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公开(公告)号：US08034268B2
公开(公告)日：2011-10-11
申请号：US12051596
申请日：2008-07-29
CPC分类号： B29C44/16 , B29C70/342 , B29C70/44 , B29C70/865 , B32B3/04 , B32B5/18 , B32B27/065 , B32B27/18 , B32B27/38 , B32B2262/106 , B32B2266/0271 , B32B2307/308 , B32B2307/718 , B32B2605/18 , Y10T428/233 , Y10T428/249953 , Y10T428/249987
摘要： A lightweight composite fairing bar (14) for use in fabricating a composite component (16) of an aircraft. The fairing bar (14) includes a core (18) and an elongated outer shell (20) surrounding the core (18). The outer shell (20) is comprised of a laminate material, and the core (18) is comprised of epoxy syntactic foam having a lower density than that of the laminate material. The outer shell (20) is configured for supporting the composite component (16) during the manufacture of the same.
摘要翻译： 一种用于制造飞行器的复合部件（16）的轻型复合整流罩（14）。 整流罩（14）包括芯（18）和围绕芯（18）的细长外壳（20）。 外壳（20）由层压材料构成，芯部（18）由密封比层压材料低的环氧复合泡沫构成。 外壳（20）构造成在其制造过程中支撑复合部件（16）。
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公开(公告)号：US07416401B2
公开(公告)日：2008-08-26
申请号：US11160192
申请日：2005-06-13
CPC分类号： B29C44/16 , B29C70/342 , B29C70/44 , B29C70/865 , B32B3/04 , B32B5/18 , B32B27/065 , B32B27/18 , B32B27/38 , B32B2262/106 , B32B2266/0271 , B32B2307/308 , B32B2307/718 , B32B2605/18 , Y10T428/233 , Y10T428/249953 , Y10T428/249987
摘要： A lightweight composite fairing bar (14) for use in fabricating a composite component (16) of an aircraft. The fairing bar (14) includes a core (18) and an elongated outer shell (20) surrounding the core (18). The outer shell (20) is comprised of a laminate material, and the core (18) is comprised of epoxy syntactic foam having a lower density than that of the laminate material. The outer shell (20) is configured for supporting the composite component (16) during the manufacture of the same.
摘要翻译： 一种用于制造飞行器的复合部件（16）的轻型复合整流罩（14）。 整流罩（14）包括芯（18）和围绕芯（18）的细长外壳（20）。 外壳（20）由层压材料构成，芯部（18）由密封比层压材料低的环氧复合泡沫构成。 外壳（20）构造成在其制造过程中支撑复合部件（16）。
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公开(公告)号：US07571527B2
公开(公告)日：2009-08-11
申请号：US10907320
申请日：2005-03-29
申请人： John L. Burnett , David W. Hackler , Timothy C. Wilson , John M. Welch , Thomas D. Popp , Christopher S. Sawyer , Leo B. Hoadley , Leroy J. Fulbright , Mitchel B. Granger , Barry B. Craig , Phillip E. Kenney
发明人： John L. Burnett , David W. Hackler , Timothy C. Wilson , John M. Welch , Thomas D. Popp , Christopher S. Sawyer , Leo B. Hoadley , Leroy J. Fulbright , Mitchel B. Granger , Barry B. Craig , Phillip E. Kenney
CPC分类号： F02K3/04 , B21D53/92 , F05D2230/20 , F05D2230/23 , F05D2230/64 , Y02T50/672 , Y10T29/37 , Y10T29/49629 , Y10T29/49815 , Y10T29/49826 , Y10T29/49867 , Y10T29/49895 , Y10T29/49902 , Y10T29/53961 , Y10T29/53983
摘要： A mandrel is disclosed for fabricating a monolithic composite nacelle panel for use on an airplane. Also disclosed is the method of constructing the mandrel, the method of assembling the mandrel, and the method of disassembling the mandrel.
摘要翻译： 公开了一种用于制造在飞机上使用的整体式复合机舱面板的心轴。 还公开了构造心轴的方法，组装心轴的方法以及拆卸心轴的方法。
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4.发明申请METHOD OF CONSTRUCTING A MANDREL FOR FABRICATION OF A MONOLITHIC NACELLE COMPOSITE PANEL 有权构造用于制造单层复合材料面板的手段的方法公开(公告)号：US20090172936A1
公开(公告)日：2009-07-09
申请号：US12400003
申请日：2009-03-09
申请人： John L. Burnett , David W. Hackler , Timothy C. Wilson , John M. Welch , Thomas D. Popp , Christopher S. Sawyer , Leo B. Hoadley , Leroy J. Fulbright , Mitchel B. Granger , Barry B. Craig , Phillip E. Kenney
发明人： John L. Burnett , David W. Hackler , Timothy C. Wilson , John M. Welch , Thomas D. Popp , Christopher S. Sawyer , Leo B. Hoadley , Leroy J. Fulbright , Mitchel B. Granger , Barry B. Craig , Phillip E. Kenney
CPC分类号： F02K3/04 , B21D53/92 , F05D2230/20 , F05D2230/23 , F05D2230/64 , Y02T50/672 , Y10T29/37 , Y10T29/49629 , Y10T29/49815 , Y10T29/49826 , Y10T29/49867 , Y10T29/49895 , Y10T29/49902 , Y10T29/53961 , Y10T29/53983
摘要： A method of constructing, assembling and disassembling a mandrel for fabricating a monolithic composite nacelle panel for use on an airplane comprises attaching a first fairing bar including an exposed ball roller assembly to a tilting plate; attaching a first outer section to said first fairing bar; attaching a second outer section to said first fairing bar; attaching a center section to said first outer section and said second outer section; attaching a nozzle section to said first fairing bar and positioned adjacent an inner wall of said first outer section, an inner wall of said center section, and an inner wall of said second outer section; attaching a second fairing bar to said first outer section, said center section, and said second outer section; and attaching a cavity section to said second fairing bar.
摘要翻译： 一种构造，组装和拆卸用于制造用于飞机上的整体式复合机舱面板的心轴的方法，包括：将包括露出的滚珠滚筒组件的第一整流罩附接到倾斜板; 将第一外部部分附接到所述第一整流罩; 将第二外部部分附接到所述第一整流罩; 将中心部分附接到所述第一外部部分和所述第二外部部分; 将喷嘴部分附接到所述第一整流罩并且定位成邻近所述第一外部部分的内壁，所述中心部分的内壁和所述第二外部部分的内壁; 将第二整流罩附接到所述第一外部部分，所述中心部分和所述第二外部部分; 以及将空腔部分附接到所述第二整流罩。
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5.发明授权公开(公告)号：US07963039B2
公开(公告)日：2011-06-21
申请号：US12400003
申请日：2009-03-09
申请人： John L. Burnett , David W. Hackler , Timothy C. Wilson , John M. Welch , Thomas D. Popp , Christopher S. Sawyer , Leo B. Hoadley , Leroy J. Fulbright , Mitchel B. Granger , Barry B. Craig , Phillip E. Kenney
发明人： John L. Burnett , David W. Hackler , Timothy C. Wilson , John M. Welch , Thomas D. Popp , Christopher S. Sawyer , Leo B. Hoadley , Leroy J. Fulbright , Mitchel B. Granger , Barry B. Craig , Phillip E. Kenney
CPC分类号： F02K3/04 , B21D53/92 , F05D2230/20 , F05D2230/23 , F05D2230/64 , Y02T50/672 , Y10T29/37 , Y10T29/49629 , Y10T29/49815 , Y10T29/49826 , Y10T29/49867 , Y10T29/49895 , Y10T29/49902 , Y10T29/53961 , Y10T29/53983
摘要： A method of constructing, assembling and disassembling a mandrel for fabricating a monolithic composite nacelle panel for use on an airplane comprises attaching a first fairing bar including an exposed ball roller assembly to a tilting plate; attaching a first outer section to said first fairing bar; attaching a second outer section to said first fairing bar; attaching a center section to said first outer section and said second outer section; attaching a nozzle section to said first fairing bar and positioned adjacent an inner wall of said first outer section, an inner wall of said center section, and an inner wall of said second outer section; attaching a second fairing bar to said first outer section, said center section, and said second outer section; and attaching a cavity section to said second fairing bar.
摘要翻译： 一种构造，组装和拆卸用于制造用于飞机上的整体式复合机舱面板的心轴的方法，包括：将包括露出的滚珠滚筒组件的第一整流罩附接到倾斜板; 将第一外部部分附接到所述第一整流罩; 将第二外部部分附接到所述第一整流罩; 将中心部分附接到所述第一外部部分和所述第二外部部分; 将喷嘴部分附接到所述第一整流罩并且定位成邻近所述第一外部部分的内壁，所述中心部分的内壁和所述第二外部部分的内壁; 将第二整流罩附接到所述第一外部部分，所述中心部分和所述第二外部部分; 以及将空腔部分附接到所述第二整流罩。
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公开(公告)号：US5020714A
公开(公告)日：1991-06-04
申请号：US336900
申请日：1989-04-12
申请人： Larry N. Miles , Cecil A. Drinnen , David W. Hackler , Tom L. Bogart , Arnold D. Macklin , Ben E. Sharpsteen , Truett M. Hyles , Herschel M. Stephens
发明人： Larry N. Miles , Cecil A. Drinnen , David W. Hackler , Tom L. Bogart , Arnold D. Macklin , Ben E. Sharpsteen , Truett M. Hyles , Herschel M. Stephens
IPC分类号： B23K37/04
CPC分类号： B23K37/0443 , B23K37/04
摘要： A method and apparatus for applying variable pressure to selected areas of a bonding assembly jig to shape a face plate to conform to the contours of contoured heads and hold the face plate in place for welding comprises two inverted U-shaped support frames including two spaced apart elongated vertical support members each having a bottom end and a top end, an elongated horizontal top beam extending between and connecting the top ends of the vertical support members, a track extending between and adjustably fastened to the horizontal top beam, and at least one hydraulic press slidably suspended from the track and adapted to apply pressure to a bonding assembly jig. The support frames are provided with wheels and one of the support frames has vertical support members spaced at a distance less that of the other support frame. This arrangement allows the tracks of each frame to be positioned proximate to each other above a bonding assembly jig.
摘要翻译： 将可变压力施加到粘合组装夹具的选定区域以形成面板以符合成型头部的轮廓并将面板保持在适当位置用于焊接的方法和装置包括两个倒置的U形支撑框架，包括两个间隔开的 每个具有底端和顶端的细长垂直支撑构件，在垂直支撑构件的顶端之间延伸并连接垂直支撑构件的顶端的细长水平顶梁，在水平顶梁之间延伸并可调节地紧固到水平顶梁的轨道，以及至少一个液压 按压可滑动地悬挂在轨道上，并适用于对接合组件夹具施加压力。 支撑框架设置有轮子，并且支撑框架中的一个支撑框架具有以比另一个支撑框架的距离更小的距离间隔开的垂直支撑构件。 这种布置允许每个框架的轨道在接合组件夹具上方彼此靠近彼此定位。
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