Patents by Inventor Jean-Claude Lacombe
Jean-Claude Lacombe 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: 11124285Abstract: An aerodynamic profile including a skin defining the outer surface of the aerodynamic profile, a leading edge, a trailing edge and a central portion representing at least 50% of the chord of the profile. The profile includes a hollow core of composite material reinforced with a textile having unidirectional fibers. The hollow core has, in cross section, an oblong shape that is rounded, in particular at each of its ends. The skin bears against the hollow core over the length of the central portion of the aerodynamic profile, both on the pressure side and on the suction side of the profile. The reinforcement with a textile having unidirectional fibers permits an ideal orientation of reinforcing fibers in order to optimize mechanical properties in certain directions. The shape of the hollow core, elongate along the chord of the profile and rounded, lends it great resistance to deformation.Type: GrantFiled: July 17, 2018Date of Patent: September 21, 2021Assignees: Airbus Operations (S.A.S.), Airbus (S.A.S.)Inventors: Rodolphe Trouve, Jean-Claude Lacombe, Julien Rodes, Thomas Schutz
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Publication number: 20190023372Abstract: An aerodynamic profile including a skin defining the outer surface of the aerodynamic profile, a leading edge, a trailing edge and a central portion representing at least 50% of the chord of the profile. The profile includes a hollow core of composite material reinforced with a textile having unidirectional fibers. The hollow core has, in cross section, an oblong shape that is rounded, in particular at each of its ends. The skin bears against the hollow core over the length of the central portion of the aerodynamic profile, both on the pressure side and on the suction side of the profile. The reinforcement with a textile having unidirectional fibers permits an ideal orientation of reinforcing fibers in order to optimize mechanical properties in certain directions. The shape of the hollow core, elongate along the chord of the profile and rounded, lends it great resistance to deformation.Type: ApplicationFiled: July 17, 2018Publication date: January 24, 2019Inventors: Rodolphe Trouve, Jean-Claude Lacombe, Julien Rodes, Thomas Schutz
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Patent number: 10150553Abstract: A device and method for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces.Type: GrantFiled: June 26, 2012Date of Patent: December 11, 2018Assignee: AIRBUS OPERATIONS (Societe par Actions Simplifiee)Inventors: Bruno Cacciaguerra, Alain Depeige, Jean-Claude Lacombe, Hélène Cazeneuve, Marc-Antoine Castanet
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Patent number: 9126671Abstract: A stiffened panel includes a panel at least one of whose surfaces is equipped with stiffeners each of which includes a base that is pressed against the surface of panel, as well as a core that is oriented orthogonally relative to the base and whose first longitudinal edge is integral to the latter. At least one of the stiffeners includes a multitude of notches that cross over a second longitudinal edge of the core opposite the first edge, so that they extend towards the outside of the stiffener.Type: GrantFiled: July 25, 2012Date of Patent: September 8, 2015Assignee: Airbus Operations S.A.S.Inventors: Jéôme Dubost, Jean Claude Lacombe
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Patent number: 8967540Abstract: A frame of an aircraft fuselage structure made from composite material, which includes a skin and several stringers fixed on the skin. The frame includes a profile elongated in a longitudinal direction which is hollow over at least a portion of its length. The profile is mounted on two legs. Each leg, intended to be fixed on the skin, includes a first portion extending continuously over the whole length of the profile and a second portion extending from this continuous portion so as to form several openings spaced apart in the longitudinal direction of the profile, in each of which a stringer passes. The presence of the hollow profile in the frame and the structure of the legs makes it possible to dispense with clips and cleats.Type: GrantFiled: December 17, 2012Date of Patent: March 3, 2015Assignee: Airbus Operations SASInventors: Jean-Claude Lacombe, Laurent Giuseppin
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Patent number: 8801885Abstract: The disclosed embodiments offer a solution for controlling the thickness of a finished structural composite part when precise tolerances must be complied with for the quality of the assembly and in order to ease the assembly operations of this part. In order to implement the method according to the disclosed embodiments, an additional layer of plies made out of a non-structural composite material, called calibrating plies, is applied onto the structural plies of the structural part, at least in an area where the thickness must be maintained within close tolerances and, after the composite material has been cured, the calibrating plies are machined in order to obtain the thickness required for the finished part. The thickness of the calibrating plies applied is determined according to the possible thicknesses of structural plies, taking into account the manufacturing spreads so that the machining operation for the calibrating plies does not affect the structural plies.Type: GrantFiled: April 9, 2008Date of Patent: August 12, 2014Assignee: Airbus Operations SASInventors: Mathieu Normand, Jean-Claude Lacombe
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Publication number: 20130181092Abstract: Device for assembling two aircraft fuselage sections each comprising a skin and longitudinal stiffeners, the device comprising fishplates fishing couples of mutually aligned longitudinal stiffeners belonging respectively to said sections, each fishplate comprising two fishplate pieces each comprising at least one longitudinal sole plate intended to be fixed to a longitudinal stiffener, and a transverse support head, and at least one demountable connecting member able to mutually clamp the respective support heads of said fishplate pieces to allow a transmission of longitudinal forces between these fishplate pieces. Set of fuselage sections assembled by means of a device of the type described above. Method of assembling two fuselage sections by means of a device of the type described above.Type: ApplicationFiled: June 26, 2012Publication date: July 18, 2013Applicant: AIRBUS OPERATIONS (Societe par Actions Simplifiee)Inventors: Bruno Cacciaguerra, Alain Depeige, Jean-Claude Lacombe, Helene Cazeneuve, Marc-Antoine Castanet
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Patent number: 8484848Abstract: A method for assembling two structural elements, at least one of the two structural elements being tube-shaped and including a skin made of a fiber-reinforced composite material. The ability of the element to adapt to the shape and perimeter of a junction interface is improved by providing longitudinal grooves distributed on the circumference of the junction interface. The grooves are of a sufficient length to provide the junction interface with the flexibility to accommodate, through relative radial movement of each portion located between two grooves, differences in shape and perimeter among the junction interfaces of the two structural elements.Type: GrantFiled: May 26, 2009Date of Patent: July 16, 2013Assignee: Airbus Operations S.A.S.Inventors: Guillaume Gallant, Jean-Claude Lacombe
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Patent number: 8395497Abstract: A radiofrequency circuit embedded onboard a satellite, data being transmitted on several channels by radiofrequency signals, includes a channel corresponding to a frequency band, and a succession of gains being able to be associated with a channel so as to generate the radiofrequency signal to be transmitted on the latter. The succession includes at least one variable-gain amplifier, the radiofrequency signals thus generated being multiplexed by a multiplexer composed of bandpass filters. The successions of gains comprise a power load arranged so as to dissipate the power of signals which is reflected by the filters of the multiplexer, said load including means for generating an alarm signal representative of the power level of the reflected signals, the alarm signal being used to control the gain of the variable-gain amplifier. The subject of the invention is also a power load.Type: GrantFiled: March 4, 2011Date of Patent: March 12, 2013Assignee: ThalesInventors: Emile Tonello, Damien Pacaud, Jean-Claude Lacombe
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Publication number: 20130026292Abstract: A stiffened panel includes a panel at least one of whose surfaces is equipped with stiffeners each of which includes a base that is pressed against the surface of panel, as well as a core that is oriented orthogonally relative to the base and whose first longitudinal edge is integral to the latter. At least one of the stiffeners includes a multitude of notches that cross over a second longitudinal edge of the core opposite the first edge, so that they extend towards the outside of the stiffener.Type: ApplicationFiled: July 25, 2012Publication date: January 31, 2013Applicant: AIRBUS OPERATIONS S.A.S.Inventors: Jérôme Dubost, Jean Claude Lacombe
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Patent number: 8340594Abstract: A microwave channel multiplexing device comprises several elementary filters connected in parallel with a common output port by way of a transverse waveguide, each filter comprising a lower end fixed to a support common to all the filters and an upper end away from the support, an external peripheral wall, at least one internal cavity defining an internal channel, a signal input connected to the internal cavity and a signal output connected to the transverse waveguide. The multiplexing device furthermore comprises a conducto-radiative device coupled mechanically and thermally to at least two filters, the conducto-radiative device comprising at least one thermally conducting plate, and linked to the external peripheral walls of each of said at least two filters, the plate being fixed at the level of the upper end of the filters. The invention applies to the field of satellite telecommunications and more particularly to signals repetition devices aboard satellites.Type: GrantFiled: August 29, 2010Date of Patent: December 25, 2012Assignee: ThalesInventors: Joël Lagorsse, Jean-Claude Lacombe
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Patent number: 8286915Abstract: An aircraft having a fuselage of composite type and more particularly to that of aircraft fuselage panels bearing cabin windows. The invention thus concerns a fuselage panel bearing a window comprising a composite structure cast in one piece, the structure comprising a main portion and at least one opening to accommodate a window, the structure having, on a zone surrounding the opening, a thickness more or less constant and greater than the thickness of the main portion of the structure. The invention also concerns an aircraft comprising a composite fuselage, the latter comprising such a panel or a similar panel made of metal material.Type: GrantFiled: March 9, 2009Date of Patent: October 16, 2012Assignee: Airbus Operations SASInventors: Alain Depeige, Jean-Claude Lacombe
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Patent number: 8215584Abstract: An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area.Type: GrantFiled: September 12, 2008Date of Patent: July 10, 2012Assignee: Airbus Operations SASInventors: Helene Cazeneuve, Bruno Cacciaguerra, Jean-Claude Lacombe, David Andissac
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Publication number: 20120056740Abstract: A radiofrequency circuit embedded onboard a satellite, data being transmitted on several channels by radiofrequency signals, includes a channel corresponding to a frequency band, and a succession of gains being able to be associated with a channel so as to generate the radiofrequency signal to be transmitted on the latter. The succession includes at least one variable-gain amplifier, the radiofrequency signals thus generated being multiplexed by a multiplexer composed of bandpass filters. The successions of gains comprise a power load arranged so as to dissipate the power of signals which is reflected by the filters of the multiplexer, said load including means for generating an alarm signal representative of the power level of the reflected signals, the alarm signal being used to control the gain of the variable-gain amplifier. The subject of the invention is also a power load.Type: ApplicationFiled: March 4, 2011Publication date: March 8, 2012Applicant: THALESInventors: Emile Tonello, Damien Pacaud, Jean-Claude Lacombe
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Publication number: 20110185555Abstract: A method for assembling two structural elements, at least one of the two structural elements being tube-shaped and including a skin made of a fiber-reinforced composite material. The ability of the element to adapt to the shape and perimeter of a junction interface is improved by providing longitudinal grooves distributed on the circumference of the junction interface. The grooves are of a sufficient length to provide the junction interface with the flexibility to accommodate, through relative radial movement of each portion located between two grooves, differences in shape and perimeter among the junction interfaces of the two structural elements.Type: ApplicationFiled: May 26, 2009Publication date: August 4, 2011Applicant: AIRBUS OPERATIONS (inc as a Societe par Act Simpl)Inventors: Guillaume Gallant, Jean-Claude Lacombe
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Publication number: 20110058809Abstract: A microwave channel multiplexing device comprises several elementary filters connected in parallel with a common output port by way of a transverse waveguide, each filter comprising a lower end fixed to a support common to all the filters and an upper end away from the support, an external peripheral wall, at least one internal cavity defining an internal channel, a signal input connected to the internal cavity and a signal output connected to the transverse waveguide. The multiplexing device furthermore comprises a conducto-radiative device coupled mechanically and thermally to at least two filters, the conducto-radiative device comprising at least one thermally conducting plate, and linked to the external peripheral walls of each of said at least two filters, the plate being fixed at the level of the upper end of the filters. The invention applies to the field of satellite telecommunications and more particularly to signals repetition devices aboard satellites.Type: ApplicationFiled: August 29, 2010Publication date: March 10, 2011Applicant: THALESInventors: Joël Lagorsse, Jean-Claude Lacombe
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Publication number: 20100264272Abstract: An aircraft structure including stiffened panels assembled at the junction, without continuity of the stiffeners. Multiple panels are used to form the fuselage, tail units and wings of an aircraft. These panels include stiffeners which are interrupted at each panel junction. However, the stresses experienced by the stiffeners must be transmitted despite these interruptions. Known solutions require the use of at least one additional part per stiffener and per interruption. In order to solve this problem, the disclosed embodiments include a doubler necessitating at most one additional part per panel junction area for all of the interrupted stiffeners in this area.Type: ApplicationFiled: September 12, 2008Publication date: October 21, 2010Applicant: AIRBUS OPERATIONS (S.A.S.)Inventors: Helene Cazeneuve, Bruno Cacciaguerra, Jean-Claude Lacombe, David Andissac
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Patent number: 7814729Abstract: A stiff panel (1) comprises a skin (2) and at least one stiffener (3) of composite material on said skin. Free surface (311) of web (31) of stiffener (3) on the stiff panel according to the invention comprises a deformable core (33) and a covering (34) which covers core (33) and joins said core with structural part (35) of web (31). The width of core (33) is equal to or greater than the width of structural part (35) of web (31) of stiffener (3), depending on the shock energy against which panel (1) must be protected.Type: GrantFiled: June 21, 2007Date of Patent: October 19, 2010Assignee: Airbus FranceInventors: Mathieu Normand, Jean-Claude Lacombe
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Publication number: 20100136309Abstract: The disclosed embodiments offer a solution for controlling the thickness of a finished structural composite part when precise tolerances must be complied with for the quality of the assembly and in order to ease the assembly operations of this part. In order to implement the method according to the disclosed embodiments, an additional layer of plies made out of a non-structural composite material, called calibrating plies, is applied onto the structural plies of the structural part, at least in an area where the thickness must be maintained within close tolerances and, after the composite material has been cured, the calibrating plies are machined in order to obtain the thickness required for the finished part. The thickness of the calibrating plies applied is determined according to the possible thicknesses of structural plies, taking into account the manufacturing spreads so that the machining operation for the calibrating plies does not affect the structural plies.Type: ApplicationFiled: April 9, 2008Publication date: June 3, 2010Applicant: AIRBUS FRANCEInventors: Mathieu Normand, Jean-Claude Lacombe
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Publication number: 20090230246Abstract: This invention relates to the design of aircraft (100) having a fuselage (104, 106, 110) of composite type and more particularly to that of aircraft fuselage panels (110) bearing cabin windows (206, 306). The invention thus concerns a fuselage panel (110) bearing a window (206) comprising a composite structure cast in one piece (200, 212), the said structure comprising a main portion (200) and at least one opening (204) to accommodate a window (206), the said structure having, on a zone (213, 214, 216)) surrounding the said opening (204), a thickness more or less constant and greater than the thickness of the main portion (200) of the said structure. The invention also concerns an aircraft (100) comprising a composite fuselage (104, 106, 110), the latter comprising such a panel or a similar panel made of metal material (110).Type: ApplicationFiled: March 9, 2009Publication date: September 17, 2009Applicant: Airbus FranceInventors: Alain Depeige, Jean-Claude Lacombe