Patents by Inventor Michel Bermudez
Michel Bermudez 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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Patent number: 11458719Abstract: A method for assembling two parts, referred to as first and second parts, the first part being produced from composite material with fibrous reinforcement embedded in a thermosetting or thermoplastic matrix, the method comprising the steps of: obtaining the first part comprising, on all or part of an outer surface, a first amorphous thermoplastic film; positioning the first part and the second part such that the first amorphous thermoplastic film is placed opposite the second part; introducing a thermosetting resin between the first amorphous thermoplastic film and the second part; at least partially polymerising the thermosetting resin. When the two parts comprise an amorphous thermoplastic film, the parts are positioned such that the respective amorphous thermoplastic films are placed opposite each other, and the thermosetting resin is introduced between the amorphous thermoplastic films.Type: GrantFiled: July 16, 2018Date of Patent: October 4, 2022Assignees: AIRBUS (S.A.S.), ARIANEGROUP S.A.S.Inventors: Frederick Cavaliere, Michel Bermudez, Bruno Thomas, Patrice Lefebure
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Fuselage and aircraft including an air distribution multifunctional substructure and assembly method
Patent number: 11034456Abstract: An aircraft fuselage including a fuselage skin, cross-members supporting a floor of the aircraft, wherein the fuselage includes a multifunctional substructure fixed to at least one of the cross-members in a lowered part of the cross-member. The multifunctional substructure comprises: at least one duct of an air distribution system having a substantially rectangular section at the location of the at least one cross-member and having lateral walls of the duct that are substantially vertical; a seat fixing track or a stiffener fixed on a first lateral wall of the duct of the multifunctional substructure, and; a seat fixing track or a stiffener fixed on a second lateral wall, opposite the first lateral wall, of the duct of the multifunctional substructure.Type: GrantFiled: July 3, 2018Date of Patent: June 15, 2021Assignee: AIRBUS SASInventors: Michel Bermudez, Bruno Thomas, Jean-Mathieu Guimard -
Publication number: 20200406600Abstract: A method for assembling two parts, referred to as first and second parts, the first part being produced from composite material with fibrous reinforcement embedded in a thermosetting or thermoplastic matrix, the method comprising the steps of: obtaining the first part comprising, on all or part of an outer surface, a first amorphous thermoplastic film; positioning the first part and the second part such that the first amorphous thermoplastic film is placed opposite the second part; introducing a thermosetting resin between the first amorphous thermoplastic film and the second part; at least partially polymerising the thermosetting resin. When the two parts comprise an amorphous thermoplastic film, the parts are positioned such that the respective amorphous thermoplastic films are placed opposite each other, and the thermosetting resin is introduced between the amorphous thermoplastic films.Type: ApplicationFiled: July 16, 2018Publication date: December 31, 2020Inventors: Frédérick CAVALIERE, Michel BERMUDEZ, Bruno THOMAS, Patrice LEFEBURE
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Patent number: 10393204Abstract: A device to absorb kinetic energy caused by an exceptional load includes an outer casing configured to maintain integrity after the exceptional load. A core of the device is made of a compactable material at least partially filling the outer casing. The core material is compacted under an exceptional load and absorbs some of the kinetic energy caused by the load. At least one stiffness element is incorporated into the core. A distribution element includes each stiffness element. An aircraft, a vehicle, an item of equipment and an installation includes such a device.Type: GrantFiled: November 18, 2015Date of Patent: August 27, 2019Assignee: AIRBUS SASInventors: Caroline Petiot, Didier Mesnage, Michel Bermudez
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Fuselage and aircraft including an air distribution multifunctional substructure and assembly method
Publication number: 20190016464Abstract: An aircraft fuselage including a fuselage skin, cross-members supporting a floor of the aircraft, wherein the fuselage includes a multifunctional substructure fixed to at least one of the cross-members in a lowered part of the cross-member. The multifunctional substructure comprises: at least one duct of an air distribution system having a substantially rectangular section at the location of the at least one cross-member and having lateral walls of the duct that are substantially vertical; a seat fixing track or a stiffener fixed on a first lateral wall of the duct of the multifunctional substructure, and; a seat fixing track or a stiffener fixed on a second lateral wall, opposite the first lateral wall, of the duct of the multifunctional substructure.Type: ApplicationFiled: July 3, 2018Publication date: January 17, 2019Inventors: Michel Bermudez, Bruno Thomas, Jean-Mathieu Guimard -
Patent number: 10029441Abstract: A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, and a foam core contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements include at least one dry composite fiber preform integrated into the foam core to dissipate, in combination with the foam core, the kinetic energy generated by the impact. A method for integrating the device for absorbing kinetic energy.Type: GrantFiled: December 16, 2013Date of Patent: July 24, 2018Assignee: AIRBUSInventors: Caroline Petiot, Michel Bermudez, Didier Mesnage
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Publication number: 20170321777Abstract: A device to absorb kinetic energy caused by an exceptional load includes an outer casing configured to maintain integrity after the exceptional load. A core of the device is made of a compactable material at least partially filling the outer casing. The core material is compacted under an exceptional load and absorbs some of the kinetic energy caused by the load. At least one stiffness element is incorporated into the core. A distribution element includes each stiffness element. An aircraft, a vehicle, an item of equipment and an installation includes such a device.Type: ApplicationFiled: November 18, 2015Publication date: November 9, 2017Applicant: AIRBUS GROUP SASInventors: CAROLINE PETIOT, DIDIER MESNAGE, MICHEL BERMUDEZ
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Patent number: 9643713Abstract: A method of manufacturing a stiffened panel having a skin and at least one substantially elongate stiffener having a longitudinal groove forming a cavity. At least one storage device for storing and releasing electrical energy. The longitudinal groove is filled with at least one storage device for storing and releasing electrical energy. The storage device is covered with a skin which forms the cavity together with the longitudinal groove of the stiffener. A stiffened ring can be derived from the method.Type: GrantFiled: September 9, 2013Date of Patent: May 9, 2017Assignee: AIRBUS GROUP SASInventors: Michel Bermudez, Didier Mesnage, Hichem Smaoui, Benoit Fleury
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Patent number: 9611030Abstract: A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, a foam core, contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core is configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements are integrated at least partially into the foam core to dissipate, combined with the form core, the kinetic energy generated by the impact. The reinforcing elements includes discontinuous threads inserted into the foam core by stitching, and each discontinuous thread includes an L- or T-shaped head, folded down outside the outer enclosure.Type: GrantFiled: December 16, 2013Date of Patent: April 4, 2017Assignee: AIRBUS GROUP SASInventors: Caroline Petiot, Michel Bermudez, Didier Mesnage
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Patent number: 9545989Abstract: An aircraft fuselage structure, includes a circumferential reinforcing frame (2) and a plurality of stringers (3) substantially perpendicular to the frame. The frame includes a mechanically weakened area able to cause its localized buckling under the effect of a compressive force exerted circumferentially thereon. The structure includes an energy absorbing device (5) having two effector members (52) secured to the frame respectively on either side of the weakened area, and a central core (51) maintained between the effector members such that a reduction in the distance between the effector members produces a deformation of the central core, which is able to absorb energy under the effect of the deformation.Type: GrantFiled: April 22, 2011Date of Patent: January 17, 2017Assignee: EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCEInventors: Jean-Mathieu Guimard, Michel Bermudez, Didier Mesnage
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Publication number: 20150353185Abstract: A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, and a foam core contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements include at least one dry composite fiber preform integrated into the foam core to dissipate, in combination with the foam core, the kinetic energy generated by the impact. A method for integrating the device for absorbing kinetic energy.Type: ApplicationFiled: December 16, 2013Publication date: December 10, 2015Inventors: CAROLINE PETIOT, MICHEL BERMUDEZ, DIDIER MESNAGE
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Publication number: 20150344125Abstract: A device for absorbing kinetic energy for an aircraft structural element undergoing a dynamic impact. The device includes an outer enclosure made from a braided composite material configured to preserve its integrity after an impact, a foam core, contained in the outer enclosure and to at least partially fill the outer enclosure. The foam core is configured to at least partially absorb the kinetic energy generated by the impact. Reinforcing elements are integrated at least partially into the foam core to dissipate, combined with the form core, the kinetic energy generated by the impact. The reinforcing elements includes discontinuous threads inserted into the foam core by stitching, and each discontinuous thread includes an L- or T-shaped head, folded down outside the outer enclosure.Type: ApplicationFiled: December 16, 2013Publication date: December 3, 2015Inventors: CAROLINE PETIOT, MICHEL BERMUDEZ, DIDIER MESNAGE
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Patent number: 9187183Abstract: A combined rescue beacon and flight recorder device for an airplane is ejectable, buoyant and/or provided with flotation devices. The combined rescue beacon and flight recorder device comprises a frame provided with at least one outer side surface having a solar panel. The combined rescue beacon and flight recorder device is configured to be placed in a housing created in an airfoil element of the aircraft.Type: GrantFiled: June 21, 2012Date of Patent: November 17, 2015Assignee: AIRBUS GROUP SASInventors: Fabien Argillier, Michel Bermudez, Hichem Smaoui, Emmanuel Joubert, Thierry Pelegrin
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Publication number: 20150225073Abstract: A method of manufacturing a stiffened panel having a skin and at least one substantially elongate stiffener having a longitudinal groove forming a cavity. At least one storage device for storing and releasing electrical energy. The longitudinal groove is filled with at least one storage device for storing and releasing electrical energy. The storage device is covered with a skin which forms the cavity together with the longitudinal groove of the stiffener. A stiffened ring can be derived from the method.Type: ApplicationFiled: September 9, 2013Publication date: August 13, 2015Applicant: AIRBUS GROUP SASInventors: Michel Bermudez, Didier Mesnage, Hichem Smaoui, Benoit Fleury
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Publication number: 20140290977Abstract: A strip of a semi-finished product (101, 102), suitable for being deposited by lay-up, for the constitution of a laminated composite material, includes, according to a cross-section and over all its length: a first conductive layer (105, 106), made of an electric conductive material; two electric insulating layers (121, 122), made of a dielectric material completely surrounding the conductive layer (105, 106), the cross sectional width of which is greater than the width of the conductive layer; and two bonding layers (111, 112), extending in thickness on either side of the insulating layers (121, 122), on the exterior of the strip (101, 102). A method for the continuous production of such a strip is also described.Type: ApplicationFiled: May 15, 2012Publication date: October 2, 2014Applicant: EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCEInventors: Jesus Aspas Puertolas, Nicolas Maisonnave, Mathieu Sauzedde, Michel Bermudez
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Publication number: 20140142803Abstract: A combined rescue beacon and flight recorder device for an airplane is ejectable, buoyant and/or provided with flotation devices. The combined rescue beacon and flight recorder device comprises a frame provided with at least one outer side surface having a solar panel. The combined rescue beacon and flight recorder device is configured to be placed in a housing created in an airfoil element of the aircraft.Type: ApplicationFiled: June 21, 2012Publication date: May 22, 2014Applicant: EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCEInventors: Fabien Argillier, Michel Bermudez, Hichem Smaoui, Emmanuel Joubert, Thierry Pelegrin
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Publication number: 20130126674Abstract: An aircraft fuselage structure, includes a circumferential reinforcing frame (2) and a plurality of stringers (3) substantially perpendicular to the frame. The frame includes a mechanically weakened area able to cause its localized buckling under the effect of a compressive force exerted circumferentially thereon. The structure includes an energy absorbing device (5) having two effector members (52) secured to the frame respectively on either side of the weakened area, and a central core (51) maintained between the effector members such that a reduction in the distance between the effector members produces a deformation of the central core, which is able to absorb energy under the effect of the deformation.Type: ApplicationFiled: April 22, 2011Publication date: May 23, 2013Applicant: EUROPEAN AERONAUTIC DEFENCE AND SPACE COMPANY EADS FRANCEInventors: Jean-Mathieu Guimard, Michel Bermudez, Didier Mesnage