公开(公告)号：US10890971B2

公开(公告)日：2021-01-12

申请号：US16549240

申请日：2019-08-23

Applicant: Airbus Operations, S.L.

Inventor： Alberto Arana Hidalgo

IPC: G06F3/01 ,  B64F5/40 ,  B64F5/10 ,  G06F3/14

Abstract: A virtual reality (VR) system for providing a real time VR visualization of a target area of an aircraft that comprises one or more reference targets established in known locations in the target area of an aircraft, hand gloves, a plurality of sensing elements established on at least the operator's hand gloves, a reception device that receives the information provided by the sensing elements to provide relative locations of the sensing elements against the one or more reference targets. The reception device comprises processing means to build the real time VR visualization that represents at least the operator's hands against the target area of the aircraft based on the sensing elements. The VR system also comprises display means that display the real time VR visualization to the operator.

公开(公告)号：US11377190B2

公开(公告)日：2022-07-05

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

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：US11845531B2

公开(公告)日：2023-12-19

申请号：US17098772

申请日：2020-11-16

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Manuel Kempf ,  Asuncion Butragueno-Martinez ,  Jorge Ballestero Méndez ,  Fernando Iniesta Lozano ,  Guillermo Hernaiz Lopez ,  Pablo Vazquez Sanchez ,  Alberto Arana Hidalgo ,  Jesus Javier Vazquez Castro

IPC: B64C1/40 ,  H01M50/116 ,  B32B7/08 ,  B32B7/12 ,  B32B9/00 ,  B32B9/02 ,  B32B9/04 ,  B32B27/12 ,  B32B27/28 ,  B32B27/30 ,  B32B27/36 ,  B64C1/00

CPC classification number: B64C1/40 ,  B32B7/08 ,  B32B7/12 ,  B32B9/005 ,  B32B9/02 ,  B32B9/045 ,  B32B9/047 ,  B32B27/12 ,  B32B27/285 ,  B32B27/304 ,  B32B27/36 ,  H01M50/116 ,  B32B2262/101 ,  B32B2262/106 ,  B32B2307/304 ,  B32B2307/3065 ,  B32B2307/7265 ,  B32B2457/10 ,  B32B2605/18 ,  B64C2001/0054 ,  H01M2220/20

Abstract: A fireproof and thermal insulator product (1) including an Alkaline Earth Silicate (AES) material (2), and at least one of the following: a liquid barrier film (5), an FRP (Fiber Reinforcement Plastic) layer (4), cork (3), wherein the liquid barrier film (5) and the FRP layer (4) are staked onto the AES material (2), and wherein the cork (3) material is also staked onto the AES material (2) or embedded into said AES material (2) in where said cork (3) is configured as a plurality of strips performing a grid structure infilled with the AES material (2).

公开(公告)号：US11267584B2

公开(公告)日：2022-03-08

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：US20140120302A1

公开(公告)日：2014-05-01

申请号：US14067655

申请日：2013-10-30

Applicant: Airbus Operations, S.L.

Inventor： Alberto Arana Hidalgo ,  Tomas Rodriguez Hernandez

IPC: B64C1/06

CPC classification number: B64C1/064 ,  B64C3/182 ,  Y10T156/10 ,  Y10T428/24124

Abstract: A stringer made of composite material for reinforcing aircraft skin panels. Plies are introduced at 90° in a segment close to the stringer run-out, and progressively reducing the number of plies at 0°, such that the majority of the number of plies is at 90° in an segment adjacent to the run-out, so the stiffness of the run-out is reduced, and the load it supports is also therefore reduced. This is an alternative solution to the solutions already existing for getting the stringer run-outs to support a smaller load, thereby reducing both the risk of the plies of the stringer peeling off and the risk of separation between stringer and skin panel. A method of manufacturing said stringer is also provided.

Abstract translation: 由复合材料制成的用于加强飞机皮肤面板的桁条。 在靠近桁条径向的部分中以90°引入板，并且在0°逐渐减少层数，使得在与缺相相邻的部分中的层数大部分为90° ，因此减少了弹出的刚度，并且因此减小了其支撑的负载。 这是解决已有的解决方案，以便使桁条镂空支撑较小的载荷，从而降低桁条剥落的风险以及桁条和皮肤面板之间分离的风险。 还提供了制造所述纵梁的方法。

公开(公告)号：US11541983B2

公开(公告)日：2023-01-03

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 ,  B64F5/10

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.

公开(公告)号：US11377204B2

公开(公告)日：2022-07-05

申请号：US16897611

申请日：2020-06-10

Applicant: Airbus Operations S.L.

Inventor： Alberto Arana Hidalgo

IPC: B64C23/06 ,  B64D41/00 ,  H01F7/06 ,  H01F7/20

Abstract: A retractable vortex generator system for an aircraft. The system comprises a skin, a slot arranged on the skin, a plate comprising a contour configured for energizing the boundary layer of an air current, and driving means configured for rotating the plate between a first and a second position. In the first position at least part of the contour of the plate protrudes through the slot, and in the second position the plate is retracted within the slot.

公开(公告)号：US09919785B2

公开(公告)日：2018-03-20

申请号：US14067655

申请日：2013-10-30

Applicant: Airbus Operations, S.L.

Inventor： Alberto Arana Hidalgo ,  Tomas Rodriguez Hernandez

IPC: B64C1/06 ,  B64C3/18

CPC classification number: B64C1/064 ,  B64C3/182 ,  Y10T156/10 ,  Y10T428/24124

Abstract: A stringer made of composite material for reinforcing aircraft skin panels. Plies are introduced at 90° in a segment close to the stringer run-out, and progressively reducing the number of plies at 0°, such that the majority of the number of plies is at 90° in an segment adjacent to the run-out, so the stiffness of the run-out is reduced, and the load it supports is also therefore reduced. This is an alternative solution to the solutions already existing for getting the stringer run-outs to support a smaller load, thereby reducing both the risk of the plies of the stringer peeling off and the risk of separation between stringer and skin panel. A method of manufacturing said stringer is also provided.

公开(公告)号：US11220354B2

公开(公告)日：2022-01-11

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: B64F5/10 ,  B64C1/26 ,  B64C3/26 ,  B64C5/02 ,  B64C1/00

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：US10906628B2

公开(公告)日：2021-02-02

申请号：US16032246

申请日：2018-07-11

Applicant: AIRBUS OPERATIONS S.L.

Inventor： Alberto Arana Hidalgo ,  Luis Rodriguez Urbina

IPC: B64C3/18 ,  B64C3/20 ,  B64C1/06 ,  B64C5/06 ,  B64C3/26 ,  B64C5/02 ,  F16L3/00 ,  H02G3/04 ,  B64C1/00

Abstract: A box structural arrangement (1) for an aircraft including first (2) and second composite layers (3), at least one spar web (4) extended between opposite edges of the first and second composite layers (2, 3) along a longitudinal direction, and a conduit piece (5) extended between opposite edges of the first and second composite layers (2, 3). The conduit piece (5) has a hollow section (6) comprising at least one conduit (7) dimensioned to receive pipes or harnesses and surrounded by a resilient material (8). The conduit piece (5) is mounted on the spar web (4) to provide a channeled box structural arrangement (1). The box structural arrangement can be applicable in a torsion box or a wing. The invention further refers to a method for manufacturing the box structural arrangement for an aircraft.