Patents by Inventor Daniel Bellet
Daniel Bellet 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: 11691717Abstract: A module includes two main landing gears and a landing gear bay containing the landing gears. The bay has two lateral walls, a roof wall, a front wall and a rear wall. The roof wall, the front wall and the rear wall together form a pressurization barrier between the bay and a pressurized compartment. By virtue of the landing gear module, it is now possible to assemble and test the main landing gears and the one or more doors and the fairing before they are installed on the aircraft.Type: GrantFiled: October 20, 2021Date of Patent: July 4, 2023Assignee: Airbus Operations (S.A.S.)Inventors: Daniel Bellet, Alexandre Legardez
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Publication number: 20220126985Abstract: A module includes two main landing gears and a landing gear bay containing the landing gears. The bay has two lateral walls, a roof wall, a front wall and a rear wall. The roof wall, the front wall and the rear wall together form a pressurization barrier between the bay and a pressurized compartment. By virtue of the landing gear module, it is now possible to assemble and test the main landing gears and the one or more doors and the fairing before they are installed on the aircraft.Type: ApplicationFiled: October 20, 2021Publication date: April 28, 2022Applicant: Airbus Operations (S.A.S.)Inventors: Daniel Bellet, Alexandre Legardez
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Patent number: 10847502Abstract: Some embodiments are directed to an optoelectronic device for converting an electrical signal into electromagnetic radiation or vice-versa, including an active zone sandwiched between first and second electrodes, the optoelectronic device having a stack of layers with a lateral edge and first and second opposite faces, the layers of the stack forming at least the active zone and the first and second electrodes, the stack being intended to receive or emit the electromagnetic radiation through the lateral edge perpendicularly to the direction of stacking of the layers.Type: GrantFiled: July 21, 2017Date of Patent: November 24, 2020Assignees: CENTRE NATIONAL DE LA RECHERCHE SCIENTIFIQUE, INSTITUT POLYTECHNIQUE DE GRENOBLEInventors: David Munoz Rojas, Maria del Carmen Jimenez Arevalo, Daniel Bellet, Stéphane Brochen
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Patent number: 10427773Abstract: In order to allow an aircraft fuselage structure to provide optimum resistance to pressurization loads in a fuselage region with a double curvature, the fuselage structure includes a circumferential frame oriented so that the web of the circumferential frame has an orientation close to the local normal to the skin of the fuselage.Type: GrantFiled: November 16, 2016Date of Patent: October 1, 2019Assignee: Airbus Operations (S.A.S.)Inventors: Daniel Bellet, Philippe Bernadet
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Publication number: 20190259740Abstract: Some embodiments are directed to an optoelectronic device for converting an electrical signal into electromagnetic radiation or vice-versa, including an active zone sandwiched between first and second electrodes, the optoelectronic device having a stack of layers with a lateral edge and first and second opposite faces, the layers of the stack forming at least the active zone and the first and second electrodes, the stack being intended to receive or emit the electromagnetic radiation through the lateral edge perpendicularly to the direction of stacking of the layers.Type: ApplicationFiled: July 21, 2017Publication date: August 22, 2019Inventors: David MUNOZ ROJAS, Maria del Carmen JIMENEZ AREVALO, Daniel BELLET, Stéphane BROCHEN
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Patent number: 10343768Abstract: An aircraft landing gear well roof including a first reinforced main structure and a second reinforced main structure spaced from each other in a transverse direction of the roof and equipped with respective mounting for articulating a structural element of the first landing gear and mounting for articulating a structural element of the second landing gear. A membrane connecting the first reinforced main structure and the second reinforced main structure is disposed between them in the transverse direction.Type: GrantFiled: December 17, 2015Date of Patent: July 9, 2019Assignee: Airbus Operations (S.A.S.)Inventors: Daniel Bellet, Guillaume Gallant, François Loyant, Alexandre Legardez, Simon Roux
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Publication number: 20190112035Abstract: An aircraft landing gear bay roof, the roof forming a pressurization barrier between a pressurized upper compartment and a landing gear bay for the housing of a landing gear, comprising a roof wall forming the pressurization barrier. The roof wall is held by longitudinal gantries to which it is linked, and which extend over the entire length of the roof wall. The roof wall comprises a lower face configured to be installed inside the landing gear bay and an upper face configured to be installed outside the landing gear bay. At least one of the gantries is installed against the lower face of the roof wall.Type: ApplicationFiled: October 16, 2018Publication date: April 18, 2019Inventors: Daniel BELLET, Francois LOYANT, Alexandra LEGARDEZ, Simon ROUX, Sebastien CROUZET, Laurent DUBREUIL, Alain PRUDENT
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Publication number: 20190112034Abstract: An aircraft landing gear bay roof for forming a pressurization barrier between an upper pressurized compartment and a landing gear bay for the housing of a landing gear. The roof comprises a main bulkhead extending in a longitudinal direction, an inclined forward bulkhead, rigidly connected to a forward edge of the main wall, and an inclined aft bulkhead, rigidly connected to an aft edge of the main bulkhead. The forward bulkhead and the aft bulkhead each form an obtuse angle with the main bulkhead. This configuration enables a better absorption of loads by the landing gear bay roof and a shorter and optimized path for transmission of the mechanical loads, in particular to the fuselage member to which the aft bulkhead is configured to be connected.Type: ApplicationFiled: October 16, 2018Publication date: April 18, 2019Inventors: Daniel BELLET, Francois LOYANT, Alexandre LEGARDEZ, Simon ROUX, Sebastien CROUZET, Laurent DUBREUIL, Alain PRUDENT
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Publication number: 20180162514Abstract: An aircraft comprising at least one power plant linked to an airfoil by a power plant support structure comprising a primary structure housed in an aerodynamic fairing. The power plant is formed overhanging behind the airfoil, mostly or wholly above the upper surface of the airfoil. The aircraft comprises a main landing gear comprising at least one landing gear element linked to the airfoil of the aircraft by a support structure. The primary structure and the support structure of the landing gear element are formed by a common structure. The use of such a common structure allows a general optimization of the architecture of the aircraft by virtue of the synergies between the positioning of the power plant, the primary structure of its strut, and the support structure of the main landing gear.Type: ApplicationFiled: December 13, 2017Publication date: June 14, 2018Inventors: Daniel BELLET, Guillaume GALLANT
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Publication number: 20170137106Abstract: In order to allow an aircraft fuselage structure to provide optimum resistance to pressurization loads in a fuselage region with a double curvature, the fuselage structure includes a circumferential frame oriented so that the web of the circumferential frame has an orientation close to the local normal to the skin of the fuselage.Type: ApplicationFiled: November 16, 2016Publication date: May 18, 2017Inventors: Daniel BELLET, Philippe BERNADET
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Publication number: 20160185451Abstract: An aircraft landing gear well roof including a first reinforced main structure and a second reinforced main structure spaced from each other in a transverse direction of the roof and equipped with respective mounting for articulating a structural element of the first landing gear and mounting for articulating a structural element of the second landing bear. A membrane connecting the first reinforced main structure and the second reinforced main structure is disposed between them in the transverse direction.Type: ApplicationFiled: December 17, 2015Publication date: June 30, 2016Inventors: Daniel BELLET, Guillaume GALLANT, François LOYANT, Alexandre LEGARDEZ, Simon ROUX
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Patent number: 9272776Abstract: A device for intermediate fastening between an aircraft fuselage and an aircraft landing gear is provided. The device includes at least one semi-open support structure comprising a pair of webs, which are substantially parallel to each other. The webs comprise first support means intended to receive the main pivot shaft of the landing gear and second support means intended to receive the stay joint or joints of the landing gear. The device includes two support structures linked together by a central box structure. The central box structure includes a front wall, a rear wall and linking walls linking those two walls.Type: GrantFiled: December 2, 2013Date of Patent: March 1, 2016Assignee: AIRBUS OPERATIONS S.A.SInventors: Daniel Bellet, Guillaume Gallant
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Patent number: 9108714Abstract: An assembly of longitudinal structural stiffeners for an aircraft including, in a front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, and a fuselage portion extending in alignment with the airplane nose up to the base of the windscreen. The stiffeners include a bending-resistance main plane and are arranged under the flap and connected to the fuselage along a force transfer line. For one or more of the stiffeners, the bending resistance main plane substantially coincides, at at least a certain number of points of the fuselage force transfer line, with the plane predetermined by the local normal to the fuselage surface and the longitudinal axis of the airplane. A method is also provided for calculating the shape of the stiffeners.Type: GrantFiled: March 15, 2010Date of Patent: August 18, 2015Assignee: AIRBUS OPERATIONS S.A.S.Inventors: Patrick Lieven, Eric Chavonet, Daniel Bellet
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Publication number: 20140151500Abstract: A device for intermediate fastening between an aircraft fuselage and an aircraft landing gear is provided. The device includes at least one semi-open support structure comprising a pair of webs, which are substantially parallel to each other. The webs comprise first support means intended to receive the main pivot shaft of the landing gear and second support means intended to receive the stay joint or joints of the landing gear. The device includes two support structures linked together by a central box structure. The central box structure includes a front wall, a rear wall and linking walls linking those two walls.Type: ApplicationFiled: December 2, 2013Publication date: June 5, 2014Applicant: Airbus Operations S.A.S.Inventors: Daniel Bellet, Guillaume Gallant
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Patent number: 8550401Abstract: A floor section for a vehicle cabin includes juxtaposed profiled elements of identical cross section. Each profiled element includes a mainly planar elongated cross member and a generally flat elongated panel. The cross member includes a lower stiffener, is positioned in a transverse vertical plane, and is attachable at two extremities to a vehicle frame. The elongated panel is positioned in a horizontal plane and includes an overlap region along one longitudinal edge and a bearing region along another longitudinal edge. The overlap region and the bearing region are of similar width and of total thickness less than or equal to a mean panel thickness. The panel is perpendicular to the cross member, and a bearing region underside is coplanar with a lower face of the elongated panel and is secured to the cross member at two or more points substantially in line with a middle of the bearing region.Type: GrantFiled: December 8, 2009Date of Patent: October 8, 2013Assignee: Airbus Operations S.A.S.Inventors: Patrick Lieven, Daniel Bellet
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Publication number: 20120132747Abstract: An assembly of longitudinal structural stiffeners for an aircraft including, in a front portion of the fuselage, a windscreen that is slightly recessed relative to the airplane nose, and a fuselage portion extending in alignment with the airplane nose up to the base of the windscreen. The stiffeners include a bending-resistance main plane and are arranged under the flap and connected to the fuselage along a force transfer line. For one or more of the stiffeners, the bending resistance main plane substantially coincides, at least a certain number of points of the fuselage force transfer line, with the plane predetermined by the local normal to the fuselage surface and the longitudinal axis of the airplane. A method is also provided for calculating the shape of the stiffeners.Type: ApplicationFiled: March 15, 2010Publication date: May 31, 2012Applicant: AIRBUS OPERATIONS (S.A.S)Inventors: Patrick Lieven, Eric Chavonet, Daniel Bellet
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Publication number: 20110278396Abstract: The floor section for a vehicle cabin consists of a juxtaposition of profiled elements (9) of identical cross section. Each profiled element comprises: a mainly planar elongated cross member (10), positioned in a transverse vertical plane, this cross member (10) being designed to be attached at its two extremities to a frame (3) of the shell structure (1) of the vehicle. a generally flat elongated panel (11), positioned in a horizontal plane and comprising a region of overlap (15) along one of its longitudinal edges and a bearing region (16) along the other longitudinal edge. The region of overlap (15) and the bearing region (16) are of similar width and of total thickness less than or equal to the mean thickness of the panel (11). The panel (11) is perpendicular to the cross member (10), secured on one face, known as the underside, at least two points to the cross member (10) substantially in line with the middle of the bearing region (16).Type: ApplicationFiled: December 8, 2009Publication date: November 17, 2011Applicant: Airbus Operations (inc as a Societe par Act Simpl)Inventors: Patrick Lieven, Daniel Bellet
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Patent number: 7677498Abstract: A radome system for fastening an aircraft radome, wherein the system includes a plurality of first fasteners each designed to put the radome into a position along two distinct axes contained in a plane approximately perpendicular to the longitudinal axis (L) of this fastener; and a plurality of second fasteners each designed to put the radome into a position along a single axis of a plane approximately perpendicular to the longitudinal axis (L) of this fastener.Type: GrantFiled: June 21, 2005Date of Patent: March 16, 2010Assignee: Airbus FranceInventors: Charlotte Jeanneau, Jean-Claude Roques, Rolland Gilabert, Daniel Bellet, Emmanuel Front, Henri Rigal
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Publication number: 20070045467Abstract: The invention relates to a device for fastening an aircraft radome (2) which comprises: a plurality of first fasteners (10) each designed to put said radome into a position along two distinct axes contained in a plane approximately perpendicular to the longitudinal axis (L) of this fastener; and a plurality of second fasteners (12) each designed to put said radome into a position along a single axis of a plane approximately perpendicular to the longitudinal axis (L) of this fastener. The invention also relates to an aircraft comprising a nose radome fixed to the aircraft using such a device, and an assembly method for assembling a radome (2) on an aircraft fuselage (1).Type: ApplicationFiled: June 21, 2005Publication date: March 1, 2007Applicant: Airbus FranceInventors: Charlotte Jeanneau, Jean-Claude Roques, Rolland Gilabert, Daniel Bellet, Emmanuel Front, Henri Rigal