Patents by Inventor Alberto Balsa Gonzalez
Alberto Balsa Gonzalez 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: 12103250Abstract: A device and a process for manufacturing a composite part, the device comprising four molding mandrels that can be arranged in a mold arrangement in which they form a mold for the composite part, as well as a locking mandrel configured to lock the molding mandrels in the mold arrangement and to be extracted from between the molding mandrels to release the molding mandrels from their mold arrangement. The locking mandrel extends from one longitudinal end of the molding mandrels to another opposite longitudinal end of the molding mandrels.Type: GrantFiled: July 27, 2022Date of Patent: October 1, 2024Assignee: Airbus Operations S.L.Inventors: Robert Kobierecki, Alberto Balsa-Gonzalez, Jose Luis Lozano Garcia
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Patent number: 12006064Abstract: A manufacturing method of a control surface of an aircraft, the control surface including an upper skin, a lower skin, ribs joining the upper skin and the lower skin and located along a chordwise direction of the control surface. The manufacturing method includes the steps of providing a single composite preform comprising the upper skin, the lower skin and the ribs, and curing the single composite preform such that an integrated box comprising the upper skin, the lower skin and the ribs is formed.Type: GrantFiled: November 22, 2022Date of Patent: June 11, 2024Assignee: Airbus Operations S.L.U.Inventors: Robert Kobierecki, David Martin Palomares, Alberto Balsa-Gonzalez
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Patent number: 11708146Abstract: A multispar lifting surface including a multispar torsion box having corner reinforcements, a movable control surface, and an axial rod fitting. The movable control surface includes a movable element, a hinged connection joined to the movable element, and an axial rod joining the hinged connection to the rear spar of the multispar torsion box. The axial rod fitting is configured to join the axial rod and the multispar torsion box; and includes a longitudinal profile resting against the rear spar, and a lug joined to the longitudinal profile at one end and to the axial rod at another end; the lug defining a plane including the longitudinal axis of the axial rod. This multispar lifting surface is able to support sideward forces without any additional structure.Type: GrantFiled: November 23, 2021Date of Patent: July 25, 2023Assignee: Airbus Operations S.L.U.Inventors: Robert Kobierecki, Alberto Balsa-Gonzalez
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Patent number: 11673645Abstract: A trailing edge for a composite lifting surface is disclosed having a spar, an upper panel and a lower panel each having a free edge, a seal, and an elongated profile located on the panels following a spanwise direction of the trailing edge. An elongated profile including a web extending along the spanwise direction of the trailing edge, and having first and second flange portions, and a transition zone in between the first and second flange portions extending at different heights with respect to each other. The first flange portion is configured to hold at least a part of the seal underneath, and the second flange portion is configured to contact the panel so that the first flange portion secures the seal to the panel, and the second flange portion secures the elongated profile to the panel.Type: GrantFiled: April 16, 2021Date of Patent: June 13, 2023Assignee: AIRBUS OPERATIONS S.L.Inventors: Robert Kobierecki, Alberto Balsa-Gonzalez
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Publication number: 20230159186Abstract: A manufacturing method of a control surface of an aircraft, the control surface including an upper skin, a lower skin, ribs joining the upper skin and the lower skin and located along a chordwise direction of the control surface. The manufacturing method includes the steps of providing a single composite preform comprising the upper skin, the lower skin and the ribs, and curing the single composite preform such that an integrated box comprising the upper skin, the lower skin and the ribs is formed.Type: ApplicationFiled: November 22, 2022Publication date: May 25, 2023Inventors: Robert KOBIERECKI, David MARTIN PALOMARES, Alberto BALSA-GONZALEZ
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Patent number: 11649034Abstract: A flight control surface comprising a main body comprising an upper and lower cover, upper and lower skins and a core member, a prolongation of their length over the length of the core member defining a stepped area. A trailing edge of the control surface comprises a U-shaped profile enclosing the prolongation, the U-shaped profile extending towards the main body in the chordwise direction up to the stepped area and comprising a section that progressively decreases. The trailing edge comprises a first and a second set of rivets located in the prolongation, the first set of rivets joining the upper and lower covers and the second set of rivets joining the U-shaped profile, the upper covers and the lower covers.Type: GrantFiled: January 16, 2020Date of Patent: May 16, 2023Assignee: Airbus Operations S.L.Inventors: Robert Kobierecki, Miguel Ángel Mendez Rodríguez, Juan Antonio Sánchez Ruiz, Alberto Balsa-Gonzalez
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Patent number: 11597496Abstract: A leading edge for an airfoil of an aircraft includes a leading plate with a convex side and a concave side, and at least one container filled with a non-Newtonian fluid. The leading edge is configured to be secured to the torsion box of the airfoil. The at least one container is arranged between the concave side of the leading plate and the torsion box of the airfoil. An airfoil is also provided including such a leading edge. A method is provided for assembling such a leading edge.Type: GrantFiled: December 16, 2020Date of Patent: March 7, 2023Assignee: Airbus Operations S.L.Inventors: Javier Carlos Gomez del Valle, Alberto Balsa-Gonzalez
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Publication number: 20230033860Abstract: A device and a process for manufacturing a composite part, the device comprising four molding mandrels that can be arranged in a mold arrangement in which they form a mold for the composite part, as well as a locking mandrel configured to lock the molding mandrels in the mold arrangement and to be extracted from between the molding mandrels to release the molding mandrels from their mold arrangement. The locking mandrel extends from one longitudinal end of the molding mandrels to another opposite longitudinal end of the molding mandrels.Type: ApplicationFiled: July 27, 2022Publication date: February 2, 2023Inventors: Robert KOBIERECKI, Alberto BALSA-GONZALEZ, Jose Luis LOZANO GARCIA
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Patent number: 11427297Abstract: A trailing edge for a composite multispar integrated lifting surface includes a first C-shape composite form that includes a web and two flanges. The web forming a portion of the rear spar of a torsion box. The two flanges extending along a skin chordwise direction. A second C-shape composite form includes a web and two flanges. The web forms an auxiliary spar. The flanges extend along the skin chordwise direction. The first C-shape composite form and the second C-shape composite form forming a first auxiliary cell and a second cell. The first auxiliary cell is delimited by the first C-shape composite form and the second C-shape composite form. The second cell is an open cell delimited by the second C-shape composite form.Type: GrantFiled: December 9, 2020Date of Patent: August 30, 2022Assignee: AIRBUS OPERATIONS S.L.U.Inventors: Alberto Balsa-Gonzalez, Jose Luis Lozano Garcia, Robert Kobierecki
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Patent number: 11407492Abstract: A leading edge (3) of a control surface (1) for an aircraft includes a balance weight (6) attached to the forward-most region of the leading edge (3). The control surface (1) rotates with respect to the stabilizer (2) around a hinge line (5). The balance weight (6) is ahead of and adjacent to the most frontal portion (7) of the leading edge (3) of the control surface (1) are is inside the trailing edge of the stabilizer (2). This arrangement allows to have an anti-flutter balance weight without any impact in aerodynamic drag.Type: GrantFiled: October 27, 2020Date of Patent: August 9, 2022Assignee: AIRBUS OPERATIONS, S.L.U.Inventors: Alberto Balsa-Gonzalez, Miguel Ángel Mendez Rodriguez, Robert Kobierecki, Juan Antonio Sánchez Ruiz
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Publication number: 20220161921Abstract: A multispar lifting surface including a multispar torsion box having corner reinforcements, a movable control surface, and an axial rod fitting. The movable control surface includes a movable element, a hinged connection joined to the movable element, and an axial rod joining the hinged connection to the rear spar of the multispar torsion box. The axial rod fitting is configured to join the axial rod and the multispar torsion box; and includes a longitudinal profile resting against the rear spar, and a lug joined to the longitudinal profile at one end and to the axial rod at another end; the lug defining a plane including the longitudinal axis of the axial rod. This multispar lifting surface is able to support sideward forces without any additional structure.Type: ApplicationFiled: November 23, 2021Publication date: May 26, 2022Inventors: Robert KOBIERECKI, Alberto BALSA-GONZALEZ
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Publication number: 20210339847Abstract: A trailing edge for a composite lifting surface is disclosed having a spar, an upper panel and a lower panel each having a free edge, a seal, and an elongated profile located on the panels following a spanwise direction of the trailing edge. An elongated profile including a web extending along the spanwise direction of the trailing edge, and having first and second flange portions, and a transition zone in between the first and second flange portions extending at different heights with respect to each other. The first flange portion is configured to hold at least a part of the seal underneath, and the second flange portion is configured to contact the panel so that the first flange portion secures the seal to the panel, and the second flange portion secures the elongated profile to the panel.Type: ApplicationFiled: April 16, 2021Publication date: November 4, 2021Inventors: Robert KOBIERECKI, Alberto BALSA-GONZALEZ
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Publication number: 20210188421Abstract: A leading edge for an airfoil of an aircraft includes a leading plate with a convex side and a concave side, and at least one container filled with a non-Newtonian fluid. The leading edge is configured to be secured to the torsion box of the airfoil. The at least one container is arranged between the concave side of the leading plate and the torsion box of the airfoil. An airfoil is also provided including such a leading edge. A method is provided for assembling such a leading edge.Type: ApplicationFiled: December 16, 2020Publication date: June 24, 2021Inventors: Javier Carlos GOMEZ DEL VALLE, Alberto BALSA-GONZALEZ
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Publication number: 20210179255Abstract: A trailing edge for a composite multispar integrated lifting surface includes a first C-shape composite form that includes a web and two flanges. The web forming a portion of the rear spar of a torsion box. The two flanges extending along a skin chordwise direction. A second C-shape composite form includes a web and two flanges. The web forms an auxiliary spar. The flanges extend along the skin chordwise direction. The first C-shape composite form and the second C-shape composite form forming a first auxiliary cell and a second cell. The first auxiliary cell is delimited by the first C-shape composite form and the second C-shape composite form. The second cell is an open cell delimited by the second C-shape composite form.Type: ApplicationFiled: December 9, 2020Publication date: June 17, 2021Inventors: Alberto BALSA-GONZALEZ, Jose Luis LOZANO GARCIA, Robert KOBIERECKI
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Publication number: 20210122459Abstract: A leading edge (3) of a control surface (1) for an aircraft includes a balance weight (6) attached to the forward-most region of the leading edge (3). The control surface (1) rotates with respect to the stabilizer (2) around a hinge line (5). The balance weight (6) is ahead of and adjacent to the most frontal portion (7) of the leading edge (3) of the control surface (1) are is inside the trailing edge of the stabilizer (2). This arrangement allows to have an anti-flutter balance weight without any impact in aerodynamic drag.Type: ApplicationFiled: October 27, 2020Publication date: April 29, 2021Inventors: Alberto BALSA-GONZALEZ, Miguel Ángel MENDEZ RODRIGUEZ, Robert KOBIERECKI, Juan Antonio SÁNCHEZ RUIZ
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Publication number: 20200231270Abstract: A flight control surface comprising a main body comprising an upper and lower cover, upper and lower skins and a core member, a prolongation of their length over the length of the core member defining a stepped area. A trailing edge of the control surface comprises a U-shaped profile enclosing the prolongation, the U-shaped profile extending towards the main body in the chordwise direction up to the stepped area and comprising a section that progressively decreases. The trailing edge comprises a first and a second set of rivets located in the prolongation, the first set of rivets joining the upper and lower covers and the second set of rivets joining the U-shaped profile, the upper covers and the lower covers.Type: ApplicationFiled: January 16, 2020Publication date: July 23, 2020Inventors: Robert KOBIERECKI, Miguel Ángel MENDEZ RODRÍGUEZ, Juan Antonio SÁNCHEZ RUIZ, Alberto BALSA-GONZALEZ
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Patent number: 9108721Abstract: The invention discloses a trailing edge (2) of an aircraft aerodynamic surface, which comprises an upper skin (6) and a lower skin (7), being the upper and lower skins (6, 7) made of composite material. In the trailing edge (2) a lightweight part (1) is assembled at an end section (13) of the upper and lower skins (6, 7). The lightweight part (1) is covered by a metallic sheet (8), and has a “V”-shaped cross section with arms and peak, where the peak of the “V”-shaped cross section has a rounded shape and is located opposite the end section (13) of the upper and lower skins (6, 7).Type: GrantFiled: February 25, 2013Date of Patent: August 18, 2015Assignee: Airbus Operations, S.L.Inventors: Yolanda De Gregorio Hurtado, Alberto Balsa Gonzalez
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Patent number: 8800149Abstract: A repair process for a composite material panel that forms part of a fuselage, wings, or stabilizers of an aircraft, with the panel having large dimensions and including irregular contours in some areas and edges prone to damages occurring from handling and assembly of the panel. The process a) locates the damage in the element of the composite material panel; b) sands the area that includes the damage in an area larger than the damage, makes a cut in the panel, having the cut of a same form as a piece that will serve to repair panel; c) places the piece in the cut, so that it is perfectly flush with the panel to be repaired; and d) attaches the piece to the composite material panel.Type: GrantFiled: May 27, 2010Date of Patent: August 12, 2014Assignee: Airbus Operations S.L.Inventors: Alberto Balsa Gonzalez, Francisco de Paula Burgos Gallego
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Publication number: 20140017445Abstract: The present invention relates to a repair part and to a repair method. The repair part is an elongated part made of a composite material comprising two attached portions forming an angle and holes in each portion arranged in the direction of the line joining both portions. The repair method includes: providing a fragment of a repair part, being long enough to cover the damaged area of the part to be repaired, maintaining a border for fixing the fragment of the repair part; making holes in both portions of the part to be repaired, such that the distance between the centers of consecutive repair holes is the same as the distance between the centers of the consecutive holes; and attaching the fragment of the repair part to the part to be repaired.Type: ApplicationFiled: June 26, 2013Publication date: January 16, 2014Inventors: Alberto Balsa Gonzalez, Jose Javier Almendros Gomez, Narciso Rodriguez Garcia, Maria Rocio Fernando Magarzo
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Patent number: 8444091Abstract: Trailing edge (3) of an aircraft stabilizer surface (1), where this surface (1) is manufactured of a composite material and comprises an outer cladding (40) and an inner cladding (41) that are connected by a connecting clip type element (20) on this trailing edge (3), the connecting clip type element (20) comprising at its ends some recesses (23) used for coupling to the inner zone of the upper and lower claddings (40, 41) of the stabilizer surface (1), such that the connecting clip type element (20) is flexible enough to be pinched so that its ends will be housed, by means of these recesses (23), between the outer and inner claddings (40, 41) of the aircraft stabilizer surface (1), whereby the outer zone of the stabilizer surface (1), on its trailing edge (3), is formed by a continuous aerodynamic surface without changes of gradient.Type: GrantFiled: February 19, 2009Date of Patent: May 21, 2013Assignee: Airbus Operations S.L.Inventors: Alberto Balsa González, Francisco de Paula Burgos Gallego