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公开(公告)号：US10604226B2
公开(公告)日：2020-03-31
申请号：US15488217
申请日：2017-04-14
摘要： An aircraft includes a composite structure, comprising an outer skin formed from a composite material and having a first thickness, an inner skin formed from a composite material and having a second thickness, the second thickness being greater than the first thickness, and a core structure positioned between the inner and outer skins to increase bending stiffness of the composite structure. During use a structural load carried by the inner skin exceeds a structural load carried by the outer skin.
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公开(公告)号：US10589837B2
公开(公告)日：2020-03-17
申请号：US15424588
申请日：2017-02-03
IPC分类号： B64C3/18 , F16B5/01 , F16B11/00 , B64F5/10 , B29C35/04 , B29C70/30 , B29C70/34 , B64C29/00 , B29K105/08 , B29L31/30
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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3.发明授权公开(公告)号：US09174731B2
公开(公告)日：2015-11-03
申请号：US13966678
申请日：2013-08-14
IPC分类号： B64C29/00
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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4.发明申请ROTOR BLADE AND STRUCTURAL SYSTEM FOR COUPLING THE ROTOR BLADE IN A ROTOR HUB 审中-公开用于将转子叶片连接在转子集线器中的转子叶片和结构系统公开(公告)号：US20150078909A1
公开(公告)日：2015-03-19
申请号：US14027733
申请日：2013-09-16
IPC分类号： F01D5/14
摘要： The rotor hub can include a rotor blade; a rotor yoke; a grip member having an inboard portion, an upper extension, and a lower extension; and a rotor blade having a root end coupled to the upper extension and the lower extension of the grip member with a first bolt, a second bolt, and a third bolt. The first bolt is located on a spanwise axis of the rotor blade. The second bolt is offset from the spanwise axis by a first chordwise distance and is offset from the first bolt by a first spanwise distance. The third bolt is offset from the spanwise axis by a second chordwise distance and is offset from the first bolt by a second spanwise distance.
摘要翻译： 转子轮毂可包括转子叶片; 转子轭; 具有内侧部分，上部延伸部和下部延伸部的握持部件; 以及转子叶片，其具有用第一螺栓，第二螺栓和第三螺栓联接到所述握持构件的上延伸部和下延伸部的根端。 第一螺栓位于转子叶片的翼展轴上。 第二螺栓与翼展方向轴线偏移第一弦向距离，并且与第一螺栓偏移第一横向距离。 第三螺栓与翼展方向轴线偏移第二弦向距离，并且从第一螺栓偏移第二横向距离。
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5.发明申请METHOD OF OPTIMIZING AND CUSTOMIZING ROTOR BLADE STRUCTURAL PROPERTIES BY TAILORING LARGE CELL COMPOSITE CORE AND A ROTOR BLADE INCORPORATING THE SAME 审中-公开通过定制大型细胞复合核心优化和定制转子叶片结构特性的方法和包含其的转子叶片公开(公告)号：US20140301856A1
公开(公告)日：2014-10-09
申请号：US14022524
申请日：2013-09-10
发明人： Paul K. Oldroyd , Wei-Yueh Lee , James D. Hethcock, JR. , John R. McCullough , Patrick R. Tisdale
IPC分类号： B64C27/473
CPC分类号： B64C27/473 , B64C3/20 , B64C2027/4736 , Y02T50/43 , Y10T29/49337
摘要： An airfoil member can have a root end, a tip end, a leading edge, and a trailing edge. The airfoil member can include an upper skin, a lower skin, and a composite core member having a plurality of cells, an upper surface network of the cells can be bonded to the upper skin, a lower surface network of the cells can be bonded to the lower skin. The composite core can have a septum layer embedded in the cells that form the composite core, the septum layer being configured to provide tailored characteristics of the airfoil member.
摘要翻译： 翼型构件可以具有根端，尖端，前缘和后缘。 翼型构件可以包括上皮，下皮和具有多个细胞的复合芯部件，细胞的上表面网络可以结合到上皮肤，细胞的下表面网络可以粘合到 较低的皮肤。 复合芯可以具有嵌入在形成复合芯的单元中的隔膜层，隔膜层被配置为提供翼型构件的定制特性。
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公开(公告)号：US10513324B2
公开(公告)日：2019-12-24
申请号：US15424095
申请日：2017-02-03
摘要： In one aspect, there is a rib assembly for an aircraft wing including a rib web having a top and a bottom, the rib web includes a first laminate, a second laminate, and a honeycomb panel having an array of large cells disposed between the first laminate and the second laminate, each cell having a width of at least 1 cm; and a plurality of skin flanges for fixedly attaching the rib web to a skin of the wing, each skin flange has a base member having a first portion and a second portion and a vertical member extending from the base member. The plurality of skin flanges can be attached to the top and the bottom of the rib web such that the second portion of the base member and the vertical member are attached to the rib web.
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公开(公告)号：US10399285B2
公开(公告)日：2019-09-03
申请号：US15423939
申请日：2017-02-03
IPC分类号： B29C70/34 , B29C35/02 , B29C70/54 , B29C70/06 , B29D99/00 , B64C1/12 , B64C3/26 , B29L31/30 , B64C29/00
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：US20180297685A1
公开(公告)日：2018-10-18
申请号：US15488217
申请日：2017-04-14
摘要： An aircraft includes a composite structure, comprising an outer skin formed from a composite material and having a first thickness, an inner skin formed from a composite material and having a second thickness, the second thickness being greater than the first thickness, and a core structure positioned between the inner and outer skins to increase bending stiffness of the composite structure. During use a structural load carried by the inner skin exceeds a structural load carried by the outer skin.
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公开(公告)号：US20170225766A1
公开(公告)日：2017-08-10
申请号：US15424095
申请日：2017-02-03
摘要： In one aspect, there is a rib assembly for an aircraft wing including a rib web having a top and a bottom, the rib web includes a first laminate, a second laminate, and a honeycomb panel having an array of large cells disposed between the first laminate and the second laminate, each cell having a width of at least 1 cm; and a plurality of skin flanges for fixedly attaching the rib web to a skin of the wing, each skin flange has a base member having a first portion and a second portion and a vertical member extending from the base member. The plurality of skin flanges can be attached to the top and the bottom of the rib web such that the second portion of the base member and the vertical member are attached to the rib web.
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公开(公告)号：US09333684B2
公开(公告)日：2016-05-10
申请号：US13663978
申请日：2012-10-30
CPC分类号： B29C44/186 , B29C44/5627 , B29L2031/082 , B29L2031/608 , B32B3/12 , B32B5/18 , B32B5/245 , B32B2260/021 , B32B2260/046 , B32B2605/18 , Y10T428/24157 , Y10T428/24612 , Y10T428/249953
摘要： A method of the present disclosure includes of repairing a core stiffened structure with structural foam. Another method includes splicing core members together using structural foam. Another method includes joining a core member to a structure using structural foam. Another method includes using structural foam to stabilize a core member during a machining process. Another method includes stabilizing a core member with structural foam to prevent the core member from crushing in autoclave pressure. The present disclosure further includes a core stiffened structure have a core member with structural foam therein.
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