Patents by Inventor Mathieu BONNET
Mathieu BONNET 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: 11987365Abstract: A device for attaching an object to an attachment rail, particularly a seat rail, in an aircraft or spacecraft. A base part has a support surface to be placed onto an outer surface of the rail, and a locking element to partially protrude from the support surface along a line of protrusion. The base part and locking element are coupled or configured to be coupled wherein the locking element can be moved relative to the base part along the line of protrusion and rotated with respect to the base part. An end section of the locking element has a tip portion shaped in a dovetail-type manner. The device includes a tensioning arrangement for tensioning the locking element with respect to the rail. An arrangement includes such a device as well as an attachment rail with a rail main body and a plurality of bushes. A method for attaching an object, and a seat rail are disclosed.Type: GrantFiled: May 19, 2022Date of Patent: May 21, 2024Assignee: Airbus Operations GmbHInventors: Torsten Noebel, Andreas Dresel, Mathieu Bonnet
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Publication number: 20220380017Abstract: A device for attaching an object to an attachment rail, particularly a seat rail, in an aircraft or spacecraft. A base part has a support surface to be placed onto an outer surface of the rail, and a locking element to partially protrude from the support surface along a line of protrusion. The base part and locking element are coupled or configured to be coupled wherein the locking element can be moved relative to the base part along the line of protrusion and rotated with respect to the base part. An end section of the locking element has a tip portion shaped in a dovetail-type manner. The device includes a tensioning arrangement for tensioning the locking element with respect to the rail. An arrangement includes such a device as well as an attachment rail with a rail main body and a plurality of bushes. A method for attaching an object, and a seat rail are disclosed.Type: ApplicationFiled: May 19, 2022Publication date: December 1, 2022Inventors: Torsten NOEBEL, Andreas DRESEL, Mathieu BONNET
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Patent number: 9086113Abstract: A link device for safety linking of a first member to a second member includes a first element, a second element, and a fluidic vibration transfer mechanism. The first element includes a first link end adapted to be directly linked to the first member, and a second link end adapted to be directly linked to the second member. The second element has a first link end adapted to be directly linked to the first member, and a second link end adapted to be directly linked to the second member. The fluidic vibration transfer mechanism links the first and second elements of the link device to one another, and includes at least two pressure chambers filled with a pressurized liquid, separated by at least one piston integral with the first or second element.Type: GrantFiled: October 10, 2011Date of Patent: July 21, 2015Assignee: AIRBUS Operations S.A.S.Inventors: Mathieu Bonnet, Benoit Valery
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Patent number: 8973885Abstract: A structural rod has a primary rod that has an axial cavity and a secondary rod inside the axial cavity so that the secondary rod is able to move inside the axial cavity along the direction of the longitudinal axis of the rod. The primary rod has a bearing for fastening the structural rod at the first end in a rigid manner and is not fastened rigidly to the structure at the second end. Conversely, the secondary rod has a bearing for fastening the structural rod at the second end in a rigid manner and is not fastened rigidly to the structure at the first end. The primary and secondary rods are joined through one or more intermediate linkage elements made of a deformable and elastic material.Type: GrantFiled: October 29, 2010Date of Patent: March 10, 2015Assignee: Airbus Operations SASInventors: Mathieu Bonnet, Frederic Journade, Laurent Lafont, Benoit Valery
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Patent number: 8960598Abstract: The invention relates to a system for attaching an element (3) capable of vibrating onto an aircraft structure (2), comprising at least one pair of scoops (10) attached onto the element capable of vibrating, as well as onto the structure, each scoop (10a, 10b) of the pair of scoops comprising: an outer rigid element (12) attached onto the structure; an inner rigid element (13) mounted inside the outer rigid element and rigidly connected to the element capable of vibrating; and a flexible element (14) placed along each outer rigid element flank, between the outer rigid element and the inner rigid element.Type: GrantFiled: July 1, 2010Date of Patent: February 24, 2015Assignee: Airbus Operations S.A.S.Inventor: Mathieu Bonnet
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Patent number: 8757579Abstract: An assembly for connecting a first body to a second body includes a first element having a connection end to the first body and a first tubular portion, and a second element having a connection end to the second body and a second tubular portion extending along the longitudinal axis. The first tubular portion and the second tubular portion are interlocked by at least one complementary tubular portion nested in the first tubular portion and around the second tubular portion. A rigid piece connects the first body to the second body and is fastened to the first and second bodies. One of the first and second bodies is connected with functional play at one of the two attachment points of the rigid connecting piece, wherein the rigid connecting piece is formed of two flat rigid pieces extending on both sides of the first and second elements along the longitudinal axis.Type: GrantFiled: July 18, 2011Date of Patent: June 24, 2014Assignee: AIRBUS Operations S.A.S.Inventors: Mathieu Bonnet, Benoit Valery
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Patent number: 8646724Abstract: An attaching system for attaching two components together, such as an aircraft engine and a mounting pylon, includes front trunnions and rear trunnions for supporting the aircraft engine. In this attaching system, at least two of the front or rear trunnions are vibration damping type trunnions that include a suspension assembly with an elastic element and resonant mass. The suspension assembly is shaped as a bent arm carrying the resonant mass on a free end and associated with the elastic element on another end. The vibration damping type trunnions also include a shackle attached between the engine and the suspension assembly so that the vibration damping type trunnions minimize any vibrations and efforts that would otherwise be applied to aircraft structure via the pylon.Type: GrantFiled: December 2, 2009Date of Patent: February 11, 2014Assignee: Airbus Operations (SAS)Inventors: Mathieu Bonnet, Eric Renaud
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Patent number: 8480025Abstract: A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.Type: GrantFiled: March 29, 2010Date of Patent: July 9, 2013Assignee: Airbus Operations S.A.S.Inventors: Laurent Lafont, Jean-Michel Saucray, Esteban Quiroz-Hernandez, Jerome Antypas, Mathieu Bonnet, Frederic Journade
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Publication number: 20120211597Abstract: The invention relates to a system for attaching an element (3) capable of vibrating onto an aircraft structure (2), comprising at least one pair of scoops (10) attached onto the element capable of vibrating, as well as onto the structure, each scoop (10a, 10b) of the pair of scoops comprising: an outer rigid element (12) attached onto the structure; an inner rigid element (13) mounted inside the outer rigid element and rigidly connected to the element capable of vibrating; and a flexible element (14) placed along each outer rigid element flank, between the outer rigid element and the inner rigid element.Type: ApplicationFiled: July 1, 2010Publication date: August 23, 2012Applicant: AIRBUS OPERATIONS (S.A.S.)Inventor: Mathieu Bonnet
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Publication number: 20120132493Abstract: The present invention relates to a device for safety linking of a first member (4) to a second member (5). The first (38) and second (30) tubular portions are in communication via a gas-filled vibration-transferring means (26), at least below a specified force threshold. It is provided with at least two pressure chambers (27, 28) filled with a pressurized liquid. The two pressure chambers (27, 28) are integral with the one between the said first tubular portion (38) and the said second tubular portion (30). The two pressure chambers (27, 28) are separated by at least one piston (29) integral with the other (30) between the said first tubular portion (38) and the said second tubular portion (30). Use, in particular for fixing a turbojet engine to an attachment pylon of an aircraft.Type: ApplicationFiled: October 10, 2011Publication date: May 31, 2012Applicant: Airbus Operations (S.A.S.)Inventors: Mathieu BONNET, Benoit Valery
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Publication number: 20120018576Abstract: A device (2) for connecting a first body to a second body comprises: a first element (20) having a connection end (21) adapted for being connected to the first body and comprising a first tubular portion (22) extending along a longitudinal axis (X); and a second element (30) having a connection end (31) adapted for being connected to the second body and comprising a second tubular portion (32) extending along the longitudinal axis (X), in the first tubular portion (22) of the first element (20). The first tubular portion (22) and the second tubular portion (32) are interlocked by at least one complementary tubular portion (41, 42, 43) extending along the longitudinal axis (X), in the first tubular portion (22) and around the second tubular portion (32). Each of the tubular portions has, in a section crosswise to the said longitudinal axis (X), a surface (S) of identical value. Use in particular in an aircraft engine assembly.Type: ApplicationFiled: July 18, 2011Publication date: January 26, 2012Applicant: Airbus Operations (S.A.S.)Inventors: Mathieu BONNET, Benoit Valery
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Publication number: 20120006937Abstract: A rear part of an aircraft including two connecting rods positioned symmetrically on either side of a median vertical plane, wherein each connecting rod has an end mounted on a support structure of the engines and another end mounted on the fuselage, wherein this part is configured to allow, by rotation of the connecting rods around their axes of rotation, an oscillating movement of limited amplitude of the assembly formed by the support structure and the engines, relative to the fuselage, through the first and second fuselage openings.Type: ApplicationFiled: March 29, 2010Publication date: January 12, 2012Applicant: AIRBUS OPERATIONS (INC AS A SOCIETE PAR ACT SIMPL)Inventors: Laurent Lafont, Jean-Michel Saucray, Esteban Quiroz-Hernandez, Jerome Antypas, Mathieu Bonnet, Frederic Journade
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Publication number: 20110296676Abstract: The invention relates to a system for attaching two components together, such as an aircraft engine and the mounting pylon thereof. According to the invention, at least two of the front (10) or rear (11) trunnions of the attaching system are vibration damping and each includes a suspension assembly (12) with an elastic element (14) and resonant mass (15).Type: ApplicationFiled: December 2, 2009Publication date: December 8, 2011Applicant: AIRBUS OPERATIONS (S.A.S.)Inventors: Mathieu Bonnet, Eric Renaud
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Publication number: 20110210229Abstract: A structural rod has a primary rod that has an axial cavity and a secondary rod inside the axial cavity so that the secondary rod is able to move inside the axial cavity along the direction of the longitudinal axis of the rod. The primary rod has a bearing for fastening the structural rod at the first end in a rigid manner and is not fastened rigidly to the structure at the second end. Conversely, the secondary rod has a bearing for fastening the structural rod at the second end in a rigid manner and is not fastened rigidly to the structure at the first end. The primary and secondary rods are joined through one or more intermediate linkage elements made of a deformable and elastic material.Type: ApplicationFiled: October 29, 2010Publication date: September 1, 2011Applicant: AIRBUS OPERATIONS (S.A.S)Inventors: Mathieu BONNET, Frederic JOURNADE, Laurent LAFONT, Benoit VALERY