Patents by Inventor Esteban Martino Gonzalez

Esteban Martino 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).

  • Patent number: 10414497
    Abstract: A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.
    Type: Grant
    Filed: September 14, 2017
    Date of Patent: September 17, 2019
    Assignee: AIRBUS OPERATIONS S.L.
    Inventors: Iker Vélez De Mendizábal Alonso, Esteban Martino González, Carlos García Nieto, Edouard Menard, Enrique Guinaldo Fernández, Soledad Crespo Peña, Jesús Javier Vázquez Castro
  • Publication number: 20190264610
    Abstract: An auxetic bi-stable structure that comprises an auxetic curved shell movable between a first and a second stable position, and a rigid element. At least part of the surface of the auxetic curved shell is joined to the rigid element such that the curved shell is movable with respect to the rigid element between the first and second stable positions.
    Type: Application
    Filed: February 21, 2019
    Publication date: August 29, 2019
    Inventors: Esteban MARTINO-GONZALEZ, Iker VELEZ DE MENDIZABAL ALONSO, Vasilis VOTSIOS, Guillermo NICOLAS GUTIERREZ, Diego SANCHEZ FRANCO, David MATESANZ HIDALGO, Jose Angel HERNANZ-MANRIQUE
  • 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
  • Publication number: 20190168480
    Abstract: A deformable auxetic structure for absorbing energy of an impact that comprises a plurality of interconnected adjoining tridimensional auxetic cells where each tridimensional auxetic cell comprises at least one surface element and a plurality of legs extending from the surface, the plurality of legs and the surface element being configured such that the sectional cut of the structure in at least two planes perpendicular to the surface element follows an auxetic pattern.
    Type: Application
    Filed: November 30, 2018
    Publication date: June 6, 2019
    Inventors: Esteban MARTINO-GONZALEZ, Iker VELEZ DE MENDIZABAL ALONSO, David APELLANIZ DE LA FUENTE
  • Publication number: 20190126572
    Abstract: A modular mold for producing a panel including a panel of fiber reinforced material. The panel is configured to form hollow cells having an undulated trapezoidal cross-section. The mold includes at least three molding bars for forming each hollow cell. One of the molding bars has a trapezoidal cross shape. The other two molding bars have a triangular cross shape. The trapezoidal molding bar is located between the two triangular molding bars. The three molding bars when put together its cross-section forms the shape of the trapezoidal cross-section of the hollow cell.
    Type: Application
    Filed: September 12, 2018
    Publication date: May 2, 2019
    Inventors: Iker VELEZ DE MENDIZABAL ALONSO, David APELLANIZ DE LA FUENTE, Esteban MARTINO-GONZALEZ - ARANJUEZ
  • Patent number: 10124876
    Abstract: An aircraft fuselage frame including a central element adapted to be located within the perimeter of the fuselage, and two lateral extensions projecting outside the perimeter of the fuselage from both sides of the central element that are a portion of a longitudinal structure of a lifting surface. The central element and the two lateral extensions are configured as an integrated piece.
    Type: Grant
    Filed: November 25, 2015
    Date of Patent: November 13, 2018
    Assignees: Airbus Operations S.L., Airbus Operations (SAS)
    Inventors: Esteban Martino Gonzalez, Diego Folch Cortes, Pablo Goya Abaurrea, Angel Pascual Fuertes, Sandra Linares Mendoza, Julien Guillemaut, Eric Bouchet, Jerome Colmagro, Jonathan Blanc
  • Publication number: 20180312239
    Abstract: A three-dimensional auxetic structure, comprising a plurality of adjoining hollow cells, each hollow cell having cell walls and a transversal cross section of the plurality hollow cells following a two-dimensional auxetic pattern, each cell wall comprising folding lines parallel to a plane containing the auxetic pattern such that peaks and valleys are defined in the cell walls and the cell walls being foldable along the folding lines.
    Type: Application
    Filed: April 19, 2018
    Publication date: November 1, 2018
    Inventors: Iker VÉLEZ DE MENDIZÁBAL ALONSO, Esteban MARTINO GONZÁLEZ, David APELLANIZ DE LA FUENTE, Alfonso PARRA RUBIO, Elena MOYA SANZ
  • Publication number: 20180281917
    Abstract: An impact resistant fuselage of an aircraft, the fuselage extending along a central longitudinal direction, wherein transversal sections of the fuselage are comprised in a vertical plane perpendicular to the central longitudinal direction. The impact resistant fuselage comprises at least a ballistic material membrane extended along the longitudinal direction for absorbing high energy impacts. The membrane according to a transversal section, comprising at least one section between two tensional elements, wherein the material membrane is located inside the fuselage of the aircraft, the at least one section of the membrane is mechanically linked to the inside of the fuselage by the tensional elements, and the two tensional elements stress the membrane.
    Type: Application
    Filed: March 14, 2018
    Publication date: October 4, 2018
    Inventors: Edouard MENARD, Esteban MARTINO GONZÁLEZ, Fernando INIESTA LOZANO
  • Patent number: 10046848
    Abstract: An aircraft rear structure comprising a substantially flat rear pressure bulkhead, with a first side and a second side, opposite to the first side. The aircraft rear structure also comprises a horizontal stabilizer and a vertical stabilizer which in turn comprises a first spar and a second spar. The first spar is attached to a first attachment zone of the second side of the rear pressure bulkhead via first attaching elements, and the second spar is attached to a second attachment zone of the second side of the rear pressure bulkhead via second attaching elements. The second attachment zone being different from the first attachment zone.
    Type: Grant
    Filed: April 4, 2016
    Date of Patent: August 14, 2018
    Assignees: AIRBUS OPERATIONS S.L., AIRBUS OPERATIONS SAS
    Inventors: Diego Folch Cortes, Esteban Martino Gonzalez, Jose Antonio Mariblanca Lopez, Lionel Diochon
  • Patent number: 10023299
    Abstract: The disclosure refers to a propeller blade for an aircraft engine that includes an airbag system contained inside the blade and comprising at least one bag and at least one gas generator, the at least one gas generator in fluid communication with at least one bag for inflating the bag, a detecting system for detecting a rupture of a part of the blade, a trigger for activating the at least one gas generator when the rupture is detected by the detecting system, and the blade skin being configured for allowing the at least one bag to pass through the blade skin for being expanded outside the blade upon the bag inflation by the gas generator.
    Type: Grant
    Filed: December 23, 2015
    Date of Patent: July 17, 2018
    Assignee: AIRBUS OPERATIONS, S.L.
    Inventors: Javier Toral Vazquez, Diego Folch Cortes, Esteban Martino Gonzalez, Pablo Goya Abaurrea, Vasilis Votsios, Michel Fouinnetau, Sylvain Roumegas
  • Publication number: 20180170563
    Abstract: In order to reduce the congestion of the attachment means for aircraft engines in a secondary vein, a first fuselage frame has two side portions for supporting the engine, each associated with one of the two partly buried side engines, these portions being curved inwards so as to surround and follow the profile of the outer shroud of an intermediate case. The side portion is attached on this shroud through first and second attachment arrangements spaced apart from each other circumferentially, these arrangements being configured in order to allow absorption of the forces related to the torque along a longitudinal direction of the engine.
    Type: Application
    Filed: December 18, 2017
    Publication date: June 21, 2018
    Inventors: Eric BOUCHET, Esteban MARTINO-GONZALEZ, Jerome COLMAGRO, Fernando INIESTA LOZANO, Julien MOULIS, Antoine ABELE
  • Publication number: 20180174565
    Abstract: An energy absorbing structure for attenuating energy received from an energy source. The structure comprises a deformable structure formed by an ensemble of one or more first layers of a material having a positive Poisson's ratio, one or more second layers of a material having a negative Poisson's ratio and one or more third layers of an elastomeric material placed between a first layer and a second layer. The ensemble is arranged with the one or more third layers joined to the first and second layers for absorbing at least part of the energy through shear forces or a combination of traction and compression forces applied to the ensemble by the first and second layers as a consequence of their differential deformation after receiving the energy.
    Type: Application
    Filed: December 18, 2017
    Publication date: June 21, 2018
    Inventors: Esteban MARTINO GONZÁLEZ, Javier TORAL VAZQUEZ
  • Publication number: 20180170520
    Abstract: An impact resistant dorsal fin structure of an aircraft comprises an upper support and ballistic material layer, wherein the ballistic material is configured to be joined to an aircraft fuselage and the ballistic material layer is arranged in a sliding manner around a sliding surface of the upper support.
    Type: Application
    Filed: December 15, 2017
    Publication date: June 21, 2018
    Inventors: Edouard MENARD, Esteban MARTINO GONZÁLEZ, Fernando INIESTA LOZANO
  • Publication number: 20180170513
    Abstract: An aircraft rear section (20) including a fuselage rear section (21) extending from the rear pressure bulkhead (23) to the end of the fuselage and an empennage (12) including at least a vertical tail plane (13). An aircraft rear section (20) with a continuous skin (31) is formed by two lateral sides placed symmetrically with respect to the middle vertical plane of the aircraft, each side including an upper portion (26) for the torsion box (14) of the vertical tail plane (13), a lower portion (28) for the fuselage rear section (21) and a transition portion (27) between the upper and lower portions (26, 28). The upper and lower portions (26, 28) of the continuous skin (31) are joined to inner structural components of the vertical tail plane (13) and the fuselage rear section (21).
    Type: Application
    Filed: December 15, 2017
    Publication date: June 21, 2018
    Inventors: Esteban MARTINO GONZÁLEZ, Diego FOLCH CORTÉS, José María PINA LÓPEZ
  • Patent number: 9995359
    Abstract: A deformable structure, such as a panel or a shock absorber, for absorbing energy from a mechanical and/or acoustic impact. The structure comprises an inner core and one or more external layers covering the inner core. The inner core comprises a set of first segments having a positive Poison's ratio and second segments having a negative Poisson's ratio. The first and second segments are arranged alternately and joined to one another so that the deformation received by one first segment is transmitted to an adjacent second segment and vice versa.
    Type: Grant
    Filed: August 25, 2016
    Date of Patent: June 12, 2018
    Assignee: Airbus Operations S.L.
    Inventors: Esteban Martino Gonzalez, Andrea Iván Marasco, Diego Folch Cortés, Javier Toral Vázquez, Vasilis Votsios, Raúl Fernandez Ballesteros, Fernando Pereira Mosqueira
  • Publication number: 20180155006
    Abstract: An aircraft stabilizer (15, 17) with an enlarged area of laminar flow. The lateral skins (45a, 45b; 65a, 65b) of its torsion box (43; 63) include joggled areas (53a, 53b; 73a, 73b) as attachment areas of its leading edge (41; 61) which are arranged in a rearward position with respect to the forward most spar of the stabilizer (15, 17).
    Type: Application
    Filed: November 2, 2017
    Publication date: June 7, 2018
    Inventors: Alberto ARANA HIDALGO, Esteban MARTINO GONZÁLEZ, Jesús Javier VÁZQUEZ CASTRO, Pablo CEBOLLA GARROFE
  • Publication number: 20180127081
    Abstract: A panel structure for an aircraft with at least one composite layer, and at least one net-shaped layer attached to the composite layer, wherein the net-shaped layer has a material suitable to improve the impact resistance of the panel structure. The net-shaped layer can be used to attach two composite layers. Alternatively, the net-shaped layer can be attached to a surface of one composite layer. In this last case, the net-shaped layer may be joined to a laminate sheet material and filled with a foam material. An impact reinforced panel structure is disclosed capable of withstanding any impact, such as a blade release, or a bird strike, without substantially modifying the manufacturing process.
    Type: Application
    Filed: November 3, 2017
    Publication date: May 10, 2018
    Inventors: Javier TORAL VÁZQUEZ, Esteban MARTINO GONZALEZ, Diego FOLCH CORTES, Pablo GOYA ABAURREA, Vasillis VOTSIOS, Michel FOUINNETAU, Sylvain ROUMEGAS
  • Publication number: 20180072423
    Abstract: A lightweight shield for aircraft protection against threat of high energy impacts, which comprises, a structural layer that has a first side and a second side, the first side being intended for receiving the impact, and a ballistic material layer for absorbing high energy impacts, having a first side and a second side. The first side of the ballistic material layer is faced to the second side of structural layer and joined to the structural layer via a progressively detachable interface and, the second side of the ballistic material layer is a free surface.
    Type: Application
    Filed: September 14, 2017
    Publication date: March 15, 2018
    Inventors: Iker VÉLEZ DE MENDIZÁBAL ALONSO, Esteban MARTINO GONZÁLEZ, Carlos GARCÍA NIETO, Edouard MENARD, Enrique GUINALDO FERNÁNDEZ, Soledad CRESPO PEÑA, Jesús Javier VÁZQUEZ CASTRO
  • Patent number: 9896181
    Abstract: An aircraft rear structure that comprises a rear pressure bulkhead, and a lifting surface located at both sides of the fuselage of the aircraft. The lifting surface comprises spars extending in the longitudinal direction of the lifting surface. The pressure bulkhead is aligned with one of the spars of the lifting surface.
    Type: Grant
    Filed: December 29, 2015
    Date of Patent: February 20, 2018
    Assignee: Airbus Operations, S.L.
    Inventors: Esteban Martino Gonzalez, Diego Folch Cortes, Pablo Goya Abaurrea, Sandra Linares Mendoza