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).

  • Patent number: 10427773
    Abstract: 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: Grant
    Filed: November 16, 2016
    Date of Patent: October 1, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Daniel Bellet, Philippe Bernadet
  • Publication number: 20190259740
    Abstract: 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: Application
    Filed: July 21, 2017
    Publication date: August 22, 2019
    Inventors: David MUNOZ ROJAS, Maria del Carmen JIMENEZ AREVALO, Daniel BELLET, Stéphane BROCHEN
  • Patent number: 10343768
    Abstract: 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: Grant
    Filed: December 17, 2015
    Date of Patent: July 9, 2019
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Daniel Bellet, Guillaume Gallant, François Loyant, Alexandre Legardez, Simon Roux
  • Publication number: 20190112034
    Abstract: 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: Application
    Filed: October 16, 2018
    Publication date: April 18, 2019
    Inventors: Daniel BELLET, Francois LOYANT, Alexandre LEGARDEZ, Simon ROUX, Sebastien CROUZET, Laurent DUBREUIL, Alain PRUDENT
  • Publication number: 20190112035
    Abstract: 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: Application
    Filed: October 16, 2018
    Publication date: April 18, 2019
    Inventors: Daniel BELLET, Francois LOYANT, Alexandra LEGARDEZ, Simon ROUX, Sebastien CROUZET, Laurent DUBREUIL, Alain PRUDENT
  • Publication number: 20180162514
    Abstract: 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: Application
    Filed: December 13, 2017
    Publication date: June 14, 2018
    Inventors: Daniel BELLET, Guillaume GALLANT
  • Publication number: 20170137106
    Abstract: 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: Application
    Filed: November 16, 2016
    Publication date: May 18, 2017
    Inventors: Daniel BELLET, Philippe BERNADET
  • Publication number: 20160185451
    Abstract: 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: Application
    Filed: December 17, 2015
    Publication date: June 30, 2016
    Inventors: Daniel BELLET, Guillaume GALLANT, François LOYANT, Alexandre LEGARDEZ, Simon ROUX
  • Patent number: 9272776
    Abstract: 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: Grant
    Filed: December 2, 2013
    Date of Patent: March 1, 2016
    Assignee: AIRBUS OPERATIONS S.A.S
    Inventors: Daniel Bellet, Guillaume Gallant
  • Patent number: 9108714
    Abstract: 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: Grant
    Filed: March 15, 2010
    Date of Patent: August 18, 2015
    Assignee: AIRBUS OPERATIONS S.A.S.
    Inventors: Patrick Lieven, Eric Chavonet, Daniel Bellet
  • Publication number: 20140151500
    Abstract: 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: Application
    Filed: December 2, 2013
    Publication date: June 5, 2014
    Applicant: Airbus Operations S.A.S.
    Inventors: Daniel Bellet, Guillaume Gallant
  • Patent number: 8550401
    Abstract: 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: Grant
    Filed: December 8, 2009
    Date of Patent: October 8, 2013
    Assignee: Airbus Operations S.A.S.
    Inventors: Patrick Lieven, Daniel Bellet
  • Publication number: 20120132747
    Abstract: 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: Application
    Filed: March 15, 2010
    Publication date: May 31, 2012
    Applicant: AIRBUS OPERATIONS (S.A.S)
    Inventors: Patrick Lieven, Eric Chavonet, Daniel Bellet
  • Publication number: 20110278396
    Abstract: 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: Application
    Filed: December 8, 2009
    Publication date: November 17, 2011
    Applicant: Airbus Operations (inc as a Societe par Act Simpl)
    Inventors: Patrick Lieven, Daniel Bellet
  • Patent number: 7677498
    Abstract: 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: Grant
    Filed: June 21, 2005
    Date of Patent: March 16, 2010
    Assignee: Airbus France
    Inventors: Charlotte Jeanneau, Jean-Claude Roques, Rolland Gilabert, Daniel Bellet, Emmanuel Front, Henri Rigal
  • Publication number: 20070045467
    Abstract: 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: Application
    Filed: June 21, 2005
    Publication date: March 1, 2007
    Applicant: Airbus France
    Inventors: Charlotte Jeanneau, Jean-Claude Roques, Rolland Gilabert, Daniel Bellet, Emmanuel Front, Henri Rigal