公开(公告)号：US20170088249A1

公开(公告)日：2017-03-30

申请号：US15279586

申请日：2016-09-29

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： Carlos GARCÍA NIETO ,  Iker VELEZ DE MENDIZABAL ALONSO ,  Enrique GUINALDO FERNANDEZ ,  Soledad CRESPO PEÑA

IPC: B64C3/18 ,  B29C70/48 ,  B64F5/00

CPC classification number: B64C3/187 ,  B29C70/48 ,  B29K2105/0872 ,  B29L2031/3085 ,  B64C3/20 ,  B64F5/45 ,  Y02T50/43

Abstract: The present disclosure refers to the configuration and manufacturing process of a rib for the construction of an aircraft torsion box. In the method, a flat stack of plies of composite material is layered up, which is then cut to form a flat pre-form having an outer contour having flanges, and an internal contour having two or more diagonal trusses with flanges at opposite sides. The flat pre-form is press-formed to fold the flanges of the outer and internal contour to form a rib pre-form, which is finally cured. The present disclosure also refers to a composite rib having a unitary body by forming a single pre-form of stacked plies. The present disclosure allows the manufacture of the rib in one-shot process, integrating all the ribs components such that the assembly time and cost of the rib are minimized.

公开(公告)号：US20170259903A1

公开(公告)日：2017-09-14

申请号：US15457499

申请日：2017-03-13

Applicant: AIRBUS OPERATIONS, S.L.

Inventor： 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: B64C3/26 ,  B29C69/00 ,  B29C45/40 ,  B29C45/00 ,  B29C45/14

CPC classification number: 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

Abstract: 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.

公开(公告)号：US20140133987A1

公开(公告)日：2014-05-15

申请号：US13943115

申请日：2013-07-16

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Enrique GUINALDO FERNANDEZ ,  Francisco Javier HONORATO RUIZ ,  Francisco Jose CRUZ DOMINGUEZ

IPC: F01D5/14

CPC classification number: F01D5/14 ,  B29D99/0028 ,  B64C3/28 ,  Y10T29/49336

Abstract: 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.

Abstract translation: 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。

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。