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11.发明授权Methods for fabricating fiber-reinforced plastic test specimen assemblies having weak adhesive bonds 有权制造具有较弱粘合剂粘合力的纤维增强塑料试样组件的方法公开(公告)号：US08342017B1
公开(公告)日：2013-01-01
申请号：US12908032
申请日：2010-10-20
Applicant: Richard Henry Bossi , Marc J. Piehl , Douglas Allen Frisch , Kay Y. Blohowiak , William B. Grace , Peter J. Van Voast
Inventor： Richard Henry Bossi , Marc J. Piehl , Douglas Allen Frisch , Kay Y. Blohowiak , William B. Grace , Peter J. Van Voast
IPC: G01N19/04
CPC classification number: G01N19/04 , G01N3/62 , G01N2001/2893 , G01N2203/021
Abstract: A method for repeatably fabricating a test specimen assembly comprising a pair of fiber-reinforced plastic (FRP) test specimens adhesively bonded together, the bonded joint having respective areas of substantially different, but consistent variable adhesive bond strengths suitable as a calibration standard. The method comprises fabricating a first FRP test specimen having a bonding surface with first and second areas that have substantially different bonded joint performance-governing characteristics and then using adhesive to bond the bonding surface of the first FRP test specimen to the bonding surface of a second FRP test specimen. The different bonded joint performance-governing characteristics are achieved by treating first and second areas of the surface of the first FRP test specimen using different respective surface preparation techniques.
Abstract translation: 一种用于重复制造测试样品组件的方法，包括一对粘合在一起的纤维增强塑料（FRP）试样，所述粘合接头具有适合作为校准标准的大致不同但一致的可变粘合剂粘合强度的相应区域。 该方法包括制造具有第一和第二区域的接合表面的第一FRP试样，所述第一和第二区域具有基本上不同的接合接头性能控制特性，然后使用粘合剂将第一FRP试样的接合表面粘合到第二FRP试样的接合表面 FRP试样。 通过使用不同的各自的表面处理技术处理第一FRP试样的表面的第一和第二区域来实现不同的接合接头性能调节特性。
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12.发明申请公开(公告)号：US20120180942A1
公开(公告)日：2012-07-19
申请号：US13436631
申请日：2012-03-30
Applicant: Michael R. Chapman , Robert M. Watson , Donald A. Anderson , Marc J. Piehl , Joseph L. Sweetin , Douglas L. Grose
Inventor： Michael R. Chapman , Robert M. Watson , Donald A. Anderson , Marc J. Piehl , Joseph L. Sweetin , Douglas L. Grose
CPC classification number: B29C70/323 , B29C70/386 , B29D99/0014 , B29L2031/3082 , B64C1/068 , B64C1/12 , B64F5/10 , Y02T50/43 , Y10T156/1028 , Y10T156/1348 , Y10T156/1702 , Y10T156/1754 , Y10T156/1788 , Y10T156/1795
Abstract: Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections, are disclosed herein. A method for manufacturing a shell structure in accordance with one embodiment of the invention includes applying composite material to an interior mold surface of a tool to form a skin extending 360 degrees around an axis. The method can further include positioning a plurality of stiffeners on an inner surface of the skin. After the stiffeners have been positioned, a vacuum bag can be installed over the stiffeners and evacuated to press the stiffeners and the skin outwardly against the interior mold surface of the tool. Next, the skin/stiffener combination can be cocured to bond the stiffeners to the skin and harden the shell structure.
Abstract translation: 本文公开了用于飞机机身和其他结构的复合部分，以及用于制造这种部分的方法和系统。 根据本发明的一个实施例的用于制造壳结构的方法包括将复合材料施加到工具的内部模具表面以形成围绕轴线360度延伸的皮肤。 该方法还可以包括将多个加强件定位在皮肤的内表面上。 在加强件已经定位之后，真空袋可以安装在加强件的上方并抽真空以将加强件和皮肤向外压靠在工具的内部模具表面上。 接下来，可以将皮肤/加强件组合物共固化以将加强件粘合到皮肤上并硬化壳体结构。
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公开(公告)号：US20110039057A1
公开(公告)日：2011-02-17
申请号：US12542594
申请日：2009-08-17
Applicant: Douglas A. Frisch , Marc J. Piehl , Kava S. Crosson-Elturan , Kirk B. Kajita
Inventor： Douglas A. Frisch , Marc J. Piehl , Kava S. Crosson-Elturan , Kirk B. Kajita
CPC classification number: B29C70/226 , B29C70/342 , B29C70/443 , B29C70/545 , B29L2031/06 , B29L2031/3082 , B32B1/08 , B32B3/28 , B32B5/02 , B32B5/12 , B32B5/24 , B32B7/03 , B32B7/05 , B32B9/007 , B32B9/04 , B32B27/06 , B32B27/38 , B32B2250/44 , B32B2260/021 , B32B2260/046 , B32B2262/02 , B32B2262/106 , B32B2307/30 , B32B2307/50 , B32B2307/58 , B32B2597/00 , B32B2605/18 , B64C1/064 , B64C1/12 , B64C2001/0072 , Y02T50/43 , Y10T156/10 , Y10T156/1052 , Y10T428/24033 , Y10T428/292 , Y10T428/2933
Abstract: A laminated composite rod includes a rod body having a generally circular or oval cross-section and comprising a plurality of laminated composite plies disposed at various orientations with respect to each other.
Abstract translation: 层叠复合棒包括具有大致圆形或椭圆形横截面的杆体，并且包括以相对于彼此的各种取向设置的多个层压复合层。
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公开(公告)号：US07115323B2
公开(公告)日：2006-10-03
申请号：US10650231
申请日：2003-08-28
Applicant: Willard Westre , David W. Evans , Edward Li , Marc J. Piehl , Eric Sager
Inventor： Willard Westre , David W. Evans , Edward Li , Marc J. Piehl , Eric Sager
CPC classification number: B32B15/08 , B32B3/14 , B32B7/12 , B32B38/08 , B32B2260/021 , B32B2260/046 , Y02T50/43 , Y10T156/1089 , Y10T156/109 , Y10T156/1092 , Y10T156/1093 , Y10T428/1234 , Y10T428/12444 , Y10T428/19 , Y10T428/192 , Y10T428/197 , Y10T428/24752
Abstract: Laminate structures and methods for forming same are disclosed. In one embodiment, a laminate structure includes a metal-polymer composite lamina. The metal-polymer composite lamina has a first face and a second face spaced apart, and extends to a terminal edge. The lamina includes a ply of fiber-reinforced polymer that extends between the first face and the second face and has an interior edge. The interior edge defines at least one cutout. A ply of metal foil extends between the first face and the second face substantially from the interior edge filling the at least one cutout.
Abstract translation: 公开了层合结构及其形成方法。 在一个实施方案中，层压结构包括金属 - 聚合物复合层。 金属 - 聚合物复合薄片具有间隔开的第一表面和第二表面，并且延伸到末端边缘。 薄片包括在第一面和第二面之间延伸并具有内部边缘的纤维增强聚合物层。 内部边缘限定至少一个切口。 一层金属箔基本上从填充至少一个切口的内边缘在第一面和第二面之间延伸。
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公开(公告)号：US08418962B2
公开(公告)日：2013-04-16
申请号：US12017009
申请日：2008-01-19
Applicant: Marc. J. Piehl , Douglas A. Frisch , Kirk B. Kajita
Inventor： Marc. J. Piehl , Douglas A. Frisch , Kirk B. Kajita
IPC: B64C1/06
CPC classification number: B32B3/18 , B64C1/12 , B64C7/00 , Y10T428/24149
Abstract: Composite panels used in aircraft are formed by a sandwich including a lightweight honeycomb core reinforced by a solid plank in medial regions of the panel. The plank is bonded to the honeycomb and forms an integral part of the core where a strut is attached to the panel. The plank distributes point loads imposed on the panel by the strut.
Abstract translation: 飞机中使用的复合板由三明治形成，其包括由板的内侧区域中的固体板加强的轻质蜂窝芯。 木板粘结在蜂窝上，并形成芯子的一部分，其中支柱连接到面板上。 板条通过支柱分配施加在面板上的点载荷。
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Patent Agency Ranking
公开(公告)号：US20090142130A1
公开(公告)日：2009-06-04
申请号：US11948042
申请日：2007-11-30
Applicant: Douglas A. Frisch , Marc J. Piehl , Douglas L. Grose , Joseph L. Sweetin , Michael R. Chapman
Inventor： Douglas A. Frisch , Marc J. Piehl , Douglas L. Grose , Joseph L. Sweetin , Michael R. Chapman
CPC classification number: F16B11/006 , E04C2/243 , Y10T156/1064 , Y10T156/1066 , Y10T156/1082 , Y10T403/39 , Y10T403/47 , Y10T403/472
Abstract: Embodiments of methods and apparatus for providing a double shear joint for bonding in structural applications are disclosed. In one embodiment, a bonded composite joint includes a base having a foot configured to couple to a member, the base including a flange extending outward from the foot. The joint further includes a panel having a core configured between opposing skins, the skins having inner walls proximate the core, the skins extending outward beyond the core on at least one end of the panel to define a recess between the skins, the recess configured to receive the flange. A bonding agent is used to couple the flange to the inner walls of the panel.
Abstract translation: 公开了用于在结构应用中提供用于接合的双剪切接头的方法和装置的实施例。 在一个实施例中，粘合的复合接头包括具有构造成联接到构件的脚的基部，该基部包括从脚向外延伸的凸缘。 该接合部还包括具有在相对表面之间配置的芯的面板，所述表层具有靠近芯的内壁，所述表面在所述面板的至少一个端部上向外延伸超过所述芯，以在所述表层之间限定凹陷， 接收法兰。 使用粘合剂将凸缘连接到面板的内壁。
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17.发明申请公开(公告)号：US20080138584A1
公开(公告)日：2008-06-12
申请号：US11965410
申请日：2007-12-27
Applicant: Douglas L. Grose , Marc J. Piehl , Douglas A. Frisch , Joseph L. Sweetin , Gary J. Peffers
Inventor： Douglas L. Grose , Marc J. Piehl , Douglas A. Frisch , Joseph L. Sweetin , Gary J. Peffers
IPC: B32B3/00
CPC classification number: B32B3/04 , B29C70/088 , B29C70/342 , B29D99/001 , B29D99/0021 , B32B3/02 , B32B3/08 , B32B5/12 , B32B27/08 , B32B27/12 , B32B27/18 , B32B2250/40 , B32B2250/44 , B32B2307/718 , B32B2607/00 , Y02T50/43 , Y10T428/195 , Y10T428/236 , Y10T428/24091 , Y10T428/24132 , Y10T428/24479 , Y10T428/24612 , Y10T428/24777 , Y10T428/249923
Abstract: A composite member with a reinforced rampdown or taper has a composite noodle bonded to an end of a core to fill the taper.
Abstract translation: 具有加强斜坡或锥形的复合构件具有结合到芯的端部以填充锥形的复合面。
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公开(公告)号：US08088242B2
公开(公告)日：2012-01-03
申请号：US12728720
申请日：2010-03-22
Applicant: Douglas A. Frisch , Marc J. Piehl , Douglas L. Grose , Joseph L. Sweetin , Michael R. Chapman
Inventor： Douglas A. Frisch , Marc J. Piehl , Douglas L. Grose , Joseph L. Sweetin , Michael R. Chapman
CPC classification number: F16B11/006 , E04C2/243 , Y10T156/1064 , Y10T156/1066 , Y10T156/1082 , Y10T403/39 , Y10T403/47 , Y10T403/472
Abstract: A bonded composite joint may include a base having a foot configured to couple to a member. The base may include a flange extending outward from the foot. The joint further may include a panel having a core positioned between opposing skins, where the skins have inner walls proximate the core and the skins extend outward beyond the core on at least one end of the panel to define a recess between the skins. The recess between the skins may receive the flange. A bonding agent may be used to couple the flange to the inner walls of the panel.
Abstract translation: 粘合复合接头可以包括具有构造成联接到构件的脚的基部。 底座可以包括从脚部向外延伸的凸缘。 接头还可以包括具有定位在相对的表面之间的芯的面板，其中表层具有靠近芯的内壁，并且表层在面板的至少一个端部上向外延伸超过芯，以在表皮之间限定凹陷。 表皮之间的凹槽可以接收凸缘。 可以使用粘合剂将凸缘连接到面板的内壁。
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公开(公告)号：US07997530B2
公开(公告)日：2011-08-16
申请号：US12138161
申请日：2008-06-12
Applicant: Douglas A. Frisch , Marc J. Piehl , Kirk B. Kajita
Inventor： Douglas A. Frisch , Marc J. Piehl , Kirk B. Kajita
IPC: B64C17/00
CPC classification number: B64C1/1446 , B64C7/00 , F16B9/026
Abstract: An airplane fairing panel adjustable fitting assembly allows for installation and removal of a fairing panel from outside the fairing. Blind retention features are provided and a pivoting link structure is facilitated to accommodate flexing of an aircraft structure in use. Kits and methods of attaching fairing panels are also disclosed.
Abstract translation: 飞机整流面板可调式接头组件允许从整流罩外部安装和拆卸整流罩。 提供了盲的保持特征，并且有利于枢转连杆结构以适应使用中的飞行器结构的弯曲。 还公开了安装整流罩的套件和方法。
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公开(公告)号：US20090314894A1
公开(公告)日：2009-12-24
申请号：US12138161
申请日：2008-06-12
Applicant: Douglas A. Frisch , Marc J. Piehl , Kirk B. Kajita
Inventor： Douglas A. Frisch , Marc J. Piehl , Kirk B. Kajita
IPC: B64C1/06
CPC classification number: B64C1/1446 , B64C7/00 , F16B9/026
Abstract: An airplane fairing panel adjustable fitting assembly allows for installation and removal of a fairing panel from outside the fairing. Blind retention features are provided and a pivoting link structure is facilitated to accommodate flexing of an aircraft structure in use. Kits and methods of attaching fairing panels are also disclosed.
Abstract translation: 飞机整流面板可调式接头组件允许从整流罩外部安装和拆卸整流罩。 提供了盲的保持特征，并且有利于枢转连杆结构以适应使用中的飞行器结构的弯曲。 还公开了安装整流罩的套件和方法。
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