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公开(公告)号：US20110203288A1
公开(公告)日：2011-08-25
申请号：US13096305
申请日：2011-04-28
Applicant: Travis L. Turner , Roberto J. Cano , Richard J. Silox , Ralph D. Buehrle , Christopher M. Cagle , Randolph H. Cabell , George C. Hilton
Inventor： Travis L. Turner , Roberto J. Cano , Richard J. Silox , Ralph D. Buehrle , Christopher M. Cagle , Randolph H. Cabell , George C. Hilton
IPC: F02K1/10
CPC classification number: F02K1/48 , F02K1/386 , F05D2300/505 , Y02T50/671
Abstract: A jet engine exhaust nozzle flow effector is a chevron formed with a radius of curvature with surfaces of the flow effector being defined and opposing one another. At least one shape memory alloy (SMA) member is embedded in the chevron closer to one of the chevron's opposing surfaces and substantially spanning from at least a portion of the chevron's root to the chevron's tip.
Abstract translation: 喷气发动机排气喷嘴流动执行器是形成有曲率半径的人字形，其中流动效应器的表面被限定并且彼此相对。 至少一个形状记忆合金（SMA）构件嵌入在更靠近人字形相对表面中的一个的人字形中，并且基本跨越人字纹根部的至少一部分到人字形尖端。
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公开(公告)号：US08683807B2
公开(公告)日：2014-04-01
申请号：US13096305
申请日：2011-04-28
Applicant: Travis L. Turner , Roberto J. Cano , Richard J. Silox , Ralph D. Buehrle , Christopher M. Cagle , Randolph H. Cabell , George C. Hilton
Inventor： Travis L. Turner , Roberto J. Cano , Richard J. Silox , Ralph D. Buehrle , Christopher M. Cagle , Randolph H. Cabell , George C. Hilton
CPC classification number: F02K1/48 , F02K1/386 , F05D2300/505 , Y02T50/671
Abstract: A jet engine exhaust nozzle flow effector is a chevron formed with a radius of curvature with surfaces of the flow effector being defined and opposing one another. At least one shape memory alloy (SMA) member is embedded in the chevron closer to one of the chevron's opposing surfaces and substantially spanning from at least a portion of the chevron's root to the chevron's tip.
Abstract translation: 喷气发动机排气喷嘴流动执行器是形成有曲率半径的人字形，其中流动效应器的表面被限定并且彼此相对。 至少一个形状记忆合金（SMA）构件嵌入在更靠近人字形相对表面中的一个的人字形中，并且基本跨越人字纹根部的至少一部分到人字形尖端。
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公开(公告)号：US20080272232A1
公开(公告)日：2008-11-06
申请号：US11762827
申请日：2007-06-14
Applicant: Christopher M. Cagle , Randolph H. Cabell , Travis L. Turner , Roberto J. Cano , Richard J. Silcox , Ralph D. Buehrle , George C. Hilton
Inventor： Christopher M. Cagle , Randolph H. Cabell , Travis L. Turner , Roberto J. Cano , Richard J. Silcox , Ralph D. Buehrle , George C. Hilton
IPC: B64C13/00
CPC classification number: F02K1/48 , F02K1/386 , F05D2300/505 , Y02T50/671
Abstract: A jet engine exhaust nozzle flow effector is a chevron formed with a radius of curvature with surfaces of the flow effector being defined and opposing one another. At least one shape memory alloy (SMA) member is embedded in the chevron closer to one of the chevron's opposing surfaces and substantially spanning from at least a portion of the chevron's root to the chevron's tip.
Abstract translation: 喷气发动机排气喷嘴流动执行器是形成有曲率半径的人字形，其中流动效应器的表面被限定并且彼此相对。 至少一个形状记忆合金（SMA）构件嵌入在更靠近人字形相对表面中的一个的人字形中，并且基本跨越人字纹根部的至少一部分到人字形尖端。
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4.发明授权Autonomous slat-cove-filler device for reduction of aeroacoustic noise associated with aircraft systems 有权用于降低与航空器系统相关的航空声学噪声的自主板条 - 灌注装置公开(公告)号：US09242720B2
公开(公告)日：2016-01-26
申请号：US13277859
申请日：2011-10-20
Applicant: Travis L. Turner , Reggie T. Kidd , David P Lockard , Mehdi R. Khorrami , Craig L. Streett , Douglas Leo Weber
Inventor： Travis L. Turner , Reggie T. Kidd , David P Lockard , Mehdi R. Khorrami , Craig L. Streett , Douglas Leo Weber
Abstract: A slat cove filler is utilized to reduce airframe noise resulting from deployment of a leading edge slat of an aircraft wing. The slat cove filler is preferably made of a super elastic shape memory alloy, and the slat cove filler shifts between stowed and deployed shapes as the slat is deployed. The slat cove filler may be configured such that a separate powered actuator is not required to change the shape of the slat cove filler from its deployed shape to its stowed shape and vice-versa. The outer contour of the slat cove filler preferably follows a profile designed to maintain accelerating flow in the gap between the slat cove filler and wing leading edge to provide for noise reduction.
Abstract translation: 利用平缝填料来减少飞机机翼的前缘板条的部署造成的机身噪音。 板条填料优选由超弹性形状记忆合金制成，并且板条填料随着板条展开而在收起和展开的形状之间移动。 板条填料可以被构造成使得不需要单独的动力致动器来将板条填充物的形状从其展开的形状改变到其收起的形状，反之亦然。 板条填料填料的外轮廓优选地遵循轮廓设计，以保持板条填充物和机翼前缘之间的间隙中的加速流动，以提供降噪。
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5.发明授权Elastically deformable side-edge link for trailing-edge flap aeroacoustic noise reduction 有权弹性变形侧边缘连接，用于后缘翼片气动噪声降低公开(公告)号：US08695925B2
公开(公告)日：2014-04-15
申请号：US13326779
申请日：2011-12-15
Applicant: Mehdi R. Khorrami , David P. Lockard , James B. Moore , Ji Su , Travis L. Turner , John C. Lin , Karen M. Taminger , Seun K. Kahng , Scott A. Verden
Inventor： Mehdi R. Khorrami , David P. Lockard , James B. Moore , Ji Su , Travis L. Turner , John C. Lin , Karen M. Taminger , Seun K. Kahng , Scott A. Verden
Abstract: A system is provided for reducing aeroacoustic noise generated by an aircraft having wings equipped with trailing-edge flaps. The system includes a plurality of elastically deformable structures. Each structure is coupled to and along one of the side edges of one of the trailing-edge flaps, and is coupled to a portion of one of the wings that is adjacent to the one of the side edges. The structures elastically deform when the trailing-edge flaps are deployed away from the wings.
Abstract translation: 提供了一种用于减少由具有后缘翼片的翼的飞行器产生的航空声学噪声的系统。 该系统包括多个可弹性变形的结构。 每个结构联接到并沿着一个后缘翼片的一个侧边缘，并且联接到与一个侧边缘相邻的翼中的一个的一部分。 当后缘襟翼远离翼片时，结构弹性变形。
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Patent Agency Ranking
6.发明申请公开(公告)号：US20120153086A1
公开(公告)日：2012-06-21
申请号：US13326779
申请日：2011-12-15
Applicant: Mehdi R. Khorrami , David P. Lockard , James B. Moore , Ji Su , Travis L. Turner , John C. Lin , Karen M. Taminger , Seun K. Kahng , Scott A. Verden
Inventor： Mehdi R. Khorrami , David P. Lockard , James B. Moore , Ji Su , Travis L. Turner , John C. Lin , Karen M. Taminger , Seun K. Kahng , Scott A. Verden
IPC: B64C9/16
Abstract: A system is provided for reducing aeroacoustic noise generated by an aircraft having wings equipped with trailing-edge flaps. The system includes a plurality of elastically deformable structures. Each structure is coupled to and along one of the side edges of one of the trailing-edge flaps, and is coupled to a portion of one of the wings that is adjacent to the one of the side edges. The structures elastically deform when the trailing-edge flaps are deployed away from the wings.
Abstract translation: 提供了一种用于减少由具有后缘翼片的翼的飞行器产生的航空声学噪声的系统。 该系统包括多个可弹性变形的结构。 每个结构联接到并沿着一个后缘翼片的一个侧边缘，并且联接到与一个侧边缘相邻的翼中的一个的一部分。 当后缘襟翼远离翼片时，结构弹性变形。
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公开(公告)号：US09796159B2
公开(公告)日：2017-10-24
申请号：US13447513
申请日：2012-04-16
Applicant: Jin Ho Kang , Emilie J. Siochi , Ronald K. Penner , Travis L. Turner
Inventor： Jin Ho Kang , Emilie J. Siochi , Ronald K. Penner , Travis L. Turner
CPC classification number: B32B15/092 , B32B15/08 , B32B25/08 , B32B25/20 , B32B27/20 , B32B27/38 , B32B2264/102 , B32B2264/108 , B32B2307/102 , B32B2307/20 , B32B2307/202 , B32B2307/51 , B32B2307/762 , B32B2571/02 , B32B2605/00 , B32B2605/18
Abstract: Provided is an electrically activated shape memory polymer composite capable of thermal shape reformation using electric power to heat the composite through its matrix glass transition temperature. The composite includes an adaptable polymer matrix component using a diglycidyl ether resin, at least one substantially well-dispersed conductive or magnetic nano-filler component, and at least one elastic, laminated layer. Also provided are methods of preparing the composite and methods of activating the composite. A shape reformation of the composite is triggered by applying an electric field at DC and/or at a frequency above about 1 μHz for a sufficient time.
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公开(公告)号：US20160193810A1
公开(公告)日：2016-07-07
申请号：US13447513
申请日：2012-04-16
Applicant: Jin Ho Kang , Emilie J. Siochi , Ronald K. Penner , Travis L. Turner
Inventor： Jin Ho Kang , Emilie J. Siochi , Ronald K. Penner , Travis L. Turner
IPC: B32B27/06 , H05B6/00 , B32B15/08 , B32B27/28 , B32B27/08 , B32B27/20 , B32B27/38 , B29C63/22 , B82Y30/00 , B82Y40/00
CPC classification number: B32B15/092 , B32B15/08 , B32B25/08 , B32B25/20 , B32B27/20 , B32B27/38 , B32B2264/102 , B32B2264/108 , B32B2307/102 , B32B2307/20 , B32B2307/202 , B32B2307/51 , B32B2307/762 , B32B2571/02 , B32B2605/00 , B32B2605/18
Abstract: Provided is an electrically activated shape memory polymer composite capable of thermal shape reformation using electric power to heat the composite through its matrix glass transition temperature. The composite includes an adaptable polymer matrix component using a diglycidyl ether resin, at least one substantially well-dispersed conductive or magnetic nano-filler component, and at least one elastic, laminated layer. Also provided are methods of preparing the composite and methods of activating the composite. A shape reformation of the composite is triggered by applying an electric field at DC and/or at a frequency above about 1 μHz for a sufficient time.
Abstract translation: 提供一种能够使用电力进行热形变换以通过其基质玻璃化转变温度加热复合材料的电激活形状记忆聚合物复合材料。 复合材料包括使用二缩水甘油醚树脂的适应性聚合物基质组分，至少一种基本上良好分散的导电或磁性纳米填料组分和至少一种弹性层叠层。 还提供了制备复合材料的方法和激活复合材料的方法。 通过在DC和/或高于约1μHz的频率施加电场足够的时间来触发复合材料的形状重新形成。
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公开(公告)号：US08763958B2
公开(公告)日：2014-07-01
申请号：US13449807
申请日：2012-04-18
Applicant: Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
Inventor： Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
IPC: B64C3/50
Abstract: A multi-element airfoil system includes an airfoil element having a leading edge region and a skin element coupled to the airfoil element. A slat deployment system is coupled to the slat and the skin element, and is capable of deploying and retracting the slat and the skin element. The skin element substantially fills the lateral gap formed between the slat and the airfoil element when the slat is deployed. The system further includes an uncoupling device and a sensor to remove the skin element from the gap based on a critical angle-of-attack of the airfoil element. The system can alternatively comprise a trailing edge flap, where a skin element substantially fills the lateral gap between the flap and the trailing edge region of the airfoil element. In each case, the skin element fills a gap between the airfoil element and the deployed flap or slat to reduce airframe noise.
Abstract translation: 多元件翼型系统包括具有前缘区域的翼型元件和连接到翼型元件的皮肤元件。 板条部署系统联接到板条和皮肤元件，并且能够展开和缩回板条和皮肤元件。 当板条展开时，皮肤元件基本上填充形成在板条和翼型件之间的横向间隙。 该系统还包括一个脱离装置和一个传感器，用于基于翼型元件的临界碰撞角度从该间隙移除皮肤元件。 该系统可以替代地包括后缘翼片，其中皮肤元件基本上填充翼片和翼型元件的后缘区域之间的横向间隙。 在每种情况下，皮肤元件填充翼型元件和展开的挡板或板条之间的间隙，以减少机身噪音。
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公开(公告)号：US20120261517A1
公开(公告)日：2012-10-18
申请号：US13449807
申请日：2012-04-18
Applicant: Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
Inventor： Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
Abstract: A multi-element airfoil system includes an airfoil element having a leading edge region and a skin element coupled to the airfoil element. A slat deployment system is coupled to the slat and the skin element, and is capable of deploying and retracting the slat and the skin element. The skin element substantially fills the lateral gap formed between the slat and the airfoil element when the slat is deployed. The system further includes an uncoupling device and a sensor to remove the skin element from the gap based on a critical angle-of-attack of the airfoil element. The system can alternatively comprise a trailing edge flap, where a skin element substantially fills the lateral gap between the flap and the trailing edge region of the airfoil element. In each case, the skin element fills a gap between the airfoil element and the deployed flap or slat to reduce airframe noise.
Abstract translation: 多元件翼型系统包括具有前缘区域的翼型元件和连接到翼型元件的皮肤元件。 板条部署系统联接到板条和皮肤元件，并且能够展开和缩回板条和皮肤元件。 当板条展开时，皮肤元件基本上填充形成在板条和翼型件之间的横向间隙。 该系统还包括一个脱离装置和一个传感器，用于基于翼型元件的临界碰撞角度从该间隙移除皮肤元件。 该系统可以替代地包括后缘翼片，其中皮肤元件基本上填充翼片和翼型元件的后缘区域之间的横向间隙。 在每种情况下，皮肤元件填充翼型元件和展开的挡板或板条之间的间隙，以减少机身噪音。
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