Patents by Inventor Diego Folch Cortes
Diego Folch Cortes 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: 10730602Abstract: An internal shield inside the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it. The internal shield is located in a suitable place inside the rear fuselage for covering the possible trajectories of fragments detached from one of the engines in a failure event that would impact critical elements of the opposite engine. The internal shield comprises an ensemble of fluid containers belonging to aircraft sub-systems, such as, particularly, the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping the fragments. An aircraft having the internal shield is also disclosed.Type: GrantFiled: June 15, 2016Date of Patent: August 4, 2020Assignees: AIRBUS OPERATIONS S.L., AIRBUS OPERATIONS S.A.S.Inventors: Javier Toral Vazquez, Esteban Martino Gonzalez, Diego Folch Cortes, Pablo Goya Abaurrea, Vasilis Votsios, Michel Fouinnetau, Sylvain Roumegas, Wolfgang Brochard
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Patent number: 10358206Abstract: 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: GrantFiled: December 18, 2015Date of Patent: July 23, 2019Assignees: 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
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Patent number: 10124876Abstract: 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: GrantFiled: November 25, 2015Date of Patent: November 13, 2018Assignees: 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
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Patent number: 10046848Abstract: 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: GrantFiled: April 4, 2016Date of Patent: August 14, 2018Assignees: AIRBUS OPERATIONS S.L., AIRBUS OPERATIONS SASInventors: Diego Folch Cortes, Esteban Martino Gonzalez, Jose Antonio Mariblanca Lopez, Lionel Diochon
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Patent number: 10023299Abstract: 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: GrantFiled: December 23, 2015Date of Patent: July 17, 2018Assignee: AIRBUS OPERATIONS, S.L.Inventors: Javier Toral Vazquez, Diego Folch Cortes, Esteban Martino Gonzalez, Pablo Goya Abaurrea, Vasilis Votsios, Michel Fouinnetau, Sylvain Roumegas
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Publication number: 20180170513Abstract: 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: ApplicationFiled: December 15, 2017Publication date: June 21, 2018Inventors: Esteban MARTINO GONZÁLEZ, Diego FOLCH CORTÉS, José María PINA LÓPEZ
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Patent number: 9995359Abstract: 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: GrantFiled: August 25, 2016Date of Patent: June 12, 2018Assignee: 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
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Publication number: 20180127081Abstract: 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: ApplicationFiled: November 3, 2017Publication date: May 10, 2018Inventors: Javier TORAL VÁZQUEZ, Esteban MARTINO GONZALEZ, Diego FOLCH CORTES, Pablo GOYA ABAURREA, Vasillis VOTSIOS, Michel FOUINNETAU, Sylvain ROUMEGAS
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Patent number: 9896181Abstract: 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: GrantFiled: December 29, 2015Date of Patent: February 20, 2018Assignee: Airbus Operations, S.L.Inventors: Esteban Martino Gonzalez, Diego Folch Cortes, Pablo Goya Abaurrea, Sandra Linares Mendoza
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Patent number: 9656736Abstract: In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.Type: GrantFiled: April 24, 2015Date of Patent: May 23, 2017Assignees: Airbus Operations (S.A.S.), Airbus Operations SLInventors: Julien Guillemaut, Esteban Martino Gonzalez, Diego Folch Cortes, Jerome Colmagro, Jonathan Blanc
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Publication number: 20170058985Abstract: 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: ApplicationFiled: August 25, 2016Publication date: March 2, 2017Inventors: Esteban MARTINO GONZALEZ, Andrea Iván MARASCO, Diego FOLCH CORTÉS, Javier TORAL VÁZQUEZ, Vasilis VOTSIOS, Raúl FERNANDEZ BALLESTEROS, Fernando PEREIRA MOSQUEIRA
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Publication number: 20160362167Abstract: An internal shield inside the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it. The internal shield is located in a suitable place inside the rear fuselage for covering the possible trajectories of fragments detached from one of the engines in a failure event that would impact critical elements of the opposite engine. The internal shield comprises an ensemble of fluid containers belonging to aircraft sub-systems, such as, particularly, the potable water and waste water sub-systems, with enough fluid for providing the energy absorption capability required for stopping the fragments. An aircraft having the internal shield is also disclosed.Type: ApplicationFiled: June 15, 2016Publication date: December 15, 2016Inventors: Javier Toral Vazquez, Esteban Martino Gonzalez, Diego Folch Cortes, Pablo Goya Abaurrea, Vasilis Votsios, Michel Fouinnetau, Sylvain Roumegas, Wolfgang Brochard
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Publication number: 20160311515Abstract: In the case of an aircraft aft portion equipped with an engine mounting structure passing across the fuselage, assembly of the aft portion presents problems caused by the moving of the box structure of the mounting structure through lateral openings in the fuselage. In order to overcome these problems, a method of assembling an aircraft aft portion is proposed, in which method the box structure of the engine mounting structure is inserted into the fuselage through a top opening extending from one side of the fuselage to the other across a vertical midplane of the fuselage such that the top opening opens to the top and to the sides of the fuselage.Type: ApplicationFiled: April 24, 2015Publication date: October 27, 2016Inventors: Julien GUILLEMAUT, Esteban MARTINO GONZALEZ, Diego FOLCH CORTES, Jerome COLMAGRO, Jonathan BLANC
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Publication number: 20160297510Abstract: 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: ApplicationFiled: April 4, 2016Publication date: October 13, 2016Inventors: Diego Folch Cortes, Esteban Martino Gonzalez, Jose Antonio Mariblanca Lopez, Lionel Diochon
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Publication number: 20160244142Abstract: An aircraft fuselage comprising a pressurized cabin and an unpressurized rear section separated by a rear pressure bulkhead. The bulkhead comprises flat portions forming one or more kinks between them. One of the kinks is contiguous to a rear border of a floor that divides a space of the pressurized cabin into upper and lower compartments.Type: ApplicationFiled: February 15, 2016Publication date: August 25, 2016Inventors: Esteban Martino Gonzalez, Pablo Goya Abaurrea, Diego Folch Cortes, Sandra Linares Mendoza
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Publication number: 20160185439Abstract: 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: ApplicationFiled: December 29, 2015Publication date: June 30, 2016Inventors: Esteban Martino Gonzalez, Diego Folch Cortes, Pablo Goya Abaurrea, Sandra Linares Mendoza
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Publication number: 20160185465Abstract: 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: ApplicationFiled: December 18, 2015Publication date: June 30, 2016Inventors: Javier TORAL VÁZQUEZ, Diego FOLCH CORTES, Esteban MARTINO GONZÁLEZ, Pablo GOYA ABAURREA, Vasillis VOTSIOS, Michel FOUINNETAU, Sylvain ROUMEGAS
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Publication number: 20160176509Abstract: 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: ApplicationFiled: December 23, 2015Publication date: June 23, 2016Inventors: Javier Toral Vazquez, Diego Folch Cortes, Esteban Martino Gonzalez, Pablo Goya Abaurrea, Vasilis Votsios, Michel Fouinnetau, Sylvain Roumegas
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Publication number: 20160161223Abstract: The disclosure refers to an impact protective multi-layered fabric comprising a pile of layers of a dry-fabric material, wherein at least one of the layers is conformed to have least one closed fold extending longitudinally across the layer, the closed fold having first and second walls substantially facing each other, and wherein the first and second walls are stitched to each other by means of at least one yarn of a dry-fabric material. According to an aspect, the first and second walls of the closed fold, are stitched to each other by means of two or more stitching lines are arranged one above the other within the closed fold, such as when an object impact on the fabric layer, the stitches of the stitching lines break sequentially one after the other, such the energy absorption capability of the layer is increased in a simple manner and without increasing its weight.Type: ApplicationFiled: December 9, 2015Publication date: June 9, 2016Inventors: Javier Toral Vazques, Pablo Goya Abaurrea, Esteban Martino Gonzalez, Diego Folch Cortes, Vasilis Votsios, Michel Fouinnetau
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Patent number: 9359085Abstract: Internal shield in the rear fuselage of an aircraft having a propulsion system formed by two engines mounted on each side of it; the rear fuselage having at least a vertical symmetry plane; the rear fuselage being made of a composite material; the internal shield being located in said vertical symmetry plane and extended in an area that covers the possible trajectories of a set of pre-defined fragments detached from one of said engines in a failure event that would impact on critical elements of the opposite engine; the internal shield having a flat shape and an energy absorption capability that allows stopping said fragments. The invention also refers to a method for determining the area of an internal shield and to an aircraft having said internal shield.Type: GrantFiled: December 21, 2012Date of Patent: June 7, 2016Inventors: Diego Folch Cortés, Eduardo Vinué Santolalla, Esteban Martino González, Julien Guillemaut, Pablo Goya Abaurrea