Patents by Inventor Francis Dazet
Francis Dazet 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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Rear door of a landing gear box comprising an air passage orifice and a closure member of the latter
Patent number: 10399671Abstract: A landing gear box of an aircraft comprising a front door with independent opening and a rear door with opening mechanically connected to the landing gear, including an orifice in the rear door provided with a closure member and a drive mechanism allowing movement of this closure member independently of any movement of the rear door.Type: GrantFiled: July 21, 2016Date of Patent: September 3, 2019Assignee: Airbus Operations SASInventor: Francis Dazet -
Patent number: 10046845Abstract: The disclosure herein relates to a part of an aircraft structure including a portion of a floor structure and a portion of a hull structure, connected to one another by a connecting element. In accordance with, the disclosure herein the connecting element includes a flexible cable fixed at one of the ends thereof to the portion of a floor structure and fixed at the other, second of the ends thereof to the portion of a hull structure. When the connection between the portion of a floor structure and the portion of a hull structure is subjected to tensile load, the flexible cable makes it possible to meet the standards of resistance to forward accelerations of the aircraft. When the connection is subjected to compressive load, the flexible cable relaxes and bends, which limits the requirements of withstanding compressive stresses and therefore the weight of the connecting element.Type: GrantFiled: May 29, 2015Date of Patent: August 14, 2018Assignee: Airbus Operations (S.A.S.)Inventors: Francis Dazet, Jérome Antypas, Laurent Bel, Philippe Delorme, Raphaël Brisbart
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Patent number: 9764816Abstract: An aircraft structure part comprising a floor structure, a hull structure, and a connecting element. The connecting element comprises a rod attached, at its first end, to one of the hull and the floor; an attachment element, attached to the other of the hull and the floor, and provided with an opening in which the second end of the rod is slidably mounted; and an endstop attached to the rod so as to engage with the attachment element, to limit the sliding amplitude of the rod in the opening. When the connection between the floor and the hull is loaded in tension, the endstop makes it possible to comply with the standards for withstanding acceleration towards the aircraft front. When the connection is loaded in compression, the rod slides freely in the opening, which limits the constraints of withstanding compressive stresses, reducing the weight of the connecting element.Type: GrantFiled: May 28, 2015Date of Patent: September 19, 2017Assignee: Airbus Operations (SAS)Inventors: Francis Dazet, Jerome Antypas, Laurent Bel, Philippe Delorme, Raphael Brisbart
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Patent number: 9573672Abstract: A device for protecting a front spar structure of a central casing -of an aircraft wing and at least one item of equipment situated in the wing, comprising: a shielding surface extending in front of the front spar of the central casing, from a surface of an intersection between the wing and the fuselage delimited by the root of the wing, transversely to the surface of intersection, to a first rib of the central casing partially surrounding at least one item of equipment; and means -for fixing the shielding surface to the central casing producing an isostatic link.Type: GrantFiled: June 20, 2013Date of Patent: February 21, 2017Assignee: AIRBUS OPERATIONS (SAS)Inventor: Francis Dazet
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REAR DOOR OF A LANDING GEAR BOX COMPRISING AN AIR PASSAGE ORIFICE AND A CLOSURE MEMBER OF THE LATTER
Publication number: 20170021919Abstract: A landing gear box of an aircraft comprising a front door with independent opening and a rear door with opening mechanically connected to the landing gear, including an orifice in the rear door provided with a closure member and a drive mechanism allowing movement of this closure member independently of any movement of the rear door.Type: ApplicationFiled: July 21, 2016Publication date: January 26, 2017Inventor: Francis Dazet -
Publication number: 20160176501Abstract: A device for protecting a front spar structure of a central casing of an aircraft wing and at least one item of equipment situated in the wing, comprising: a shielding surface extending in front of the front spar of the central casing, from a surface of an intersection between the wing and the fuselage delimited by the root of the wing, transversely to the surface of intersection, to a first rib of the central casing partially surrounding at least one item of equipment; and means—for fixing the shielding surface to the central casing producing an isostatic link.Type: ApplicationFiled: June 20, 2013Publication date: June 23, 2016Applicant: AIRBUS OPERATIONS (SAS)Inventor: Francis Dazet
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Publication number: 20150344120Abstract: The disclosure herein relates to a part of an aircraft structure including a portion of a floor structure and a portion of a hull structure, connected to one another by a connecting element. In accordance with, the disclosure herein the connecting element includes a flexible cable fixed at one of the ends thereof to the portion of a floor structure and fixed at the other, second of the ends thereof to the portion of a hull structure. When the connection between the portion of a floor structure and the portion of a hull structure is subjected to tensile load, the flexible cable makes it possible to meet the standards of resistance to forward accelerations of the aircraft. When the connection is subjected to compressive load, the flexible cable relaxes and bends, which limits the requirements of withstanding compressive stresses and therefore the weight of the connecting element.Type: ApplicationFiled: May 29, 2015Publication date: December 3, 2015Inventors: Francis Dazet, Jérome Antypas, Laurent Bel, Philippe Delorme, Raphaël Brisbart
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Publication number: 20150344119Abstract: An aircraft structure part comprising a floor structure, a hull structure, and a connecting element. The connecting element comprises a rod attached, at its first end, to one of the hull and the floor; an attachment element, attached to the other of the hull and the floor, and provided with an opening in which the second end of the rod is slidably mounted; and an endstop attached to the rod so as to engage with the attachment element, to limit the sliding amplitude of the rod in the opening. When the connection between the floor and the hull is loaded in tension, the endstop makes it possible to comply with the standards for withstanding acceleration towards the aircraft front. When the connection is loaded in compression, the rod slides freely in the opening, which limits the constraints of withstanding compressive stresses, reducing the weight of the connecting element.Type: ApplicationFiled: May 28, 2015Publication date: December 3, 2015Inventors: Francis Dazet, Jerome Antypas, Laurent Bel, Philippe Delorme, Raphael Brisbart
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Patent number: 9174721Abstract: An aircraft windshield assembly includes at least one window pane, a frame against which the pane bears, at least one flange for clamping the pane against the frame, and at least one cavity delimited between the pane, the frame and the flange. A member of profiled cross-section substantially fills the cavity and over at least part of its periphery has formations in relief in the form of flutes which with a facing surface define seal-forming baffles.Type: GrantFiled: December 4, 2013Date of Patent: November 3, 2015Assignee: Airbus Operations S.A.S.Inventor: Francis Dazet
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Patent number: 9102106Abstract: In the method of making a sealed junction between elongate aircraft parts that extend locally in main directions that are not mutually parallel, the following steps are performed: assembling a plurality of portions of a mold on the parts; and injecting a sealing material into the mold.Type: GrantFiled: November 30, 2010Date of Patent: August 11, 2015Assignee: Airbus Operations SASInventor: Francis Dazet
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Patent number: 8816916Abstract: The invention relates to a radome (1) for an aircraft, and more specifically to a device for connecting said radome to the structure of said aircraft. The radome that is the subject of the invention comprises a plurality of locking units able to bring together the opposing surfaces of the aircraft's fuselage (10) and the radome (1), each unit comprising: locking means (20) able to exercise a traction force on the surface of the fuselage, substantially normal to the surface, via attachment means; centering means able to withstand the shear forces substantially tangential to the opposing surfaces of the fuselage and radome; the locking means (20) are placed such that they are located inside the cone of resulting forces on the centering means so as to minimize the bending stresses generated by the assembly in the radome (1).Type: GrantFiled: September 10, 2010Date of Patent: August 26, 2014Assignee: Airbus Operations S.A.S.Inventor: Francis Dazet
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Patent number: 8777160Abstract: The aircraft includes a structural portion such as a fuselage, a wing, or a tail, the structural portion including a wall separating the inside from the outside of the portion and including fractions defining between them an inside volume of the portion and at least one structural partition separating zones of the volume, e.g. a front zone and a rear zone, from each other, the partition including at least one flexible diaphragm suitable for deforming and at least two preferably rigid supports supporting the diaphragm in discontinuous manner.Type: GrantFiled: November 30, 2010Date of Patent: July 15, 2014Assignee: Airbus Operations (S.A.S.)Inventor: Francis Dazet
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Publication number: 20140166809Abstract: An aircraft windshield assembly includes at least one window pane, a frame against which the pane bears, at least one flange for clamping the pane against the frame, and at least one cavity delimited between the pane, the frame and the flange. A member of profiled cross-section substantially fills the cavity and over at least part of its periphery has formations in relief in the form of flutes which with a facing surface define seal-forming baffles.Type: ApplicationFiled: December 4, 2013Publication date: June 19, 2014Applicant: AIRBUS OPERATIONS S.A.S.Inventor: Francis Dazet
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Patent number: 8668181Abstract: Devices associated with an interface that is advantageous for the customized attachment of pieces of furniture to the floor of an aircraft. The interface includes rails extending longitudinally in the aircraft cabin, able to receive anchoring devices for connecting the furniture elements to these rails. The anchoring devices include axial and radial claw clamping devices which are associated together in pairs and operated together in pairs by a single and same lever (58, 95).Type: GrantFiled: December 24, 2008Date of Patent: March 11, 2014Assignee: Airbus Operations S.A.S.Inventors: Francis Dazet, Francois Rouyre, Alain Depeige
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Publication number: 20120280083Abstract: In the method of making a sealed junction between elongate aircraft parts that extend locally in main directions that are not mutually parallel, the following steps are performed: assembling a plurality of portions of a mold on the parts; and injecting a sealing material into the mold.Type: ApplicationFiled: November 30, 2010Publication date: November 8, 2012Applicant: AIRBUS OPERATIONS (S.A.S.)Inventor: Francis Dazet
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Publication number: 20120267478Abstract: The aircraft includes a structural portion such as a fuselage, a wing, or a tail, the structural portion including a wall separating the inside from the outside of the portion and including fractions defining between them an inside volume of the portion and at least one structural partition separating zones of the volume, e.g. a front zone and a rear zone, from each other, the partition including at least one flexible diaphragm suitable for deforming and at least two preferably rigid supports supporting the diaphragm in discontinuous manner.Type: ApplicationFiled: November 30, 2010Publication date: October 25, 2012Applicant: AIRBUS OPERATIONS (S.A.S.)Inventor: Francis Dazet
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Publication number: 20120212391Abstract: The invention relates to a radome (1) for an aircraft, and more specifically to a device for connecting said radome to the structure of said aircraft. The radome that is the subject of the invention comprises a plurality of locking units able to bring together the opposing surfaces of the aircraft's fuselage (10) and the radome (1), each unit comprising: locking means (20) able to exercise a traction force on the surface of the fuselage, substantially normal to the surface, via attachment means; centering means able to withstand the shear forces substantially tangential to the opposing surfaces of the fuselage and radome; the locking means (20) are placed such that they are located inside the cone of resulting forces on the centering means so as to minimize the bending stresses generated by the assembly in the radome (1).Type: ApplicationFiled: September 10, 2010Publication date: August 23, 2012Applicant: AIRBUS OPERATIONS (S.A.S)Inventor: Francis Dazet
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Publication number: 20100314495Abstract: Devices associated with an interface that is advantageous for the customized attachment of pieces of furniture to the floor of an aircraft. The interface includes rails extending longitudinally in the aircraft cabin, able to receive anchoring devices for connecting the furniture elements to these rails. The anchoring devices include axial and radial claw clamping devices which are associated together in pairs and operated together in pairs by a single and same lever (58, 95).Type: ApplicationFiled: December 24, 2008Publication date: December 16, 2010Applicant: AIRBUS OPERATIONS (S.A.S.)Inventors: Francis Dazet, Francois Rouyre, Alain Delpeige
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Publication number: 20090123224Abstract: A method for assembling two non-integral elements to form an articulated mechanical joint, a first element including, at the joint, an end piece including two yokes, a second element including, at the joint, a yoke, the method including at least one step for drilling bores in the yokes of each element, and one step for the snug fit assembly of rings or ball joints on inner surfaces of yokes of the two elements. An additional step of shot-peening of the inner surfaces of the bores of the yokes of the two elements is carried out, for each bore, between the step of drilling bores and the step of interference mounting of the ring or of the ball joint.Type: ApplicationFiled: October 10, 2008Publication date: May 14, 2009Applicant: Airbus FranceInventor: Francis Dazet
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Patent number: 7384015Abstract: A shield for a nose of a large aircraft. The shield is float-mounted on a frame of the aircraft in one embodiment. To this end, the shield and the frame are respectively provided with fingers and receptacles that engage with each other. To prevent loosening, peripheral elastic links are distributed on the rim of the shield. Through this approach, it is shown that the shield retains only about one degree of freedom relative to the frame. This degree of freedom is oriented in the direction of the fingers.Type: GrantFiled: December 20, 2004Date of Patent: June 10, 2008Assignee: Airbus France SAInventors: Francis Dazet, Noël Maurens