Patents by Inventor Philippe Bernadet

Philippe Bernadet 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: 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
  • Patent number: 9180625
    Abstract: A process for the production of an aircraft panel made of double-curved composite material, with the panel being obtained from a three-dimensional preform that includes fibers that are distributed in a defined arrangement, includes manufacturing a flat fiber preform (22), and deforming the flat preform (22) in such a way as to produce the three-dimensional preform, with the fibers following suitable trajectories at the flat preform in such a way as to obtain the defined arrangement of the fibers after deformation.
    Type: Grant
    Filed: July 11, 2012
    Date of Patent: November 10, 2015
    Assignee: AIRBUS OPERATIONS (SAS)
    Inventors: Philippe Bernadet, Laurent Giuseppin
  • Publication number: 20150147529
    Abstract: In a fuselage portion for an aircraft, in order to reduce the assembly clearance between the soleplate of a circumferential frame and a fuselage skin in composite material while limiting the mass of the fuselage portion, a ply drop-off is used comprising two portions oriented in the circumferential direction and having different respective slopes.
    Type: Application
    Filed: November 20, 2014
    Publication date: May 28, 2015
    Inventors: Philippe Bernadet, Romain Delahaye
  • Publication number: 20150001343
    Abstract: An aircraft fuselage member and a frame are linked by a clip and a spacer. An assembly includes an aircraft fuselage member, having a skin and stringers linked to the skin, a reinforcing frame, and a clip rigidly linking the fuselage member and the frame. The clip is rigidly linked to the skin via a spacer, independent from the stringers, interposed between the fuselage member and the clip. An aircraft fuselage part includes several assemblies so defined. The cost of a fuselage is thereby reduced by standardization of the clips and/or reduction of the maximum width of the stringers.
    Type: Application
    Filed: June 24, 2014
    Publication date: January 1, 2015
    Inventors: Philippe BERNADET, Yannick MARIN
  • 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
  • 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
  • Patent number: 8567720
    Abstract: The invention relates to a section of fuselage for an aircraft, including frames and bays for receiving cabin windows. According the disclosed embodiments, at least some of the frames include at least one frame segment that surrounds at least one bay, the frame segment having two branches that are disposed to the side of the bay. The ends of the branches are attached to each of the ends of the frame segment such as to form a Y.
    Type: Grant
    Filed: January 3, 2008
    Date of Patent: October 29, 2013
    Assignee: Airbus Operations (S.A.S.)
    Inventors: Guillaume Gallant, Damien Aguera, Philippe Bernadet
  • Patent number: 8524352
    Abstract: A stiffener for a structure submitted to tensile and/or compression and/or shear stresses, that includes a shaped section including: a contact area with an element to be stiffened having a closed cross-section and providing stability, the aforementioned area including first and second legs; and a core normal to the element to be stiffened that provides a support surface capable of element recovery, the aforementioned core being formed by one of the two legs. Application in aircraft structures.
    Type: Grant
    Filed: August 30, 2007
    Date of Patent: September 3, 2013
    Assignee: Airbus Operations (SAS)
    Inventors: Mathieu Forzan, Philippe Bernadet
  • Patent number: 8480031
    Abstract: A system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections.
    Type: Grant
    Filed: September 12, 2008
    Date of Patent: July 9, 2013
    Assignee: Airbus Operations SAS
    Inventors: Laurent Gauthie, Philippe Bernadet
  • Patent number: 8371531
    Abstract: A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, where the cabin window including an outer transparent element and at least one inner transparent element, includes making a non-through hole in a portion of the side wall. The outer transparent element includes a first part having a diameter greater than that of the bay and which is shaped to co-operate with the portion of the side wall to block the outer transparent element in the bay both laterally and longitudinally. A second part of the outer transparent element has a groove that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove.
    Type: Grant
    Filed: January 3, 2008
    Date of Patent: February 12, 2013
    Assignee: Airbus Operations SAS
    Inventors: Guillaume Gallant, Damien Aguera, Philippe Bernadet
  • Publication number: 20130015602
    Abstract: A process for the production of an aircraft panel made of double-curved composite material, with the panel being obtained from a three-dimensional preform that includes fibers that are distributed in a defined arrangement, includes manufacturing a flat fiber preform (22), and deforming the flat preform (22) in such a way as to produce the three-dimensional preform, with the fibers following suitable trajectories at the flat preform in such a way as to obtain the defined arrangement of the fibers after deformation.
    Type: Application
    Filed: July 11, 2012
    Publication date: January 17, 2013
    Applicant: AIRBUS OPERATIONS SAS
    Inventors: Philippe BERNADET, Laurent GIUSEPPIN
  • Publication number: 20100297390
    Abstract: A stiffener for a structure submitted to tensile and/or compression and/or shear stresses, that includes a shaped section including: a contact area with an element to be stiffened having a closed cross-section and providing stability, the aforementioned area including first and second legs; and a core normal to the element to be stiffened that provides a support surface capable of element recovery, the aforementioned core being formed by one of the two legs. Application in aircraft structures.
    Type: Application
    Filed: August 30, 2007
    Publication date: November 25, 2010
    Applicant: AIRBUS FRANCE
    Inventors: Mathieu Forzan, Philippe Bernadet
  • Publication number: 20100258676
    Abstract: A system for transmitting stresses at the intersection between a reinforcing frame and a stiffener in a fuselage and to a method for producing one such system. An aircraft fuselage includes stiffeners interrupted by reinforcing frames. At aforementioned interruptions, the stresses experienced by the stiffeners must be transmitted despite the presence of the reinforcing frames. Known solutions are difficult to manufacture and install and do not provide a simple stress transmission path when produced solely from composite materials. In order to solve this problem, the disclosed embodiments include the creation of battens that cover the ends of consecutive sections of a stiffener and the skin of the fuselage, extending under the reinforcing frame in order to join aforementioned two consecutive sections.
    Type: Application
    Filed: September 12, 2008
    Publication date: October 14, 2010
    Applicant: AIRBUS OPERATIONS (S.A.S.)
    Inventors: Laurent Gauthie, Philippe Bernadet
  • Patent number: 7810756
    Abstract: A beam for reinforcing the structure of an aircraft is located inside the fuselage of the aircraft. The fuselage includes at least one pressurized zone (P) that is separated by at least one airtight wall (18) of at least one other non-pressurized zone (16), the beam and the at least one airtight wall being intersecting. The beam traverses the at least one airtight wall (18) that includes a cutaway that is adapted to the section of the beam, whereby sealing elements (30) are provided to ensure the sealing between the beam and the airtight wall (18) that is traversed.
    Type: Grant
    Filed: May 14, 2007
    Date of Patent: October 12, 2010
    Assignee: Airbus Operations SAS
    Inventors: Sebastien Alby, Laurent Gauthie, Philippe Bernadet
  • Publication number: 20100044513
    Abstract: A method for assembling a cabin window to a bay in a side wall of an aircraft fuselage, the cabin window including an outer transparent element and at least one inner transparent element. A non-through hole is made in a portion of the side wall along the edge of the bay. Subsequently, the outer transparent element is positioned in the bay from the exterior of the fuselage. The element includes a first part which has a diameter greater than that of the bay and which is shaped to co-operate with the above mentioned portion such as to block the outer transparent element in the bay both laterally and longitudinally. A second part of the outer transparent element has a groover that projects into the fuselage. The outer transparent element and the at least one inner transparent element are welded to the fuselage using a strap which presses a seal against at least the fuselage and the inner wall of the groove.
    Type: Application
    Filed: January 3, 2008
    Publication date: February 25, 2010
    Applicant: AIRBUS FRANCE
    Inventors: Guillaume Gallant, Damien Aguera, Philippe Bernadet
  • Publication number: 20100032523
    Abstract: The invention relates to an aircraft fuselage comprising a nose cone, a tail section and a central section, the central section comprising longitudinal panels assembled directly with one another, at least one of these longitudinal panels having a length corresponding to the distance between the nose cone and the tail section in order to connect said nose cone with said tail section.
    Type: Application
    Filed: October 4, 2007
    Publication date: February 11, 2010
    Applicant: Airbus France
    Inventors: Guillaume Gallant, Philippe Bernadet