Patents by Inventor Stéphane Levert
Stéphane Levert 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: 8613404Abstract: The present invention relates to a take-up device for thrust forces (14) for an aircraft engine attachment pylon (4), comprising a first fitting (194) attached to a rigid structure (108) of the attachment pylon, and two lateral connecting rods (14a) for take-up of thrust forces. It also comprises an axis system (190) bearing three first ball joint organs (192a, 196a) arranged along the latter and belonging respectively to a primary ball joint (192) and two secondary ball joints (196) arranged on either side of the primary ball joint, the first fitting (194) integrating a second ball joint organ (192b) cooperating with the first organ (192a) of the primary ball joint (192), and an end of each of the two connecting rods (14a) integrating a second ball joint organ (196b) cooperating respectively with the first organs (196a) of the two secondary ball joints (196).Type: GrantFiled: September 22, 2011Date of Patent: December 24, 2013Assignee: AIRBUS Operations S.A.S.Inventors: Laurent Lafont, Stephane Combes, Stephane Levert
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Patent number: 8322651Abstract: A mounting structure for an aircraft engine including a rigid structure and a mechanism to mount the engine on the rigid structure. The mounting mechanism includes a thrust load device including two side thrust links each including an aft end mounted on an evener bar of the device, via a mechanical connection. Each connection is formed by a lug provided on the evener bar and passing through an orifice made in the aft end, the lug being arranged so as to extend substantially laterally relative to the mounting structure.Type: GrantFiled: July 9, 2007Date of Patent: December 4, 2012Assignee: Airbus Operations SASInventors: Stephane Levert, Jacques Beaufort
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Publication number: 20120080555Abstract: The present invention relates to a take-up device for thrust forces (14) for an aircraft engine attachment pylon (4), comprising a first fitting (194) attached to a rigid structure (108) of the attachment pylon, and two lateral connecting rods (14a) for take-up of thrust forces. It also comprises an axis system (190) bearing three first ball joint organs (192a, 196a) arranged along the latter and belonging respectively to a primary ball joint (192) and two secondary ball joints (196) arranged on either side of the primary ball joint, the first fitting (194) integrating a second ball joint organ (192b) cooperating with the first organ (192a) of the primary ball joint (192), and an end of each of the two connecting rods (14a) integrating a second ball joint organ (196b) cooperating respectively with the first organs (196a) of the two secondary ball joints (196).Type: ApplicationFiled: September 22, 2011Publication date: April 5, 2012Applicant: Airbus Operations (S.A.S.)Inventors: Laurent LAFONT, Stéphane COMBES, Stéphane LEVERT
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Patent number: 8087608Abstract: An arrangement configured to connect an evener bar onto a rigid structure of an aircraft engine mount, including a pin system slidingly mounted in a first passageway of a bracket to permit its displacement along a first longitudinal axis, in a first direction from a normal extended position to a retracted position in which the pin system is retracted within this same bracket, and conversely. The arrangement also includes a pin extending member carried by the system and configured to be moved parallel to the longitudinal axis, in a second direction from a normal retracted position to an extended position in which the pin extending member is joined to the system and projects beyond the system, and conversely.Type: GrantFiled: August 31, 2006Date of Patent: January 3, 2012Assignee: Airbus Operations SASInventors: Stéphane Combes, Stéphane Levert, Laurent Lafont, Dominique Moreau
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Patent number: 8042764Abstract: A nut system including a nut including a main thread with pitch p1 and arranged along a screwing axis of the nut. A threaded device is coupled in rotation with the nut, the threaded device including a secondary non-screwed thread on the main thread from which it is separated, the secondary thread being arranged along the screwing axis and having a pitch p2 different from p1. Such a nut system may find application with a device for resistance of thrusts generated by an aircraft engine.Type: GrantFiled: October 10, 2006Date of Patent: October 25, 2011Assignee: Airbus Operations SASInventor: Stephane Levert
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Patent number: 7942580Abstract: A rear suspension (10) for an aircraft engine assembly comprises a structure comprising two three-point shackles (12, 12?) and one two-point shackle (14). One of the hinge pins in waiting on the two-point shackle (14), preferably the hinge pin (26) fixed to the engine yoke joint, is mounted with clearance and with a damping ring acting as a spring to prevent vibrations of the engines as long as the hinge pin (26) is not engaged. Each of the suspension connecting pins (10) is a ball joint connection, the beam (16) of the suspension (10) being provided with five aligned orifices (24, 24a, 28, 24?, 24a?).Type: GrantFiled: December 11, 2006Date of Patent: May 17, 2011Assignee: Airbus FranceInventors: Virginie Audart-Noel, Stephane Levert
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Patent number: 7891604Abstract: An engine attachment pylon for an aircraft including an aft engine attachment fitted with an aft attachment body and a first shear pin capable of resisting forces applied along a transverse direction of the pylon. The first pin passes through a lower spar of a rigid structure of the pylon and includes a lower end housed in the aft attachment body. The lower end includes a reaming through which a first pin passes, that also passes through the aft attachment body.Type: GrantFiled: June 27, 2006Date of Patent: February 22, 2011Assignee: AIRBUS FranceInventors: Stephane Combes, Laurent Lafont, Stephane Levert
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Patent number: 7607609Abstract: A mounting device for an aircraft engine includes a rigid structure and a device for mounting the engine on the rigid structure, the mounting device including a thrust load recovery device with two lateral thrust load recovery rods each having a rear end mounted on a crossbar of the recovery device with a first mechanical connection. At the rear end of each of the two rods, there is also provided a second mechanical connection with play between the rear end and a support fitting integral with the rigid structure. The first mechanical connection is implemented using a pin provided on the crossbar, passing through an orifice provided in the rear end of the rod.Type: GrantFiled: June 27, 2007Date of Patent: October 27, 2009Assignee: Airbus FranceInventor: Stéphane Levert
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Publication number: 20090200419Abstract: A mounting structure for an aircraft engine including a rigid structure and a mechanism to mount the engine on the rigid structure. The mounting mechanism includes a thrust load device including two side thrust links each including an aft end mounted on an evener bar of the device, via a mechanical connection. Each connection is formed by a lug provided on the evener bar and passing through an orifice made in the aft end, the lug being arranged so as to extend substantially laterally relative to the mounting structure.Type: ApplicationFiled: July 9, 2007Publication date: August 13, 2009Applicant: AIRBUS FRANCEInventors: Stéphane Levert, Jacques Beaufort
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Publication number: 20080296430Abstract: An arrangement configured to connect an evener bar onto a rigid structure of an aircraft engine mount, including a pin system slidingly mounted in a first passageway of a bracket to permit its displacement along a first longitudinal axis, in a first direction from a normal extended position to a retracted position in which the pin system is retracted within this same bracket, and conversely. The arrangement also includes a pin extending member carried by the system and configured to be moved parallel to the longitudinal axis, in a second direction from a normal retracted position to an extended position in which the pin extending member is joined to the system and projects beyond the system, and conversely.Type: ApplicationFiled: August 31, 2006Publication date: December 4, 2008Applicant: Airbus FranceInventors: Stéphane Combes, Stephane Levert, Laurent Lafont, Dominique Moreau
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Publication number: 20080232924Abstract: The invention relates to a nut system (100) comprising a nut (104) provided with a main thread (106) with pitch p1 and arranged along a screwing axis (108) of the nut. According to the invention, it also comprises a threaded device (116) coupled in rotation with the nut, this threaded device comprising a secondary non-screwed thread (122) on the main thread (106) from which it is separated, the secondary thread being arranged along the screwing axis and having a pitch p2 different from p1. Application of the invention with a device for resistance of thrusts generated by an aircraft engine.Type: ApplicationFiled: October 10, 2006Publication date: September 25, 2008Applicant: Airbus FranceInventor: Stephane Levert
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Publication number: 20080197233Abstract: An engine attachment pylon for an aircraft including an aft engine attachment fitted with an aft attachment body and a first shear pin capable of resisting forces applied along a transverse direction of the pylon. The first pin passes through a lower spar of a rigid structure of the pylon and includes a lower end housed in the aft attachment body. The lower end includes a reaming through which a first pin passes, that also passes through the aft attachment body.Type: ApplicationFiled: June 27, 2006Publication date: August 21, 2008Applicant: Airbus FranceInventors: Stephane Combes, Laurent Lafont, Stephane Levert
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Publication number: 20080169377Abstract: The present invention relates to a mounting device for an aircraft engine comprising a rigid structure and means for mounting the engine on the rigid structure, the mounting means comprising a thrust load recovery device (14) comprising two lateral thrust load recovery rods (26) each having a rear end (26b) mounted on a crossbar (28) of the device (14), by means of a first mechanical connection (44). At the rear end of each of the two rods, there is also provided a second mechanical connection (46) with play between the rear end (26b) and a support fitting (60) integral with the rigid structure. According to the invention, the first mechanical connection (44) is implemented using a pin (48) provided on the crossbar, passing through an orifice (50) provided in the rear end of the rod (26).Type: ApplicationFiled: June 27, 2007Publication date: July 17, 2008Applicant: Airbus FranceInventor: Stephane Levert
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Publication number: 20070138337Abstract: A rear suspension (10) for an aircraft engine assembly comprises a structure comprising two three-point shackles (12, 12?) and one two-point shackle (14). One of the hinge pins in waiting on the two-point shackle (14), preferably the hinge pin (26) fixed to the engine yoke joint, is mounted with clearance and with a damping ring acting as a spring to prevent vibrations of the engines as long as the hinge pin (26) is not engaged. Each of the suspension connecting pins (10) is a ball joint connection, the beam (16) of the suspension (10) being provided with five aligned orifices (24, 24a, 28, 24?, 24a?).Type: ApplicationFiled: December 11, 2006Publication date: June 21, 2007Applicant: Airbus FranceInventors: Virginie Audart-Noel, Stephane Levert
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Patent number: 6682015Abstract: A device attaches an engine to an aircraft. The device (10) is inserted between the engine (14) and a pylon (12) designed to be attached to an aircraft structure, such as a wing or fuselage section. The attachment device (10) generally includes two brackets (18a, 18b) joined together and secured to the pylon (12) and two pairs of rods (20a, 20b, 22a, 22b) inserted between the two brackets (18a, 18b) and a part (24) of the structure of the engine (14). Thus the integrity of the link between the pylon (12) and the engine (14) is preserved in the event of failure of any of the parts which constitute the device, without there being any need for a backup attachment system.Type: GrantFiled: July 29, 2002Date of Patent: January 27, 2004Assignee: Airbus FranceInventors: Stéphane Levert, Sébastien Roszak
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Patent number: 6648271Abstract: A device for recovering forces generated by an aircraft engine has an engine strut (10), capable of being fixed to a wing or a fuselage of an aircraft, and an attachment device (12) fixed to the engine strut (10) and on which the engine is mounted. An intermediate fitting (24) of large dimensions, capable of recovering exceptionally high forces is fixed to several strut fittings (30) independent from each other, for example by bolts (28), across a lower spar (14) of the engine strut (10).Type: GrantFiled: June 7, 2002Date of Patent: November 18, 2003Assignee: Airbus FranceInventors: Stéphane Levert, Sébastien Roszak
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Publication number: 20030173456Abstract: Device for recovering forces generated by an aircraft engine.Type: ApplicationFiled: June 7, 2002Publication date: September 18, 2003Inventors: Stephane Levert, Sebastien Roszak
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Publication number: 20030025033Abstract: The attachment device (10) is inserted between the engine (14) and a pylon (12) designed to be attached to an aircraft structure, such as a wing or fuselage section. The attachment device (10) generally includes two brackets (18a, 18b) joined together and secured to the pylon (12) and two pairs of rods (20a, 20b, 22a, 22b) inserted between the two brackets (18a, 18b) and a part (24) of the structure of the engine (14). Thus the integrity of the link between the pylon (16) and the engine (14) is preserved in the event of failure of any of the parts which constitute the device, without there being any need for a backup attachment system.Type: ApplicationFiled: July 29, 2002Publication date: February 6, 2003Inventors: Stephane Levert, Sebastien Roszak
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Patent number: 6494403Abstract: Device for aircraft thrust reovery capable of linking a turboshaft engine and an engine strut. A device for thrust recovery (16) linking a turboshaft engine to an aircraft engine strut comprising an attachment fitting (22) fixed to an engine strut, a control bar (38) articulated on the attachment fittings (22) and two coupling rods (24) linking the control bar (38) to the central engine casing, almost along the longitudinal axis of the latter. Links with play are envisaged between each of the coupling rods (24) and the attachment fitting (22), to ensure transmission of thrust forces in the event of rupture of one of the parts of the device. These links with play comprise pivoting axes (48) which intersect the longitudinal axes of the corresponding coupling rods (24).Type: GrantFiled: March 14, 2001Date of Patent: December 17, 2002Assignee: Eads Aribus SAInventors: Pascal Jule, Stéphane Levert
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Patent number: 6398161Abstract: An aircraft propulsion system (10) is connected to a strut, fixed to the wing or fuselage, by a fixing device comprising at least one rear mount (22) and two front mounts (24, 26). The rear mount (22) and a first (24) of the front mounts connect a main part (12a) of the frame (12) of the strut to the central casing (16) of the engine. The other front mount (26) connects a front part (12b) projecting from the strut frame (12) to the fan stator case (20) and mainly takes up the vertical forces (Z). Thus, the first front mount (24) can be simplified and bending or sagging of the engine is reduced.Type: GrantFiled: April 20, 2000Date of Patent: June 4, 2002Assignee: Aerospatiale AirbusInventors: Pascal Jule, Alain Porte, Stéphane Levert