Patents by Inventor Luis A. Lozano
Luis A. Lozano 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: 8177169Abstract: Joining structure for aircraft fairing (7), said fairing (7) being arranged between the horizontal stabilizer and the vertical stabilizer or fuselage section (6) of the aircraft, the structure comprising fittings (2) in the shape of angle, the fittings in turn comprising a vertical surface and a horizontal surface, the fittings (2) being joined via their vertical surface to the fairing (7) with removable fixing parts (12), the structure also comprising a deformable resilient element (13) between the fairing (7) and the vertical surface of the fitting (2), such that the resilient element (13) is able to compensate for the necessary deformation play and the manufacturing and assembly tolerances of the fittings (2), the fairing (7), the horizontal stabilizer and the vertical stabilizer or fuselage section (6) with different torques for tightening of the above parts.Type: GrantFiled: June 4, 2009Date of Patent: May 15, 2012Assignee: Airbus Operations S.L.Inventors: Abel Lobo Barros, Jose Luis Lozano Garcia
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Patent number: 8091829Abstract: A lifting structure for aircraft is essentially applicable to a horizontal stabilizer that includes two side symmetrical boxes that converge at one end (its root) thereof in a shared center area in order to connect integrally in the central area. Both boxes connect by a single part that constitutes a center rib with a double T-shaped profile. The root of the side boxes overlap converging on the inside surfaces of the wings of the center rib. The connection is ensured with rivets (lap joint). The proposed connection simplifies the assembly process (single part) and lead to a weight reduction since a carbon fiber connecting rib can be used.Type: GrantFiled: March 10, 2008Date of Patent: January 10, 2012Assignee: Airbus Operations, S.L.Inventors: Gonzalo Ramírez Blanco, Daniel Barroso Vloedgraven, Jose Luis Lozano García, Miguel Luque Buzo
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Patent number: 8016235Abstract: The invention relates to a cover for the access opening in a composite material aircraft structure, characterized in that it comprises the following elements: an outer cover (18) arranged on the outer part of the aircraft skin (28), the carbon fiber layers (14) forming the skin (28) being deformed towards the inner part of the aircraft structure, leaving enough space between the aircraft structure and the outer part of the skin (28) for the seating of the outer cover (18). a composite material plate (15) arranged in the outer part of the skin (28) and surrounding the area for installing the outer cover (18); an inner cover (27) arranged on the inner part of the aircraft skin (28).Type: GrantFiled: August 28, 2007Date of Patent: September 13, 2011Assignee: Airbus Espana S.L.Inventors: Gonzalo Ramirez Blanco, Jose Luis Lozano Garcia, Daniel Barroso Vloedgraven
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Publication number: 20110111605Abstract: Applicable in aeronautical structures provided with a first fixed component (1) and a second component (2) displaceable with respect to the first. The first (1) and second (2) components include electrically conducting surfaces. It is characterized in that it includes a first conductive piece (6, 10) fixed to the first component (1) and a second conductive piece (9) fixed to a second component (2). The first (6, 10) and second (9) piece are joined together with the possibility of sliding one on the other, in such a way that the first piece (6, 10) is connected to the conductive surface of the first component (1) and the second piece (9) to the conductive surface of the second component (2), so that, when displacements take place of the second component (2) with respect to the first (1), the first piece (1) slides on the second piece (9) maintaining the electrical conductivity between the first (1) and second (2) component.Type: ApplicationFiled: September 15, 2010Publication date: May 12, 2011Inventors: Vicente MARTÍNEZ VALDEGRAMA, José Luis LOZANO GARCÍA, Gonzalo RAMÍREZ BLANCO
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Publication number: 20100243810Abstract: Joining structure for aircraft fairing (7), said fairing (7) being arranged between the horizontal stabilizer and the vertical stabilizer or fuselage section (6) of said aircraft, said structure comprising fittings (2) in the shape of angle, said fittings in turn comprising a vertical surface and a horizontal surface, the fittings (2) being joined via their vertical surface to the fairing (7) by means of removable fixing parts (12), said structure also comprising a deformable resilient element (13) between the fairing (7) and the vertical surface of the fitting (2), such that said resilient element (13) is able to compensate for the necessary deformation play and the manufacturing and assembly tolerances of the fittings (2), the fairing (7), the horizontal stabilizer and the vertical stabilizer or fuselage section (6) by means of different torques for tightening of the above parts.Type: ApplicationFiled: June 4, 2009Publication date: September 30, 2010Applicant: AIRBUS ESPANA, S.L.Inventors: Abel LOBO BARROS, Jose Luis Lozano Garcia
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Publication number: 20100247903Abstract: A part (5) of composite material having a wedge (13) between two zones (11, 15), the second zone (15) being shorter than the first zone (11), whose structure comprises from its outer surface (21) to its inner surface (23): a first section (31) formed from at least two continuous sheets (41) extending parallel to its outer surface (21), the gradient of the wedge (13) being between 20% and 50%; a wedge (33) in the shape of a triangular prism with its larger surface (27) dimensioned in such a way that it forms a wedge having a gradient of less than 20%; a second section (35) formed by a plurality of continuous sheets (45) extending parallel to the surface bounded by the said first section (31) with the said wedge (33) placed upon it. The invention also relates to a process for manufacture of the part (5).Type: ApplicationFiled: June 4, 2009Publication date: September 30, 2010Applicant: AIRBUS ESPANA S.L.Inventors: Vicente MARTINEZ VALDEGRAMA, Jose Luis LOZANO GARCIA, Jose Orencio GRANADO MACARRILLA
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Publication number: 20100163672Abstract: The invention relates to a fairing system for a horizontal stabiliser of an aircraft and to a process for installing said system, such that the fairing system for the sealing of the horizontal stabiliser (2) and the fuselage (1) of the aircraft comprises a primary fairing (50, 51) arranged on the horizontal stabiliser (2) of the aircraft, the mentioned primary fairing (50, 51) being solidly connected to the mentioned horizontal stabiliser (2) which is in turn trimmable with respect to the fuselage (1), the fairing system in turn comprising a secondary fairing (80, 81) such that the primary fairing (50, 51) is coupled to the horizontal stabiliser (2) through supports (30) arranged in the direction of the chord of the primary fairing (50, 51), said supports (30) being located in the outer part of said primary fairing (50, 51) with respect to the fuselage (1), the secondary fairing (80, 81) being arranged in the outer part of the supports (30), the purpose of said secondary fairing (80, 81) being to cover the meType: ApplicationFiled: March 2, 2009Publication date: July 1, 2010Applicant: AIRBUS ESPANA S.L.Inventors: Gonzalo RAMIREZ BLANCO, Jose Luis Lozano Garcia
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Patent number: 7722944Abstract: The invention relates to a piece made of composite material with areas of different thickness manufactured from a stack of composite material fabrics comprising at least two adjacent areas (11, 15) of different thickness and a transition area (13) between both configured with a single slope (17), in which the stack is structured by: a first and a fourth section formed by at least two continuous fabrics (21, 21?; 29, 29?) extending along the three mentioned areas (11, 13, 15); a second section formed by one or more symmetrical and balanced fabric packets (23) ending in the transition area (13) placed among one or more continuous fabrics (25); a third section formed by a symmetrical and balanced fabric packet (27) extending along the three mentioned areas (11, 13, 15) placed among one or more continuous fabrics (25).Type: GrantFiled: February 21, 2008Date of Patent: May 25, 2010Assignee: Airbus Espana, S.L.Inventors: Vicente Martinez Valdegrama, Oscar De la Cruz Garcia, José Luis Lozano Garcia, Antonio De Julian Aguado, Pedro Nogueroles Viñes
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Publication number: 20100108810Abstract: The lifting surface consists of a torsion box capable of bearing aerodynamic and inertial loads, and the semi-parts (1, 1?) comprising it are connected together with joining means conventionally consisting of a rib in one piece in its plane of symmetry, the final assembly of said lifting surfaces requiring some inspection openings or holes for being able to gain access to the corresponding joints. The invention provides other joining means which avoid that rib and which consist of a plurality of bars (2) modularly arranged in the manner of a lattice, in such a is way that the required amount of said inspection holes is reduced, and a sequential assembly connecting the upper and lower ends of the bars (2) is facilitated.Type: ApplicationFiled: January 8, 2009Publication date: May 6, 2010Inventors: Abel Lobo Barros, Jesus Vicente Bajo Gonzalez, Jose Luis Lozano Garcia, Antonio Francisco Pintor Archilla, Jesus Rodriguez Bodas
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Publication number: 20090321575Abstract: Aircraft aerofoil structure, in particular rear spar structure (1) for the joining of lateral box beams (2) of a horizontal stabilizer of an aircraft, said rear spar (1) comprising a right rear spar (5) and a left rear spar (6), moreover said structure of said rear spar (1) includes a central section formed by an integrated component (10), and said integrated component (10) includes fittings (11) that serve for joining said rear spar structure (1) to the aircraft fuselage and projections (12) that serve for joining the central section formed by the integrated component (10) to the right rear spar (5) and left rear spar (6).Type: ApplicationFiled: August 29, 2008Publication date: December 31, 2009Inventors: Daniel BARROSO VLOEDGRAVEN, Gonzalo Ramirez Blanco, Jose Luis Lozano Garcia, Miguel Luque Buzo
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Publication number: 20090321985Abstract: Method of manufacture of one or more pairs of components in composite material (11, 13; 11?, 13?) intended to form part of aerofoils located on both sides of the axis of symmetry of an aircraft whose shape has a conical tendency in the longitudinal direction, the angle of conicity being less than 10°, that comprises the following stages: a) Lay-up of layers on a flat tape lay-up table forming the laminate of a hypothetical component formed by all of the components of said pairs (11, 13; 11?, 13?), the components of each pair being arranged adjacently and the first components (11, 11?) and the second components (13, 13?) of each pair being arranged alternately, and the whole being arranged symmetrically relative to a hypothetical horizontal axis X-X of the tape lay-up jig; b) Cutting of the flat laminates corresponding to each of said components); c) Forming and curing said components.Type: ApplicationFiled: September 9, 2008Publication date: December 31, 2009Inventors: Antonio De Julian Aguado, Jose Luis Lozano Garcia
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Publication number: 20090294591Abstract: The invention relates to a cover for the access opening in a composite material aircraft structure, characterized in that it comprises the following elements: an outer cover (18) arranged on the outer part of the aircraft skin (28), the carbon fiber layers (14) forming the skin (28) being deformed towards the inner part of the aircraft structure, leaving enough space between the aircraft structure and the outer part of the skin (28) for the seating of the outer cover (18). a composite material plate (15) arranged in the outer part of the skin (28) and surrounding the area for installing the outer cover (18); an inner cover (27) arranged on the inner part of the aircraft skin (28).Type: ApplicationFiled: August 28, 2007Publication date: December 3, 2009Inventors: Gonzalo Ramirez Blanco, Jose Luis Lozano Garcia, Daniel Barroso Vloedgraven
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Publication number: 20090159742Abstract: It is essentially applicable to a horizontal stabilizer that includes two side symmetrical boxes that converge at one end (its root) thereof in a shared center area in order to connect integrally in said central area. It is characterized in that both boxes connect by means of a single part that constitutes a center rib with a double T-shaped profile. The root of the side boxes overlap converging on the inside surfaces of the wings of the center rib. The connection is ensured with rivets (lap joint). The proposed connecting means simplifies the assembly process (single part) and lead to a weight reduction since that a carbon fiber connecting rib can be used.Type: ApplicationFiled: March 10, 2008Publication date: June 25, 2009Inventors: Gonzalo Ramirez Blanco, Daniel Barroso Vloedgraven, Jose Luis Lozano Garcia, Miguel Luque Buzo
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Publication number: 20080235672Abstract: One embodiment relates to a computer-implemented method of compiling a software program into an executable binary file, including determining a data layout in the binary file and a data layout in the executable's dynamically allocated memory. The method includes taking into account data types of data as a factor in determining a data layout for the binary file and for the executable's dynamically allocated memory, wherein the data types include a floating-point data type and a non-floating-point data type. Other embodiments, aspects and features are also disclosed herein.Type: ApplicationFiled: March 20, 2007Publication date: September 25, 2008Inventors: Luis A. Lozano, Robert Hundt, Shin-Ming Liu, Sandya S. Mannarswamy, Sungdo Moon