Patents by Inventor Matthieu Fargues

Matthieu Fargues 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).

  • Patent number: 9845707
    Abstract: An aircraft turbojet engine nacelle comprising an air intake assembly of substantially annular shape, the air intake assembly comprising an external wall and an internal wall which are connected to one another upstream by an air intake lip and downstream by an annular rear structure. The annular rear structure comprises, arranged concentrically, one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone, and at least one connecting ring which provides the connection with at least one of the external and internal walls. The annular rear structure thus has increased structural mechanical strength.
    Type: Grant
    Filed: December 18, 2014
    Date of Patent: December 19, 2017
    Assignee: Airbus Operations (SAS)
    Inventors: Alain Porte, Matthieu Fargues
  • Patent number: 9567905
    Abstract: An aircraft nacelle comprising a first duct secured to an air intake and a second duct secured to a powerplant, the first duct comprising an exterior surface and an end portion connected to the second duct. The nacelle includes a hollow section piece in contact with the exterior surface of the first duct which extends over at least part of the circumference of that end portion of the first duct that is connected to the second duct.
    Type: Grant
    Filed: November 21, 2013
    Date of Patent: February 14, 2017
    Assignee: Airbus Operations (SAS)
    Inventors: Alain Porte, Matthieu Fargues, Martial Marro
  • Patent number: 9139306
    Abstract: An aircraft nacelle with a connecting device between a first conduit of an air intake and a second conduit of a motor, both conduits being arranged end-to-end, the connecting device including an annular flange connected to the air intake, an annular flange connected to the motor pressed against annular flange of the air intake, the flanges extending in a plane perpendicular to the longitudinal axis of the nacelle; bolt holes formed in annular flanges and disposed plumb to one another; and connecting elements located in bolt holes, for connecting the annular flanges, wherein at least one flange includes at least one opening interposed between a bolt hole and junction zone of the flange and/or between a bolt hole and outer edge of the flange.
    Type: Grant
    Filed: August 3, 2012
    Date of Patent: September 22, 2015
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Alain Porte, Stéphane Dida, Matthieu Fargues, Martial Marro, Emeric Chancerelle
  • Patent number: 9102413
    Abstract: A fastening device includes a first annular flange connected to an air intake, a second annular flange connected to a powerplant pressed against the second annular flange and fastening elements that allow the annular flanges to be linked. For at least a first fastening element, a blade is fitted between the first fastening element and the first annular flange, the blade including at least a central part linked to the first fastening element, radially mobile relative to the first annular flange, and at least one offset part for which at least radial centripetal displacement is limited relative to the first annular flange, the central part and the offset part being offset relative to one another along the direction of the circumference.
    Type: Grant
    Filed: August 3, 2012
    Date of Patent: August 11, 2015
    Assignee: AIRBUS OPERATIONS SAS
    Inventors: Alain Porte, Stephane Dida, Matthieu Fargues, Martial Marro
  • Publication number: 20150191239
    Abstract: An aircraft turbojet engine nacelle comprising an air intake assembly of substantially annular shape, the air intake assembly comprising an external wall and an internal wall which are connected to one another upstream by an air intake lip and downstream by an annular rear structure. The annular rear structure comprises, arranged concentrically, one or more monolithic panels forming a first annular zone and comprising one or more hollow casings forming at least a second annular zone, and at least one connecting ring which provides the connection with at least one of the external and internal walls. The annular rear structure thus has increased structural mechanical strength.
    Type: Application
    Filed: December 18, 2014
    Publication date: July 9, 2015
    Inventors: Alain Porte, Matthieu Fargues
  • Patent number: 9067686
    Abstract: An aircraft nacelle includes an outside wall (22), at least one air system with at least one air intake (30), whereby the nacelle is connected by connecting element to a mast that is itself connected to the aircraft, with the connecting element allowing a relative movement between the nacelle and the mast in the longitudinal direction of the nacelle, whereby at the front of the junction zone with the nacelle, the mast includes an aerodynamic surface that is called a fairing (24) that covers and exposes a zone of the outside wall called an overlapping zone (28) based on the position of the nacelle (10) relative to the mast, characterized in that an air intake (30) for an air system is arranged at the overlapping zone (28).
    Type: Grant
    Filed: June 8, 2011
    Date of Patent: June 30, 2015
    Assignee: AIRBUS OPERATIONS (SAS)
    Inventors: Alain Porte, Matthieu Fargues, Thomas Stevens
  • Patent number: 8757546
    Abstract: An aircraft nacelle includes an air intake (12) followed at the upper part by a part (14) integral with the mast, called a cap, and at least one door (16) with a curved profile, and a device for encircling it in the form of at least one flexible element (38), guide elements (40) for allowing the at least one flexible element (38) to follow the curved profile of the at least one door, a first anchoring point (42) of the at least one flexible element (38) integral with a first edge (78) of the cap and another anchoring point of the at least one flexible element (38) integral with a second edge (80) of the cap, whereby the anchoring points (42) allow a relative translational movement, in a direction that is parallel to the longitudinal axis of the nacelle, between the cap (14) and the at least one door (16).
    Type: Grant
    Filed: July 15, 2009
    Date of Patent: June 24, 2014
    Assignee: Airbus Operations S.A.S.
    Inventors: Alain Porte, Robert Andre, Matthieu Fargues
  • Publication number: 20140144519
    Abstract: An aircraft nacelle comprising a first duct secured to an air intake and a second duct secured to a powerplant, the first duct comprising an exterior surface and an end portion connected to the second duct. The nacelle includes a hollow section piece in contact with the exterior surface of the first duct which extends over at least part of the circumference of that end portion of the first duct that is connected to the second duct.
    Type: Application
    Filed: November 21, 2013
    Publication date: May 29, 2014
    Inventors: Alain Porte, Matthieu Fargues, Martial Marro
  • Patent number: 8646723
    Abstract: An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake.
    Type: Grant
    Filed: September 17, 2009
    Date of Patent: February 11, 2014
    Assignee: Airbus Operations SAS
    Inventors: Alain Porte, Matthieu Fargues, Jacques Lalane
  • Patent number: 8439298
    Abstract: An aircraft nacelle includes an air intake followed at the upper part by a part that is integral with the mast, called a cap, and at least one door with a curved profile that includes a stiffening device arranged at the edge upstream from the door and which includes: a flexible element that follows the curved profile of the door between two remote anchoring points, at least one safety index including a latch pivotable around an axis of rotation, and connected to the door so as to occupy a locked position in which the end of the latch rests against the inside surface of an edge upstream from the door, and an unlocked position in which the end of the latch is offset relative to the edge, whereby in the locked position, the latch prevents the scooping phenomena by limiting movements of the door in the radial direction toward the outside of the nacelle, and elements for stretching the flexible element between the two anchoring points and for controlling the pivoting in the locked position of the latch.
    Type: Grant
    Filed: July 15, 2009
    Date of Patent: May 14, 2013
    Assignee: Airbus Operations SAS
    Inventors: Alain Porte, Robert Andre, Matthieu Fargues
  • Publication number: 20130033036
    Abstract: A fastening device includes an annular flange connected to an air intake, an annular flange connected to a powerplant pressed against the annular flange and fastening elements that allow the annular flanges to be linked, and for at least a first fastening element, a blade is fitted between the fastening element and the annular flange, the blade consisting of at least a central part linked to the first fastening element, radially mobile relative to the annular flange, and at least one part offset for which at least radial centripetal displacement is limited relative to the annular flange, the two parts being offset along the direction of the circumference.
    Type: Application
    Filed: August 3, 2012
    Publication date: February 7, 2013
    Applicant: AIRBUS OPERATIONS (SAS)
    Inventors: Alain Porte, Stéphane Dida, Matthieu Fargues, Martial Marro
  • Publication number: 20110168839
    Abstract: An aircraft nacelle includes an air intake that makes it possible to channel the air in a pipe in the direction of a pipe of a power plant that is arranged in the extension of the pipe, whereby the pipe of the air intake includes at least one panel that integrates an acoustic treatment with an acoustically resistive porous layer that is in contact with the aerodynamic stream that enters into the nacelle, at least one alveolar structure, and a reflective or impermeable layer that forms the rear surface of the panel, a flange that ensures the connection between the air intake and the power plant including at least one wing that is connected to the air intake by a number of connecting elements, characterized in that some of the connecting elements have axes that are secant with the edge of the panel that delimits the pipe of the air intake.
    Type: Application
    Filed: September 17, 2009
    Publication date: July 14, 2011
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Alain Porte, Matthieu Fargues, Jacques Lalane
  • Publication number: 20110114796
    Abstract: An aircraft nacelle includes an air intake (12) followed at the upper part by a part (14) integral with the mast, called a cap, and at least one door (16) with a curved profile, and a device for encircling it in the form of at least one flexible element (38), guide elements (40) for allowing the at least one flexible element (38) to follow the curved profile of the at least one door, a first anchoring point (42) of the at least one flexible element (38) integral with a first edge (78) of the cap and another anchoring point of the at least one flexible element (38) integral with a second edge (80) of the cap, whereby the anchoring points (42) allow a relative translational movement, in a direction that is parallel to the longitudinal axis of the nacelle, between the cap (14) and the at least one door (16).
    Type: Application
    Filed: July 15, 2009
    Publication date: May 19, 2011
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Alain Porte, Robert Andre, Matthieu Fargues
  • Publication number: 20110116916
    Abstract: An aircraft nacelle includes an air intake followed at the upper part by a part that is integral with the mast, called a cap, and at least one door with a curved profile that includes a stiffening device arranged at the edge upstream from the door and which includes: a flexible element that follows the curved profile of the door between two remote anchoring points, at least one safety index including a latch pivotable around an axis of rotation, and connected to the door so as to occupy a locked position in which the end of the latch rests against the inside surface of an edge upstream from the door, and an unlocked position in which the end of the latch is offset relative to the edge, whereby in the locked position, the latch prevents the scooping phenomena by limiting movements of the door in the radial direction toward the outside of the nacelle, and elements for stretching the flexible element between the two anchoring points and for controlling the pivoting in the locked position of the latch.
    Type: Application
    Filed: July 15, 2009
    Publication date: May 19, 2011
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Alain Porte, Robert Andre, Matthieu Fargues