Patents by Inventor Julián Sánchez Fernández
Julián Sánchez Fernández 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: 8956495Abstract: 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: GrantFiled: June 7, 2011Date of Patent: February 17, 2015Assignee: Airbus Operations, S.L.Inventors: Augusto Pérez Pastor, Julián Sánchez Fernández, Fernando Esquivias Garía
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Patent number: 8943664Abstract: Method of manufacturing “T” shaped stringers (1) with an angle different from 90° between the web (2) and the foot (3) whereby the “T” shaped stringers have a stringer web and a stringer foot. The method comprises, after placing together two hot-formed “L” shaped semi-stringers to form a “T” shaped stringer, placing the “T” shaped stringer inside an invar alloy angle leaving a gap between the stringer web and the invar alloy angle. Afterwards, a heating device (7) is moved over the stringer feet (3) surface and a roller (8) slides over said stringer feet (3) surface to adapt the geometry of the stringer feet to the geometry of the invar alloy angle. The resulting “T” shaped stringer is co-bonded on a cured skin with an adhesive line between the stringer and the cured skin, and finally the obtained “T” shaped stringer is cured.Type: GrantFiled: May 30, 2012Date of Patent: February 3, 2015Assignee: Airbus Operations, S.L.Inventors: Yolanda Miguez Charines, Antonio Jose Fuentes Espejo, Oscar Miguel Macias Jareno, Julian Sanchez Fernandez
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Patent number: 8696340Abstract: A re-usable retainer designed to be used in the curing process of co-bonding uncured stringers. The re-usable retainer is made of metal so it is not necessary to manufacture one retainer for each manufactured stringer. The metallic retainer is placed in direct contact with the uncured resin so the cured stringer has a very good surface quality. The re-usable retainer has a special shape that allows a mild transition of the vacuum bag that avoids vacuum bag breakages. The re-usable retainer is easy to install and to remove.Type: GrantFiled: October 27, 2011Date of Patent: April 15, 2014Assignee: Airbus Operations, S.L.Inventors: Julián Sánchez Fernández, Federico López Pérez, Yolanda Miguez Charines
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Publication number: 20130133171Abstract: Method of manufacturing “T” shaped stringers (1) with an angle different from 90° between the web (2) and the foot (3) whereby the “T” shaped stringers have a stringer web and a stringer foot. The method comprises, after placing together two hot-formed “L” shaped semi-stringers to form a “T” shaped stringer, placing the “T” shaped stringer inside an invar alloy angle leaving a gap between the stringer web and the invar alloy angle. Afterwards, a heating device (7) is moved over the stringer feet (3) surface and a roller (8) slides over said stringer feet (3) surface to adapt the geometry of the stringer feet to the geometry of the invar alloy angle. The resulting “T” shaped stringer is co-bonded on a cured skin with an adhesive line between the stringer and the cured skin, and finally the obtained “T” shaped stringer is cured.Type: ApplicationFiled: May 30, 2012Publication date: May 30, 2013Applicant: AIRBUS OPERATIONS, S.L.Inventors: Yolanda Miguez Charines, Antonio Jose Fuentes Espejo, Oscar Miguel Macias Jareno, Julian Sanchez Fernandez
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Publication number: 20120267046Abstract: The present invention provides a closed composite material structure for aircraft fuselage shaped on a male jig from which it can be separated in a certain direction, said structure comprising a single outer panel and a plurality of inner longitudinal stiffeners integrated in said panel, such that the expansion coefficient of the male jig is greater than the expansion coefficient of the composite material of the structure, thus being able to remove the already manufactured structure, formed by the panel and the integrated inner stiffeners, in a single operation. The present invention further provides a process for manufacturing such a closed structure.Type: ApplicationFiled: June 29, 2012Publication date: October 25, 2012Inventors: Alberto Ramon MARTINEZ CEREZO, Yolanda Miguez Charines, Javier Jordán Carnicero, Julián Sánchez Fernández
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Publication number: 20120107435Abstract: A re-usable retainer designed to be used in the curing process of co-bonding uncured stringers. The re-usable retainer is made of metal so it is not necessary to manufacture one retainer for each manufactured stringer. The metallic retainer is placed in direct contact with the uncured resin so the cured stringer has a very good surface quality. The re-usable retainer has a special shape that allows a mild transition of the vacuum bag that avoids vacuum bag breakages. The re-usable retainer is easy to install and to remove.Type: ApplicationFiled: October 27, 2011Publication date: May 3, 2012Applicant: AIRBUS OPERATIONS, S.L.Inventors: Julian SÁNCHEZ FERNÁNDEZ, Federico López Pérez, Yolanda Miguez Charines
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Patent number: 8122576Abstract: The system has special application in the manufacture of aircraft wing covers (10 made of carbon fiber and the stringers (3) cured jointly with the wing cover during the polymerization in autoclave. The tool pieces (4) being used are defined by angular elements (5, 6) copying the geometry of the stringers (3). The shape of these stringers corresponds to the “T” section. The angular elements (5, 6) comprise, in their upper part, a pair of battlements (7) in order to be caught by part of the clamps (9) of a head (10) linked to a robot (11) of the spherical type with articulated arm with six axes. The angular elements (5, 6) are made of INVAR material and they are used to keep in position the stringers during the curing cycle in the autoclave.Type: GrantFiled: April 30, 2009Date of Patent: February 28, 2012Assignee: Airbus Operations, S.L.Inventors: José Manuel Santos Gómez, José Manuel Menéndez Martín, Antonio Durán Quiroga, Aquilino García García, Julián Sánchez Fernández
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Publication number: 20110315307Abstract: 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 geometry 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 method characterised in that 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: ApplicationFiled: June 7, 2011Publication date: December 29, 2011Inventors: Augusto PÉREZ PASTOR, Julián Sánchez Fernández, Fernando Esquivias GARCÍA
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Publication number: 20110186209Abstract: The invention proposes a forming process for forming geometrically complex laminates made of composite material which allows obtaining very complex folded geometries, reducing the area of influence of the formed areas and making its effect local, handling the geometry of the laminate near the area to he formed, replacing the formed geometries with folded geometries, this way forcing the area of influence of the forming to be local, such that the length of the reinforcing fibers affected by said forming is minimal. The present invention also relates to complex geometries of laminates made of composite material obtained by means of the previous forming process.Type: ApplicationFiled: April 4, 2011Publication date: August 4, 2011Inventors: Jose Manuel Mendez Martin, Julian Sanchez Fernandez
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Publication number: 20100154186Abstract: The system has special application in the manufacture of aircraft wing covers (1) made of carbon fiber and the stringers (3) cured jointly with the wing cover during the polymerization in autoclave. The tool pieces (4) being used are defined by angular elements (5, 6) copying the geometry of the stringers (3). The shape of these stringers corresponds to the “T” section. The angular elements (5, 6) comprise, in their upper part, a pair of battlements (7) in order to be caught by part of the clamps (9) of a head (10) linked to a robot (11) of the spherical type with articulated arm with six axes. The angular elements (5, 6) are made of INVAR material and they are used to keep in position the stringers during the curing cycle in the autoclave.Type: ApplicationFiled: April 30, 2009Publication date: June 24, 2010Inventors: Jose Manuel Santos Gomez, Jose Manuel Menendez Martin, Antonio Duran Quiroga, Aquilino Garcia Garcia, Julian Sanchez Fernandez
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Publication number: 20100154608Abstract: In the state of the art, a composite prepreg lamination (2) is obtained, arranged on a cutting table (1), the lamination being affix to the table (1) by means of applying a vacuum, and the cutting of the lamination (2) being done in longitudinal strips (3) between which remain wasting material strips (4), being manually removed in order to continue with the subsequent post-processing of the longitudinal strips (3) and obtain the longitudinal pieces. The aim of the invention is to automate the process of removing the wasting material strips (4) so that, prior to their removal, one end (4a) of the strips (4) is affix on a rolled up device (5) and the strips (4) are rolled up in the longitudinal direction of the lamination (2). The device basically comprises a roller (5) provided with means for affixing the ends (4a) of the strips (4) for carrying out the said automation.Type: ApplicationFiled: April 21, 2009Publication date: June 24, 2010Inventors: Yolanda Miguez Charines, Julian Sanchez Fernandez, Mauricio Sanchez De La O
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Patent number: 7497115Abstract: The invention relates to a quality control process for an adhesive joint of two sub-components of a structure comprising the following steps: a) Providing the structure of composite material to be controlled; b) Providing at least one premanufactured testing device (1) representative of one of the sub-components of the structure; c) Bonding the at least one premanufactured testing device (1) to the other sub-component (7) of the structure in conditions similar to those of the real adhesive joint of the sub-components; d) Carrying out at least one mechanical test on the at least one premanufactured testing device (1) which allows assessing the quality of the adhesive joint.Type: GrantFiled: September 5, 2006Date of Patent: March 3, 2009Assignee: Airbus Espana, S.L.Inventors: José Manuel Menendez Martin, Julián Sánchez Fernández
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Publication number: 20080283668Abstract: The present invention provides a closed composite material structure for aircraft fuselage shaped on a male jig from which it can be separated in a certain direction, said structure comprising a single outer panel and a plurality of inner longitudinal stiffeners integrated in said panel, such that the expansion coefficient of the male jig is greater than the expansion coefficient of the composite material of the structure, thus being able to remove the already manufactured structure, formed by the panel and the integrated inner stiffeners, in a single operation. The present invention further provides a process for manufacturing such a closed structure.Type: ApplicationFiled: March 30, 2007Publication date: November 20, 2008Inventors: Alberto Ramon Martinez Cerezo, Yolanda Miguez Charines, Javier Jordan Carnicero, Julian Sanchez Fernandez
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Publication number: 20080268208Abstract: The invention proposes a forming process for forming geometrically complex laminates made of composite material which allows obtaining very complex folded geometries, reducing the area of influence of the formed areas and making its effect local, handling the geometry of the laminate near the area to be formed, replacing the formed geometries with folded geometries, this way forcing the area of influence of the forming to be local, such that the length of the reinforcing fibers affected by said forming is minimal. The present invention also relates to complex geometries of laminates made of composite material obtained by means of the previous forming process.Type: ApplicationFiled: July 2, 2007Publication date: October 30, 2008Inventors: Jose Manuel Menedez Martin, Julian Sanchez Fernandez
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Publication number: 20080011075Abstract: The invention relates to a quality control process for an adhesive joint of two sub-components of a structure comprising the following steps: a) Providing the structure of composite material to be controlled; b) Providing at least one premanufactured testing device (1) representative of one of the sub-components of the structure; c) Bonding said at least one premanufactured testing device (1) to the other sub-component (7) of the structure in conditions similar to those of the real adhesive joint of said sub-components; d) Carrying out at least one mechanical test on said at least one premanufactured testing device (1) which allows assessing the quality of said adhesive joint.Type: ApplicationFiled: September 5, 2006Publication date: January 17, 2008Inventors: Jose Manuel Menendez Martin, Julian Sanchez Fernandez