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1.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
申请人： Travis L. Turner , Reggie T. Kidd , David P Lockard , Mehdi R. Khorrami , Craig L. Streett , Douglas Leo Weber
发明人： Travis L. Turner , Reggie T. Kidd , David P Lockard , Mehdi R. Khorrami , Craig L. Streett , Douglas Leo Weber
摘要： 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.
摘要翻译： 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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2.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
申请人： 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
发明人： 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
摘要： 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.
摘要翻译： 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：US08763958B2
公开(公告)日：2014-07-01
申请号：US13449807
申请日：2012-04-18
申请人： Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
发明人： Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
IPC分类号： B64C3/50
摘要： 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.
摘要翻译： 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
申请人： Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
发明人： Travis L. Turner , Mehdi R. Khorrami , David P. Lockard , Martin J. McKenney , Raymond D. Atherley , Reggie T. Kidd
摘要： 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.
摘要翻译： 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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5.发明申请Autonomous Slat-Cove-Filler Device for Reduction of Aeroacoustic Noise Associated with Aircraft Systems 有权用于减少与飞机系统相关的航空声学噪声的自主板式填充装置公开(公告)号：US20120097791A1
公开(公告)日：2012-04-26
申请号：US13277859
申请日：2011-10-20
申请人： Travis L. Turner , Reggie T. Kidd , David P. Lockard , Mehdi R. Khorrami , Craig L. Streett , Douglas Leo Weber
发明人： Travis L. Turner , Reggie T. Kidd , David P. Lockard , Mehdi R. Khorrami , Craig L. Streett , Douglas Leo Weber
摘要： 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.
摘要翻译： 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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公开(公告)号：US08695915B1
公开(公告)日：2014-04-15
申请号：US13417347
申请日：2012-03-12
CPC分类号： B64C1/40 , B64C9/18 , B64C21/10 , B64C23/005 , B64C2025/003 , B64C2220/00 , B64C2230/14 , B64C2230/22 , B64C2230/24 , Y02T50/166 , Y02T50/32
摘要： One or more acoustic liners comprising internal chambers or passageways that absorb energy from a noise source on the aircraft are disclosed. The acoustic liners may be positioned at the ends of flaps of an aircraft wing to provide broadband noise absorption and/or dampen the noise producing unsteady flow features, and to reduce the amount of noise generated due to unsteady flow at the inboard and/or outboard end edges of a flap.
摘要翻译： 公开了一种或多种声学衬垫，其包括从飞机上的噪声源吸收能量的内部腔室或通道。 声学衬垫可以定位在飞机机翼的翼片的端部，以提供宽带噪声吸收和/或抑制产生不稳定流动特征的噪声，并且减少由于内侧和/或外侧的不稳定流动而产生的噪声量 翼片的末端边缘。
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7.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
申请人： 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
发明人： 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分类号： B64C9/16
摘要： 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.
摘要翻译： 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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