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公开(公告)号：US20170225769A1
公开(公告)日：2017-08-10
申请号：US15423888
申请日：2017-02-03
CPC分类号： B29C70/34 , B29C35/02 , B29C65/48 , B29C70/06 , B29C70/30 , B29C70/545 , B29C2793/009 , B29D99/001 , B29D99/0089 , B29L2031/3076 , B29L2031/3085 , B32B3/12 , B32B7/12 , B32B2250/05 , B32B2305/024 , B32B2605/18 , B64C1/12 , B64C3/185 , B64C3/24 , B64C3/26 , B64C29/0033 , B64F5/00 , B64F5/10 , Y02T50/43
摘要： A method of manufacturing a tiltrotor wing structure including providing a spar mold having a plurality of bores extending from an exterior surface of the mold to an interior surface of the mold, the plurality of bores corresponding to a plurality of primary coordination holes in a spar member, the spar mold having a periphery defined by a top edge, a bottom edge and outboard ends; selecting a plurality of resin impregnated plies to ensure that the plies continuously extend beyond the periphery of the spar mold; laying the plies in the spar mold; curing the plies in the mold to form a cured spar member that extends beyond the periphery of the spar mold; and accurately drilling a plurality of primary coordination holes in the cured spar member in the spar mold using a tool positioned in the plurality of bores.
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12.发明申请公开(公告)号：US20150048213A1
公开(公告)日：2015-02-19
申请号：US13966678
申请日：2013-08-14
CPC分类号： B64C29/0033
摘要： A tiltrotor aircraft includes a fuselage; a wing member having a first rib, a second rib, a first spar, second spar; and an upper wing skin; an engine disposed at a fixed location relative to the wing member; and a proprotor having a spindle gearbox, rotor mast, and a plurality of rotor blades drivable in rotation about the rotor mast, the spindle gearbox being rotatable about a conversion axis. The spindle gearbox is located above the upper wing skin of the wing member.
摘要翻译： 一架俯仰式飞机包括机身; 翼构件，具有第一肋，第二肋，第一翼梁，第二翼梁; 和上翼皮; 设置在相对于翼构件的固定位置的发动机; 以及具有主轴齿轮箱，转子桅杆和可围绕转子桅杆旋转驱动的多个转子叶片的推进器，所述主轴齿轮箱可围绕转换轴线旋转。 主轴齿轮箱位于机翼构件的上翼面上方。
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公开(公告)号：US20210308926A1
公开(公告)日：2021-10-07
申请号：US17242014
申请日：2021-04-27
IPC分类号： B29C48/05 , B29C63/00 , B64C11/16 , B32B27/02 , B64C3/00 , B29C70/52 , B29C64/118 , B29C33/38 , B64F5/10 , B29C65/78 , B29C65/00 , B25B11/02 , B29C70/54
摘要： In one embodiment, a method includes fastening a plurality of components of a composite structure in an assembly fixture, wherein the assembly fixture comprises a plurality of strands of a fiber-reinforced thermoplastic material, wherein the fiber-reinforced thermoplastic material comprises a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands, and wherein the assembly fixture further comprises an anisotropic thermal expansion property based on an orientation of the plurality of reinforcement fibers within the assembly fixture; and heating the assembly fixture in an autoclave to bond the plurality of components of the composite structure.
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公开(公告)号：US11077596B2
公开(公告)日：2021-08-03
申请号：US16814622
申请日：2020-03-10
IPC分类号： B29C65/00 , B29C48/05 , B29C63/00 , B64C11/16 , B32B27/02 , B64C3/00 , B29C70/52 , B29C64/118 , B29C33/38 , B64F5/10 , B29C65/78 , B25B11/02 , B29C70/54 , B29K105/10 , B29K105/14 , B29L31/00 , B29L31/08 , B29L31/30
摘要： In one embodiment, an assembly fixture may include a base structure including a plurality of strands of a fiber-reinforced thermoplastic material comprising a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands, and wherein the base structure further comprises an anisotropic thermal expansion property based on an orientation of the plurality of reinforcement fibers within the base structure, The assembly fixture may further include a plurality of fastening structures coupled to the base structure, wherein the plurality of fastening structures is configured to fasten a plurality of components of a composite structure for assembly using a heated bonding process.
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公开(公告)号：US20200346382A1
公开(公告)日：2020-11-05
申请号：US16814622
申请日：2020-03-10
IPC分类号： B29C48/05 , B29C63/00 , B64C11/16 , B32B27/02 , B64C3/00 , B29C70/52 , B29C64/118 , B29C33/38
摘要： In one embodiment, an assembly fixture may include a base structure including a plurality of strands of a fiber-reinforced thermoplastic material comprising a thermoplastic embedded with a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is aligned within each strand of the plurality of strands, and wherein the base structure further comprises an anisotropic thermal expansion property based on an orientation of the plurality of reinforcement fibers within the base structure, The assembly fixture may further include a plurality of fastening structures coupled to the base structure, wherein the plurality of fastening structures is configured to fasten a plurality of components of a composite structure for assembly using a heated bonding process.
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公开(公告)号：US10654208B2
公开(公告)日：2020-05-19
申请号：US15710797
申请日：2017-09-20
IPC分类号： B29C41/02 , B29C48/05 , B29C63/00 , B64C11/16 , B32B27/02 , B64C3/00 , B29C70/52 , B29C64/118 , B29C33/38 , B29K105/10 , B29K105/14 , B29L31/00
摘要： In one embodiment, a method may comprise heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic and a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is randomly arranged within the thermoplastic. The method may further comprise extruding a plurality of strands of the composite material, wherein extruding the plurality of strands causes the plurality of reinforcement fibers within each strand to align. The method may further comprise arranging the plurality of strands of the composite material to form an assembly fixture, wherein the assembly fixture comprises an anisotropic thermal expansion property, and wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the assembly fixture.
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公开(公告)号：US20190084192A1
公开(公告)日：2019-03-21
申请号：US15710811
申请日：2017-09-20
发明人： David G. Carlson
IPC分类号： B29C33/38
摘要： In one embodiment, a method may comprise heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic and a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is randomly arranged within the thermoplastic. The method may further comprise extruding a plurality of strands of the composite material, wherein extruding the plurality of strands causes the plurality of reinforcement fibers within each strand to align. The method may further comprise arranging the plurality of strands of the composite material to form a mold tool, wherein the mold tool is configured to mold a composite structure at a heated temperature, and wherein the mold tool comprises an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the mold tool.
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公开(公告)号：US20180001579A1
公开(公告)日：2018-01-04
申请号：US15423939
申请日：2017-02-03
IPC分类号： B29C70/34 , B29C70/54 , B29C35/02 , B29C70/06 , B29D99/00 , B29L31/30 , B64C1/12 , B64C3/26 , B64C29/00
CPC分类号： B29C70/34 , B29C35/02 , B29C65/48 , B29C70/06 , B29C70/30 , B29C70/545 , B29C2793/009 , B29D99/001 , B29D99/0089 , B29L2031/3076 , B29L2031/3085 , B32B3/12 , B32B7/12 , B32B2250/05 , B32B2305/024 , B32B2605/18 , B64C1/12 , B64C3/185 , B64C3/24 , B64C3/26 , B64C29/0033 , B64F5/00 , B64F5/10 , Y02T50/43
摘要： In one aspect, there is a method of making a pre-cured laminate having a total number of plies in a mold, the mold having a periphery defined by a forward edge, an aft edge, and outboard ends. The method includes selecting a first plurality of resin impregnated plies that continuously extend beyond the periphery of the mold, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies; laying the plies in a mold; compacting the plies in a mold; and pre-curing the plies to form a pre-cured laminate, which can extend beyond the periphery of the mold. In an embodiment, a pre-cured laminate includes a first plurality of resin impregnated plies that continuously extend beyond the periphery of the mold, the first plurality of resin impregnated plies includes at least 50 percent of the total number of plies.
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公开(公告)号：US20170225765A1
公开(公告)日：2017-08-10
申请号：US15424588
申请日：2017-02-03
IPC分类号： B64C3/18
摘要： In one aspect, there is provided a spar member for an aircraft wing including a support beam having an interior surface, an exterior surface, and opposing ends configured for an aircraft wing, the interior surface and exterior surface disposed between the opposing ends; and a first spar flange extending generally laterally from the exterior surface, the first spar flange configured for attachment with a first wing skin. The first spar flange can be an upper or lower spar flange. In some embodiments, the first spar flange is at an acute angle relative to the exterior surface of the support beam. In certain embodiments, the first spar flange is at an angle of from about 50 degrees to about 85 degrees relative to the exterior surface of the support beam.
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公开(公告)号：US11123900B2
公开(公告)日：2021-09-21
申请号：US15710811
申请日：2017-09-20
发明人： David G. Carlson
摘要： In one embodiment, a method may comprise heating a composite material into a viscous form, wherein the composite material comprises a thermoplastic and a plurality of reinforcement fibers, wherein the plurality of reinforcement fibers is randomly arranged within the thermoplastic. The method may further comprise extruding a plurality of strands of the composite material, wherein extruding the plurality of strands causes the plurality of reinforcement fibers within each strand to align. The method may further comprise arranging the plurality of strands of the composite material to form a mold tool, wherein the mold tool is configured to mold a composite structure at a heated temperature, and wherein the mold tool comprises an anisotropic thermal expansion property, wherein the anisotropic thermal expansion property is based on an orientation of the plurality of reinforcement fibers within the mold tool.
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