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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
CPC分类号： F16B11/006 , E04C2/243 , Y10T156/1064 , Y10T156/1066 , Y10T156/1082 , Y10T403/39 , Y10T403/47 , Y10T403/472
摘要： 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.
摘要翻译： 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
IPC分类号： B64C1/14
CPC分类号： F16B11/006 , E04C2/243 , Y10T156/1064 , Y10T156/1066 , Y10T156/1082 , Y10T403/39 , Y10T403/47 , Y10T403/472
摘要： 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.
摘要翻译： 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：US20090142130A1
公开(公告)日：2009-06-04
申请号：US11948042
申请日：2007-11-30
CPC分类号： F16B11/006 , E04C2/243 , Y10T156/1064 , Y10T156/1066 , Y10T156/1082 , Y10T403/39 , Y10T403/47 , Y10T403/472
摘要： 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.
摘要翻译： 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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公开(公告)号：US08088242B2
公开(公告)日：2012-01-03
申请号：US12728720
申请日：2010-03-22
CPC分类号： F16B11/006 , E04C2/243 , Y10T156/1064 , Y10T156/1066 , Y10T156/1082 , Y10T403/39 , Y10T403/47 , Y10T403/472
摘要： 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.
摘要翻译： 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：US20080138584A1
公开(公告)日：2008-06-12
申请号：US11965410
申请日：2007-12-27
IPC分类号： B32B3/00
CPC分类号： 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
摘要： A composite member with a reinforced rampdown or taper has a composite noodle bonded to an end of a core to fill the taper.
摘要翻译： 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：US08084114B2
公开(公告)日：2011-12-27
申请号：US11965410
申请日：2007-12-27
CPC分类号： 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
摘要： A composite member with a reinforced rampdown or taper has a composite noodle bonded to an end of a core to fill the taper.
摘要翻译： 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：US07531058B2
公开(公告)日：2009-05-12
申请号：US11065350
申请日：2005-02-24
CPC分类号： 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
摘要： A composite member with a reinforced rampdown or taper has a composite noodle bonded to an end of a core to fill the taper.
摘要翻译： 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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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
申请人： Michael R. Chapman , Robert M. Watson , Donald A. Anderson , Marc J. Piehl , Joseph L. Sweetin , Douglas L. Grose
发明人： Michael R. Chapman , Robert M. Watson , Donald A. Anderson , Marc J. Piehl , Joseph L. Sweetin , Douglas L. Grose
CPC分类号： 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
摘要： 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.
摘要翻译： 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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9.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
申请人： Michael R. Chapman , Robert M. Watson , Donald A. Anderson , Marc J. Piehl , Joseph L. Sweetin , Douglas L. Grose
发明人： Michael R. Chapman , Robert M. Watson , Donald A. Anderson , Marc J. Piehl , Joseph L. Sweetin , Douglas L. Grose
CPC分类号： 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
摘要： 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.
摘要翻译： 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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10.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
申请人： Michael R. Chapman , Robert M. Watson , Donald A. Anderson , Marc J. Piehl , Joseph L. Sweetin , Douglas L. Grose
发明人： Michael R. Chapman , Robert M. Watson , Donald A. Anderson , Marc J. Piehl , Joseph L. Sweetin , Douglas L. Grose
CPC分类号： 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
摘要： 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.
摘要翻译： 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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