Patents by Inventor Patrick Lieven

Patrick Lieven 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).

  • Publication number: 20170066077
    Abstract: System for friction stir welding of two parts which includes a welding unit which includes at least one welding head fitted with a rotating pin and a counter-bearing unit which has a support surface to support the parts against a pressure exerted by the welding head, and wherein each welding head can be moved relative to the support surface in a first direction parallel to an axis of rotation of the rotating pin and in a second direction orthogonal to the axis of rotation, and wherein the support surface can be moved in the second direction and is formed of two coaxial clamp rollers which are set apart from each other.
    Type: Application
    Filed: November 18, 2016
    Publication date: March 9, 2017
    Inventors: Christophe MIALHE, Patrick LIEVEN, Romain DELAHAYE
  • Patent number: 9517529
    Abstract: System for friction stir welding of two parts which includes a welding unit which includes at least one welding head fitted with a rotating pin and a counter-bearing unit which has a support surface to support the parts against a pressure exerted by the welding head, and wherein each welding head can be moved relative to the support surface in a first direction parallel to an axis of rotation of the rotating pin and in a second direction orthogonal to the axis of rotation, and wherein the support surface can be moved in the second direction and is formed of two coaxial clamp rollers which are set apart from each other.
    Type: Grant
    Filed: August 30, 2013
    Date of Patent: December 13, 2016
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Christophe Mialhe, Patrick Lieven, Romain Delahaye
  • Patent number: 9446834
    Abstract: Simplification of the manufacture of composite material fuselages for aircraft, as well as mass reduction of fuselage sections and space optimization inside such fuselage sections. To accomplish this, it is proposed to use stringers of a new type which have a closed transverse section, and which are thus able to be self-positioned relative to one another by being positioned edge-to-edge on a stringer supporting structure, such as the outer surface of a mandrel. The installation of the stringers in grooves of conjugate shape is by this means made unnecessary. The stringers have cut-outs located between circumferential frames, and are able to house utility systems.
    Type: Grant
    Filed: December 25, 2013
    Date of Patent: September 20, 2016
    Assignee: AIRBUS OPERATIONS (SAS)
    Inventors: Patrick Lieven, Romain Delahaye
  • Patent number: 9428260
    Abstract: Device intended for a double glazing including at least one outer glazing and one inner glazing separated by an intermediary space filled with a gas, used to isolate an inside environment from an outside environment, a pressure variation being liable to occur between these environments, for example in the case of an aircraft in flight, includes means for conserving the outer glazing and the inner glazing of this double glazing mainly parallel, independently of this pressure variation. The invention also concerns a double glazing including this device, the process for maintaining parallelism and software using the process.
    Type: Grant
    Filed: December 16, 2010
    Date of Patent: August 30, 2016
    Assignee: Airbus Operations S.A.S.
    Inventors: Pascal Chaumel, Patrick Lieven
  • Patent number: 9387826
    Abstract: Wiper blade for a surface of double curvature type, the said wiper blade including a flexible longitudinal wiper and means for exerting a bearing force at at least one point of the said wiper along a direction Z mainly normal to the surface, also including a longitudinal 15 part, attached to the wiper at several points, and means to vary over time and in at least one segment of the longitudinal rod the rigidity in bending of this longitudinal rod in a plane XZ normal to the surface between previously chosen values. The longitudinal part is a metallic blade where the inertias on the two axes of its section are very different.
    Type: Grant
    Filed: December 14, 2010
    Date of Patent: July 12, 2016
    Assignee: Airbus Operations S.A.S.
    Inventors: Patrick Lieven, Pascal Chaumel
  • Patent number: 9377529
    Abstract: A meteorological radar installed on board an aircraft, including a mechanical support fixed to a bulkhead of a nose of the aircraft, wherein an antenna is mounted on the mechanical support to enable turning mobility around an axis of rotation. The antenna includes a pedestal, on which at least one blade, extending radially along the axis of rotation, is installed. A free side of the blade, along which a plurality of radiating elements is distributed, perceptibly has the shape of a portion of conic in a plane including the axis of rotation. Because the blade is mobile only in rotation along the axis of rotation, and the selection of the emission/reception direction is performed electronically, not mechanically, the space and length requirements of the meteorological radar are fixed, whether the meteorological radar is in operation or not, and are determined based on the eccentricity and parameter of the conic.
    Type: Grant
    Filed: April 14, 2014
    Date of Patent: June 28, 2016
    Assignee: Airbus Operations (SAS)
    Inventor: Patrick Lieven
  • Publication number: 20160159457
    Abstract: A rudder bar for an aircraft comprising a floor, a steering connecting rod and a braking connecting rod. The rudder bar comprises a base fixed above the floor, a pedal arm mounted rotatably on the base about a first axis of rotation and having a lower end and an upper end, a pedal mounted rotatably on the lower end about a second axis of rotation, a first transmission assembly configured to transmit a movement to the steering connecting rod when the pedal arm pivots about the first axis of rotation, and a second transmission assembly configured to transmit a movement to the braking connecting rod when the pedal pivots about the second axis of rotation.
    Type: Application
    Filed: December 7, 2015
    Publication date: June 9, 2016
    Inventors: Laurent Saint-Marc, Christophe Mialhe, Patrick Lieven, Romain Delahaye, Marc Audibert, Nicolas Chatrenet
  • Patent number: 9321519
    Abstract: A support plate for the passage of systems between two zones at different pressurizations of an aircraft, in the region of a bulkhead separating the two zones. The support plate comprises a connection plate including at least one retaining element and at least one sealing joint and is provided with a plurality of holes intended for the passage of an assembly of systems which have to pass through said bulkhead.
    Type: Grant
    Filed: May 23, 2014
    Date of Patent: April 26, 2016
    Assignee: Airbus Operations SAS
    Inventors: Marc Tomasi, Patrick Lieven, Romain Delahaye, Matthieu De Kergommeaux
  • Patent number: 9242716
    Abstract: Device intended for a double glazing including at least one outer glazing and one inner glazing separated by an intermediary space filled with a gas, used to isolate an inside environment from an outside environment, a pressure variation being liable to occur between these environments, for example in the case of an aircraft in flight, includes means for conserving the outer glazing and the inner glazing of this double glazing mainly parallel, independently of this pressure variation. The invention also concerns a double glazing including this device, the process for maintaining parallelism and software using the process.
    Type: Grant
    Filed: December 16, 2010
    Date of Patent: January 26, 2016
    Assignee: Airbus Operations S.A.S.
    Inventors: Pascal Chaumel, Patrick Lieven
  • Publication number: 20150367929
    Abstract: The disclosure herein relates to an aircraft fuselage stiffener including a heel, a flange, and a web connecting the heel and the flange, this stiffener comprising a folded sheet extending along the length of the heel, the web and the flange. In addition, to improve the mechanical behaviour of the stiffener, the folded sheet includes on the one hand a main portion extending along the length of the heel, the web and the flange, and on the other hand at least one folded-over portion forming a lining of the main portion over at least part of the web and/or the heel and/or the flange.
    Type: Application
    Filed: June 17, 2015
    Publication date: December 24, 2015
    Inventors: Christophe Mialhe, Patrick Lieven, Philippe Rodrigo
  • Publication number: 20150344123
    Abstract: In order to limit the number of openings in an aircraft fuselage and to reduce the mass thereof, the invention makes provision for an item of aircraft fuselage equipment which is intended to be mounted in an opening of the fuselage, the item of equipment being configured to block/release an access passage which affords access to the inner side of the aircraft and which also comprises a discharge control valve for pressurization air.
    Type: Application
    Filed: May 27, 2015
    Publication date: December 3, 2015
    Inventors: Marc Tomasi, Patrick Lieven, Romain Delahaye, Matthieu De Kergommeaux, Laurent Lache, Didier Poirier
  • Patent number: 9114870
    Abstract: The present invention relates to an aircraft window, of the type including a holding frame for securing the window to the fuselage of an aircraft and at least one pane mounted in the holding frame by a sealing system, the at least one pane having an inner surface and an outer surface, characterized in that: the pane includes, in a first state called the rest state, at least one concavity in its outer surface when there is no pressure difference between the outer surface and the inner surface of the pane, and the at least one concavity of the pane is at least partially eradicated in a second state in which there is a pressure difference between the outer surface and the inner surface of the pane.
    Type: Grant
    Filed: May 17, 2013
    Date of Patent: August 25, 2015
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Pascal Chaumel, Patrick Lieven, Serge Cassagnes
  • 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
  • Patent number: 9090327
    Abstract: An intermediate support structure for the cockpit of an aircraft is provided. The intermediate support structure includes a raised floor and at least one structural element extending as an arch above the raised floor, the arched structure being adapted to hold in position at least one item of equipment in the upper part of the cockpit. The intermediate support structure also includes a fastener for mounting the intermediate support structure onto a fuselage primary structure, where the fuselage primary structure defines a portion of the cockpit of the aircraft.
    Type: Grant
    Filed: July 3, 2012
    Date of Patent: July 28, 2015
    Assignee: AIRBUS OPERATIONS (S.A.S.)
    Inventors: Marc Tomasi, Patrick Lieven, Romain Delahaye
  • Patent number: 9085283
    Abstract: The wiper blade for a surface of the type with a dual curvature, the wiper blade including a flexible blade element and a means of applying a pressing force to at least one point of the blade element in a direction Z mostly normal to the surface, also including means of varying the pressing force over time, at least some of the points, between pre-chosen positive and negative limit values, and means of commanding the pressing force. These means for bringing about local pressure or lift are electromagnetic.
    Type: Grant
    Filed: November 24, 2009
    Date of Patent: July 21, 2015
    Assignee: Airbus Operations S.A.S.
    Inventor: Patrick Lieven
  • Patent number: 8915470
    Abstract: An aircraft nose structure includes a fuselage, a floor for a pressurized space and a nose landing gear bay arranged under the floor, on the opposite side to the space. The bay includes walls that form a pressure barrier, of which there are two lateral panels mechanically secured to the floor by load-reacting members, an upper panel adjacent to the floor and extending between the lateral panels, and a rear panel extending between the upper panel and the fuselage.
    Type: Grant
    Filed: December 11, 2012
    Date of Patent: December 23, 2014
    Assignee: Airbus Operations S.A.S.
    Inventors: Philippe Bernadet, Patrick Lieven, Marc Dugerie, Romain Delahaye
  • Publication number: 20140361924
    Abstract: A meteorological radar installed on board an aircraft, including a mechanical support fixed to a bulkhead of a nose of the aircraft, wherein an antenna is mounted on the mechanical support to enable turning mobility around an axis of rotation. The antenna includes a pedestal, on which at least one blade, extending radially along the axis of rotation, is installed. A free side of the blade, along which a plurality of radiating elements is distributed, perceptibly has the shape of a portion of conic in a plane including the axis of rotation. Because the blade is mobile only in rotation along the axis of rotation, and the selection of the emission/reception direction is performed electronically, not mechanically, the space and length requirements of the meteorological radar are fixed, whether the meteorological radar is in operation or not, and are determined based on the eccentricity and parameter of the conic.
    Type: Application
    Filed: April 14, 2014
    Publication date: December 11, 2014
    Applicant: Airbus Operations (SAS)
    Inventor: Patrick Lieven
  • Patent number: 8905352
    Abstract: An aircraft nose structure includes a fuselage and a pressuretight bulkhead fixed at its periphery to the fuselage and transversely dividing the fuselage into a pressurized upper zone and an unpressurized lower zone for accommodating retractable nose landing gear. The pressuretight bulkhead includes a floor of the pressurized upper zone, and a substantially flat rear panel extending between a rear edge of the floor and the fuselage. The floor and the rear panel are fixed laterally to the fuselage. The fuselage includes an exterior wall and reinforcing transverse frames to which the exterior wall is fixed. In line with the pressuretight bulkhead, at least some of the transverse reinforcing frames extend along the outline of the pressurized upper zone and constitute members that reinforce the pressuretight bulkhead.
    Type: Grant
    Filed: December 11, 2012
    Date of Patent: December 9, 2014
    Assignee: Airbus Operations S.A.S.
    Inventors: Philippe Bernadet, Patrick Lieven, Marc Dugerie, Christophe Mialhe, Romain Delahaye
  • Publication number: 20140346276
    Abstract: A support plate for the passage of systems between two zones at different pressurizations of an aircraft, in the region of a bulkhead separating the two zones. The support plate comprises a connection plate including at least one retaining element and at least one sealing joint and is provided with a plurality of holes intended for the passage of an assembly of systems which have to pass through said bulkhead.
    Type: Application
    Filed: May 23, 2014
    Publication date: November 27, 2014
    Inventors: Marc Tomasi, Patrick Lieven, Romain DELAHAYE, Matthieu De Kergommeaux
  • Patent number: 8894010
    Abstract: An aircraft fuselage frame assembly includes a first lower frame element having a cross member and a curved fuselage tub frame. A second upper frame element of the assembly has a cross member and a curved upper frame segment. A third frame element of the assembly is made of a cross member section, floor strut section and frame section. The third frame element is formed as a single, integral triangle element having a hypotenuse that is curved to adopt a curvature of the aircraft fuselage and joining portions at angle areas of the triangle. A lower frame link is joined to the first upper frame and at a first angle area of the triangle element; an upper frame link is joined to the second upper frame and at a second angle area of the triangle element; and a floor cross member is joined at a third angle area of the triangle element.
    Type: Grant
    Filed: September 7, 2012
    Date of Patent: November 25, 2014
    Assignee: Airbus Operations SAS
    Inventors: Romain Delahaye, Patrick Lieven, Christophe Mialhe