Patents by Inventor Nicolas NGUYEN
Nicolas NGUYEN 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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Publication number: 20240017821Abstract: An aircraft undercarriage comprising: a leg connected to an aircraft structure to be movable between a deployed position and a retracted position; a brace member for holding the leg in its deployed position and comprising a first rod hinged to the aircraft structure and a second rod hinged to the first link and to the leg; a stabilizer member for holding the first and second rods in an aligned position and comprising a first link and a second link that are hinged to each other, with at least one of them being hinged to the brace member; and a spring for elastically urging the hinges of the first and second links into a generally aligned position. The spring comprises at least one spring blade arranged to be subjected to an axial compression force when the first and second links leave the generally aligned position.Type: ApplicationFiled: October 14, 2021Publication date: January 18, 2024Applicant: AFRAN LANDING SYSTEMSInventors: Clément CASTELLAN, Matteo CAPURRO, Thierry BLANPAIN, Nicolas NGUYEN
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Patent number: 11753153Abstract: A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.Type: GrantFiled: July 10, 2020Date of Patent: September 12, 2023Assignee: SAFRAN LANDING SYSTEMSInventors: Alexandre Daulny, Thierry Blanpain, Nicolas Nguyen, Yves Courtois de Lourmel
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Publication number: 20230045934Abstract: An actuator includes a body and at least a first offset connection port that is connected to the body by a first duct projecting from the body. The first connection port is mechanically connected to the body at least by first and second struts. The first strut and the second strut extend from the first connection port, respectively, to a first segment of the body and to a second segment of the body that is axially spaced apart from the first segment. An undercarriage includes such an actuator as its locking or unlocking actuator.Type: ApplicationFiled: January 20, 2021Publication date: February 16, 2023Applicant: SAFRAN LANDING SYSTEMSInventors: Yves COURTOIS DE LOURMEL, Sébastien MESSE, Jean-Baptiste KAMIS, Arnaud LE BRETON, Nicolas NGUYEN
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Publication number: 20220266993Abstract: A landing gear includes structural parts arranged to connect a wheel to a structure of an aircraft, each structural part including two or more interfaces for connection to one or more other of the structural parts or to the structure of the aircraft and two or more webs which extend so as to face one another while delimiting between them a free space and which connect the two interfaces in order to transmit the forces from one to the other.Type: ApplicationFiled: July 10, 2020Publication date: August 25, 2022Applicant: SAFRAN LANDING SYSTEMSInventors: Alexandre DAULNY, Thierry BLANPAIN, Nicolas NGUYEN, Yves COURTOIS de LOURMEL
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Patent number: 10974821Abstract: An aircraft undercarriage having a sliding rod slidably mounted in a strut-leg, and a scissors linkage (4) having one branch (4a) hinged to the strut-leg or to a turning element of a control for steering the sliding rod mounted to turn in the strut-leg, and one branch (4b) hinged to the sliding rod, the branches being hinged to each other by a pivot pin (12), the undercarriage being fitted with a shimmy-attenuator device (10a, 10b) placed on the pivot pin of the shimmy-attenuator, the attenuator device including threshold resilient return means generating a force returning the branches towards a rest position, and at least damping means generating a damping force when the branches move axially along the pivot pin. The attenuator device comprises two modules (10a, 10b) placed on either side of the scissors linkage in order to co-operate with the pivot pin, each of the modules performing at least one of the damping function and the threshold resilient return function.Type: GrantFiled: August 14, 2017Date of Patent: April 13, 2021Assignee: SAFRAN LANDING SYSTEMSInventors: Nicolas Nguyen, Laurent Mallet, Frédéric Ivaldi, Thierry Blanpain, Philippe Henrion
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Publication number: 20180086440Abstract: An aircraft undercarriage having a sliding rod slidably mounted in a strut-leg, and a scissors linkage (4) having one branch (4a) hinged to the strut-leg or to a turning element of a control for steering the sliding rod mounted to turn in the strut-leg, and one branch (4b) hinged to the sliding rod, the branches being hinged to each other by a pivot pin (12), the undercarriage being fitted with a shimmy-attenuator device (10a, 10b) placed on the pivot pin of the shimmy-attenuator, the attenuator device including threshold resilient return means generating a force returning the branches towards a rest position, and at least damping means generating a damping force when the branches move axially along the pivot pin. The attenuator device comprises two modules (10a, 10b) placed on either side of the scissors linkage in order to co-operate with the pivot pin, each of the modules performing at least one of the damping function and the threshold resilient return function.Type: ApplicationFiled: August 14, 2017Publication date: March 29, 2018Applicant: SAFRAN LANDING SYSTEMSInventors: Nicolas NGUYEN, Laurent MALLET, Frédéric IVALDI, Thierry BLANPAIN, Philippe HENRION
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Patent number: 9676473Abstract: Aircraft landing gear having a leg (12) for hinging to a structure of the aircraft so as to be movable between a deployed position and a retracted position, a main brace (15), a secondary brace (20), and a double-acting type unlocking actuator (30) having a first end coupled to the secondary brace and controllable for causing its links to move out of alignment against the action of the resilient member during retraction or deployment of the landing gear. The landing gear includes couplers (31, 33) for coupling to a second end of the unlocking actuator, which couplers ensure movement of said second end relative to the leg so that, for a given action, the unlocking actuator tends to break the alignment of the links when the landing gear is in one of its positions and tends to confirm said alignment when the landing gear is in its other position.Type: GrantFiled: November 29, 2013Date of Patent: June 13, 2017Assignee: MESSIER-BUGATTI-DOWTYInventors: Philippe Henrion, Dominique Ducos, Nicolas Nguyen
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Publication number: 20150314860Abstract: The invention relates to aircraft landing gear comprising: a leg (12) for hinging to a structure of the aircraft so as to be movable between a deployed position and a retracted position, a main brace (15), a secondary brace (20), and an unlocking actuator (30) having a first end coupled to the secondary brace and controllable for causing its links to move out of alignment against the action of the resilient member during retraction or deployment of the landing gear. According to the invention, the unlocking actuator is of the double-acting type and the landing gear includes coupling means (31, 33) for coupling to a second end of the unlocking actuator, which means ensure movement of said second end relative to the leg so that, for a given action, the unlocking actuator tends to break the alignment of the links when the landing gear is in one of its positions and tends to confirm said alignment when the landing gear is in its other position.Type: ApplicationFiled: November 29, 2013Publication date: November 5, 2015Applicant: MESSIER-BUGATTI-DOWTYInventors: Philippe HENRION, Dominique DUCOS, Nicolas NGUYEN