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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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2.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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3.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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