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1.发明授权公开(公告)号：US08828515B2
公开(公告)日：2014-09-09
申请号：US13902816
申请日：2013-05-26
申请人： The Boeing Company
CPC分类号： B64C1/06 , B29C73/10 , B29L2031/3076 , Y10T428/18 , Y10T428/20 , Y10T428/21 , Y10T428/24124 , Y10T428/24752 , Y10T428/24942 , Y10T428/2495 , Y10T428/24959 , Y10T428/24983 , Y10T428/24992
摘要： A patch for reworking an inconsistent area in a composite structure includes a composite laminate patch and a layer of adhesive for bonding the laminate patch to the composite structure. The laminate patch has at least first and second regions for releasing strain energy around the inconsistent area respectively at different rates.
摘要翻译： 用于重新组合复合结构中不一致区域的补片包括复合层压贴片和用于将层压贴片粘合到复合结构的粘合剂层。 层压贴片具有至少第一和第二区域，用于以不同的速率分别在不一致区域周围释放应变能。
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公开(公告)号：US20140238579A1
公开(公告)日：2014-08-28
申请号：US14267220
申请日：2014-05-01
申请人： The Boeing Company
发明人： Eugene A. Dan-Jumbo
CPC分类号： B29C73/10 , B29L2031/3076 , B32B43/00 , B64C2001/0072 , B64F5/40 , C09J7/29 , Y02T50/43 , Y10T428/24802 , Y10T428/24959
摘要： A method and apparatus for reworking a composite structure. A composite rework patch system comprises a composite rework patch and a plurality of adhesive layers. The composite rework patch includes a first side having a contour conforming to an inconsistent area on the composite structure. The composite re patch comprises a plurality of regions having different structural properties. The plurality of adhesive layers is on the first side of the composite rework patch. The plurality of adhesive layers change in thickness within at least one region of the composite rework patch to form tapered adhesive sections.
摘要翻译： 一种用于重新组合复合结构的方法和装置。 复合返修贴片系统包括复合返修片和多个粘合剂层。 复合返修贴片包括具有与复合结构上的不一致区域一致的轮廓的第一侧。 复合补片包括具有不同结构特性的多个区域。 多个粘合剂层位于复合返修片的第一侧上。 多个粘合剂层在复合返修片的至少一个区域内的厚度变化，以形成锥形粘合剂部分。
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公开(公告)号：US10155581B2
公开(公告)日：2018-12-18
申请号：US15191527
申请日：2016-06-24
申请人： The Boeing Company
发明人： Eugene A. Dan-Jumbo
IPC分类号： B64C3/20 , B32B5/12 , B32B5/26 , B32B27/08 , B32B27/20 , B32B27/38 , B32B3/10 , B64C3/18 , B64C5/02 , B64C5/06 , B32B7/02
摘要： An all-composite assembly such as a composite laminate aircraft empennage has vertical and horizontal stabilizers with differing sets of interlaminar fracture toughnesses and differing stiffnesses to improve flight characteristics. Composite laminate skins are bonded to unitized and stiffened understructure to reduce weight and improve damage containment.
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公开(公告)号：US09518907B2
公开(公告)日：2016-12-13
申请号：US14157211
申请日：2014-01-16
申请人： The Boeing Company
发明人： Eugene A. Dan-Jumbo
CPC分类号： G01N13/02 , B64C1/12 , B64C3/26 , B64C2001/0072 , G01M5/0016 , G01N2013/0208
摘要： Apparatus and methods to determine structural integrity of composites are described herein. One described example method for determining sufficiency of structural integration of a composite structure for an aircraft includes applying a fluid droplet to a surface of the composite structure, determining a three-dimensional contact angle between the surface and a portion of the droplet, comparing the three-dimensional contact angle to a threshold angle, and determining whether the structural integration of the composite structure is sufficient based on the comparison.
摘要翻译： 本文描述了确定复合材料的结构完整性的装置和方法。 一种用于确定飞行器的复合结构的结构整合的充分性的示例性方法包括将流体液滴施加到复合结构的表面，确定表面和液滴的一部分之间的三维接触角，将三 基于比较，确定复合结构的结构集成是否足够。
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公开(公告)号：US09492975B2
公开(公告)日：2016-11-15
申请号：US14267220
申请日：2014-05-01
申请人： The Boeing Company
发明人： Eugene A. Dan-Jumbo
CPC分类号： B29C73/10 , B29L2031/3076 , B32B43/00 , B64C2001/0072 , B64F5/40 , C09J7/29 , Y02T50/43 , Y10T428/24802 , Y10T428/24959
摘要： A method and apparatus for reworking a composite structure. A composite rework patch system comprises a composite rework patch and a plurality of adhesive layers. The composite rework patch includes a first side having a contour conforming to an inconsistent area on the composite structure. The composite re patch comprises a plurality of regions having different structural properties. The plurality of adhesive layers is on the first side of the composite rework patch. The plurality of adhesive layers change in thickness within at least one region of the composite rework patch to form tapered adhesive sections.
摘要翻译： 一种用于重新组合复合结构的方法和装置。 复合返修贴片系统包括复合返修片和多个粘合剂层。 复合返修贴片包括具有与复合结构上的不一致区域一致的轮廓的第一侧。 复合补片包括具有不同结构特性的多个区域。 多个粘合剂层位于复合返修片的第一侧上。 多个粘合剂层在复合返修片的至少一个区域内的厚度变化，以形成锥形粘合剂部分。
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公开(公告)号：US20140020221A1
公开(公告)日：2014-01-23
申请号：US13945475
申请日：2013-07-18
申请人： The Boeing Company
IPC分类号： B23P19/04
CPC分类号： B23P19/04 , B29C73/10 , B29L2031/3076 , Y10T29/49764 , Y10T428/20 , Y10T428/24942
摘要： A composite laminate patch for reworking an inconsistent area in a structure has inner and outer control regions possessing differing interlaminar fracture toughnesses for controlling the advance of a disbond in the patch. One or more separation zones in the patch between the control regions aids in diffusing the fracture energy of the disbond as the disbond advances from the inner region to the outer region.
摘要翻译： 用于重新构造结构中不一致区域的复合层压贴片具有内部和外部控制区域，其具有不同的层间断裂韧性，用于控制贴片中脱粘的进行。 控制区域之间的补片中的一个或多个分离区有助于随着脱离从内部区域前进到外部区域而扩散解离的断裂能。
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公开(公告)号：US20160297512A1
公开(公告)日：2016-10-13
申请号：US15191527
申请日：2016-06-24
申请人： The Boeing Company
发明人： Eugene A. Dan-Jumbo
CPC分类号： B64C3/20 , B32B3/10 , B32B5/12 , B32B5/26 , B32B7/02 , B32B27/08 , B32B27/20 , B32B27/38 , B32B2262/106 , B32B2307/544 , B32B2307/546 , B32B2307/552 , B32B2307/558 , B32B2603/00 , B32B2605/18 , B64C3/182 , B64C3/185 , B64C5/02 , B64C5/06
摘要： An all-composite assembly such as a composite laminate aircraft empennage has vertical and horizontal stabilizers with differing sets of interlaminar fracture toughnesses and differing stiffnesses to improve flight characteristics. Composite laminate skins are bonded to unitized and stiffened understructure to reduce weight and improve damage containment.
摘要翻译： 全复合组件如复合层压飞机后轮具有垂直和水平稳定器，具有不同的层间断裂韧性和不同的刚度，以改善飞行特性。 复合层压板表层结合在一体化和加强的底层结构上以减轻重量并改善损伤容纳。
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8.发明授权Apparatus, system, and method for in situ strength testing of a bonded joint 有权用于接合接头的原位强度试验的装置，系统和方法公开(公告)号：US09261444B1
公开(公告)日：2016-02-16
申请号：US13954732
申请日：2013-07-30
申请人： The Boeing Company
IPC分类号： G01N17/00 , G01N3/02 , G01N3/08 , G01N3/30 , G01N3/307 , G01N19/04 , G01N19/00 , G01L5/00 , G01N29/04 , G01N1/22 , G01N3/00
CPC分类号： G01N3/02 , G01L5/008 , G01N1/2208 , G01N3/00 , G01N3/08 , G01N3/30 , G01N3/307 , G01N19/00 , G01N19/04 , G01N29/045 , G01N29/2475 , G01N2203/0051 , G01N2203/0244 , G01N2203/0246 , G01N2203/0296 , G01N2203/0676 , G01N2291/0258 , G01N2291/02827
摘要： The present disclosure relates to a system for testing the strength of a bonded joint between at least two components, wherein the system includes at least one element force energizer that creates an actual mechanical stress in the bonded joint when actuated, wherein the element force energizer is coupled with the at least two components. The system further includes an energy interface that is connectable to a power source, the energy interface being in electrical communication with the at least one element force energizer, and a sensor that detects the actual mechanical stress or strain in the bonded joint. The system may also include a recording device that records and/or transmits the detected mechanical stress or strain in the bonded joint. In one example, the element force energizers include piezoelectric materials.
摘要翻译： 本公开涉及一种用于测试至少两个部件之间的接合接头的强度的系统，其中所述系统包括至少一个元件施力器，其在致动时在所述接合接头中产生实际机械应力，其中所述元件力增力器 加上至少两个组件。 该系统还包括能够连接到电源的能量接口，能量接口与至少一个元件力激励器电连通，以及传感器，其检测接合接头中的实际机械应力或应变。 该系统还可以包括记录和/或传送在接合接头中检测到的机械应力或应变的记录装置。 在一个示例中，元件力激发器包括压电材料。
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9.发明授权公开(公告)号：US09133365B2
公开(公告)日：2015-09-15
申请号：US14569561
申请日：2014-12-12
申请人： The Boeing Company
CPC分类号： C09D179/08 , B29C65/00 , B29C65/02 , B29C66/70 , B29C66/712 , B29C66/723 , B29C66/72321 , B29C66/72322 , B29C66/742 , B29C66/744 , B29C66/746 , B32B5/00 , B32B7/00 , B32B15/00 , B32B37/00 , C09D179/085 , C09J5/02 , C09J2463/00 , C09J2479/08 , Y10T29/49 , Y10T29/49826 , Y10T29/49888 , Y10T156/10 , Y10T428/31678
摘要： There is provided a high temperature hybridized molecular functional group adhesion barrier coating for a composite structure. The coating has one or more hybridized molecular functional groups attached to a composite surface of the composite structure, wherein the one or more hybridized molecular functional groups are hybridized through a chemical derivatization process. The coating further has one or more chemical derivatization compounds attached to the one or more hybridized molecular functional groups via a condensation reaction. The coating is resistant to high heat temperatures in a range of from about 350 degrees Fahrenheit to about 2000 degrees Fahrenheit, and the coating is a thermally protective, toughened adhesion coating that mitigates effects of a hostile operating environment.
摘要翻译： 提供了用于复合结构的高温杂化分子官能团粘合屏障涂层。 涂层具有连接到复合结构的复合表面的一个或多个杂化分子官能团，其中一个或多个杂化分子官能团通过化学衍生化过程进行杂交。 涂层还具有通过缩合反应连接到一个或多个杂化分子官能团的一种或多种化学衍生化合物。 该涂层耐高温约350华氏度至约2000华氏度的温度，该涂层是一种耐热韧性增强的粘合涂层，可减轻恶劣的操作环境的影响。
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10.发明申请公开(公告)号：US20150099133A1
公开(公告)日：2015-04-09
申请号：US14569561
申请日：2014-12-12
申请人： The Boeing Company
IPC分类号： C09D179/08
CPC分类号： C09D179/08 , B29C65/00 , B29C65/02 , B29C66/70 , B29C66/712 , B29C66/723 , B29C66/72321 , B29C66/72322 , B29C66/742 , B29C66/744 , B29C66/746 , B32B5/00 , B32B7/00 , B32B15/00 , B32B37/00 , C09D179/085 , C09J5/02 , C09J2463/00 , C09J2479/08 , Y10T29/49 , Y10T29/49826 , Y10T29/49888 , Y10T156/10 , Y10T428/31678
摘要： There is provided a high temperature hybridized molecular functional group adhesion barrier coating for a composite structure. The coating has one or more hybridized molecular functional groups attached to a composite surface of the composite structure, wherein the one or more hybridized molecular functional groups are hybridized through a chemical derivatization process. The coating further has one or more chemical derivatization compounds attached to the one or more hybridized molecular functional groups via a condensation reaction. The coating is resistant to high heat temperatures in a range of from about 350 degrees Fahrenheit to about 2000 degrees Fahrenheit, and the coating is a thermally protective, toughened adhesion coating that mitigates effects of a hostile operating environment.
摘要翻译： 提供了用于复合结构的高温杂化分子官能团粘合屏障涂层。 涂层具有连接到复合结构的复合表面的一个或多个杂化分子官能团，其中一个或多个杂化分子官能团通过化学衍生化过程进行杂交。 涂层还具有通过缩合反应连接到一个或多个杂化分子官能团的一种或多种化学衍生化合物。 该涂层耐高温约350华氏度至约2000华氏度的温度，该涂层是一种耐热韧性增强的粘合涂层，可减轻恶劣的操作环境的影响。
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