventor： Frederick T. Calkins ,  James H. Mabe ,  Jonathan K. Brown

IPC: F03G7/06

CPC classification number: F03G7/065

Abstract: A scalable multi-element shape memory alloy (SMA) rotary motor employs a plurality of SMA tubes. A ratcheting gear transmission couples the plurality of SMA tubes in parallel to a common output. A controller provides power to a plurality of heaters associated with each of the plurality of SMA tubes, sequentially heating selected heaters to provide continuous rotational motion of the common output.

公开(公告)号：US20200331639A1

公开(公告)日：2020-10-22

申请号：US16913855

申请日：2020-06-26

Applicant: THE BOEING COMPANY

Inventor： Eric S. Mindock ,  James H. Mabe ,  Frederick Theodore Calkins ,  Abraham NaroII Gissen ,  Miguel A. Estevez

IPC: B64G1/50 ,  F28D21/00 ,  H05K7/20 ,  H01L23/427 ,  H01L23/42 ,  F28F13/00 ,  H01L23/373

Abstract: An apparatus includes a thermally conductive interface assembly including a first component associated with a first interface surface and a second component associated with a second interface surface. The apparatus also includes a shape memory alloy component coupled to the thermally conductive interface assembly and configured to move one or more components of the thermally conductive interface assembly between a first state and a second state based on a temperature of the shape memory alloy component. In the first state, the first interface surface is in physical contact with the second interface surface, and in the second state, a gap is defined between the first interface surface and the second interface surface.