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公开(公告)号：US09782960B1
公开(公告)日：2017-10-10
申请号：US15057031
申请日：2016-02-29
申请人： The Boeing Company
CPC分类号： B32B37/1018 , B29C65/00 , B29C66/00145 , B29C70/44 , B29D99/0003 , B32B37/00 , B32B37/0046 , B32B37/10 , B32B2605/18 , B64C1/00 , B64C1/06 , B64C1/061 , B64C1/064 , B64C1/068 , B64C1/069 , B64C3/18 , B64C3/182 , B64C3/24 , B64C3/26 , B64C3/28 , B64C3/30 , B64C2001/0072 , B64F5/10 , Y02T50/43
摘要： A method and apparatus for compacting composite stringers. In one illustrative embodiment, an apparatus comprises a compacting structure, a compactor vacuum system, and a carrier vacuum system. The compacting structure has a shape configured to contact layers of uncured composite material for a composite stringer. The compactor vacuum system is associated with the compacting structure. The compactor vacuum system is configured to cause the compacting structure to apply a pressure to the layers of uncured composite material when a compactor vacuum is applied to the compactor vacuum system. The carrier vacuum system is associated with the compacting structure. The carrier vacuum system is configured to hold the layers of uncured composite material against the compacting structure when a carrier vacuum is applied to the carrier vacuum system.
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公开(公告)号：US08870120B2
公开(公告)日：2014-10-28
申请号：US13401951
申请日：2012-02-22
CPC分类号： B64C3/24 , B29C70/207 , B29C70/222 , B29L2031/3082 , B29L2031/3085 , B64C3/185 , B64C3/26 , Y02T50/43 , Y10T428/24174 , Y10T428/24628 , Y10T428/24752
摘要： A composite structure has a first section, a second section, and a curved corner joining the first and second sections. The structure has a stack of fiber-reinforced plies including first and second external plies which run from the first section into the second section on an inside and an outside of the corner, respectively. A discontinuous first internal ply is sandwiched between the first and second external plies so that more of the first internal ply is located within the first section than within the second section. A second internal ply is sandwiched between the first and second external plies. The fibers of the first internal ply run at an angle θ to the fibers of the second internal ply. In some embodiments the angle θ is greater than 3° but less than 20°. In one embodiment the angle θ is between 35° and 42°.
摘要翻译： 复合结构具有第一部分，第二部分和连接第一和第二部分的弯曲角。 该结构具有一叠纤维增强帘布层，包括第一和第二外层，其分别从第一部分延伸到角部的内侧和外侧的第二部分。 不连续的第一内部层夹在第一和第二外层之间，使得更多的第一内部层位于第一区段内比在第二区段内更多。 第二内层夹在第一和第二外层之间。 第一内层的纤维以一定角度运行; 到第二内层的纤维。 在一些实施例中，角度和角度; 大于3°但小于20°。 在一个实施例中，角度和角度; 在35°和42°之间。
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公开(公告)号：US08844872B2
公开(公告)日：2014-09-30
申请号：US13400898
申请日：2012-02-21
CPC分类号： B64C3/185 , B29C70/207 , B29C70/222 , B29L2031/3082 , B29L2031/3085 , B64C3/24 , B64C3/26 , Y02T50/43 , Y10T428/24124 , Y10T428/24132 , Y10T428/24174 , Y10T428/24612 , Y10T428/24752
摘要： A composite structure has first and second sections, and a curved corner joining the first and second sections. The structure includes a stack of fiber-reinforced plies. First and second external plies run from the first section into the second section round an inside and an outside of the corner, respectively. First and second internal plies are sandwiched between the first and second external plies, and run from the first section into the second section round the corner. The first internal fly is dropped off inside the second section. The second internal ply is dropped off inside the first section. The structure has an increased thickness where the first and second internal plies overlap.
摘要翻译： 复合结构具有第一和第二部分，以及连接第一和第二部分的弯曲角。 该结构包括一叠纤维增强层。 第一和第二外部帘布层分别从第一部分延伸到第二部分的内部和外部。 第一和第二内层夹在第一和第二外层之间，并从第一部分延伸到第二部分。 第一个内部飞行在第二部分内掉落。 第二个内部帘布层在第一部分内掉落。 该结构具有增加的厚度，其中第一和第二内层重叠。
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公开(公告)号：US08146865B2
公开(公告)日：2012-04-03
申请号：US11807903
申请日：2007-05-30
IPC分类号： B64D1/00
CPC分类号： B64C3/24 , B64C3/28 , B64C5/00 , B64C11/205 , B64C27/473 , Y10T29/49622
摘要： The present invention relates to a leading edge (1) for aircraft made of composite material, characterized in that it comprises on its inner face a metallic-type reinforcement (2) firmly adhered to the mentioned inner face of the leading edge (1) arranged such that it confers the leading edge (1) with better capacity to adapt to deformability and greater absorption of energy due to impacts. The invention also relates to a method of manufacturing a leading edge (1) with a metallic reinforcement (2) for aircraft made of composite material.
摘要翻译： 本发明涉及一种由复合材料制成的飞行器的前缘（1），其特征在于，在其内表面上包括牢固地粘附到前缘（1）的所述内表面上的金属型加强件（2） 使得其具有更好的容量以适应变形能力和由于冲击而对能量的更大吸收的前缘（1）。 本发明还涉及一种用复合材料制造的飞机用金属加强件（2）制造前缘（1）的方法。
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公开(公告)号：US20120034093A1
公开(公告)日：2012-02-09
申请号：US12852390
申请日：2010-08-06
IPC分类号： F04D29/38
CPC分类号： B64C3/26 , B64C3/187 , B64C3/24 , B64C27/473 , B64C2027/4736
摘要： A rotor blade has a chord and a span length perpendicular to the chord. The rotor blade includes a first skin having an inner surface and a first plurality of elements extending from the inner surface. The first plurality of elements are distributed along at least a portion of the span length and inclined with respect to the chord of the rotor blade. A second skin is attached to the first skin so as to form an outer surface of the rotor blade. The second skin has a second plurality of elements extending towards the inner surface of the first skin and engaging with the first plurality of elements to form a plurality of ribs within the rotor blade.
摘要翻译： 转子叶片具有垂直于弦的弦和跨距长度。 转子叶片包括具有从内表面延伸的内表面和第一多个元件的第一皮肤。 第一多个元件沿跨度长度的至少一部分分布并相对于转子叶片的弦倾斜。 将第二皮肤附接到第一皮肤，以形成转子叶片的外表面。 第二皮肤具有朝向第一皮肤的内表面延伸的第二多个元件，并与第一多个元件接合以在转子叶片内形成多个肋。
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6.发明申请METHODS FOR MAKING COMPOSITE MATERIAL COMPONENTS ESPECIALLY USEFUL FOR AIRCRAFT, AND COMPOSITE MATERIAL COMPONENTS THEREOF 有权用于制造特别适用于飞机的复合材料组分的方法及其复合材料组分公开(公告)号：US20090110871A1
公开(公告)日：2009-04-30
申请号：US11923247
申请日：2007-10-24
CPC分类号： B29C66/721 , B29C65/50 , B29C66/1122 , B29C66/43 , B29C66/4342 , B29C66/7212 , B29C70/30 , B29K2105/06 , B29K2307/00 , B29K2309/08 , B64C3/24 , B64C5/02 , B64C5/04 , B64C5/06 , Y02T50/43 , Y10T156/10 , Y10T428/24058 , Y10T428/24091 , Y10T428/24099 , Y10T428/24116 , B29K2307/04
摘要： Methods and resulting laminate structures are provided wherein the lay-up of composite materials is accomplished more symmetrically and more continuously as compared to prior techniques to form a composite structure from two composite parts in which their principal laminate directions form a non-singular angle. According to one exemplary implementation, a method for making a composite structure comprised of at least two parts joined to one another at a central junction zone with a non-singular angle, is provided by laying up 0° composite material plies relative to a central coordinate system COORD C of the central junction zone so as to achieve +(90°−θ°/2) plies relative to left and right coordinate systems COORD L and COORD R, respectively, of the at least two parts, and laying up +(180°−θ°) and −(180°−θ°) plies relative to the central coordinate system COORD C of the central junction zone so as to achieve −(90°−θ°/2) plies relative to left and right coordinate systems COORD L and COORD R, respectively, of the at least two parts. Additionally or alternatively, the method may comprise laying up 90° composite material plies relative to the central coordinate system COORD C of the central junction zone so as to achieve −θ°/2 plies relative to the left and right coordinate systems COORD L and COORD R, respectively, of the at least two parts; and laying up +(90°−θ°) and −(90°−θ°) composite material plies relative to the central coordinate system COORD C of the central junction zone so as to achieve +θ°/2 plies relative to the left and right coordinate systems COORD L and COORD R, respectively, of the at least two parts.
摘要翻译： 提供了方法和所得到的层压结构，其中复合材料的层叠比现有技术更为对称和更连续地实现，以便从两个复合材料构件形成复合结构，其中它们的主层叠方向形成非奇异角。 根据一个示例性实施方式，通过相对于中心坐标放置0°复合材料层来提供用于制造由至少两个部分组成的复合结构的方法，所述至少两个部分在具有非奇异角的中心连接区彼此连接 系统中心连接区的COORD C，以分别相对于至少两个部分的左右坐标系COORD L和COORD R实现+（90°-θ°/ 2）层，并铺设+（ 180°-θ°）和 - （180°-θ°）相对于中心连接区域的中心坐标系COORD C，以便相对于左和右坐标实现 - （90°-θ°/ 2） 系统分别为COORD L和COORD R，至少两部分。 另外或替代地，该方法可以包括相对于中心连接区域的中心坐标系COORD C放置90°复合材料层，以便相对于左右坐标系COORD L和COORD实现-θ°/ 2层 R分别为至少两部分; 并且相对于中心连接区域的中心坐标系COORD C铺设+（90°-θ）和 - （90°-θ°）复合材料层，以便相对于左边实现+θ°/ 2层 和至少两个部分的右坐标系COORD L和COORD R。
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公开(公告)号：US20090072088A1
公开(公告)日：2009-03-19
申请号：US11855357
申请日：2007-09-14
CPC分类号： B64C3/24 , A63B2209/02 , B64C3/185 , B64C3/187 , Y02T50/43
摘要： An aircraft wing made of a composite material, and its method of manufacture, require a plurality of kabobs (i.e. substantially rectangular shaped hollow tubes having an open end and a closed end). Of these kabobs, several are aligned end-to-end, to create a section. Several sections are then positioned side-by-side and covered by a layer of composite material to define an aerodynamic surface for the wing. The juxtaposed sections also establish spar webs for the wing, and the closed ends of the juxtaposed sections establish transverse ribs for the wing. Thus, the kabobs form the main load-bearing member of the wing. The sections of composite material are co-cured with the composite material of the aerodynamic surface.
摘要翻译： 由复合材料制成的飞机机翼及其制造方法需要多个卡布巴（即具有开口端和封闭端的大致矩形的中空管）。 在这些kabobs中，几个对齐端到端，以创建一个部分。 然后将几个部分并排设置并被一层复合材料覆盖以限定机翼的空气动力学表面。 并列部分还建立翼的翼梁网，并列的部分的封闭端设置用于机翼的横向肋。 因此，卡布尔形成机翼的主承重构件。 复合材料的截面与空气动力学表面的复合材料共同固化。
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8.发明申请Methods and Systems for Manufacturing a Family of Aircraft Wings and Other Composite Structures 有权制造一系列飞机翅膀和其他复合结构的方法和系统公开(公告)号：US20090056109A1
公开(公告)日：2009-03-05
申请号：US12136392
申请日：2008-06-10
CPC分类号： B29C70/30 , B29C33/307 , B29C33/308 , B29C70/386 , B29L2031/3085 , B64C3/18 , B64C3/24 , B64C3/26 , B64F5/10 , Y02T50/43 , Y10T29/49867 , Y10T29/53004 , Y10T29/53039 , Y10T29/53313
摘要： Methods and systems for manufacturing composite aircraft wings and other structures are disclosed herein. A tool assembly for use in manufacturing composite laminates in accordance with one embodiment of the invention includes a tool plate carried by a movable support system. The tool plate includes a tool surface configured to support fiber-reinforced resin material and define an outer mold line (OML) of the fiber-reinforced resin material. The movable support system is configured to respond to signals from a controller to automatically change the shape of the tool surface and alter the OML of the finished part to suit the particular application. In one embodiment, the movable support system can include a plurality of telescoping actuators operably coupled to the tool plate.
摘要翻译： 本文公开了用于制造复合飞机机翼和其它结构的方法和系统。 根据本发明的一个实施例的用于制造复合层压板的工具组件包括由可移动支撑系统承载的工具板。 工具板包括被配置为支撑纤维增强树脂材料并限定纤维增强树脂材料的外模线（OML）的工具表面。 可移动支撑系统被配置为响应来自控制器的信号以自动改变工具表面的形状并改变成品部件的OML以适合特定应用。 在一个实施例中，可移动支撑系统可以包括可操作地联接到工具板的多个可伸缩致动器。
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9.发明授权Methods and systems for manufacturing a family of aircraft wings and other composite structures 有权用于制造飞机机翼和其他复合结构系列的方法和系统公开(公告)号：US07398586B2
公开(公告)日：2008-07-15
申请号：US11264608
申请日：2005-11-01
CPC分类号： B29C70/30 , B29C33/307 , B29C33/308 , B29C70/386 , B29L2031/3085 , B64C3/18 , B64C3/24 , B64C3/26 , B64F5/10 , Y02T50/43 , Y10T29/49867 , Y10T29/53004 , Y10T29/53039 , Y10T29/53313
摘要： Methods and systems for manufacturing composite aircraft wings and other structures are disclosed herein. A tool assembly for use in manufacturing composite laminates in accordance with one embodiment of the invention includes a tool plate carried by a movable support system. The tool plate includes a tool surface configured to support fiber-reinforced resin material and define an outer mold line (OML) of the fiber-reinforced resin material. The movable support system is configured to respond to signals from a controller to automatically change the shape of the tool surface and alter the OML of the finished part to suit the particular application. In one embodiment, the movable support system can include a plurality of telescoping actuators operably coupled to the tool plate.
摘要翻译： 本文公开了用于制造复合飞机机翼和其它结构的方法和系统。 根据本发明的一个实施例的用于制造复合层压板的工具组件包括由可移动支撑系统承载的工具板。 工具板包括被配置为支撑纤维增强树脂材料并限定纤维增强树脂材料的外模线（OML）的工具表面。 可移动支撑系统被配置为响应来自控制器的信号以自动改变工具表面的形状并改变成品部件的OML以适合特定应用。 在一个实施例中，可移动支撑系统可以包括可操作地联接到工具板的多个可伸缩致动器。
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10.发明授权Process for manufacturing pre-cured parts of composite material with green-applied stiffeners 有权用绿色加固加固件制造复合材料预固化部件的工艺公开(公告)号：US06508909B1
公开(公告)日：2003-01-21
申请号：US09625877
申请日：2000-07-26
申请人： Carlos Cerezo Pancorbo , Rafael Dominguez Casado , Manuel De Castro Nodal , Augusto Perez Pastor , Aquilino Garcia Garcia , Manuel Huertas Garcia
发明人： Carlos Cerezo Pancorbo , Rafael Dominguez Casado , Manuel De Castro Nodal , Augusto Perez Pastor , Aquilino Garcia Garcia , Manuel Huertas Garcia
IPC分类号： B29C7044
CPC分类号： B64C3/182 , B29C70/44 , B29K2105/24 , B29K2105/246 , B29L2031/003 , B64C3/24 , Y02T50/43 , Y10S264/42
摘要： A process for manufacturing pre-cured parts of composite material with green-applied stiffeners, comprising the lamination of superimposed pre-impregnated composite material sheets to obtain a base part (1) and a second part (2) intended to be bonded with it; curing the base part (1); hot forming the laminate destined to form the second part (2); removing the second part (2) from the forming tool thereof and deposit it over the base part (1), intercalating a structural adhesive sheet between both of them; closing the assembly of both parts inside a vacuum bag and loading said bag in an autoclave, carrying out a curing cycle of the second part (2) under pressure and temperature, so that it is strongly adhered to the base part (1). The invention is applicable to the field of aeronautics.
摘要翻译： 一种制备具有绿色加固件的复合材料的预固化部分的方法，包括叠加预浸复合材料片的叠层以获得预期与之结合的基部（1）和第二部分（2）; 固化基部（1）; 热成型用于形成第二部分（2）的层压体; 将第二部分（2）从其成形工具中取出并将其沉积在基部（1）上，在两者之间插入结构粘合片; 将两部分的组件封闭在真空袋内并将所述袋装入高压釜中，在压力和温度下进行第二部分（2）的固化循环，使其牢固地粘附到基部（1）上。 本发明适用于航空领域。
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