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1.发明申请公开(公告)号：US20190382136A1
公开(公告)日：2019-12-19
申请号：US16440317
申请日：2019-06-13
发明人： 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
摘要： 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.
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公开(公告)号：US20190016437A1
公开(公告)日：2019-01-17
申请号：US16032246
申请日：2018-07-11
摘要： 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.
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公开(公告)号：US20210147063A1
公开(公告)日：2021-05-20
申请号：US17096108
申请日：2020-11-12
发明人： Manuel KEMPF , Asuncion BUTRAGUENO-MARTINEZ , Jorge BALLESTERO MÉNDEZ , Fernando INIESTA LOZANO , Guillermo HERNAIZ LOPEZ , Javier GUERRERO MARTÍN , Alberto ARANA HIDALGO , Jesus Javier VAZQUEZ CASTRO
摘要： A fireproof and thermal insulator product which includes a honey-comb core infilled with Alkaline Earth Silicate material. The material of the honey-comb core can be metallic or polymeric. The product may further include a FRP layer, and/or a liquid barrier film, preferably being of thermoplastic material. An adhesive layer may be further deposited between the layer of honey-comb core infilled with AES and the layer of FRP.
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公开(公告)号：US20210147062A1
公开(公告)日：2021-05-20
申请号：US17098772
申请日：2020-11-16
发明人： 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分类号： B64C1/40 , B32B7/12 , B32B7/08 , B32B9/00 , B32B9/04 , B32B27/12 , B32B27/30 , B32B27/36 , B32B27/28 , B32B9/02 , H01M2/02
摘要： 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).
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公开(公告)号：US20190382137A1
公开(公告)日：2019-12-19
申请号：US16441448
申请日：2019-06-14
发明人： 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
摘要： 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.
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6.发明申请公开(公告)号：US20190161211A1
公开(公告)日：2019-05-30
申请号：US16197719
申请日：2018-11-21
摘要： An aircraft with a system for rearward mounting and dismounting an engine, the engine being placed inside the rear part of the aircraft when mounted. The system for rearward mounting and dismounting the engine comprises a first removable attachment device arranged to attach the engine to the fuselage in the rear part of the aircraft, internal supports fixed in the rear part of the aircraft, at least two longitudinal detachable rails, to be placed on the internal supports and under the engine, and a slider to attach to the engine via a second removable attachment device, to be placed on the longitudinal detachable rails.
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公开(公告)号：US20180022436A1
公开(公告)日：2018-01-25
申请号：US15654912
申请日：2017-07-20
CPC分类号： B64C1/1446 , E05C19/16
摘要： A union arrangement between a non-structural panel of the outer surface of an aircraft and a supporting member belonging to the aircraft resistant structure using mechanical and magnetic devices as an attachment arrangement. The magnetic devices comprise permanent magnets located in one of the non-structural panel or the supporting member and devices cooperating with the permanent magnets located in the other of the supporting member or the non-structural panel. The magnetic devices are used for both facilitating the self-clamping of the non-structural panel to the supporting member during the union operation and serving as fastening devices together with mechanical devices such as bolts installed in holes.
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公开(公告)号：US20200064919A1
公开(公告)日：2020-02-27
申请号：US16549240
申请日：2019-08-23
摘要： 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.
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公开(公告)号：US20200023934A1
公开(公告)日：2020-01-23
申请号：US16515330
申请日：2019-07-18
发明人： 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
摘要： 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).
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公开(公告)号：US20190382096A1
公开(公告)日：2019-12-19
申请号：US16442688
申请日：2019-06-17
发明人： 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分类号： B64C1/26
摘要： 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.
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