公开(公告)号：US20140138486A1

公开(公告)日：2014-05-22

申请号：US14085381

申请日：2013-11-20

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Enrique GUINALDO FERNADEZ ,  Francisco CRUZ DOMINGUEZ ,  Francisco Javier HONORATO RUIZ ,  Paula MÁS MÁS ,  Iker VÉLEZ DE MENDIZÁBAL ALONSO ,  Carlos GARCIA NIETO

IPC: B64C3/18

CPC classification number: B64C3/185 ,  B64C3/18 ,  B64C3/187 ,  Y10T156/10

Abstract: 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.

Abstract translation: 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。

公开(公告)号：US20190382136A1

公开(公告)日：2019-12-19

申请号：US16440317

申请日：2019-06-13

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Esteban MARTINO-GONZALEZ ,  Alberto ARANA HIDALGO ,  Melania SANCHEZ PEREZ ,  Carlos GARCIA NIETO ,  Jesus Javier VAZQUEZ CASTRO ,  Edouard MENARD ,  Fernando INIESTA LOZANO ,  Maria Almudena CANAS RIOS

IPC: B64F5/10 ,  B64C5/02 ,  B64C1/06 ,  B64C1/12

Abstract: A method for manufacturing an aircraft rear section including a tail cone and a vertical tail plane, the method includes: providing pre-cured frames (1) each of which includes a section of the tail cone (2) and a section of the vertical tail plane (3); providing pre-cured stringers (4); placing the pre-cured stringers (4) each in respective positions within the pre-cured frames (1); placing a skin (5) around an external surface of the pre-cured frames (1); and curing the pre-cured frames (1), the pre-cured stringers (4), and the skin (5), forming the final aircraft rear section.

公开(公告)号：US20150375846A1

公开(公告)日：2015-12-31

申请号：US14753986

申请日：2015-06-29

Applicant: Airbus Operations, S.L.

Inventor： Carlos GARCIA NIETO ,  Enrique GUINALDO FERNÁNDEZ ,  Iker VELEZ DE MENDIZÁBAL ALONSO ,  Luis RAMOS GARCIA

IPC: B64C3/28 ,  B64C3/18 ,  B21J15/02 ,  B29D99/00

CPC classification number: B64C3/28 ,  B21J15/02 ,  B29C70/30 ,  B29D99/0003 ,  B29D99/0028 ,  B29K2105/256 ,  B64C3/185 ,  B64C3/20 ,  Y02T50/43

Abstract: A method for manufacturing a leading edge of an aircraft lifting surface, the leading edge having a leading edge skin and a supporting structure including at least two spars span-wise arranged and fixed internally to the leading edge skin. In the method of the invention, the supporting structure is obtained from a single laminate of plies of composite material, which is conformed in such that in a cross-sectional view, the laminate includes a trapezoidal configuration which forms a front spar and a rear spar of the supporting structure. A leading edge obtained by the above-described method is disclosed. Since the supporting structure of the leading edge is obtained from a single component, namely the laminate, the manufacturing method is simplified and production costs are significantly reduced.

Abstract translation: 一种用于制造飞机提升表面的前缘的方法，所述前缘具有前缘皮肤和支撑结构，所述支撑结构包括跨越方向布置并固定在所述前缘皮肤内部的至少两个翼梁。 在本发明的方法中，支撑结构由复合材料层的单层层叠体获得，该复合材料层叠在一起，在横截面图中，层压板包括形成前翼梁和后翼梁的梯形构型 的支撑结构。 公开了通过上述方法获得的前沿。 由于前缘的支撑结构是从单一部件即层压板获得的，所以制造方法简单化，生产成本显着降低。

公开(公告)号：US20190382137A1

公开(公告)日：2019-12-19

申请号：US16441448

申请日：2019-06-14

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Esteban MARTINO-GONZALEZ ,  Alberto ARANA HIDALGO ,  Melania SANCHEZ PEREZ ,  Carlos GARCIA NIETO ,  Jesus Javier VAZQUEZ CASTRO ,  Edouard MENARD ,  Fernando INIESTA LOZANO ,  Maria Almudena CANAS RIOS

IPC: B64F5/10 ,  B64C1/06

Abstract: A method for manufacturing a composite assembly of an empennage and rear-fuselage having a continuous skin solution. The method obtains parts of the sub-structure. For each part, it is obtained a plurality of stringers performs and frames preforms by composite tooling. The frames are transferred to curing frames molds and a sub-structure skin is obtained. Furthermore, the method includes integrating the parts over an integration tool having cavities for locating the curing frames molds and the stringer performs. Furthermore, the method includes co-curing the integration tool in one shot on an autoclave, demolding the sub-structure skin sections and disassembling the curing frame molds to obtain the composite assembly of the rear section.

公开(公告)号：US20190145550A1

公开(公告)日：2019-05-16

申请号：US16190732

申请日：2018-11-14

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Francisco Javier HONORATO RUIZ ,  Diego SANCHEZ FRANCO ,  Luis RODRIGUEZ URBINA ,  Enrique GUINALDO FERNANDEZ ,  Carlos GARCIA NIETO

IPC: F16L3/123 ,  H02G3/00

CPC classification number: 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

Abstract: 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).

公开(公告)号：US20170334545A1

公开(公告)日：2017-11-23

申请号：US15523074

申请日：2015-10-30

Applicant: Airbus Operations, S.L.

Inventor： Enrique GUINALDO FERNANDEZ ,  Carlos GARCIA NIETO ,  Iker VELEZ DE MENDIZABAL ALONSO ,  Javier Francisco HONORATO RUIZ ,  Jose Francisco CRUZ DOMINGUEZ ,  Luis RAMOS GARCIA

IPC: B64C5/02 ,  B64C1/26

CPC classification number: B64C5/02 ,  B64C1/26

Abstract: An aircraft horizontal tail plane (HTP) of the continuous type, wherein the inner-most ribs of the right-hand side and left-hand side torsion boxes are arranged to have one end joined right at the joint zone where both rear spars meet at axis of symmetry of the HTP. In this way, the loads at this central region of the HTP are concentrated at the joint zone where the inner-most ribs and the rear spars converge. The HTP can be manufactured with a reduced number of components.

公开(公告)号：US20140151506A1

公开(公告)日：2014-06-05

申请号：US14086424

申请日：2013-11-21

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Enrique GUINALDO FERNANDEZ ,  Francisco CRUZ DOMINGUEZ ,  Francisco Javier HONORATO RUIZ ,  Paula MÁS MÁS ,  Iker VÉLEZ DE MENDIZÁBAL ALONSO ,  Carlos GARCIA NIETO

IPC: B64C3/18 ,  B29C70/30 ,  B29C35/02 ,  B29D99/00

CPC classification number: B64C3/182 ,  B29C35/0238 ,  B29C70/30 ,  B29D99/0014 ,  B29L2031/3085 ,  B64C3/185 ,  B64C3/187 ,  B64C3/20 ,  B64C5/02 ,  Y02T50/43

Abstract: 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).

Abstract translation: 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。

公开(公告)号：US20200023934A1

公开(公告)日：2020-01-23

申请号：US16515330

申请日：2019-07-18

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Esteban MARTINO-GONZALEZ ,  Alberto ARANA HIDALGO ,  Melania SANCHEZ PEREZ ,  Carlos GARCIA NIETO ,  Jesus Javier VAZQUEZ CASTRO ,  Edouard MENARD ,  Fernando INIESTA LOZANO ,  Maria Almudena CANAS RIOS

IPC: B64C1/12 ,  B64C5/02 ,  B64C1/06 ,  B64C1/26

Abstract: A method for manufacturing a composite rear section assembly having a continuous skin solution including obtaining a vertical tail plane tooling that has intermediate tooling for tooling intermediate preforms of a vertical tail plane (800), obtaining a fuselage barrel tooling (420a), (420b), (420c) and (420d) the fuselage barrel tooling having a cut-out (503a), (503b), (503c) and longitudinal cavities (501a), (501b), (501c) and (501d), attaching the vertical tail plane tooling to the fuselage barrel tooling by the cut-out of the fuselage barrel tooling, performing a composite skin lay-up (801) over the fuselage barrel tooling and the vertical tail plane tooling to obtain a continuous skin, curing the composite skin lay-up, the vertical tail plane tooling and the fuselage barrel tooling and demolding the tools to obtain the composite assembly with a continuous skin (1300), (1600).

公开(公告)号：US20190382096A1

公开(公告)日：2019-12-19

申请号：US16442688

申请日：2019-06-17

Applicant: Airbus Operations S.L.

Inventor： Esteban MARTINO-GONZALEZ ,  Alberto ARANA HIDALGO ,  Melania SANCHEZ PEREZ ,  Carlos GARCIA NIETO ,  Jesus Javier VAZQUEZ CASTRO ,  Edouard MENARD ,  Fernando INIESTA LOZANO ,  Maria Almudena CANAS RIOS

IPC: B64C1/26

Abstract: A method for manufacturing a composite assembly with a continuous skin for a rear end of an aircraft by obtaining an upper part of the rear end by composite tooling. The upper part comprises a multi-spar vertical tail plane. The spars of the vertical tail plane comprise widening roots that form an upper shell of the rear end and an upper skin. Furthermore, a lower part comprises a lower shell of the rear end including semi-complete frames and stringers and a lower skin. The upper and lower parts are assembled with a joining procedure. The upper and lower skins are joined to obtain the composite assembly with the continuous skin.