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公开(公告)号：EP3150484B1
公开(公告)日：2018-12-12
申请号：EP15382472.7
申请日：2015-09-29
发明人： GARCÍA NIETO, Carlos , VELEZ DE MENDIZABAL ALONSO, Iker , GUINALDO FERNANDEZ, Enrique , CRESPO PEÑA, Soledad
CPC分类号： B64C3/187 , B29C70/48 , B29K2105/0872 , B29L2031/3085 , B64C3/20 , B64F5/45 , Y02T50/43
摘要： The present invention refers to the configuration and manufacturing process of a rib (22) for the construction of an aircraft torsion box. In the method a flat stack of plies of composite material (13) is layered up, which is then cut to form a flat pre-form (14) having an outer contour (15) configuring flanges, and an internal contour configuring two or more diagonal truss (16) with flanges (17) at opposite sides. The flat pre-form (14) is press-formed to fold the flanges of the outer and internal contour to form a rib pre-form, which is finally cured. The invention also refers to a composite rib (22) obtained as an unitary body by conforming a single pre-form of stacked plies. The invention allows the manufacture of the rib (22) in one-shot process, integrating all its components, such as the assembly time and cost of the rib are minimized.
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公开(公告)号：EP3173328A1
公开(公告)日：2017-05-31
申请号：EP15382588.0
申请日：2015-11-26
发明人： GUINALDO FERNANDEZ, Enrique , CEBOLLA GARROFE, Pablo , VÉLEZ DE MENDIZABAL ALONSO, Iker , CRESPO PEÑA, Soledad , GARCÍA NIETO, Carlos , HONORATO RUIZ, Francisco, Javier , CALERO CASANOVA, Alvaro , TORRES SALAS, Álvaro
IPC分类号： B64C21/06
摘要： The present invention refers to the configuration of a leading edge section (1) with laminar flow control, wherein the leading edge comprises: a perforated outer skin (2), an inner surface (3), a plurality of suction chambers (4) formed between the outer skin (2) and the inner surface (3) and a plurality of radial structural elements (5) to withstand structural loads at the leading edge. The radial structural elements (5) are arranged to define the suction chambers (4) together with the outer skin (2) and the inner surface (3), and the radial structural elements (5) and/or the inner surface (3) are perforated, such that an exterior region of the leading edge is communicated with an interior region of the leading edge through said suction chambers (4). The invention provides an optimized leading edge with a laminarflow control system, from a structural point of view, including improved bird impact performance.
摘要翻译： 本发明涉及具有层流控制的前缘部分（1）的构造，其中前缘包括：穿孔外蒙皮（2），内表面（3），形成的多个抽吸室（4） 在所述外蒙皮（2）和所述内表面（3）之间以及多个径向结构元件（5）以承受所述前缘处的结构载荷。 径向结构元件（5）布置成与外壳（2）和内表面（3）以及径向结构元件（5）和/或内表面（3）一起限定吸入室（4） 被穿孔，使得前缘的外部区域通过所述抽吸室（4）与前缘的内部区域连通。 从结构的角度来看，本发明提供了具有层流控制系统的优化的前缘，包括改进的鸟撞击性能。
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公开(公告)号：EP3501799A1
公开(公告)日：2019-06-26
申请号：EP17382866.6
申请日：2017-12-19
发明人： GUINALDO FERNANDEZ, Enrique , JARA RODELGO, Alvaro , TORRES SALAS, Alvaro , HERNAIZ LOPEZ, Guillermo , LOPEZ ROMANO, Bernardo , PICO BOLAÑO, Alejandro , GARCIA MOSTOLES, Fernando
IPC分类号： B29C64/25 , B29C64/364
摘要： The invention refers to an impression chamber (1) for a 3D printer (6) adapted to receive a High Performance Plastic filament (19) and comprising a print head (7) and a printing bed (8), wherein the impression chamber (1) comprises a thermally insulated plate (2) and a polyimide film (3) attached to the plate (2) for delimiting a printing space (20). The plate (2) is dimensioned to have a surface (2a) equal or larger than the major surface of the piece (5) to be printed, and the film (3) is dimensioned to surround the printing bed (8). The plate (2) is provided with a first through-hole (15) for allowing the passage of at least part of the print head (7), so that the plate (2) is moved by the movement of the print head (7) and the film (3) is dragged by said movement providing a flexible impression chamber (1).
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公开(公告)号：EP3219458B1
公开(公告)日：2019-05-08
申请号：EP16382109.3
申请日：2016-03-14
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公开(公告)号：EP3241742A1
公开(公告)日：2017-11-08
申请号：EP16382198.6
申请日：2016-05-06
发明人： GARCIA NIETO, Carlos , PEREIRA MOSQUEIRA, Fernando , VELEZ DE MENDIZABAL ALONSO, Iker , GUINALDO FERNANDEZ, Enrique , HONORATO RUIZ, Francisco Javier
摘要： An aircraft aerodynamic surface (1) comprising a torsion box (2) having a front spar (21) and rear spar (22), a first control surface (3) comprising a front spar (31) and a trailing edge (32) and a second control surface (4) comprising a front spar (41), a trailing edge (42), and means (5, 6, 7, 8) for pivotally attaching the first control surface (3) and the second control surface (4) to the rear spar (22) of the torsion box (2), the first control surface is an inboard control surface (4) comprising two lateral ribs (9, 9'), six inner ribs (11, 12, 13, 14, 15, 10) and an inner spar (16), and the second control surface (3) is an outboard control surface which comprising two lateral ribs (20, 20'), three internal ribs (17, 18, 19), two internal spars (24, 24') and one internal spar (23).
摘要翻译： 一种包括具有前翼梁（21）和后翼梁（22）的扭力箱（2）的飞机空气动力学表面（1），包括前翼梁（31）和后缘（32）的第一控制表面（3）以及 （3）和第二控制表面（4）的装置（5,6,7,8）的第二控制表面（4），所述第二控制表面包括前翼梁（41），后缘（42） ）连接到扭力箱（2）的后翼梁（22），第一控制表面是内侧控制表面（4），该内侧控制表面包括两个侧肋（9,9'），六个内肋（11,12,13,14 ，所述第二控制表面（3）是外侧控制表面，所述外侧控制表面包括两个侧肋（20,20'），三个内肋（17,18,19），两个内肋 内部翼梁（24,24'）和一个内部翼梁（23）。
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6.发明公开METHOD, INJECTION MOULDING TOOL FOR MANUFACTURING A LEADING EDGE SECTION WITH HYBRID LAMINAR FLOW CONTROL FOR AN AIRCRAFT, AND LEADING EDGE SECTION WITH HYBRID LAMINAR FLOW CONTROL OBTAINED THEREOF 审中-公开方法，用于制造具有用于飞机的混合层流控制的主导边缘部分的注射成型工具，以及具有由其获得的混合层流控制的主导边缘部分
公开(公告)号：EP3219458A1
公开(公告)日：2017-09-20
申请号：EP16382109.3
申请日：2016-03-14
发明人： CEBOLLA GARROFE, Pablo , CALERO CASANOVA, Álvaro , CRESPO PEÑA, Soledad , GARCÍA NIETO, Carlos , VÉLEZ DE MENDIZABAL ALONSO, Iker , GUINALDO FERNANDEZ, Enrique , HONORATO RUIZ, Francisco, Javier , TORRES SALAS, Álvaro
CPC分类号： B64C3/26 , B29C33/30 , B29C33/48 , B29C45/0005 , B29C45/0055 , B29C45/14475 , B29C45/40 , B29C69/001 , B29K2105/06 , B29K2105/12 , B29L2031/3076 , B29L2031/3085 , B64C3/28 , B64C21/06 , B64C2230/22
摘要： The invention refers to the manufacturing of a leading edge section (1) with hybrid laminar flow control for an aircraft comprising providing an outer hood (4), a plurality of elongated modules (2), first and second C-shaped profiles (5, 7) comprising cavities (10), and an inner mandrel (3); assembling an injection moulding tool by placing each profile (5, 7) on each end of the inner mandrel (3), arranging a first extreme of each elongated module (2) in one cavity (10) of the first profile (5) and a second extreme of the module (2) in another cavity (10) of the second profile (7), both cavities (10) positioned in the same radial direction; and placing the hood (4) on first and second profiles (5, 7) to close the tool. Further, the injection moulding tool is closed and filled with an injection compound comprising thermoplastic and short-fiber. Finally, the compound is hardened and demoulded.
摘要翻译： 本发明涉及制造具有用于飞行器的混合层流控制的前缘部分（1），其包括提供外罩（4），多个细长模块（2），第一和第二C形型材（5,5） 7）包括空腔（10）和内心轴（3）; 通过将每个型材（5,7）放置在内心轴（3）的每个端部上，将每个细长模块（2）的第一端部布置在第一型材（5）的一个空腔（10）中来组装注塑成型工具， 所述模块（2）的第二极端位于所述第二轮廓（7）的另一空腔（10）中，两个空腔（10）位于相同的径向方向上; 并将罩（4）放置在第一和第二型材（5,7）上以关闭工具。 此外，注塑成型工具被封闭并填充包含热塑性塑料和短纤维的注塑料。 最后，化合物硬化并脱模。
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7.发明公开AIRCRAFT AIRFOIL HAVING A STITCHED TRAILING EDGE AND MANUFACTURING METHOD THEREOF 审中-公开具有经过缝纫的后缘的飞机机翼及其制造方法
公开(公告)号：EP3210883A1
公开(公告)日：2017-08-30
申请号：EP16382084.8
申请日：2016-02-29
发明人： CRESPO PEÑA, Soledad , GARCÍA NIETO, Carlos , VELEZ DE MENDIZABAL ALONSO, Iker , GUINALDO FERNANDEZ, Enrique
CPC分类号： B32B5/028 , B29C70/24 , B29L2031/3085 , B32B5/02 , B32B5/06 , B32B15/02 , B32B37/14 , B32B2038/008 , B32B2260/021 , B32B2260/046 , B32B2262/106 , B32B2305/076 , B32B2305/72 , B32B2605/18 , B64C1/00 , B64C3/20 , B64C9/00 , B64C2001/0072 , B64D45/02 , D05D2209/12 , Y02T50/43
摘要： The present invention refers in general to the configuration and manufacturing method for a trailing edge (3) of an aircraft airfoil (2), such as a control surface or a lifting surface. The trailing edge of the invention is formed and configured by upper and lower composite covers (4,5), which are stitched to each other with a metallic wire (9), such as the metallic wire (9) is electrically in contact with upper and lower metallic meshes (6,7) to provide electrical continuity between meshes. According to the method of the invention, upper and lower covers (4,5) configuring the trailing edge (3), are stitched with the metallic wire (9) before curing the covers, so that the metallic wire gets embedded within the composite material. The invention provides a trailing edge (3) for an aircraft airfoil (2), which is easy to manufacture and that at the same time fulfills aerodynamic, mechanical and electrical conductivity requirements.
摘要翻译： 本发明总体上涉及用于飞机机翼（2）的后缘（3）的构造和制造方法，例如控制表面或提升表面。 本发明的后缘由上部和下部复合盖（4,5）形成和构造，所述上部和下部复合盖（4,5）利用金属丝（9）彼此缝合，例如金属丝（9）与上部 和较低的金属网（6,7）以提供网眼之间的电连续性。 根据本发明的方法，在固化盖之前，将构成后缘（3）的上盖和下盖（4,5）与金属丝（9）缝合，使得金属丝嵌入复合材料 。 本发明提供了用于飞机机翼（2）的后缘（3），其容易制造并且同时满足空气动力学，机械和导电性要求。
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公开(公告)号：EP3501799B1
公开(公告)日：2020-08-05
申请号：EP17382866.6
申请日：2017-12-19
发明人： GUINALDO FERNANDEZ, Enrique , JARA RODELGO, Alvaro , TORRES SALAS, Alvaro , HERNAIZ LOPEZ, Guillermo , LOPEZ ROMANO, Bernardo , PICO BOLAÑO, Alejandro , GARCIA MOSTOLES, Fernando
IPC分类号： B29C64/25 , B29C64/364
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公开(公告)号：EP3173328B1
公开(公告)日：2020-01-01
申请号：EP15382588.0
申请日：2015-11-26
发明人： GUINALDO FERNANDEZ, Enrique , CEBOLLA GARROFE, Pablo , VÉLEZ DE MENDIZABAL ALONSO, Iker , CRESPO PEÑA, Soledad , GARCÍA NIETO, Carlos , HONORATO RUIZ, Francisco, Javier , CALERO CASANOVA, Alvaro , TORRES SALAS, Álvaro
IPC分类号： B64C21/06
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公开(公告)号：EP3248864A1
公开(公告)日：2017-11-29
申请号：EP16382226.5
申请日：2016-05-24
发明人： VELEZ DE MENDIZABAL ALONSO, Iker , GUINALDO FERNANDEZ, Enrique , GARCÍA NIETO, Carlos , HONORATO RUIZ, Francisco, Javier , VOTSIOS, Vasilis
CPC分类号： B64C3/28 , B64D7/00 , B64D2033/022
摘要： The invention refers to an aerodynamic surface (1) for an aircraft comprising a torsion box having a front spar (5), and a composite leading edge section that comprises an outer surface (2) shaped with an aerodynamic leading edge profile, an inner surface (3) internally arranged with respect to the outer surface (2), and a blanket (4) spanwise arranged between the outermost point of the inner surface (3) and the front spar (5), wherein the blanket is made of fibre material having a specific energy absorption ranging from 47 to 72 J•g- 1 and a longitudinal wave speed ranging from 6 to 15 km•s -1 , wherein the major part of the blanket (4) is of dry fibre material, and wherein the blanket (4) is joined to at least two opposing areas of the inner surface (3) for absorbing a bird strike, to prevent the damage of the front spar (5).
摘要翻译： 本发明涉及一种用于飞行器的空气动力学表面（1），其包括具有前翼梁（5）的扭转箱以及复合前缘部分，所述复合前缘部分包括形成有空气动力学前缘轮廓的外表面（2），内表面 （3）相对于外表面（2）内部布置，以及在内表面（3）的最外点和前翼梁（5）之间翼展布置的橡皮布（4），其中橡皮布由纤维材料 具有47至72J·g -1的特定能量吸收和6至15km·s-1的纵波速度，其中，橡皮布（4）的主要部分是干纤维材料，并且其中 橡皮布（4）连接到内表面（3）的至少两个相对区域以吸收鸟击，以防止前翼梁（5）的损坏。
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