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11.发明授权公开(公告)号：US09805150B2
公开(公告)日：2017-10-31
申请号：US14447171
申请日：2014-07-30
Applicant: THE BOEING COMPANY
Inventor： Alan E. Landmann , Mark A. Negley , Bret A. Voss , Jaffar S. Iqbal
IPC: G06F17/50
CPC classification number: G06F17/5018 , G06F17/5095 , G06F2217/82
Abstract: A computer system enables a noise level associated with a structural substrate to be reduced. The computer system includes a memory device for storing data, and a processor in communication with the memory device. The processor is programmed to define a modulus of elasticity, a thickness, and/or a distribution associated with one or more damping elements coupleable to the structural substrate, define at least one operating parameter associated with the structural substrate and the one or more damping elements, simulate a first performance of the structural substrate and/or the one or more damping elements to generate a first performance data set; and determine whether the first performance data set satisfies a predetermined threshold. The first performance data set is associated with the at least one operating parameter and the modulus of elasticity, the thickness, and/or the distribution associated with the one or more damping elements.
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12.发明申请METHODS AND SYSTEMS FOR DETERMINING A STRUCTURAL PARAMETER FOR NOISE AND VIBRATION CONTROL 有权用于确定噪声和振动控制的结构参数的方法和系统公开(公告)号：US20160034611A1
公开(公告)日：2016-02-04
申请号：US14447171
申请日：2014-07-30
Applicant: THE BOEING COMPANY
Inventor： Alan E. Landmann , Mark A. Negley , Bret A. Voss , Jaffar S. Iqbal
IPC: G06F17/50
CPC classification number: G06F17/5018 , G06F17/5095 , G06F2217/82
Abstract: A computer system enables a noise level associated with a structural substrate to be reduced. The computer system includes a memory device for storing data, and a processor in communication with the memory device. The processor is programmed to define a modulus of elasticity, a thickness, and/or a distribution associated with one or more damping elements coupleable to the structural substrate, define at least one operating parameter associated with the structural substrate and the one or more damping elements, simulate a first performance of the structural substrate and/or the one or more damping elements to generate a first performance data set; and determine whether the first performance data set satisfies a predetermined threshold. The first performance data set is associated with the at least one operating parameter and the modulus of elasticity, the thickness, and/or the distribution associated with the one or more damping elements.
Abstract translation: 计算机系统能够降低与结构基底相关联的噪声水平。 计算机系统包括用于存储数据的存储装置，以及与存储装置通信的处理器。 处理器被编程为定义与一个或多个可耦合到结构基底的阻尼元件相关联的弹性模量，厚度和/或分布，限定与结构基底和一个或多个阻尼元件相关联的至少一个操作参数 模拟结构基板和/或一个或多个阻尼元件的第一性能以产生第一性能数据集; 并且确定第一性能数据集是否满足预定阈值。 第一性能数据集与至少一个操作参数和与一个或多个阻尼元件相关联的弹性模量，厚度和/或分布相关联。
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公开(公告)号：US20160031195A1
公开(公告)日：2016-02-04
申请号：US14447107
申请日：2014-07-30
Applicant: THE BOEING COMPANY
Inventor： Alan E. Landmann , Mark A. Negley , Jaffar S. Iqbal , Bret A. Voss , Mark M. Gmerek , Giacomo Licciardi
CPC classification number: B32B27/12 , B32B5/02 , B32B27/40 , B32B37/18 , B32B2307/51 , B32B2307/56 , B32B2315/085 , B32B2605/18 , B64D13/00 , F16F9/306
Abstract: A panel includes a structural substrate and a damping element including a viscoelastic material (VEM) layer coupleable to the structural substrate of the aircraft, and a constraining layer coupled to the VEM layer. The VEM layer is configured to dampen a vibration of the structural substrate. The constraining layer is configured to apply a shear force to the VEM layer.
Abstract translation: 面板包括结构基板和阻尼元件，该阻尼元件包括可耦合到飞行器的结构基底的粘弹性材料（VEM）层，以及耦合到VEM层的约束层。 VEM层被配置成抑制结构基底的振动。 约束层被配置为向VEM层施加剪切力。
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公开(公告)号：US10442120B2
公开(公告)日：2019-10-15
申请号：US14599475
申请日：2015-01-17
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Mark A. Negley , William Preston Geren
Abstract: A system for inductively heating a workpiece may include an induction coil, at least one susceptor face sheet, and a current controller coupled. The induction coil may be configured to conduct an alternating current and generate a magnetic field in response to the alternating current. The susceptor face sheet may be configured to have a workpiece positioned therewith. The susceptor face sheet may be formed of a ferromagnetic alloy having a Curie temperature and being inductively heatable to an equilibrium temperature approaching the Curie temperature in response to the magnetic field. The current controller may be coupled to the induction coil and may be configured to adjust the alternating current in a manner causing a change in at least one heating parameter of the susceptor face sheet.
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公开(公告)号：US20190289681A1
公开(公告)日：2019-09-19
申请号：US15923902
申请日：2018-03-16
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Mark A. Negley
Abstract: Disclosed herein is a method of forming a multi-layered metallic part. The method comprises forming a plurality of ductile layers made of a metallic material having a first ductility. The method also comprises forming at least one high-strength powder layer made of a powdered metallic material having a second ductility higher than the first ductility. The method further comprises assembling the plurality of ductile layers and the at least one high-strength powder layer in an alternating and stacked formation to form a multi-layered metallic assembly. The method additionally comprises oscillating a crystallographic phase of the powdered metallic material of the at least one high-strength powder layer between a first crystallographic phase and a second crystallographic phase.
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Patent Agency Ranking
公开(公告)号：US10350863B2
公开(公告)日：2019-07-16
申请号：US14447107
申请日：2014-07-30
Applicant: THE BOEING COMPANY
Inventor： Alan E. Landmann , Mark A. Negley , Jaffar S. Iqbal , Bret A. Voss , Mark M. Gmerek , Giacomo Licciardi
Abstract: A panel includes a structural substrate and a damping element including a viscoelastic material (VEM) layer coupleable to the structural substrate of the aircraft, and a constraining layer coupled to the VEM layer. The VEM layer is configured to dampen a vibration of the structural substrate. The constraining layer is configured to apply a shear force to the VEM layer.
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公开(公告)号：US09862175B2
公开(公告)日：2018-01-09
申请号：US14795209
申请日：2015-07-09
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Mark A. Negley , Marc J. Piehl , Kay Y. Blohowiak , Alan E. Landmann , Richard H. Bossi , Robert L. Carlsen , Gregory Alan Foltz , Geoffrey A. Butler , Liam S. Cavanaugh Pingree , Stephen G. Moore , John Mark Gardner , Robert A. Anderson
IPC: B32B37/00 , B32B37/14 , B32B7/12 , B32B15/00 , B32B15/08 , B32B19/02 , B32B27/00 , B32B3/06 , B29C73/10
CPC classification number: B32B37/144 , B29C73/10 , B32B3/06 , B32B7/12 , B32B15/00 , B32B15/08 , B32B19/02 , B32B27/00 , B32B2250/42 , B32B2260/021 , B32B2305/08 , B32B2307/202 , B32B2307/204 , B32B2307/54 , B32B2307/558 , B32B2311/00 , B32B2398/00 , B32B2405/00 , B32B2605/18 , Y10T29/49208 , Y10T29/49885 , Y10T156/10 , Y10T428/24752 , Y10T428/31678
Abstract: A method of forming a molybdenum composite hybrid laminate is disclosed. The method includes treating a surface of each of a plurality of molybdenum foil layers. The method further includes interweaving the surface treated molybdenum foil layers with a plurality of composite material layers. The method further includes bonding with an adhesive layer each of the surface treated molybdenum foil layers to adjacent composite material layers to form a molybdenum composite hybrid laminate having improved yield strength.
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公开(公告)号：US20150306859A1
公开(公告)日：2015-10-29
申请号：US14795209
申请日：2015-07-09
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Mark A. Negley , Marc J. Piehl , Kay Y. Blohowiak , Alan E. Landmann , Richard H. Bossi , Robert L. Carlsen , Gregory Alan Foltz , Geoffrey A. Butler , Liam S. Cavanaugh Pingree , Stephen G. Moore , John Mark Gardner , Robert A. Anderson
CPC classification number: B32B37/144 , B29C73/10 , B32B3/06 , B32B7/12 , B32B15/00 , B32B15/08 , B32B19/02 , B32B27/00 , B32B2250/42 , B32B2260/021 , B32B2305/08 , B32B2307/202 , B32B2307/204 , B32B2307/54 , B32B2307/558 , B32B2311/00 , B32B2398/00 , B32B2405/00 , B32B2605/18 , Y10T29/49208 , Y10T29/49885 , Y10T156/10 , Y10T428/24752 , Y10T428/31678
Abstract: A method of forming a molybdenum composite hybrid laminate is disclosed. The method includes treating a surface of each of a plurality of molybdenum foil layers. The method further includes interweaving the surface treated molybdenum foil layers with a plurality of composite material layers. The method further includes bonding with an adhesive layer each of the surface treated molybdenum foil layers to adjacent composite material layers to form a molybdenum composite hybrid laminate having improved yield strength.
Abstract translation: 公开了一种形成钼复合混合层压板的方法。 该方法包括处理多个钼箔层中的每一个的表面。 该方法还包括用多个复合材料层交织经表面处理的钼箔层。 该方法还包括将每个表面处理的钼箔层的粘合剂层粘合到相邻的复合材料层，以形成具有改进的屈服强度的钼复合混合层合物。
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公开(公告)号：US20150048080A1
公开(公告)日：2015-02-19
申请号：US14530826
申请日：2014-11-02
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Mark A. Negley
CPC classification number: H05B6/44 , B29C33/06 , B29C35/00 , B29C35/0272 , B29C35/0805 , B29C65/18 , B29C65/32 , B29C65/36 , B29C65/3644 , B29C65/3668 , B29C65/3676 , B29C65/368 , B29C66/721 , B29C66/80 , B29C2035/0811 , B29K2071/00 , B29K2101/12 , B29K2105/06 , B29K2305/00 , B29K2307/00 , B29K2307/02 , B29L2031/082 , B29L2031/7504 , F03D1/065 , F05B2230/00 , F05B2280/4007 , F05C2225/08 , H05B6/40 , Y02E10/721
Abstract: A method of fabricating a thermoplastic component using inductive heating is described. The method includes positioning a plurality of induction heating coils to define a process area for the thermoplastic component, wherein the plurality of induction heating coils comprises a first set of coils and a second set of coils. The method also includes controlling a supply of electricity provided to the plurality of inductive heating coils to intermittently activate the coils. The intermittent activation is configured to facilitate prevention of electromagnetic interference between adjacent coils.
Abstract translation: 描述了使用感应加热制造热塑性组分的方法。 该方法包括定位多个感应加热线圈以限定热塑性部件的处理区域，其中多个感应加热线圈包括第一组线圈和第二组线圈。 该方法还包括控制提供给多个感应加热线圈的电力间歇地启动线圈。 间歇激活被配置为便于防止相邻线圈之间的电磁干扰。
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公开(公告)号：US20150020975A1
公开(公告)日：2015-01-22
申请号：US14507829
申请日：2014-10-07
Applicant: The Boeing Company
Inventor： Marc R. Matsen , Mark A. Negley , Kim E. Peterson
Abstract: A composite part layup is cured using a set of tools adapted to hold the layup and which include at least one tool face contacting the layup. Means are provided for heating the tool face to cure the part layup, and for selectively cooling sections of the tool face.
Abstract translation: 使用一组适于保持叠层的工具固化复合材料叠层，并且其包括与叠层接触的至少一个工具面。 提供了用于加热工具面以固化部件叠层并且用于选择性地冷却工具面部分的装置。
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