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公开(公告)号：EP2671793B1
公开(公告)日：2018-03-07
申请号：EP12709671.7
申请日：2012-01-31
摘要： Torsion box of an aircraft stabilizing surface comprising a front spar (15), a rear spar (17), ribs (21) and upper and lower stiffened skins, in which at least one of said skins (31) is stiffened with a plurality of stringers (33, 43), preferably omega-shaped stringers, extending all of them along the full skin span, preferably in a "conical" distribution, and having a decreasing cross section towards the skin outer edge.
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2.发明公开TORSION BOX SKIN STIFFENED WITH NON-PARALLEL STRINGERS. 有权麻省理工学院和平学院BÄNDERNVERSTEIFTEHÜLLEEINER TORSIONSBOX
公开(公告)号：EP2671793A2
公开(公告)日：2013-12-11
申请号：EP12709671.7
申请日：2012-01-31
摘要： Torsion box of an aircraft stabilizing surface comprising a front spar (15), a rear spar (17), ribs (21) and upper and lower stiffened skins, in which at least one of said skins (31) is stiffened with a plurality of stringers (33, 43), preferably omega-shaped stringers, extending all of them along the full skin span, preferably in a "conical" distribution, and having a decreasing cross section towards the skin outer edge.
摘要翻译： 包括前翼梁（15），后翼梁（17），肋（21）和上下加固皮的飞机稳定表面的扭转盒，其中至少一个所述皮肤（31）被加强成多个 桁条（33,43），优选为Ω形桁条，其全部沿着整个皮肤跨度延伸，优选为“锥形”分布，并且朝向皮肤外边缘具有减小的横截面。
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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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公开(公告)号：EP3552952A1
公开(公告)日：2019-10-16
申请号：EP18382247.7
申请日：2018-04-11
发明人： HONORATO RUIZ, Francisco Javier , GUINALDO FERNÁNDEZ, Enrique , GARCÍA NIETO, Carlos , ARANA HIDALGO, Alberto , CEBOLLA GARROFE, Pablo , NÚÑEZ DELGADO, Julio , MARTÍN PALOMARES, David , CRUZ DOMÍNGUEZ, Francisco José
摘要： Aircraft laminar multispar lifting surface (1), made of Composite Fibre Reinforced Plastic and comprising a multispar torsion box (2) and a leading edge (3),
the multispar torsion box (2) comprising a forward spar (5), a rear spar (6) and intermediate spars (7),
the leading edge (3) comprising at least one spar (13),
the outer skin (4) of the aircraft laminar multispar lifting surface (1) comprising an upper cover (8), a lower cover (9) and a nose cup (11) covering the nose tip of the leading edge (3),
the leading edge (3) being integrated with the multispar torsion box (2) in a single structure,
wherein the upper cover (8) and the lower cover (9) of the outer skin (4) of the aircraft laminar multispar lifting surface (1) extend over the torsion box (2) and partially over the leading edge (3), with an overlapping area (12) between each of the upper and lower covers (8, 9) and the nose cup (11).-
公开(公告)号：EP3272646B1
公开(公告)日：2020-07-08
申请号：EP16382351.1
申请日：2016-07-20
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6.发明公开
公开(公告)号：EP3590824A1
公开(公告)日：2020-01-08
申请号：EP18382506.6
申请日：2018-07-06
发明人： HONORATO RUIZ, Francisco Javier , VÁZQUEZ CASTRO, Jesús Javier , GUINALDO FERNÁNDEZ, Enrique , GARCÍA NIETO, Carlos , VÉLEZ DE MENDIZÁBAL ALONSO, Iker
摘要： Method for manufacturing the trailing edge ribs (1) and the bearing ribs (2) of trailing edges (3) of aircraft lifting surfaces, in which the trailing edge ribs (1) and the bearing ribs (2) are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final trailing edge ribs (1) and bearing ribs (2), such that the manufacturing of the simple C-shaped parts uses the same tooling both for the trailing edge ribs (1) and the bearing ribs (2), and the manufacturing of the simple L-shaped parts uses the same tooling both for the trailing edge ribs (1) and the bearing ribs (2).
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公开(公告)号：EP3486074A1
公开(公告)日：2019-05-22
申请号：EP17382773.4
申请日：2017-11-15
发明人： GARCIA NIETO, Carlos , RODRIGUEZ URBINA, Luis Manuel , HONORATO RUIZ, Francisco Javier , GUINALDO FERNANDEZ, Enrique , SANCHEZ FRANCO, Diego
IPC分类号： B29C65/50 , F16B5/06 , B29C70/74 , B29C65/56 , B29L31/00 , B29L31/30 , F16B2/10 , F16B7/04 , F16B9/02
摘要： Composite structure (1) for an aircraft, having at least one insert (2) for receiving attachment devices, each insert (2) comprising a core (3) having a mayor dimension and containing at least one through-hole (4), and a composite strip arrangement formed by a first section (5) surrounding the core (3) and attached to said core (3) by an adhesive polymeric layer, and a second section (6) comprising at least one free end (6a). The first (5) and the second portion (6) of the composite strip arrangement are disposed over a first surface (1a) of the composite structure (1), such that the mayor dimension of the core (3) is positioned transversal to said first surface (1a). The at least one insert (2) is co-cured with the composite structure (1).
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公开(公告)号：EP3241742B1
公开(公告)日：2018-12-12
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).
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9.发明公开MONOLITHIC PRIMARY STRUCTURAL PART FOR AIRCRAFT AND PROCESSES FOR MANUFACTURING IT 审中-公开整体结构主要成分为及其生产航空器与方法
公开(公告)号：EP3124218A1
公开(公告)日：2017-02-01
申请号：EP15382393.5
申请日：2015-07-29
CPC分类号： B29C70/54 , B29C70/30 , B29C70/34 , B29K2105/06 , B29K2307/04 , B29K2309/08 , B29L2031/3076 , B32B5/26 , B32B17/067 , B32B2262/101 , B32B2262/106 , B32B2605/18 , B64C1/00 , B64C2001/0072 , G01N3/08 , G01N3/24 , Y02T50/43
摘要： Monolithic primary structural part for aircraft, made of carbon fiber composite material and glass fiber composite material, covered completely by at least one glass fiber ply on its external face over multiple carbon fiber plies. The invention also discloses processes to manufacture the monolithic primary structural part for aircraft, which comprise calculating the number of glass fiber plies using the Damage Tolerance criteria for sizing structural parts, in which a number of glass fiber plies replaces a number of carbon fiber plies. These processes can be applied to thin parts or thick parts, with different detectability-energy curves.
摘要翻译： 对于飞机整体主要结构部件，由碳纤维复合材料和玻璃纤维复合材料制成，覆盖由至少一个玻璃纤维帘布层在其外表面上在多个碳纤维层完全呼叫。 因此，本发明的盘以下过程制造用于飞行器的整体主要结构部分，其包括计算的玻璃纤维的数使用所述损伤容限标准尺寸的结构部件，其中，多个玻璃纤维层片的取代的多个碳纤维层的层片。 这些方法可以适用于薄壁部或厚的部分，具有不同的可检测性能曲线。
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