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1. 发明申请

US20190145550A1 COMPOSITE STRUCTURE HAVING AN INTEGRATED SUPPORT 审中-公开
公开(公告)号：US20190145550A1
公开(公告)日：2019-05-16
申请号：US16190732
申请日：2018-11-14
申请人： AIRBUS OPERATIONS S.L.
发明人： Francisco Javier HONORATO RUIZ , Diego SANCHEZ FRANCO , Luis RODRIGUEZ URBINA , Enrique GUINALDO FERNANDEZ , Carlos GARCIA NIETO
IPC分类号： F16L3/123 , H02G3/00
CPC分类号： F16L3/123 , B29C65/5014 , B29C65/5042 , B29C65/561 , B29C65/562 , B29C66/112 , B29C66/114 , B29C66/474 , B29C66/532 , B29C66/721 , B29C66/72143 , B29C66/727 , B29C66/73751 , B29C66/7392 , B29C70/74 , B29L2031/3076 , B29L2031/737 , F16B2/10 , F16B5/0685 , F16B7/0433 , F16B9/02 , H02G3/26
摘要： A composite structure (1) for an aircraft, having at least one insert (2) for receiving attachment devices, each insert (2) includes a core (3) having a major 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) including 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 major dimension of the core (3) is positioned transversal to said first surface (1 a). The at least one insert (2) is co-cured with the composite structure (1).

2. 发明申请

US20140151506A1 HIGHLY INTEGRATED STRUCTURE INCLUDING LEADING AND TRAILING EDGE RIBS FOR AN AIRCRAFT LIFTING SURFACE 有权
标题翻译：高度集成的结构，包括飞机提升表面的引导和跟踪边缘
公开(公告)号：US20140151506A1
公开(公告)日：2014-06-05
申请号：US14086424
申请日：2013-11-21
申请人： AIRBUS OPERATIONS S.L.
发明人： Enrique GUINALDO FERNANDEZ , Francisco CRUZ DOMINGUEZ , Francisco Javier HONORATO RUIZ , Paula MÁS MÁS , Iker VÉLEZ DE MENDIZÁBAL ALONSO , Carlos GARCIA NIETO
IPC分类号： B64C3/18 , B29C70/30 , B29C35/02 , B29D99/00
CPC分类号： B64C3/182 , B29C35/0238 , B29C70/30 , B29D99/0014 , B29L2031/3085 , B64C3/185 , B64C3/187 , B64C3/20 , B64C5/02 , Y02T50/43
摘要： The invention provides an aircraft lifting surface with a monolithic main supporting structure (14) of a composite material comprising an upper skin (21) including at least a part of the upper aerodynamic profile of the leading edge (11) and/or of the trailing edge (15), a lower skin, a front spar (18), a rear spar (20), a plurality of leading edge ribs and/or a plurality of trailing edge ribs. This main supporting structure allows a weight and cost reduction of aircraft lifting surfaces. The invention also provides a manufacturing method of said monolithic main supporting structure (14).
摘要翻译：本发明提供一种具有复合材料的整体式主支撑结构（14）的飞行器提升表面，该复合材料包括上皮（21），上皮（21）包括前缘（11）的上空气动力轮廓和/或尾部边缘（15），下皮，前翼梁（18），后翼梁（20），多个前缘肋和/或多个后缘肋。这种主要的支撑结构允许飞机提升表面的重量和成本降低。本发明还提供了一种所述单块主支撑结构（14）的制造方法。

3. 发明申请

US20140048652A1 HIGHLY INTEGRATED INNER STRUCTURE OF A TORSION BOX OF AN AIRCRAFT LIFTING SURFACE 审中-公开
标题翻译：飞机提升表面扭转箱的高度集成的内部结构
公开(公告)号：US20140048652A1
公开(公告)日：2014-02-20
申请号：US13964400
申请日：2013-08-12
申请人： AIRBUS OPERATIONS S.L.
发明人： Francisco Javier HONORATO RUIZ , Francisco José CRUZ DOMINGUEZ
IPC分类号： B64C3/28
CPC分类号： B64C3/28 , B29C35/0227 , B29C65/02 , B29C66/721 , B29C66/7212 , B29C66/72141 , B29C66/73752 , B29C70/42 , B29L2031/3085 , B64C3/18 , B64C3/20 , Y02T50/43 , B29K2307/04
摘要： The invention provides a method for manufacturing a monolithic torsion box inner structure (40) of an aircraft lifting surface comprising the following steps: a) providing a set of laminated preforms of a composite material for forming said torsion box inner structure (40), each laminated preform being configured for constituting a part of one component of the torsion box inner structure (40); b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demoulding the curing tooling in a vertical direction. The invention also provides an aircraft lifting surface wherein: the inner structure (40) of each torsion box (13) is manufactured by said method and the upper and lower skins (31, 33) are attached to the torsion box inner structure (40) with mechanical attachment means.
摘要翻译：本发明提供一种用于制造飞行器提升表面的整体式扭转箱内部结构（40）的方法，包括以下步骤：a）提供一组用于形成所述扭转箱内部结构（40）的复合材料的层压预制件，每组叠层预成型件构成为构成扭转箱内部结构（40）的一个部件的一部分; b）将所述层压预制件布置在固化工具中，并使组件经受高压釜循环以共同固化所述层压预制件; c）在垂直方向脱模固化工具。本发明还提供了一种飞机提升表面，其中：每个扭转箱（13）的内部结构（40）由所述方法制造，上部和下部表皮（31,33）附接到扭转箱内部结构（40）具有机械附接装置。

4. 发明申请

US20200010218A1 METHOD FOR MANUFACTURING THE TRAILING EDGE RIBS AND THE BEARING RIBS OF TRAILING EDGES OF AIRCRAFT LIFTING SURFACES 审中-公开
公开(公告)号：US20200010218A1
公开(公告)日：2020-01-09
申请号：US16502436
申请日：2019-07-03
申请人： Airbus Operations, S.L.
发明人： Francisco Javier HONORATO RUIZ , Jesús Javier VÁZQUEZ CASTRO , Enrique GUINALDO FERNÁNDEZ , Carlos GARCÍA NIETO , Iker VÉLEZ DE MENDIZÁBAL ALONSO
IPC分类号： B64F5/10 , B64C3/18
摘要： A method for manufacturing the trailing edge ribs and the bearing ribs of trailing edges of aircraft lifting surfaces, in which the trailing edge ribs and the bearing ribs are made by joining simple C-shaped parts and/or simple L-shaped parts so as to obtain the final trailing edge ribs and bearing ribs. The manufacturing of the simple C-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs, and the manufacturing of the simple L-shaped parts uses the same tooling both for the trailing edge ribs and the bearing ribs.

5. 发明申请

US20170259903A1 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
公开(公告)号：US20170259903A1
公开(公告)日：2017-09-14
申请号：US15457499
申请日：2017-03-13
申请人： AIRBUS OPERATIONS, S.L.
发明人： Pablo CEBOLLA GARROFE , Álvaro CALERO CASANOVA , Soledad CRESPO PEÑA , Carlos GARCÍA NIETO , Iker VÉLEZ DE MENDIZÁBAL ALONSO , Enrique GUINALDO FERNANDEZ , Francisco Javier HONORATO RUIZ , Alvaro TORRES SALAS
IPC分类号： B64C3/26 , B29C69/00 , B29C45/40 , B29C45/00 , B29C45/14
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 , B64C21/06 , B64C2230/22
摘要： This disclosure relates to the manufacturing of a leading edge section with hybrid laminar flow control for an aircraft. A manufacturing method involves: providing an outer hood, a plurality of elongated modules, first and second C-shaped profiles having comprising cavities, and an inner mandrel; assembling an injection moulding tool by placing each profile on each end of the inner mandrel, arranging a first extreme of each elongated module in one cavity of the first profile and a second extreme of the module in another cavity of the second profile, both cavities positioned in the same radial direction; and placing the hood on first and second profiles 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.

6. 发明申请

US20150183508A1 HORIZONTAL TAIL PLANE OF AN AIRCRAFT 审中-公开
标题翻译：飞机的水平尾翼飞机
公开(公告)号：US20150183508A1
公开(公告)日：2015-07-02
申请号：US14584480
申请日：2014-12-29
申请人： AIRBUS OPERATIONS S.L.
发明人： Andrea Ivan MARASCO , Fernando PEREIRA MOSQUEIRA , Enrique GUINALDO FERNÁNDEZ , Carlos GARCÍA NIETO , Francisco Javier HONORATO RUIZ , Francisco José CRUZ DOMÍNGUEZ
IPC分类号： B64C5/02 , B64C3/18
CPC分类号： B64C5/02 , B64C3/18
摘要： Horizontal tail plane of an aircraft which comprises a single torsion box which also comprises a front spar (1), a rear spar (2), an upper cover and a lower cover, ribs and two closing ribs (3), the front spar (1), the rear spar (2) and the upper and lower covers extending between said two closing ribs (3) and along the whole span of the horizontal tail plane in a symmetric layout with respect to the symmetry axis of the aircraft.
摘要翻译：飞机的水平尾翼平面包括一个单一的扭转箱，它还包括前翼梁（1），后翼梁（2），上盖和下盖，肋和两个关闭肋（3），前翼梁后翼梁（2）和上盖和下盖在所述两个关闭肋（3）之间延伸并且沿着相对于飞行器的对称轴线的对称布局沿着水平尾翼平面的整个跨度延伸。

7. 发明申请

US20140133987A1 HIGHLY INTEGRATED LEADING EDGE OF AN AIRCRAFT LIFTING SURFACE 有权
标题翻译：飞机提升表面的高度集成的领先优势
公开(公告)号：US20140133987A1
公开(公告)日：2014-05-15
申请号：US13943115
申请日：2013-07-16
申请人： AIRBUS OPERATIONS S.L.
发明人： Enrique GUINALDO FERNANDEZ , Francisco Javier HONORATO RUIZ , Francisco Jose CRUZ DOMINGUEZ
IPC分类号： F01D5/14
CPC分类号： F01D5/14 , B29D99/0028 , B64C3/28 , Y10T29/49336
摘要： A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demoulding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile.
摘要翻译：提供一种用于制造飞行器提升表面的前缘轮廓部分的方法。该方法包括以下步骤：a）提供一组复合材料的叠层预成型件，该复合材料被构造成用于构成前缘型材部分的合适形状; b）将所述层压预制件布置在固化工具中，并使组件经受高压釜循环以共同固化所述层压预制件; c）沿翼展方向将飞机对称平面上的固化工具脱模。本发明还包括通过所述方法制造的前缘轮廓部分，除了前缘轮廓部分的皮肤之外，还包括一个或多个以下结构元件：辅助翼梁，加强辅助翼梁的纵向加强筋，纵向纵梁加强前缘轮廓的皮肤。

8. 发明申请

US20150343702A1 METHOD FOR MANUFACTURING AN AERONAUTICAL TORSION BOX, TORSION BOX AND TOOL FOR MANUFACTURING AN AERONAUTICAL TORSION BOX 有权
标题翻译：用于制造气动扭矩箱的方法，制造箱和工具用于制造气动扭矩箱
公开(公告)号：US20150343702A1
公开(公告)日：2015-12-03
申请号：US14494012
申请日：2014-09-23
申请人： AIRBUS OPERATIONS S.L.
发明人： Diego GARCÍA MARTÍN , Carlos ROMÓN BANOGON , Pablo CEBOLLA GARROFE , Francisco Javier HONORATO RUIZ , Aquilino GARCíA GARCíA , Francisco Javier CHAMORRO ALONSO , Julio NÚÑEZ DELGADO
IPC分类号： B29C65/48 , B64C3/18
CPC分类号： B29C65/4805 , B29C33/30 , B29C33/485 , B29D99/0014 , B29L2031/3076 , B64C3/00 , B64C3/18 , B64C3/24 , B64C5/00 , B64F5/10
摘要： Method for manufacturing a base structure (8) of an aeronautical torsion box (1) for an aircraft (11) characterized in that it comprises the steps of: a.—providing at least a fresh skin (3), at least one fresh stringer (4), at least a fresh front spar (5) and fresh rear spar (6), b.—positioning the fresh skin (3), the at least one fresh stringer, the fresh spars (5, 6) in a curing tool in a configuration corresponding to that of a base structure (8), c.—subjecting the structure (8) to a single curing cycle, obtaining a cured base structure (8).
摘要翻译：一种用于制造用于飞行器（11）的航空扭转箱（1）的基座结构（8）的方法，其特征在于，其包括以下步骤：a。至少提供一个新鲜的皮肤（3），至少一个新的纵梁（4），至少一个新鲜的前翼梁（5）和新鲜的后翼梁（6），b。将新鲜的皮肤（3），至少一个新的纵梁，新鲜的翼梁（5,6）定位在固化工具具有对应于基部结构（8）的构造，c。使结构（8）进行单个固化循环，获得固化的基础结构（8）。

9. 发明申请

US20140138486A1 OPTIMIZED TORSION BOX FOR AN AIRCRAFT 有权
标题翻译：优化的机舱扭矩箱
公开(公告)号：US20140138486A1
公开(公告)日：2014-05-22
申请号：US14085381
申请日：2013-11-20
申请人： AIRBUS OPERATIONS S.L.
发明人： Enrique GUINALDO FERNADEZ , Francisco CRUZ DOMINGUEZ , Francisco Javier HONORATO RUIZ , Paula MÁS MÁS , Iker VÉLEZ DE MENDIZÁBAL ALONSO , Carlos GARCIA NIETO
IPC分类号： B64C3/18
CPC分类号： B64C3/185 , B64C3/18 , B64C3/187 , Y10T156/10
摘要： The invention provides an aircraft lifting surface with a torsion box (13) of a composite material comprising an upper skin (21), a lower skin (23), a front spar (18), a rear spar (20), one or more intermediate spars (19, 19′) and a plurality of transverse ribs (25, 25′, . . . ) arranged between the rear spar (20) and its adjacent intermediate spar (19′) and/or between the front spar (18) and the adjacent intermediate spar (19) for improving its structural behavior. The invention also provides a manufacturing method of said torsion box.
摘要翻译：本发明提供一种具有复合材料的扭转箱（13）的飞机提升表面，该复合材料包括上皮（21），下皮（23），前翼梁（18），后翼梁（20），一个或多个中间翼梁（19,19'）和布置在后翼梁（20）和其相邻的中间翼梁（19'）之间和/或前翼梁（18）之间的多个横向肋（25,25'...））和相邻的中间梁（19），用于改善其结构行为。本发明还提供了所述扭转箱的制造方法。

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