Patents Assigned to Airbus Operations, S.L.
  • Patent number: 10773824
    Abstract: A structural composite component, in particular for an aircraft or spacecraft, includes: a lightning strike protection layer; and a composite battery including a cathode layer and a separation layer, wherein the lightning strike protection layer is formed integrated with the cathode layer, and wherein the separation layer is configured for providing acoustic damping, and/or fire barrier, and/or impact resistance to the structural composite component. A method for configuring such a structural composite component; and an aircraft or spacecraft including such a structural composite component are also described.
    Type: Grant
    Filed: November 20, 2017
    Date of Patent: September 15, 2020
    Assignee: Airbus Operations, S.L.
    Inventors: Tamara Blanco Varela, José Sanchez Gomez, Leire Segura Martinez De Ilarduya, Mariano Morales Monge
  • Patent number: 10759512
    Abstract: An aircraft composite panel assembly includes a first panel having upper and lower faces, the lower face having a recess on a first side of the panel, a second panel having upper and lower faces, the lower face having an outward projection at a first side of the panel, the outward projection received on the recess forming a lower continuous face; and a forward stack of plies of composite material bonded to the upper face of the first panel, the forward stack of plies having an edge overlapping the first side of the first panel, and the number of plies of the forward stack of plies decreasing toward the opposite side of the first side of the first panel.
    Type: Grant
    Filed: November 28, 2017
    Date of Patent: September 1, 2020
    Assignee: Airbus Operations, S.L.
    Inventors: Miguel Ángel Rocher Pastor, Victor Tabernero Martínez
  • Patent number: 10745105
    Abstract: A tip structure for an aircraft airfoil, such as a control surface (ailerons, flaps, elevators, rudders, etc) and/or a lifting surface (wings, HTP's, VTP's) is a unitary body and includes a tip shell and a metallic material on the outer surface of the tip shell suitable to withstand a lighting strike. The tip shell has been obtained by a single-stage injection molding process using a thermoplastic composite material having fibers dispersed therein, and the metallic material has been integrally formed with the tip shell.
    Type: Grant
    Filed: July 10, 2017
    Date of Patent: August 18, 2020
    Assignee: Airbus Operations, S.L.
    Inventors: Soledad Crespo Peña, Francisco Javier Honorato Ruiz, Iker Vélez De Mendizabal Alonso, Carlos García Nieto, Enrique Guinaldo Fernández, Álvaro Torres Salas, Pablo Cebolla Garrofe, Álvaro Calero Casanova
  • Patent number: 10710751
    Abstract: A rigging tool for a control surface of an aircraft, including a laser for outputting a low energy laser beam, a target assembly including a plate including a target point, and a support to sustain the target assembly on a surface of a control surface, and a laser platform provided with structure to rest on a surface of a control surface, having backward and forward extremes, the backward extreme being configured to hold the laser, and the forward extreme including a pair of holes at opposite positions aligned with the output of the laser, such that, in operation, when the laser beam passes through the holes and incises in the target point, a neutral position of a control surface is indicated.
    Type: Grant
    Filed: February 15, 2018
    Date of Patent: July 14, 2020
    Assignee: Airbus Operations, S.L.
    Inventors: Alejandro Monleón de la Lluvia Jordá, Alejandro Rosique Gómez
  • Patent number: 10549836
    Abstract: A harness routing electrically connects a rear fuselage section of an aircraft and a trimmable Horizontal Tail Plane (HTP) installed at this rear section. The aircraft rear section includes a first clipping point wherein the harness is attached to a fuselage frame located in front of the torsion box front spar, and a second clipping point wherein the harness is attached to a front spar of the HTP torsion box. The second clipping point is located downstream from the first clipping point from the fuselage towards the torsion box interior, and the harness passes through the front spar towards the interior of the torsion box downstream the second clipping point.
    Type: Grant
    Filed: February 28, 2017
    Date of Patent: February 4, 2020
    Assignee: Airbus Operations, S.L.
    Inventors: Felipe Abellán Alzallu, Alberto Ramos Guerrero, Adolfo Ávila Gutierrez, Juan Carlos Monje Martin
  • Patent number: 10549492
    Abstract: The present disclosure refers to a method for manufacturing carbon fiber panels stiffened with omega stringers for the construction of aircraft structures, such as fuselage sections, wing panels, etc. One tubular pressure member is provided for each omega stringer of the structure to be manufactured, wherein the tubular pressure member is configured with the shape of the omega stringer. Each tubular pressure member is enclosed between the omega stringer and part of the laminate, and autoclave pressure is applied to the interior of the tubular pressure member, so that the tubular pressure member is used to consolidate the omega stringers and/or part of the laminate from the interior of these two elements, while these two elements are being co-cured or co-bonded in an autoclave. Imperfections on those internal surfaces such as resin wrinkles of the structure are reduced.
    Type: Grant
    Filed: May 29, 2015
    Date of Patent: February 4, 2020
    Assignee: Airbus Operations, S.L.
    Inventors: Gabriel Cruzado Parla, Fernando Munoz Ajenjo, Jose Cuenca Rincon, Maria Mora Medias
  • Patent number: 10532807
    Abstract: A leading edge section with laminar flow control includes: a perforated outer skin, a perforated inner skin, and a plurality of suction chambers formed between the outer skin and the inner skin. The leading edge section includes a plurality of stringers span-wise arranged at the leading edge section, and integrally formed with the outer skin, such that the inner skin is joined to the stringers. A method for manufacturing a leading edge section integrating a laminar flow control system is described, wherein a perforated inner skin is joined with a perforated outer skin having a plurality of stringers integrally formed with the outer skin, such that suction chambers are defined by a part of the outer skin, a part of the inner skin and a pair of stringers.
    Type: Grant
    Filed: January 10, 2017
    Date of Patent: January 14, 2020
    Assignee: Airbus Operations, S.L.
    Inventors: Carlos García Nieto, Enrique Guinaldo Fernández, Pablo Cebolla Garrofe, Iker Vélez De Mendizabal Alonso, Soledad Crespo Peña, Francisco Javier Honorato Ruiz, Álvaro Torres Salas, Álvaro Calero Casanova
  • Patent number: 10507622
    Abstract: A system for curing polymer matrix composite parts out of autoclave in manufacturing and repairing processes including: (i) an inner vacuum bag (3) placed over the lay-up to be cured located over a working area (15, 18) with the edges of the inner vacuum bag (3) joined to the working area by first sealing elements (8); (ii) a Perforated bulkhead (4) located over the inner vacuum bag (3), (iii) an Outer vacuum bag (2) over a perforated bulkhead (4) and over the edges of the inner vacuum bag with the edges of the outer vacuum bag (2) joined to the working area (15, 18) by second sealing elements (1), (iv) a vacuum device (5, 7, 6) and (v) a heating source (9, 20).
    Type: Grant
    Filed: October 6, 2017
    Date of Patent: December 17, 2019
    Assignee: Airbus Operations S.L.
    Inventors: Jose Cuenca Rincon, Juan Salamero Laorden, Ana Teresa Rodriguez-Bellido
  • Patent number: 10494999
    Abstract: A gas turbine engine for an aircraft includes a compressor, a combustion chamber, and a turbine having at least one stator, and at least one rotor. Each stator and rotor is formed by a plurality of blades, a fluid channel is formed between two consecutive blades, and each blade has two opposing surfaces. The compressor is in fluid communication with a first group of stator channels, and the combustion chamber is in fluid communication with a second group of stator channels, such that heat exchange can be performed through two opposing surfaces of at least one stator blade. The outer and the inner walls define a duct for the passage of the heated fluid through the rotor blades, and the outer wall is also arranged for directing the compressed air towards the combustion chamber.
    Type: Grant
    Filed: December 14, 2016
    Date of Patent: December 3, 2019
    Assignee: Airbus Operations, S.L.
    Inventor: Alexandre Garde La Casa
  • Patent number: 10472073
    Abstract: An air conditioning system 1 for a cabin 10 including a pressurized air source 2, a cooling air source 3, a main heat exchanger 4, a compressor 5, a manifold 6 and a mixing chamber 7. An inlet 43 to a cold side of the main heat exchanger 4 is in fluid communication with the cooling air source 3. An inlet 41 of a hot side of the main heat exchanger 4 is in fluid communication with the pressurized air source 2. An inlet 51 of the compressor is in fluid communication with the outlet 44 of the cold side of the main heat exchanger 4.
    Type: Grant
    Filed: December 30, 2016
    Date of Patent: November 12, 2019
    Assignee: Airbus Operations S.L.
    Inventor: Carlos Casado Montero
  • Patent number: 10371049
    Abstract: A propulsion engine comprising at least a first propulsion unit including a first fan encased by a geared ring and a gas turbine engine driving a first shaft connected to the first fan, at least a second propulsion unit including a second fan encased by a geared ring connected to a second shaft operatively coupled to an electric machine and at least an electric storage device connected to the electric machine. The geared rings are configured to transmit torque between the fans so that they can rotate in conjunction (directly or through an intermediate gear) when they are driven by at least one of said first and second shafts. The propulsion engine is arranged for controlling the torque to be supplied to the assembly of the first and second fans by the gas turbine engine and/or by the electric machine acting as a motor or as a generator.
    Type: Grant
    Filed: September 17, 2015
    Date of Patent: August 6, 2019
    Assignee: Airbus Operations S.L.
    Inventors: Nicolas Bailey Noval, Raul Llamas Sandin
  • Patent number: 10369762
    Abstract: A sandwich structure architecture for high speed impact resistant structure includes sandwich skins which enclose a sandwich core formed by a plurality of spacing layers and a plurality of trigger layers, wherein these layers are stacked alternatively in the core. The walls of the trigger layers are thicker than the walls of the spacing layers and/or the walls of the trigger layers include at least one part inclined with respect to the walls of the spacing layers. The spacing and the trigger layers are made of the same type of material, preferably composite materials or metallic materials. The structure is capable of absorbing high-speed impacts, and at the same time can be used as load carrying structure in aircraft fuselages, wings, vertical or horizontal stabilizers.
    Type: Grant
    Filed: March 3, 2017
    Date of Patent: August 6, 2019
    Assignee: Airbus Operations, S.L.
    Inventors: Fernando Pereira Mosqueira, Andrea Ivan Marasco, Esteban Martino Gonzalez
  • Patent number: 10358206
    Abstract: A self-destruction device adapted to be installed in a propeller blade, the self-destruction device including a detector adapted to detect a release of the propeller blade, a warning mechanism adapted to send a release alarm in the event of the detector detecting release of the propeller blade, and a destruction mechanism adapted to destroy the propeller blade in the event of receiving a release alarm from the warning mechanism. An engine and an aircraft are also provided.
    Type: Grant
    Filed: December 18, 2015
    Date of Patent: July 23, 2019
    Assignees: Airbus Operations, S.L., Airbus Operations (S.A.S.)
    Inventors: Javier Toral Vázquez, Diego Folch Cortes, Esteban Martino González, Pablo Goya Abaurrea, Vasillis Votsios, Michel Fouinnetau, Sylvain Roumegas
  • Patent number: 10359278
    Abstract: The present disclosure refers to a method for measuring thickness in any type of carbon fiber component, even in components having parts with different thickness and integrating at least a second material. The method includes measuring with the maximum and minimum real thickness of the component, and measuring with ultrasonic equipment the time that the ultrasound takes to propagate across the component part with maximum and with minimum thickness, calculating a thickness correction value, and calculating an ultrasound test speed from said thickness correction value, said measured times, and said measured maximum and minimum real thickness. Then, the total thickness of each of the parts of the component are measured, using ultrasounds with the same calculated ultrasound test speed, and the thickness correction value is applied to each of the measuring total thickness of each part, to determine a corrected carbon fiber thickness for each part.
    Type: Grant
    Filed: July 22, 2016
    Date of Patent: July 23, 2019
    Assignee: Airbus Operations, S.L.
    Inventors: Luis Jara Blazquez, David Torres Macarrilla, Sergio Bermejo Gonzalez, David Lopez Bravo
  • Patent number: 10315360
    Abstract: A manufacturing method of structures formed co-bonding second structural components to a first structural component. The method comprises the following steps: a) preparing for each second structural component an ensemble wherein a preform of the second structural component, surrounded by a band of a suitable material to form a vacuum bag, is disposed between curing tools which are thus in contact with the bag and not with the preform; b) positioning the ensembles on the first structural component and forming the vacuum bag for the complete structure joining the bands and complementary pieces; c) applying to the resulting assembly an autoclave cycle.
    Type: Grant
    Filed: April 28, 2016
    Date of Patent: June 11, 2019
    Assignee: Airbus Operations S.L.
    Inventors: Yolanda Miguez Charines, Francisco Javier Jordan Carnicero, Augusto Perez Pastor, Angel Pablo Gordo, Laura Alvarez Antonon
  • Patent number: 10293557
    Abstract: The present disclosure refers to the manufacturing process of an aperture surrounding frame for an aircraft fuselage. The method includes providing a tubular braiding material (2) with a perimeter equal to the perimeter of the frame to be manufactured, cutting the tubular braiding material (2) to obtain annular-shaped braiding slices (3), providing an annular-shaped inner mold (4) where the annular-shaped inner mold has a surface with a desired shape for the aperture surrounding frame, layering up at least one braiding slice (3) around the inner mold (4), forming the at least one braiding slice (3) around the inner mold (4), and curing the aperture surrounding frame pre-form. The present disclosure also refers to an aperture surrounding frame (1) for an aircraft fuselage formed as a continuous body by at least one annular-shaped braiding slice (3) with a perimeter equal to the perimeter of the desired aperture surrounding frame.
    Type: Grant
    Filed: November 4, 2016
    Date of Patent: May 21, 2019
    Assignee: Airbus Operations, S.L.
    Inventors: David Alfonso Cerezo Arce, Melania Sanchez Perez, Alvaro Calero Casanova
  • Patent number: 10286993
    Abstract: A pressure bulkhead for an aircraft comprising a fuselage. The pressure bulkhead comprises an inflatable element, suitable for being filled with air, which in turn comprises a cover which delimits an inner zone. The pressure bulkhead further comprises a seal suitable for providing an airtight seal between the cover and the fuselage of the aircraft.
    Type: Grant
    Filed: December 1, 2016
    Date of Patent: May 14, 2019
    Assignee: Airbus Operations S.L.
    Inventors: Jesús Javier Vázquez Castro, Fernando Pereira Mosqueira
  • Patent number: 10259587
    Abstract: An aircraft comprising a heat exchanging pack comprising an energy recovering module with a hot and a cold side, the hot side thermally contacting the cold side, providing a heat exchange. The heat exchanging pack also comprises a secondary heat exchanger and a compressor coupled with a turbine. The hot side module inlet fluidly communicates with the bleed air duct, the cold side module inlet fluidly communicates with the ram air duct, the hot side module outlet fluidly communicates with the compressor inlet, the compressor outlet fluidly communicates with the hot side secondary inlet, the hot side secondary outlet fluidly communicates with the turbine inlet, and the cold side secondary inlet fluidly communicates with the ram air duct. The energy recovering module comprises a conversion apparatus, configured to generate energy out from the heat exchange taking place in the energy recovering module between the hot and cold sides.
    Type: Grant
    Filed: March 15, 2016
    Date of Patent: April 16, 2019
    Assignee: Airbus Operations S.L.
    Inventor: David Vicente Oliveros
  • Patent number: 10196124
    Abstract: An external part of an aircraft (such as a fairing) comprising a skin made with flexible materials attached to rigid supporting elements (such as longerons and frames) arranged in, at least, two directions. The skin comprises inner inflatable panels in all bays delimited by the rigid supporting elements and/or an external inflatable panel. The skin is joined to the supporting elements so that its external surface complies with aerodynamic requirements.
    Type: Grant
    Filed: July 5, 2016
    Date of Patent: February 5, 2019
    Assignees: Airbus Operations S.L., Airbus Operations Ltd.
    Inventors: Jesús Javier Vazquez Castro, Fernando Pereira Mosqueira, Juan José Gutierrez Santiago, Anthony Langley, Guy Tothill, Davood Sarchamy, Miguel Marín Muñoz
  • Patent number: 10179253
    Abstract: A system for making an autoclave inert such that flame propagation is prevented in the event of spontaneous internal combustion, which thus prevents damaging the actual system or equipment, tools and parts, for which it essentially has sodium azide capsules which produce a chemical reaction when they reach an activation temperature, releasing nitrogen, making the chamber inert, venting equipment to prevent damage due to overpressure inside the chamber when the capsules have come into action and released the gas, a main cooling circuit and an additional cooling circuit for the capsules, all of this automatically controlled and managed by a control device.
    Type: Grant
    Filed: May 29, 2015
    Date of Patent: January 15, 2019
    Assignee: Airbus Operations, S.L.
    Inventors: Jose Manuel Santos Gomez, Ramón Ramos