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1.发明授权Methods for manufacturing composite sections for aircraft fuselages and other structures 有权制造飞机机身和其他结构的复合材料段的方法公开(公告)号：US08303758B2
公开(公告)日：2012-11-06
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: Methods for manufacturing composite sections for aircraft fuselages and other structures 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: 本文公开了用于制造飞机机身和其他结构的复合部分的方法。 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：US08084114B2
公开(公告)日：2011-12-27
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
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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3.发明申请COMPOSITE SECTIONS FOR AIRCRAFT FUSELAGES AND OTHER STRUCTURES, AND METHODS AND SYSTEMS FOR MANUFACTURING SUCH SECTIONS 有权飞机燃油和其他结构的组合部分，以及制造这些部分的方法和系统公开(公告)号：US20090139641A1
公开(公告)日：2009-06-04
申请号：US12367479
申请日：2009-02-06
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
IPC: B29C69/00
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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4.发明授权Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections 有权飞机机身和其他结构的复合部分，以及制造这些部分的方法和系统公开(公告)号：US07503368B2
公开(公告)日：2009-03-17
申请号：US10996922
申请日：2004-11-24
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：US07491289B2
公开(公告)日：2009-02-17
申请号：US11530582
申请日：2006-09-11
Applicant: Willard N. Westre , David W Evans , Edward Li , Marc J. Piehl , Eric Sager
Inventor： Willard N. 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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Patent Agency Ranking
公开(公告)号：US09090043B2
公开(公告)日：2015-07-28
申请号：US13197750
申请日：2011-08-03
Applicant: 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
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: B32B7/00 , B32B3/14 , B32B15/08 , B32B3/00 , B32B7/12 , B32B15/00 , B32B19/02 , B32B27/00 , B32B3/06
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: In an embodiment of the disclosure, there is provided a molybdenum composite hybrid laminate. The laminate has a plurality of composite material layers. The laminate further has a plurality of surface treated molybdenum foil layers interweaved between the composite material layers. The laminate further has a plurality of adhesive layers disposed between and bonding adjacent layers of the composite material layers and the molybdenum foil layers.
Abstract translation: 在本公开的一个实施方案中，提供了钼复合混合层合物。 层压体具有多个复合材料层。 层压体还具有交织在复合材料层之间的多个经表面处理的钼箔层。 层压体还具有多个粘合剂层，其设置在复合材料层和钼箔层之间并粘附在相邻的层之间。
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公开(公告)号：US20130034705A1
公开(公告)日：2013-02-07
申请号：US13197750
申请日：2011-08-03
Applicant: 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
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: B32B15/08 , H01R43/20 , B23P25/00 , B32B37/02 , B32B38/00 , B32B37/10 , B32B37/14 , B32B38/16 , C23F1/00 , B32B7/12 , B32B37/12
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: In an embodiment of the disclosure, there is provided a molybdenum composite hybrid laminate. The laminate has a plurality of composite material layers. The laminate further has a plurality of surface treated molybdenum foil layers interweaved between the composite material layers. The laminate further has a plurality of adhesive layers disposed between and bonding adjacent layers of the composite material layers and the molybdenum foil layers.
Abstract translation: 在本公开的一个实施方案中，提供了钼复合混合层合物。 层压体具有多个复合材料层。 层压体还具有交织在复合材料层之间的多个经表面处理的钼箔层。 层压体还具有多个粘合剂层，其设置在复合材料层和钼箔层之间并粘附在相邻的层之间。
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8.发明授权Composite sections for aircraft fuselages and other structures, and methods and systems for manufacturing such sections 有权飞机机身和其他结构的复合部分，以及制造这些部分的方法和系统公开(公告)号：US08168023B2
公开(公告)日：2012-05-01
申请号：US12367479
申请日：2009-02-06
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：US20100230042A1
公开(公告)日：2010-09-16
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：US07712993B2
公开(公告)日：2010-05-11
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
IPC: B64C1/14
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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