Patents by Inventor Yann Simonneaux
Yann Simonneaux 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: 20230002038Abstract: A method for pressurizing and depressurizing a shock absorber of an aircraft. More specifically, it relates to a method in which an aircraft weight and ambient temperature are used to calculate a required pressurization level of a shock absorber. As such, the shock absorber may be pressurized to the correct level without applying an iterative approach, greatly reducing initialization time.Type: ApplicationFiled: September 7, 2022Publication date: January 5, 2023Applicant: Safran Landing Systems UK LTDInventors: Yann Simonneaux, Jon Smith
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Patent number: 11479347Abstract: A method for pressurizing and depressurizing a shock absorber of an aircraft. More specifically, it relates to a method in which an aircraft weight and ambient temperature are used to calculate a required pressurization level of a shock absorber. As such, the shock absorber may be pressurized to the correct level without applying an iterative approach, greatly reducing initialization time.Type: GrantFiled: May 30, 2017Date of Patent: October 25, 2022Inventors: Yann Simonneaux, Jon Smith
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Publication number: 20220297825Abstract: An aircraft comprising a fuselage, a pair of wings connected to an upper portion of the fuselage, and a pair of wing support struts, each wing support strut being connected between a lower portion of the fuselage and an underside of the adjacent wing, wherein at least one centre landing gear assembly is connected to the fuselage and is configured to be retractable within the fuselage, and a respective outrigger landing gear is connected to each wing support strut, each outrigger landing gear being configured to be retractable within the respective wing support strut.Type: ApplicationFiled: April 15, 2020Publication date: September 22, 2022Applicant: SAFRAN LANDING SYSTEMS UK LTDInventor: Yann Simonneaux
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Patent number: 10794407Abstract: A centre seeking actuator having an outer cylinder, a slave cylinder slidably disposed within the outer cylinder, and a rod assembly having a piston slidably disposed within the slave cylinder and a rod extending from the piston to a point outside the outer cylinder. One or more first dynamic seals are arranged to act on a side wall of the rod to inhibit working fluid leaking from the outer cylinder, and one or more second dynamic seals are arranged to act on a sidewall of the slave cylinder to inhibit working fluid leaking from the outer cylinder.Type: GrantFiled: December 7, 2017Date of Patent: October 6, 2020Assignee: Safran Landing Systems UK LTDInventor: Yann Simonneaux
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Patent number: 10112699Abstract: A method of preloading an aircraft assembly involving a step of operating an extendible preloading tool to move a landing gear strut to decrease the distance between first and second link attachment joints for attachment of a preloading linkage. A tool and aircraft assembly are also provided.Type: GrantFiled: June 23, 2016Date of Patent: October 30, 2018Assignee: Safran Landing Systems UK LTDInventors: Yann Simonneaux, Andrew Paddock
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Publication number: 20180172035Abstract: A centre seeking actuator having an outer cylinder, a slave cylinder slidably disposed within the outer cylinder, and a rod assembly having a piston slidably disposed within the slave cylinder and a rod extending from the piston to a point outside the outer cylinder. One or more first dynamic seals are arranged to act on a side wall of the rod to inhibit working fluid leaking from the outer cylinder, and one or more second dynamic seals are arranged to act on a sidewall of the slave cylinder to inhibit working fluid leaking from the outer cylinder.Type: ApplicationFiled: December 7, 2017Publication date: June 21, 2018Inventor: Yann Simonneaux
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Publication number: 20170349270Abstract: A method for pressurizing and depressurizing a shock absorber of an aircraft. More specifically, it relates to a method in which an aircraft weight and ambient temperature are used to calculate a required pressurization level of a shock absorber. As such, the shock absorber may be pressurized to the correct level without applying an iterative approach, greatly reducing initialization time.Type: ApplicationFiled: May 30, 2017Publication date: December 7, 2017Inventors: Yann Simonneaux, Jon Smith
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Publication number: 20170016502Abstract: A magnetic shock absorber having a first body slidably coupled to a second body via a first bearing arranged to move in sliding engagement with a first counter-face portion. A first array of magnets associated with the first body is arranged to magnetically interact with a second array of magnets associated with the second body to absorb compression or extension loads applied to the shock absorber. The first bearing and the first counter-face portion each have a non-circular cross section profile to inhibit axial relative rotation between the bodies.Type: ApplicationFiled: July 1, 2016Publication date: January 19, 2017Inventors: Yann Simonneaux, Steven Whitman
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Publication number: 20160375989Abstract: A method of preloading an aircraft assembly involving a step of operating an extendible preloading tool to move a landing gear strut to decrease the distance between first and second link attachment joints for attachment of a preloading linkage. A tool and aircraft assembly are also provided.Type: ApplicationFiled: June 23, 2016Publication date: December 29, 2016Inventors: Yann Simonneaux, Andrew Paddock
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Patent number: 9527582Abstract: Aircraft undercarriage leg including an axle (3) that bears at least one wheel (4), the undercarriage leg being equipped with a unit (6) for driving rotation of the wheel, wherein the drive unit is rigidly fixed to the axle and a deformable support (12) extends between a cantilevered portion of the drive unit and a portion of the undercarriage leg not including the axle to support the cantilevered portion of the drive unit.Type: GrantFiled: July 31, 2014Date of Patent: December 27, 2016Assignee: MESSIER-BUGATTI-DOWTYInventors: Thierry Blanpain, Edouard Campbell, Yann Simonneaux, Martial Monseu, Remi Finet
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Patent number: 9440733Abstract: An aircraft brake assembly comprising a support leg, a main wheel rotatably mounted on the support leg, a brake comprising a first sub-assembly fixed to the main wheel and a second sub-assembly moveably mounted on the support leg and a ground reaction wheel coupled to the second sub-assembly, wherein on application of the brake, the first sub-assembly engages with the second sub-assembly to exert a braking force on the second sub-assembly; and wherein the ground reaction wheel is arranged to transfer the braking force from the second sub-assembly to the ground.Type: GrantFiled: April 15, 2013Date of Patent: September 13, 2016Assignee: Messier-Dowty LimitedInventors: Chris Green, Yann Simonneaux
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Patent number: 9346538Abstract: An aircraft landing gear including wheels and a fairing arranged to be moveable between a first and a second configuration, wherein in the first configuration the fairing is arranged to shield an element of the landing gear from incident airflow and wherein in the second configuration the fairing is arranged to deflect debris or spray propelled from one or more of the wheels.Type: GrantFiled: January 23, 2013Date of Patent: May 24, 2016Assignee: Messier-Dowty LimitedInventors: Yann Simonneaux, Simon D. Harris
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Publication number: 20150314859Abstract: Aircraft undercarriage leg including an axle (3) that bears at least one wheel (4), the undercarriage leg being equipped with a unit (6) for driving rotation of the wheel, wherein the drive unit is rigidly fixed to the axle and a deformable support (12) extends between a cantilevered portion of the drive unit and a portion of the undercarriage leg not including the axle to support the cantilevered portion of the drive unit.Type: ApplicationFiled: July 31, 2014Publication date: November 5, 2015Applicant: MESSIER-BUGATTI-DOWTYInventors: Thierry BLANPAIN, Edouard CAMPBELL, Yann SIMONNEAUX, Martial MONSEU, Remi FINET
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Patent number: 9174727Abstract: A landing gear assembly for an aircraft, the landing gear assembly including: an elongate bogie beam; a first axle bearing having an outer part rotatably coupled to an inner part, the outer part being coupled to the bogie beam, the inner part including a mounting aperture; and an elongate axle provided through the mounting aperture of the inner part and coupled thereto, wherein the axle is coupled to the inner part of the first axle bearing in a configuration such that the longitudinal axis of the axle is spaced from the axis of rotation of the inner part, such that rotation of the inner part causes a change in the orientation of the axle relative to the bogie beam.Type: GrantFiled: December 21, 2011Date of Patent: November 3, 2015Assignee: Messier-Dowty LimitedInventors: Stuart Lacy, Yann Simonneaux
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Publication number: 20150136902Abstract: An aircraft brake assembly comprising a support leg, a main wheel rotatably mounted on the support leg, a brake comprising a first sub-assembly fixed to the main wheel and a second sub-assembly moveably mounted on the support leg and a ground reaction wheel coupled to the second sub-assembly, wherein on application of the brake, the first sub-assembly engages with the second sub-assembly to exert a braking force on the second sub-assembly; and wherein the ground reaction wheel is arranged to transfer the braking force from the second sub-assembly to the ground.Type: ApplicationFiled: April 15, 2013Publication date: May 21, 2015Inventors: Chris Green, Yann Simonneaux
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Patent number: 9027878Abstract: An aircraft landing gear including a fairing (12) arranged to be moveable between first and second configurations, wherein in the first configuration the fairing shields an element of the landing gear from an incident airflow, the fairing being arranged to be in the first configuration when the landing gear is deployed but unloaded, and wherein in the second configuration the fairing exposes the landing gear element to the incident airflow, the fairing being arranged to be in the second configuration when the landing gear is deployed and loaded.Type: GrantFiled: April 30, 2010Date of Patent: May 12, 2015Assignee: Messier-Dowty LimitedInventor: Yann Simonneaux
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Publication number: 20150083857Abstract: An aircraft landing gear including wheels and a fairing arranged to be moveable between a first and a second configuration, wherein in the first configuration the fairing is arranged to shield an element of the landing gear from incident airflow and wherein in the second configuration the fairing is arranged to deflect debris or spray propelled from one or more of the wheels.Type: ApplicationFiled: January 23, 2013Publication date: March 26, 2015Inventors: Yann Simonneaux, Simon D. Harris
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Patent number: 8955798Abstract: An aircraft landing gear includes at least one load bearing longitudinal structural element. The longitudinal structural element is hollow and is arranged to have a non-structural element located inside.Type: GrantFiled: April 30, 2010Date of Patent: February 17, 2015Assignee: Messier-Dowty LimitedInventor: Yann Simonneaux
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Publication number: 20140048645Abstract: A landing gear assembly for an aircraft, the landing gear assembly including: an elongate bogie beam; a first axle bearing having an outer part rotatably coupled to an inner part, the outer part being coupled to the bogie beam, the inner part including a mounting aperture; and an elongate axle provided through the mounting aperture of the inner part and coupled thereto, wherein the axle is coupled to the inner part of the first axle bearing in a configuration such that the longitudinal axis of the axle is spaced from the axis of rotation of the inner part, such that rotation of the inner part causes a change in the orientation of the axle relative to the bogie beam.Type: ApplicationFiled: December 21, 2011Publication date: February 20, 2014Applicant: MESSIER-DOWTY LIMITEDInventors: Stuart Lacy, Yann Simonneaux
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Publication number: 20120292442Abstract: An aircraft landing gear including a fairing (12) arranged to be moveable between first and second configurations, wherein in the first configuration the fairing shields an element of the landing gear from an incident airflow, the fairing being arranged to be in the first configuration when the landing gear is deployed but unloaded, and wherein in the second configuration the fairing exposes the landing gear element to the incident airflow, the fairing being arranged to be in the second configuration when the landing gear is deployed and loaded.Type: ApplicationFiled: April 30, 2010Publication date: November 22, 2012Applicant: Messier-Dowty LimitedInventor: Yann Simonneaux