Patents Assigned to Airbus Operations, S.L.
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Patent number: 8025467Abstract: A countersinking-carrier nozzle has a flat front surface with a central hole via which emerges a countersinking drill, such that said flat front surface establishes a limit to the penetration depth of the countersinking nozzle. The nozzle includes a flexible retainer for the nozzle front surface so that it swivels when making contact with a curved countersinking surface, adapting itself tangentially to it while the headstock presses against the countersinking surface. The flexible retainer is defined by a ball-and-socket joint including a curvo-concave retaining receptacle, with the possibility of swivelling, with a complementary curvo-convex portion provided in the rear part of the flat front surface. This portion projects with respect to the receptacle to allow it to swivel when pressed against the countersinking surface, at which moment the complementary curvo-convex portion of the rear part of the front surface swivels in the receptacle of the headstock.Type: GrantFiled: February 26, 2008Date of Patent: September 27, 2011Assignee: Airbus Operations, S.L.Inventors: Juan Ramón Astorga Ramírez, Manuel Barrios Flores, Paloma Peinado Aguayo
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Patent number: 8019472Abstract: The robot comprises a chassis (1) with a first set of legs (2a, 2b) with suction pads (6) on tilting supports (7) mounted in a linearly displaceable manner with regard to the chassis and a second set of legs (4) with suction pads (17) mounted in a rotary manner with regard to the chassis. Certain control means are adapted in order to control the functioning of said first and second sets of legs in a coordinated manner for displacing the chassis in any direction on the work surface (S). It includes support feet (9) and a system for leveling the chassis in relation to a curvature of the work surface. Fitted on the chassis is a work unit (44) with a head (19) for working on the work surface via an opening (12) in the chassis. It includes means for displacing said head along three axes and pivoting the head on two axes with respect to the chassis.Type: GrantFiled: May 3, 2007Date of Patent: September 13, 2011Assignee: Airbus Operations, S.L.Inventors: Pedro Montero SanJuan, José Luis Ramallo Gutierrez
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Patent number: 8006932Abstract: A pivoting coupling system of a large dihedral empennage to the tail fuselage of an aircraft, in which the empennage includes a right lateral box and a left lateral box arranged at a large dihedral angle in the tail fuselage of the aircraft. The pivoting coupling system including a horizontal central box joining the lateral boxes, and which includes a rear spar; and a linkage for horizontally linking the central box to a frame structure of the tail fuselage of the aircraft, which allow the empennage to rotate vertically about a horizontal linkage shaft between a negative maximum angle of incidence and a positive maximum angle of incidence in response to the actuation of an actuator which is connected to the empennage and to a structural element of the fuselage of the aircraft.Type: GrantFiled: February 28, 2007Date of Patent: August 30, 2011Assignee: Airbus Operations, S.L.Inventors: Francisco Javier Honorato Ruiz, Angel García Sacristán
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Patent number: 7938366Abstract: Opening and secure-closing system for doors comprising two doors (1,2) for accessing the interior of a chamber, which open towards the outside being hinged around two hinging axes (19,20), both doors (1,2) comprising a set of bolts (17,18) and the opening and closing system comprising additional means of opening/closing operation (26) and an overpressure door (3) located in one of the doors (1,2) which opens towards the outside, in such a way that the means of opening/closing operation (26) comprise a blocking bar (4), a blocking fitting (7) and means of retention (10) between the two doors (1,2) in order to provide a controlled and sequential opening/closing operation of the chamber, and the overpressure door (3) is opened automatically in the event of emergency due to overpressure, and it also participates in the controlled and sequential opening/closing operation of the chamber.Type: GrantFiled: August 4, 2006Date of Patent: May 10, 2011Assignee: Airbus Operations, S.L.Inventors: José Román Martinez Rueda, José Alberto Rojo Carrión, José Luis Sen Pacios, Juan Pablo Melián Brinquis, Nicolás Rojo Saiz, David Martin Calvo, Steffan Prys Thomas, Antonio Márquez Gavilán, María Aranzazu García Patino
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Patent number: 7909286Abstract: Support system suitable for sustaining an auxiliary power unit of an aircraft to a fixed structure (2) belonging to a compartment of the auxiliary power unit (6) of the aircraft. The support system is made in a high mechanical strength material and with high resistance to ignition, and comprises three fittings (3, 4, 5) two of which are frusto-conical and one with a substantially cylindrical. Fittings (3, 4, 5) being able to be hollow and being able to comprise an array of lateral ribs. Each one of them presenting a first end (7) comprising means of attachment of the support system (8) to the fixed structure (2) and a second end (9) comprising means of securing of the support system (8) which are joined to the auxiliary power unit (1) in the periphery of the extension of said auxiliary power unit (1).Type: GrantFiled: August 4, 2006Date of Patent: March 22, 2011Assignee: Airbus Operations, S.L.Inventors: José Román Martinez Rueda, José Alberto Rojo Carrión, José Luis Sen Pacios, Juan Pablo Melián Brinquis, Nicolás Rojo Saiz, David Martin Calvo, Steffan Prys Thomas, Antonio Márquez Gavilán, María Aranzazu García Patino
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Patent number: 7878041Abstract: A method and device are provided for verification of the quality of placing of blind rivets. The verification method involves successively carrying out, during the application of traction force to a stem, initial measurements in an initial state of the application of the traction force to obtain an initial traction force and an initial displacement of the rivet stem relative to the rivet body, intermediate measurements in an intermediate stage of the application of the traction force to obtain an intermediate traction force and an intermediate displacement, and terminal measurements in a terminal stage of the application of the traction force to obtain a terminal traction force and a terminal displacement. The obtained values are compared to acceptable values in an assignment table.Type: GrantFiled: March 6, 2008Date of Patent: February 1, 2011Assignee: Airbus Operations, S.L.Inventor: Desiderio Sánchez-Brunete Álvarez
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Patent number: 7850119Abstract: Sealing system for the gap (2) between the fuselage (3) and the elevator (4) of the orientable horizontal stabiliser (5) of an aircraft, extended with an aerodynamic fairing (8) for sealing of the opening (24) between the fuselage (3) and said orientable horizontal stabiliser (5) which comprises a main body (1) and an aerodynamic fairing (8) which is extended from the main body (1) in continuity with the latter, and a plurality of first elastic sealing profiles (9) between the first surface (11) of the main body (1) including the aerodynamic fairing (8) and the outer surface of the fuselage (3) and making contact with them, and a plurality of second elastic sealing profiles (13) between the second surface (12) of the main body (1) and the first end of the elevator (15) and making contact with them, in such a way that the sealing takes place of the gap (2) and the opening (24) and an aerodynamic continuity is produced between the orientable horizontal stabiliser (5), the fuselage (3) and the elevator (4) whenType: GrantFiled: April 25, 2007Date of Patent: December 14, 2010Assignee: Airbus Operations, S.L.Inventor: Agustín Mariano Martin Hernandez
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Patent number: 7819001Abstract: A minimum aerodynamic interference support for models in a cryogenic wind tunnel includes two main pieces: a front sting substantially parallel to the longitudinal axis of the model and a blade, integrated together and describing an obtuse angle. The support is connected to the model by means of the blade, being the model such that it emulates a tail section and/or wings of an aircraft. The front sting of the support comprises an extension, extended horizontally underneath a frontal zone of the fuselage of the model, starting from the point where the blade starts and extending past the point where the blade is connected to the model, in such a way that the length and area dimensions of the cross-section of the extension are obtained by applying the aerodynamic principle, area rule, to the ensemble made up by the front sting, the blade, the model and the extension.Type: GrantFiled: September 23, 2008Date of Patent: October 26, 2010Assignee: Airbus Operations, S.L.Inventors: Esteban Amo Garrido, Jesús De Pablo Pérez, Mario Jiménez De Lago
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Patent number: 7815147Abstract: Reinforced cover for cut-outs in an aerodynamic contour of a vehicle, with a first attachment section 1a attachable to a structural element (2,5) of the vehicle (11); a second elastic section 1c which covers the cut-out (4) which is located between a fixed part 5 and a moving part (6, 12) of the vehicle (11), and provided with a low-friction layer (8) on its inner surface (1e), which comprises a first area (1i) in a rectangular configuration and a second area (1j) with a second cross-section smaller than that of the first area (1i); an outer surface (1k) with a fiberglass layer (7a); a main internal body (9) of a flexible material, a transition section (1g) thickened between the first and the second section, (1a, 1c); flushing the outer surface (1k) of the second section (1c) with the outer surface (5a).Type: GrantFiled: August 1, 2007Date of Patent: October 19, 2010Assignee: Airbus Operations, S.L.Inventor: Agustin Mariano Martín Hernández
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Patent number: 7810758Abstract: A device for coupling a coupling pivot for a trimmable horizontal stabilizer to the tail fuselage of an aircraft, with an inner plate, an outer plate with first fastening holes and first passage holes in the inner plate respectively facing second fastening holes and second passage holes in the outer plate for the passage of a coupling pivot of the horizontal stabilizer, and with an upper lug and a lower lug respectively located above and below a cut-out for the horizontal stabilizer. The lugs are integral with separate reinforced zones of the covering in respective neighboring areas of the cut-out, in such a way that the plates between them clasp the respective reinforced zones in which the lugs are provided.Type: GrantFiled: April 19, 2007Date of Patent: October 12, 2010Assignee: Airbus Operations, S.L.Inventors: Agustín Garcia Laja, Carlos Garcia Manzano
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Patent number: 7770846Abstract: Fixing system for a modular leading edge (2) to the structure of an aircraft lift plane (1), in which the leading edge (2) has a covering (4) formed from a first lamina (5) and a second lamina (6) between which there is an interior airtight chamber, and the fixing system comprises a main attachment element (3) whose cross-section has a central element (13), a first arm (14) which is fixed to the first lamina (5) of the covering (4) of the leading edge (2), and a second arm (15) which is fixed to the second lamina (6) of the covering (4), and the central element (13) is in turn fixed to a covering (10) of the torsion box (8) of the structure of the lift plane (1).Type: GrantFiled: April 30, 2007Date of Patent: August 10, 2010Assignee: Airbus Operations, S.L.Inventors: David Perez Rodriguez, Jorge Ballestero Mendez
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Patent number: 7731207Abstract: A mobile transport platform for the handling of aeronautical parts with a frame has an array of telescopic actuators vertically arranged in rows and columns, each telescopic actuator is coupled by one end to the frame, and has a coupled head (2c) at its opposite end; a control system connected to each telescopic actuator for individually controlling the actuation of each telescopic actuator so that the telescopic actuator can adapt a position between that of maximum extension in which the head and at least part of the shaft of the telescopic actuator project from the plane of the load surface, and that of maximum retraction in which at least the shaft of the telescopic actuator does not project from the plane of the load surface.Type: GrantFiled: March 12, 2007Date of Patent: June 8, 2010Assignee: Airbus Operations, S.L.Inventor: José Manuel Santos Gómez
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Patent number: 7699266Abstract: A sealing system for a gap (2) existing between the fuselage (3) and the elevator (4) of a orientable horizontal stabilizer (5) of an aircraft, comprises a main body (1) formed by an upper surface (18) and a lower surface (19) and at least one longitudinal vertical element (22) arranged between the two surfaces (18,19) which grants rigidity to the main body (1), and a plurality of first elastic sealing profiles (9) between the first surface (11) of the main body (1) and the outer surface of the fuselage (3) and making contact with them, and a plurality of second elastic sealing profiles (13) between the second surface (12) of the main body (1) and the first end of the elevator (15) and making contact with them, in such a way that the sealing of the gap (2) takes place and an aerodynamic continuity is produced between the fuselage (3) and the elevator (4) when the elevator (4) is at rest in the plane of the orientable horizontal stabilizer (5) for any of the orientation positions of the orientable horizontal sType: GrantFiled: April 25, 2007Date of Patent: April 20, 2010Assignee: Airbus Operations, S.L.Inventor: Agustin Mariano Martin Hernandez
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Patent number: 7677102Abstract: A head for ultrasonic inspection with a semidry coupling system involving a roller (4) and an ultrasound scanner that rolls on the surface (5) of the part to be inspected, includes a first frame (1) to which the roller (4) is connected and pivots around a stationary axis (4a) in a direction that is perpendicular to the probe's movement; a second frame (2) from which linear vertical guides (6) emerge and is connected in an oscillatory manner to the first frame (1) through an oscillating axis (11a) that is perpendicular to the stationary axis (4a): a third frame (3) that slides vertically through the linear guides (6); and at least two actuators of vertical adjustment (9) anchored to the third frame (3) and to the second frame (2), their corresponding laterally aligned pivotal axes (10), connected to the first frame (1) in a rotating manner and parallel to and lower from the plane of the stationary axis (4a) and the respective ends of the stationary axis (4a).Type: GrantFiled: March 12, 2007Date of Patent: March 16, 2010Assignee: Airbus Operations, S.L.Inventor: Alvaro Espada Tejedor