Patents by Inventor Jose Sanchez Gomez
Jose Sanchez Gomez 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: 11466136Abstract: A multifunctional diffusion barrier comprising at least one organic polymer and a 2D graphene or 2D graphene derivative material and a method for preparing the multifunctional barrier. The multifunctional diffusion barrier can be used as a liquid and/or gas barrier, or as structural material, or as sealing material, or as a self-cleaning material or as protective material against UV radiation in aeronautical, automotive, marine or building field. The multifunctional diffusion barrier is suitable in producing parts of aircraft such as a fuel tank, a fuel tank conduit and a gasket.Type: GrantFiled: March 16, 2018Date of Patent: October 11, 2022Assignee: Airbus Operations S.L.Inventors: Tamara Blanco Varela, Jose Sánchez Gómez, Silvia Lazcano Ureña, Vincenzo Palermo, Emanuele Treossi, Nicola Mirotta
-
Publication number: 20220184857Abstract: Methods for recycling plastic Nylon 6,6 from vacuum bags to obtain filaments or powder for 3D printing processes. The method to obtain filaments includes a step of providing used Nylon 6,6 vacuum bags, a quality control step to check the status of the used vacuum bags, a step to form smaller parts, such as smaller pieces or pellets, from the used vacuum bags, quality control step to check the status of the smaller pieces or the pellets, an extrusion step wherein the smaller pieces or the pellets are introduced into an extruder, where they are melted, and the molten mixture is cooled and expelled through the die of the extruder to produce the recycled filaments, and a winding step wherein the recycled filaments that go out of the extruder are rolled up in coils.Type: ApplicationFiled: April 6, 2020Publication date: June 16, 2022Inventors: Enrique GUINALDO FERNÁNDEZ, Tamara BLANCO VARELA, Guillermo HERNÁIZ LÓPEZ, José SÁNCHEZ GÓMEZ
-
Publication number: 20210299947Abstract: A method for manufacturing a part layer-upon-layer using Additive Manufacturing technology suitable for structural applications. The method includes selectively depositing at least a first type filament and a second type filament, wherein the second type filament differs from the first type filament at least in the cross-sectional dimension.Type: ApplicationFiled: March 25, 2021Publication date: September 30, 2021Inventors: Asuncion BUTRAGUENO-MARTINEZ, Guillermo HERNAIZ LOPEZ, Jose SANCHEZ-GOMEZ
-
Publication number: 20210138722Abstract: A three-dimensional printing system including: a printing bed (3) where a printed material is deposited to form an object (1), a bobbin (4) configured to hold a filament (2) of thermoplastic material reinforced with a continuous electrically conductive element, a printing head (5) fed by the bobbin (4) and configured to deposit, e.g., print, the filament on the printing bed (3) to form an object and first and second electrodes (7, 8) connected to a power supply (6), wherein the first electrode (7) is connected to the printing bed (3), and the second electrode (8) is connected to the filament, wherein an electric circuit is created through the continuous conductive element in the filament to heat the printed material.Type: ApplicationFiled: November 6, 2020Publication date: May 13, 2021Inventors: Asuncion BUTRAGUENO-MARTINEZ, Guillermo HERNAIZ LOPEZ, Jose SANCHEZ GOMEZ
-
Patent number: 10773824Abstract: 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: GrantFiled: November 20, 2017Date of Patent: September 15, 2020Assignee: Airbus Operations, S.L.Inventors: Tamara Blanco Varela, José Sanchez Gomez, Leire Segura Martinez De Ilarduya, Mariano Morales Monge
-
Publication number: 20200102437Abstract: A multifunctional diffusion barrier comprising at least one organic polymer and a 2D graphene or 2D graphene derivative material and a method for preparing the multifunctional barrier. The multifunctional diffusion barrier can be used as a liquid and/or gas barrier, or as structural material, or as sealing material, or as a self-cleaning material or as protective material against UV radiation in aeronautical, automotive, marine or building field. The multifunctional diffusion barrier is suitable in producing parts of aircraft such as a fuel tank, a fuel tank conduit and a gasket.Type: ApplicationFiled: March 16, 2018Publication date: April 2, 2020Inventors: Tamara BLANCO VARELA, Jose SÁNCHEZ GÓMEZ, Silvia LAZCANO UREÑA, Vincenzo PALERMO, Emanuele TREOSSI, Nicola MIROTTA
-
Publication number: 20190386474Abstract: A method for printed cable installation in a harness system of an aircraft. The method includes: printing at least a first conductive trace comprising conductive particles to a surface of an aircraft with a printing technology; printing at least second conductive trace comprising conductive particles to the surface of an aircraft with the printing technology; sintering the first and the second conductive traces by a laser, and interposing an insulating film between the first and the second conductive traces. For a trace length less than 5 meters, the first and second conductive traces provide the electromagnetic compatibility of a twisted pair of wires when printed with a guard trace.Type: ApplicationFiled: June 13, 2019Publication date: December 19, 2019Inventors: Alain RODEGHIERO, Jose SANCHEZ-GOMEZ, Tamara BLANCO VARELA, Cristobal Federico BRITO MAUR
-
Patent number: 10189123Abstract: A system for out of autoclave bonded repairs which including a fixing structure (1) to the composite area to be repaired, including a frame (4) and fixing parts (5, 19) attached to the frame (4), a movable structure (2) able to be attached either to the fixing structure (1) or to the patch manufacturing table (3), which includes three shafts (6, 6?, 6?) and three engines (7, 7?, 7?) configured to be able to move the tooling support in the three axes X, Y and Z, and a tooling support of either scanning tool (9), milling tool (10), patch cutting tool (11) or composite patch handle tool (11), and a patch manufacturing structure (3).Type: GrantFiled: October 5, 2016Date of Patent: January 29, 2019Assignee: Airbus Operations SLInventors: Ana Rodriguez Bellido, Jose Sanchez Gomez, Rafael Avila Dominguez, Enric Vila Papell, Rebeca Anguiano Zarranz, Juan Ignacio Forcen Carvalho
-
Patent number: 10040258Abstract: A method for obtaining a composite piece of n plies, at least one ply having a fiber volume greater than 58% in weight, the method comprising the steps of laying uncured prepreg plies and performing ultrasound compaction over each laid uncured laminate ply, wherein at least one of the uncured laminate plies has a fiber volume greater than 58% in weight. Finally, the composite laminate is cured. The step of performing ultrasound compaction comprises applying an ultrasonic compactor over each laid laminate ply.Type: GrantFiled: April 30, 2015Date of Patent: August 7, 2018Assignee: Airbus Operations S.L.Inventors: Jose Sanchez Gomez, Rafael Avila Dominguez, Hector Alonso Pintado
-
Publication number: 20180155055Abstract: 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: ApplicationFiled: November 20, 2017Publication date: June 7, 2018Applicant: Airbus Operations, S.L.Inventors: Tamara Blanco Varela, José Sanchez Gomez, Leire Segura Martinez De Ilarduya, Mariano Morales Monge
-
Publication number: 20170095894Abstract: A system for out of autoclave bonded repairs which including a fixing structure (1) to the composite area to be repaired, including a frame (4) and fixing parts (5, 19) attached to the frame (4), a movable structure (2) able to be attached either to the fixing structure (1) or to the patch manufacturing table (3), which includes three shafts (6, 6?, 6?) and three engines (7, 7?, 7?) configured to be able to move the tooling support in the three axes X, Y and Z, and a tooling support of either scanning tool (9), milling tool (10), patch cutting tool (11) or composite patch handle tool (11), and a patch manufacturing structure (3).Type: ApplicationFiled: October 5, 2016Publication date: April 6, 2017Inventors: Ana RODRIGUEZ BELLIDO, Jose SANCHEZ GOMEZ, Rafael AVILA DOMINGUEZ, Enric VILA PAPELL, Rebeca ANGUIANO ZARRANZ, Juan Ignacio FORCEN CARVALHO
-
Publication number: 20150314539Abstract: A method for obtaining a composite piece of n plies, at least one ply having a fiber volume greater than 58% in weight, the method comprising the steps of laying uncured prepreg plies and performing ultrasound compaction over each laid uncured laminate ply, wherein at least one of the uncured laminate plies has a fiber volume greater than 58% in weight. Finally, the composite laminate is cured. The step of performing ultrasound compaction comprises applying an ultrasonic compactor over each laid laminate ply.Type: ApplicationFiled: April 30, 2015Publication date: November 5, 2015Inventors: Jose Sanchez Gomez, Rafael Avila Dominguez, Hector Alonso Pintado
-
Patent number: 8371530Abstract: The invention relates to an aircraft with a protection shield for the rear composite material, fuselage 25) for conducting tail impact tests, in addition to a tail absorber, the shield (11) being formed by a plurality of pieces (21) joined to supports (23) fixed to the rear fuselage (25) behind the tail absorber (1), said pieces (21) having a laminar structure with an outer steel sheet (13), an inner composite sheet (17) and an intermediate high resistance silicon sheet (15).Type: GrantFiled: December 29, 2005Date of Patent: February 12, 2013Assignee: Airbus Operations, S.L.Inventors: Cesar Bautista De La Llave, Bernardo Lopez Romano, Angel Postigo Rodriguez, Jose Sanchez Gomez
-
Patent number: 8197625Abstract: The present invention relates to a process for manufacturing composite structures formed by two subcomponents of the same material, characterized in that it comprises the following steps: providing a first subcomponent (13), particularly a skin; providing a tool (15) made of a composite and precured for the manufacture of the second subcomponent (17), particularly a stiffener; positioning said tool (15) on said first subcomponent (13); applying preimpregnated composite (21) on said tool (15) so as to form the second subcomponent (17); consolidating the composite structure by means of a process of curing the assembly resulting from the previous steps under suitable pressure and/or temperature conditions.Type: GrantFiled: June 28, 2006Date of Patent: June 12, 2012Assignee: Airbus Espana S. L.Inventors: Enrique Garate Fel, Enrique Redondo Vara, Jose Sanchez Gomez, Rafael Ruiseco Salgado, César Serrano Velaz
-
Publication number: 20100252180Abstract: This invention relates to a process for manufacturing a piece of composite material made with a polymer resin and fiber reinforcement from at least two subcomponents comprising the following steps: a) providing the first subcomponent partially cured in a curing cycle in an autoclave at a maximum temperature T1, comprised between the resin gelling temperature GT and the resin curing temperature CT, applied for a predetermined time PT1 such that the exothermal component is released from the first subcomponent in a degree exceeding 50%; b) providing the second subcomponent in a fresh or cured state; c) assembling the two subcomponents and then joining them to one another in a curing cycle in an autoclave at a maximum temperature T2 comprised between 90% and 100% of the resin curing temperature CT, applied for a predetermined time PT2.Type: ApplicationFiled: September 26, 2006Publication date: October 7, 2010Inventors: Jose Cuenca Rincon, Jose Sanchez Gomez, Begona Santoro Alvarez
-
Publication number: 20100059627Abstract: The invention relates to an aircraft with a protection shield for the rear composite material, fuselage 25) for conducting tail impact tests, in addition to a tail absorber, the shield (11) being formed by a plurality of pieces (21) joined to supports (23) fixed to the rear fuselage (25) behind the tail absorber (1), said pieces (21) having a laminar structure with an outer steel sheet (13), an inner composite sheet (17) and an intermediate high resistance silicon sheet (15).Type: ApplicationFiled: December 29, 2005Publication date: March 11, 2010Inventors: Cesar Bautista De La Llave, Bernardo Lopez Romano, Angel Postigo Rodriguez, Jose Sanchez Gomez
-
Publication number: 20090151865Abstract: The invention relates to a jig (9) for manufacturing composite material parts out-of-autoclave, comprising a base (11) the upper surface of which includes a stacking table (13) having a rotating movement and a shifting movement in the laminating direction, and a head (15) supported on a portal frame (17) through means allowing the shift perpendicular to the laminating direction on the mentioned table (13), the head (15) in turn comprising: automatic means (21) for placing tapes or roves of composite material in the form of prepreg; compacting means (23) for compacting the composite material and curing means (25) for polymerizing the composite material. The invention also relates to an out-of-autoclave process for manufacturing composite material structures.Type: ApplicationFiled: February 14, 2008Publication date: June 18, 2009Inventors: Asuncion Butragueno Martinez, Jose Sanchez Gomez, Rafael Avila Dominguez
-
Publication number: 20090029113Abstract: Structural component of non-conductive composite material, particularly for aircraft (panel (1), frame (3), stringer (2), etc), that comprises in the surface a metal-type layer (4), such that the mentioned structural component together with the remaining metallized structural components can provide the aircraft with the sufficient conductive metal mass. According to a second aspect of the invention, a metallization method is proposed in the manufacture of a structural component, particularly for aircraft, made of composite material, which method allows the geometric configuration of the add-on by applying it in an extensive or limited manner to predetermined contours by means of using templates. This constructive feature allows creating integrated electric circuits in the airplane structure by means of creating independent tracks with different widths and thicknesses.Type: ApplicationFiled: September 27, 2007Publication date: January 29, 2009Inventors: Pedro Ramon Garcia Sanchez, Desiderio Sanchez-Brunete Alvarez, Jose Luis Cifuentes Martin, Jose Sanchez Gomez
-
Publication number: 20080023130Abstract: This invention relates to a tool (9) for manufacturing pieces of composite material outside an autoclave comprising a stacking table (11); a movable head (15) on said stacking table (11) provided with: automatic means for placing tapes (19) of composite material; compacting means for compacting the composite material and microwave emission means (25) to cure the composite material. The invention also relates to a process for manufacturing pieces of composite material outside an autoclave, comprising the following steps: a) Placing composite material in the form of tapes on a tool with the shape of the piece to be manufactured, compacting it and partially curing it after its placement until completing a layer of the piece; b) Repeating step a) until completing the stacking of the piece and c) Curing the last layer of the piece until the required degree of curing.Type: ApplicationFiled: April 6, 2007Publication date: January 31, 2008Inventors: Jose Sanchez Gomez, Rafael Avila Dominguez, Asuncion Butragueno Martinez
-
Publication number: 20070151657Abstract: The present invention relates to a process for manufacturing composite structures formed by two subcomponents of the same material, characterized in that it comprises the following steps: providing a first subcomponent (13), particularly a skin; providing a tool (15) made of a composite and precured for the manufacture of the second subcomponent (17), particularly a stiffener; positioning said tool (15) on said first subcomponent (13); applying preimpregnated composite (21) on said tool (15) so as to form the second subcomponent (17); consolidating the composite structure by means of a process of curing the assembly resulting from the previous steps under suitable pressure and/or temperature conditions.Type: ApplicationFiled: June 28, 2006Publication date: July 5, 2007Inventors: Enrique Garate Fel, Enrique Redondo Vara, Jose Sanchez Gomez, Rafael Ruiseco Salgado, Cesar Serrano Velaz