Patents Assigned to Airbus Operations, S.L.
  • Highly integrated structure including leading and trailing edge ribs for an aircraft lifting surface
    Patent number: 9381991
    Abstract: An aircraft lifting surface with a monolithic main supporting structure of a composite material including an upper skin having at least a part of the upper aerodynamic profile of the leading edge and/or of the trailing edge, a lower skin, a front spar, a rear spar, and leading edge ribs and/or a trailing edge ribs. The main supporting structure allows a weight and cost reduction of aircraft lifting surfaces.
    Type: Grant
    Filed: November 21, 2013
    Date of Patent: July 5, 2016
    Assignee: Airbus Operations S.L.
    Inventors: Enrique Guinaldo Fernandez, Francisco Cruz Dominguez, Francisco Javier Honorato Ruiz, Paula Más Más, Iker Vélez De Mendizábal Alonso, Carlos Garcia Nieto
  • Highly integrated leading edge of an aircraft lifting surface
    Patent number: 9322276
    Abstract: A method for manufacturing a leading edge profile section of an aircraft lifting surface is provided. The method comprises the following steps: a) providing a set of laminated preforms of a composite material configured with a suitable shape for constituting the leading edge profile section; b) arranging said laminated preforms in a curing tooling and subjecting the assembly to an autoclave cycle to co-cure said laminated preforms; c) demolding the curing tooling in a spanwise direction towards the aircraft symmetry plane. The invention also comprises a leading edge profile section manufactured by said method comprising in addition to the skin of the leading edge profile section, one or more of the following structural elements: an auxiliary spar, a longitudinal stiffener reinforcing an auxiliary spar, a longitudinal stringer reinforcing the skin of the leading edge profile.
    Type: Grant
    Filed: July 16, 2013
    Date of Patent: April 26, 2016
    Assignee: Airbus Operations S.L.
    Inventors: Enrique Guinaldo Fernandez, Francisco Javier Honorato Ruiz, Francisco Jose Cruz Dominguez
  • Method for assembling elements of composite material for aircrafts, with stress relaxation in the elements
    Patent number: 9321219
    Abstract: The invention relates to a method of assembling composite material parts (10, 12). The method makes provision for: mounting (S6) the parts for assembly under stress on a stand (14), which parts have been partially polymerized; heating (S7) these parts so as to polymerize them completely, thereby enabling the stresses in the parts to be relaxed and enabling them to match the shape of the sand; cooling (S8) the parts; and assembling (S9) in conventional manner the parts as cooled in this way.
    Type: Grant
    Filed: January 29, 2014
    Date of Patent: April 26, 2016
    Assignees: Airbus Operations (S.A.S.), Airbus Operations, Airbus Operations S.L.
    Inventors: Pierre Zahlen, Virginie Charbonnier, Philippe Blot, Melania Perez-Sanchez
  • Drainage mast of the compartment of the auxiliary power unit of an aircraft
    Patent number: 9321520
    Abstract: A drainage mast for draining liquids from an APU compartment of an aircraft with a first end connected to the APU compartment and a second end for discharging the liquids to the atmosphere. The drainage mast is configured with at least a sector having decreasing cross section areas towards the second end. The area of the initial cross section of the sector is lesser than the area of any cross section of the drainage mast closer to the first end. The invention also refers to an aircraft comprising the drainage mast.
    Type: Grant
    Filed: April 23, 2012
    Date of Patent: April 26, 2016
    Assignee: Airbus Operations S.L.
    Inventors: Jose Grana Otero, Ignacio Esteban Parra Fabian, Carlos Casado Montero
  • Riveting device for aircraft fuselages
    Patent number: 9296076
    Abstract: A head of a riveting device—for Hi-Lite type rivets—of at least two components of a structure for installing automatically collars on pins previously inserted in the structure. The head comprises: a collar installation tool; a collar supply to supply collars to the collar installation tool; a tool actuating device; a linear displacement device to linearly move the tool during the threading operation; a withdrawal device arranged to withdraw the second part of the collars; a control arrangement configured to automatically perform the installation of collars on pins and after this the withdrawal of the second part of the collars, using tools and collars appropriate for the pins. Also a robot having as end-effector the head and to a method of riveting two components of an aircraft fuselage are provided.
    Type: Grant
    Filed: February 20, 2013
    Date of Patent: March 29, 2016
    Assignee: Airbus Operations S.L.
    Inventors: Jorge Juan Soto Martinez, Juan Francisco Garcia Amado, Marta Gimenez Olazabal, Jose Gorrotxategi Txurruka, Jokin Lekunberri Urkidi, Jon Ander Altamira Ugarte
  • Aircraft landing gear
    Patent number: 9248905
    Abstract: An aircraft (11) with at least an inflatable device (41) installed in a cavity (21) in its external surface which is equipped with a door (25) for opening/closing said cavity (21) is provided. The inflatable device (41), comprising a cushion (45) and a gas generator is configured for filling the cavity (21) with the cushion (45) when it is inflated with the gas supplied by said gas generator, without protruding from the cavity (21) for reducing the downstream air flow disturbances generated by said cavity (21) when the door (25) is open. The inflatable device (41) includes control means for inflating the cushion (45) in predetermined circumstances, being the door (25) open. The invention is particularly applicable to the cavities of the Main Landing Gear (31) for avoiding power losses to a Ram Air Turbine (51) placed behind it.
    Type: Grant
    Filed: May 15, 2013
    Date of Patent: February 2, 2016
    Assignees: Airbus Operations S.L., Airbus SAS
    Inventors: Ludovic Gerard, Alejandro Gutiérrez García, Julián Maldonado
  • Optimized torsion box for an aircraft
    Patent number: 9216812
    Abstract: An aircraft lifting surface with a torsion box of a composite material including an upper skin, a lower skin, a front spar, a rear spar, one or more intermediate spars and transverse ribs arranged between the rear spar and an adjacent intermediate spar and/or between the front spar and the adjacent intermediate spar.
    Type: Grant
    Filed: November 20, 2013
    Date of Patent: December 22, 2015
    Assignee: Airbus Operations S.L.
    Inventors: Enrique Guinaldo Fernadez, Francisco Cruz Dominguez, Francisco Javier Honorato Ruiz, Paula Más Más, Iker Vélez De Mendizábal Alonso, Carlos Garcia Nieto
  • Method for prevention of porosity in composite material parts
    Patent number: 9108359
    Abstract: The invention discloses a method for prevention of porosity in composite material parts (1), which is applied when the curing stage of the part (1) is being carried out on a female tool (2). In the curing stage, an adhesive (4) is placed on at least one of the areas of the radii (5) of the composite material part (1), so that the possible subsequent appearance of porosity in said areas of the composite material part (1) is prevented. Thus, the adhesive (4) acquires the fluidization temperature before the resin of the composite material and it is displaced filling the holes generated during the placement of the part (1) on the female tool (2), in the area of the radii (5) of the part (1), during the coupling between the part (1) and the female tool (2).
    Type: Grant
    Filed: April 26, 2013
    Date of Patent: August 18, 2015
    Assignee: Airbus Operations, S.L.
    Inventors: Jose David Cano Cediel, Pedro Nogueroles Vines
  • Trailing edge of an aircraft aerodynamic surface
    Patent number: 9108721
    Abstract: 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: Grant
    Filed: February 25, 2013
    Date of Patent: August 18, 2015
    Assignee: Airbus Operations, S.L.
    Inventors: Yolanda De Gregorio Hurtado, Alberto Balsa Gonzalez
  • Composite rod, manufacturing method and tool
    Patent number: 9091387
    Abstract: The present invention describes composite rods keeping two elements apart a determined distance carrying the loads between them, such as railways, industrial premises, etc. Besides, the manufacturing method thereof and the tool involved in this process are also described.
    Type: Grant
    Filed: December 20, 2012
    Date of Patent: July 28, 2015
    Assignee: Airbus Operations, S.L.
    Inventor: Andres Quintana Rio
  • System for increasing controllability for an aircraft
    Patent number: 9079655
    Abstract: The system includes deflection transmission means (16) to provide a deflection position of the high-lift device (8) for each setting angle position of an adjustable HTP (2). Preferably, the deflection transmission means (18,20,23) comprise essentially of a mechanical linkage connected between the high-lift device (8) and the aircraft (1).
    Type: Grant
    Filed: September 8, 2011
    Date of Patent: July 14, 2015
    Assignee: Airbus Operations, S.L.
    Inventors: Pilar Vela Orge, Arnaud Namer, Angel Pascual Fuertes, Francisco Javier Simon Calero
  • Measurement of the inertial properties of an aircraft movable control surface
    Patent number: 9067673
    Abstract: A method for obtaining the inertial properties of a movable rotating around a hinge line in an aircraft control surface. The method includes the steps of removing the mechanical connections of the actuators from the movable, leaving the movable free to rotate around its hinge line, further balancing the movable and calculating in a first approach its coarse static moment. The method includes refining the coarse static moment and obtaining simultaneously a frictional moment of the movable; incorporating an elastic element on the control surface and configuring a second order mechanical system; inducing forced oscillations on the movable at a certain frequency, this frequency being increased until it is sensibly close to the resonance frequency of the movable to produce a wave response; calculating, from the wave response, the moment of inertia of the movable.
    Type: Grant
    Filed: March 18, 2013
    Date of Patent: June 30, 2015
    Assignee: Airbus Operations S.L.
    Inventors: Justo Alonso Gago, Pedro Valera Rodriguez
  • Injection interface device
    Patent number: 9033695
    Abstract: An injection interface device comprising a wedge having a first surface mountable over the joint between the mold and the terminal element and a second surface being inclined with respect to the first surface. A fixation element is mountable against the second surface and an attachment element. The device is configured so that it avoids or prevents the movement of the wedge in a direction parallel to the mold and the movement of the fixation element in a direction perpendicular to the mold so that a displacement of the fixation element parallel to the mold makes a displacement of the wedge in a direction perpendicular to the mold so that the wedge presses against the terminal element to seal it.
    Type: Grant
    Filed: July 22, 2014
    Date of Patent: May 19, 2015
    Assignee: Airbus Operations S.L.
    Inventors: David Alfonso Cerezo Arce, Melania Sanchez Perez, Aquilino Garcia Garcia
  • Lightning and corrosion protection arrangement in an aircraft structural component
    Patent number: 9016615
    Abstract: A lightning and corrosion protection arrangement for a joint between an outer metallic part (11) and an aircraft structural component (13) completely or partially made of CFRP by means of a row of metallic rivets (15), that comprise inner and outer metallic layers (21, 25) and an intermediate dielectric layer (23), the inner metallic layer (21) in contact with said structural component (13) being thinner and bigger than the outer metallic layer (21) in contact with the metallic part (11), the intermediate dielectric layer (23) extending in an area bigger than the area of the foot (12) of the metallic part (11) by a predetermined minimum linear distance D1 between its edges, the outer metallic layer (25) extending in an area bigger than the area of the intermediate dielectric layer (23) by a predetermined minimum linear distance D2 between its edges.
    Type: Grant
    Filed: February 23, 2011
    Date of Patent: April 28, 2015
    Assignee: Airbus Operations S.L.
    Inventors: José Orencio Granado Macarrilla, Vincente Martínez Valdegrama, Alberto Lozano Sevilla, Daniel Casares Rodríguez
  • Computer-assisted method for optimising surfaces of composite-material structures
    Patent number: 9002681
    Abstract: Computer-assisted method for optimizing surfaces of composite-material structures as part of a design process that includes the following stages: a) Providing a multi-cell surface (11) of the structure obtained using aerodynamic calculations; b) Transforming said multi-cell surface (11) into an optimized surface (13) with fewer cells, concatenating contiguous cells and maintaining point and tangent continuity between them; c) Using said optimized surface (13) as geometric master when designing the components of the structure. The method is particularly applicable to the design of structures with a plurality of components and in particular fuselages of aircraft made of composite material. The invention also relates to a computer program for performing the method.
    Type: Grant
    Filed: May 12, 2010
    Date of Patent: April 7, 2015
    Assignee: Airbus Operations S.L.
    Inventors: Antonio Navarro Luna, José Valeriano La Torre
  • Rear fuselage of an aircraft
    Patent number: 8991759
    Abstract: Rear fuselage of an aircraft comprising a tail cone end and a rest of the real fuselage whereby the tail cone end is attached to the rest of the rear fuselage by means of an attachment system comprising two upper lugs, two lower lugs and a detachable balancer fitting. The balancer fitting is an adjustable fitting, being locked in a Z and Y directions of a Cartesian axis and being movable along an X direction of the Cartesian axis providing guidance for the tail cone end and the rest of the rear fuselage.
    Type: Grant
    Filed: September 23, 2011
    Date of Patent: March 31, 2015
    Assignee: Airbus Operations, S.L.
    Inventors: Ma Aránzazu García Patino, Angel Postigo Rodríguez, David López Fernández
  • METHOD AND DEVICE FOR MANUFACTURING COMPOSITE MATERIAL PARTS
    Publication number: 20150053332
    Abstract: The manufacturing method object of the invention comprises the following stages: A) stacking strips of prepreg material on a laminating tool (14), so that an angled laminated part (2) is obtained comprising a central section (2a) contained in a first plane (12), at least one side section (2b) contained in a second plane (13), and at least one bending axis (5) between the central section (2a) and the at least one side section (2b), so that, the first plane and the second plane form an angle ?; B) forming of the angled laminated part (2) comprising bending along the bending axis (5) the, at least, one side section with respect to the central section (2a), obtaining a formed part (6); C) curing, of the formed part (6).
    Type: Application
    Filed: March 22, 2013
    Publication date: February 26, 2015
    Applicant: Airbus Operations, S.L.
    Inventors: David Cano Cediel, Ruth Chinarro Vera, Francisco Escobar Benavides, Pedro Nogueroles Viñes
  • Impact resistant and damage tolerant aircraft fuselage
    Patent number: 8960603
    Abstract: An aircraft fuselage part (31) located in a section of an aircraft (11) having a propulsion system (13) attached by upstream pylons (17), the fuselage part includes a skin (35); a plurality of frames (37) arranged perpendicularly to a longitudinal axis (33); a single or internally divided upper longitudinal box (41) and a single or internally divided lower longitudinal box (51) which are configured to form with the skin (35) a multi-cell structure, belonging in each cell the external side to the skin (35) and the internal sides to the longitudinal boxes (41, 51); a plurality of lateral beams (61) that are interconnected with the frames (37) to form together with the skin (35) a structural unity. The fuselage components (35, 37, 41, 51, 61) are dimensioned so that the aircraft can withstand the effect of pre-defined failure events keeping a sufficient number of closed cells.
    Type: Grant
    Filed: February 15, 2011
    Date of Patent: February 24, 2015
    Assignee: Airbus Operations S.L.
    Inventors: Eduardo Vinué Santolalla, César Bautista de La Llave, Pablo Timoteo Sanz Martínez, Diego Folch Cortés, Esteban Martino Gonzáles, Ana Reyes Moneo Peñacoba
  • Marking and defect recognition procedure in prepreg material
    Patent number: 8964174
    Abstract: A defect recognition procedure in prepreg materials (1) draws a first transversal cross line (4b) at the beginning boundary (3b) of a defective area (2) in a prepreg material (1). A second transversal cross line (4e) at the end boundary (3e) of a defective area (2) is drawn as well. The cross lines (4b, 4e) form an angle (?) with respect to the prepreg material (1) motion direction (5). Each transversal cross line (4b, 4e) delimiting the beginning and the end of a defective area (2) has identification codes (Bi, Ei).
    Type: Grant
    Filed: June 26, 2012
    Date of Patent: February 24, 2015
    Assignee: Airbus Operations, S.L.
    Inventors: Jose David Cano Cediel, Georgina Galera Cordoba
  • Method of manufacturing “T” shaped stringers for an aircraft and curing tool used thereof
    Patent number: 8956495
    Abstract: A method of manufacturing “T” shaped stringers for an aircraft whereby the “T” shaped stringers have a stringer web and a stringer foot, the method comprising: a first step of hot-forming a carbon fiber laminate in order to achieve semi-stringers with an “L” shaped cross-section, a second step of placing together two hot-formed “L” shaped semi-stringers in order to form a “T” shaped stringer, a third step of co-bonding the resulting “T” shaped stringer on a cured skin with an adhesive line between them, and a fourth step of curing the obtained “T” shaped stringer inside a vacuum bag using invar alloy angles as curing tools. The invar alloy angles are cut at a radius area eliminating a part of the invar alloy angles covering the stringer foot in order to define an invar alloy piece having no foot.
    Type: Grant
    Filed: June 7, 2011
    Date of Patent: February 17, 2015
    Assignee: Airbus Operations, S.L.
    Inventors: Augusto Pérez Pastor, Julián Sánchez Fernández, Fernando Esquivias Garía