Patents by Inventor Alberto Arana Hidalgo
Alberto Arana Hidalgo has filed for patents to protect the following inventions. This listing includes patent applications that are pending as well as patents that have already been granted by the United States Patent and Trademark Office (USPTO).
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Patent number: 11845531Abstract: 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).Type: GrantFiled: November 16, 2020Date of Patent: December 19, 2023Assignee: AIRBUS OPERATIONS S.L.Inventors: Manuel Kempf, Asuncion Butragueno-Martinez, Jorge Ballestero Méndez, Fernando Iniesta Lozano, Guillermo Hernaiz Lopez, Pablo Vazquez Sanchez, Alberto Arana Hidalgo, Jesus Javier Vazquez Castro
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Publication number: 20230364867Abstract: A device (40) and a method for manufacturing composite parts such as aircraft bulkheads (23), in which a component of the composite part is placed on a first mold (11) with a robotic device (21), a component of another composite part is placed on a second mold (12) with a robotic device (22), the second mold (12) having a surface identical to the surface the first mold (11), and the first mold and the second mold being mounted on a frame in a central symmetric arrangement around a symmetry central point (15), such that components are placed on the molds (11, 12) symmetrically so as to obtain two identical composite parts at the same time.Type: ApplicationFiled: May 11, 2022Publication date: November 16, 2023Inventors: Alberto Arana Hidalgo, Pedro Nogueroles Vines
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Patent number: 11541983Abstract: 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.Type: GrantFiled: June 17, 2019Date of Patent: January 3, 2023Assignee: AIRBUS OPERATIONS S.L.Inventors: 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
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Patent number: 11377204Abstract: 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.Type: GrantFiled: June 10, 2020Date of Patent: July 5, 2022Assignee: Airbus Operations S.L.Inventor: Alberto Arana Hidalgo
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Patent number: 11377190Abstract: 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.Type: GrantFiled: June 13, 2019Date of Patent: July 5, 2022Assignee: AIRBUS OPERATIONS S.L.Inventors: 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
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Patent number: 11267584Abstract: 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.Type: GrantFiled: June 14, 2019Date of Patent: March 8, 2022Assignee: Airbus Operations S.L.Inventors: 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
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Patent number: 11225015Abstract: A method for manufacturing, layer-upon-layer, an integral composite aeronautical structure, wherein the method comprises: (a) providing an additive manufacturing tool comprising a depositing mold shaping an aerodynamic surface and at least one head configured to be moved over the depositing mold and to deposit fibrous material reinforcement and/or meltable material; (b) depositing fibrous material reinforcement embedded within meltable material onto the depositing mold, at least one layer of a lower aerodynamic face-sheet being built thereby; (c) depositing meltable material onto at least a portion of the outer layer of the lower aerodynamic face-sheet, at least one layer of core structure being built thereby; and (d) depositing fibrous material reinforcement embedded within meltable material onto at least the outer layer of the core structure, at least one layer of an upper aerodynamic face-sheet being built thereby; wherein steps (b), (c) and (d) are performed using Additive Manufacturing technology.Type: GrantFiled: January 14, 2019Date of Patent: January 18, 2022Assignee: Airbus Operations S.L.U.Inventors: Francisco Javier Honorato Ruiz, Enrique Guinaldo Fernández, Carlos García Nieto, Guillermo Hernáiz López, Jesús Javier Vázquez Castro, Diego Lastra Gil, Iker Vélez De Mendizábal Alonso, Alberto Arana Hidalgo
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Patent number: 11220354Abstract: 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).Type: GrantFiled: July 18, 2019Date of Patent: January 11, 2022Assignee: Airbus Operations S.L.U.Inventors: 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
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Publication number: 20210147062Abstract: 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).Type: ApplicationFiled: November 16, 2020Publication date: May 20, 2021Inventors: Manuel KEMPF, Asuncion BUTRAGUENO-MARTINEZ, Jorge BALLESTERO MÉNDEZ, Fernando INIESTA LOZANO, Guillermo HERNAIZ LOPEZ, Pablo VAZQUEZ SANCHEZ, Alberto ARANA HIDALGO, Jesus Javier VAZQUEZ CASTRO
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Publication number: 20210147063Abstract: 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.Type: ApplicationFiled: November 12, 2020Publication date: May 20, 2021Inventors: Manuel KEMPF, Asuncion BUTRAGUENO-MARTINEZ, Jorge BALLESTERO MÉNDEZ, Fernando INIESTA LOZANO, Guillermo HERNAIZ LOPEZ, Javier GUERRERO MARTÍN, Alberto ARANA HIDALGO, Jesus Javier VAZQUEZ CASTRO
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Patent number: 10906628Abstract: 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.Type: GrantFiled: July 11, 2018Date of Patent: February 2, 2021Assignee: Airbus Operations S.L.Inventors: Alberto Arana Hidalgo, Luis Rodriguez Urbina
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Patent number: 10890971Abstract: 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.Type: GrantFiled: August 23, 2019Date of Patent: January 12, 2021Assignee: AIRBUS OPERATIONS S.L.Inventor: Alberto Arana Hidalgo
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Publication number: 20200391854Abstract: 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.Type: ApplicationFiled: June 10, 2020Publication date: December 17, 2020Inventor: Alberto ARANA HIDALGO
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Publication number: 20200064919Abstract: 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.Type: ApplicationFiled: August 23, 2019Publication date: February 27, 2020Inventor: Alberto ARANA HIDALGO
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Publication number: 20200023934Abstract: 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).Type: ApplicationFiled: July 18, 2019Publication date: January 23, 2020Inventors: 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
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Publication number: 20190382096Abstract: 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.Type: ApplicationFiled: June 17, 2019Publication date: December 19, 2019Inventors: 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
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Publication number: 20190382137Abstract: 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.Type: ApplicationFiled: June 14, 2019Publication date: December 19, 2019Inventors: 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
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Publication number: 20190382136Abstract: 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.Type: ApplicationFiled: June 13, 2019Publication date: December 19, 2019Inventors: 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
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Publication number: 20190217536Abstract: A method for manufacturing, layer-upon-layer, an integral composite aeronautical structure, wherein the method comprises: (a) providing an additive manufacturing tool comprising a depositing mold shaping an aerodynamic surface and at least one head configured to be moved over the depositing mold and to deposit fibrous material reinforcement and/or meltable material; (b) depositing fibrous material reinforcement embedded within meltable material onto the depositing mold, at least one layer of a lower aerodynamic face-sheet being built thereby; (c) depositing meltable material onto at least a portion of the outer layer of the lower aerodynamic face-sheet, at least one layer of core structure being built thereby; and (d) depositing fibrous material reinforcement embedded within meltable material onto at least the outer layer of the core structure, at least one layer of an upper aerodynamic face-sheet being built thereby; wherein steps (b), (c) and (d) are performed using Additive Manufacturing technology.Type: ApplicationFiled: January 14, 2019Publication date: July 18, 2019Inventors: Francisco Javier HONORATO RUIZ, Enrique GUINALDO FERNÁNDEZ, Carlos GARCÍA NIETO, Guillermo HERNÁIZ LÓPEZ, Jesús Javier VÁZQUEZ CASTRO, Diego LASTRA GIL, Iker VÉLEZ DE MENDIZÁBAL ALONSO, Alberto ARANA HIDALGO
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Publication number: 20190161211Abstract: 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.Type: ApplicationFiled: November 21, 2018Publication date: May 30, 2019Inventors: Alberto ARANA HIDALGO, José Luis MARTÍNEZ MUÑOZ