Patents by Inventor Claude Hubert
Claude Hubert 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: 10184398Abstract: A nacelle may comprise a noise suppressing structure. The noise suppressing structure may comprise a plurality of noise suppressing cells situated between a perforated layer of material and a non-perforated layer of material. The plurality of noise suppressing cells may contact the perforated layer of material and the non-perforated layer of material at an acute angle (e.g., between twenty and seventy-five degrees) such that the plurality of noise suppressing cells are non-orthogonal to the perforated layer of material and the non-perforated layer of material. Further, each of the plurality of noise suppressing cells may comprise a hexagonal cross-sectional profile. Further still, the noise suppressing structure may comprise a support structure comprising a plurality of support members, wherein the plurality of noise suppressing cells are situated within the support structure.Type: GrantFiled: October 17, 2013Date of Patent: January 22, 2019Assignee: ROHR, INC.Inventors: Charles Michael Biset, Song Chiou, Claude Hubert, Michael Layland, Christian Soria
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Patent number: 9897007Abstract: A panel for a nacelle structure that surrounds a jet engine core includes a longitudinally extending, generally semicircular center region, an upper bifurcation region, a lower bifurcation region, a hinge beam region extending from the upper bifurcation region and configured to receive an upper thrust reverser track guide, and a latch beam region extending from the lower bifurcation region and configured to receive a lower thrust reverser track guide. A bypass duct is formed in a space between the panel and the nacelle structure. A hinge beam structure and latch beam structure are integrally formed with the panel. An inner skin layer extends continuously across a bond panel surface generally facing the engine core and an outer skin layer extends continuously across a bond panel surface generally facing the bypass duct, the inner and outer skin layers extending across the center region, upper and lower bifurcation regions, hinge beam region, and latch beam region.Type: GrantFiled: July 24, 2013Date of Patent: February 20, 2018Assignee: Rohr, Inc.Inventors: Christian Soria, Song Chiou, Michael J. Layland, Claude Hubert
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Patent number: 9016042Abstract: An inner fixed structure of a thrust reverser includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially between the inner skin and the outer skin.Type: GrantFiled: May 11, 2012Date of Patent: April 28, 2015Assignee: Rohr, Inc.Inventors: Song Chiou, Jia Yu, Claude Hubert, Michael Layland
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Publication number: 20150110603Abstract: A nacelle may comprise a noise suppressing structure. The noise suppressing structure may comprise a plurality of noise suppressing cells situated between a perforated layer of material and a non-perforated layer of material. The plurality of noise suppressing cells may contact the perforated layer of material and the non-perforated layer of material at an acute angle (e.g., between twenty and seventy-five degrees) such that the plurality of noise suppressing cells are non-orthogonal to the perforated layer of material and the non-perforated layer of material. Further, each of the plurality of noise suppressing cells may comprise a hexagonal cross-sectional profile. Further still, the noise suppressing structure may comprise a support structure comprising a plurality of support members, wherein the plurality of noise suppressing cells are situated within the support structure.Type: ApplicationFiled: October 17, 2013Publication date: April 23, 2015Applicant: ROHR, INC.Inventors: Charles Michael Biset, Song Chiou, Claude Hubert, Michael Layland, Christian Soria
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Publication number: 20140030087Abstract: A panel for a nacelle structure that surrounds a jet engine core includes a longitudinally extending, generally semicircular center region, an upper bifurcation region, a lower bifurcation region, a hinge beam region extending from the upper bifurcation region and configured to receive an upper thrust reverser track guide, and a latch beam region extending from the lower bifurcation region and configured to receive a lower thrust reverser track guide. A bypass duct is formed in a space between the panel and the nacelle structure. A hinge beam structure and latch beam structure are integrally formed with the panel. An inner skin layer extends continuously across a bond panel surface generally facing the engine core and an outer skin layer extends continuously across a bond panel surface generally facing the bypass duct, the inner and outer skin layers extending across the center region, upper and lower bifurcation regions, hinge beam region, and latch beam region.Type: ApplicationFiled: July 24, 2013Publication date: January 30, 2014Applicant: Rohr, Inc.Inventors: Christian Soria, Song Chiou, Michael J. Layland, Claude Hubert
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Publication number: 20120291416Abstract: An inner fixed structure of a thrust reverser includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially between the inner skin and the outer skin.Type: ApplicationFiled: May 11, 2012Publication date: November 22, 2012Applicant: Rohr, Inc.Inventors: Song Chiou, Jia Yu, Claude Hubert, Michael Layland
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Patent number: 8196704Abstract: A linear acoustic liner for an aircraft includes a cellular core having a first surface and an opposed second surface. A substantially imperforate back skin covers the first surface, and a perforate face skin covers the second surface of the core. The perforate face skin includes an outer face skin layer having a first plurality of spaced openings, an inner face skin layer having a second plurality of spaced openings, and a porous layer disposed between the outer face skin layer and the inner face skin layer. Each of the first plurality of spaced openings are substantially aligned with one of the second plurality of spaced openings.Type: GrantFiled: March 14, 2011Date of Patent: June 12, 2012Assignee: Rohr, Inc.Inventors: Song Chiou, Jia Yu, Claude Hubert, Michael Layland, Hwa-Wan Kwan
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Publication number: 20110162910Abstract: A linear acoustic liner for an aircraft includes a cellular core having a first surface and an opposed second surface. A substantially imperforate back skin covers the first surface, and a perforate face skin covers the second surface of the core. The perforate face skin includes an outer face skin layer having a first plurality of spaced openings, an inner face skin layer having a second plurality of spaced openings, and a porous layer disposed between the outer face skin layer and the inner face skin layer. Each of the first plurality of spaced openings are substantially aligned with one of the second plurality of spaced openings.Type: ApplicationFiled: March 14, 2011Publication date: July 7, 2011Applicant: Rohr, Inc.Inventors: Song Chiou, Jia Yu, Claude Hubert, Michael Layland, Hwa-Wan Kwan
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Patent number: 7921966Abstract: A linear acoustic liner for an aircraft includes a cellular core having a first surface and an opposed second surface. A substantially imperforate back skin covers the first surface, and a perforate face skin covers the second surface of the core. The perforate face skin includes an outer face skin layer having a first plurality of spaced openings, an inner face skin layer having a second plurality of spaced openings, and a porous layer disposed between the outer face skin layer and the inner face skin layer. Each of the first plurality of spaced openings are substantially aligned with one of the second plurality of spaced openings.Type: GrantFiled: August 13, 2008Date of Patent: April 12, 2011Assignee: Rohr, Inc.Inventors: Song Chiou, Jia Yu, Claude Hubert, Michael Layland, Hwa-Wan Kwan
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Patent number: 7798285Abstract: An acoustic inner barrel for an aircraft engine nacelle inlet is constructed from a composite material and is formed as a single, 360-degree annular segment. The barrel includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially from the inner skin to the outer skin.Type: GrantFiled: November 14, 2008Date of Patent: September 21, 2010Assignee: Rohr, Inc.Inventors: Song Chiou, Jia Yu, Claude Hubert, Michael Layland
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Publication number: 20100122868Abstract: An acoustic inner barrel for an aircraft engine nacelle inlet is constructed from a composite material and is formed as a single, 360-degree annular segment. The barrel includes an inner skin, an outer skin, a cellular core disposed between the inner skin and the outer skin, and at least one crack and delamination stopper extending radially from the inner skin to the outer skin.Type: ApplicationFiled: November 14, 2008Publication date: May 20, 2010Inventors: Song Chiou, Jia Yu, Claude Hubert, Michael Layland
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Publication number: 20090045009Abstract: A linear acoustic liner for an aircraft includes a cellular core having a first surface and an opposed second surface. A substantially imperforate back skin covers the first surface, and a perforate face skin covers the second surface of the core. The perforate face skin includes an outer face skin layer having a first plurality of spaced openings, an inner face skin layer having a second plurality of spaced openings, and a porous layer disposed between the outer face skin layer and the inner face skin layer. Each of the first plurality of spaced openings are substantially aligned with one of the second plurality of spaced openings.Type: ApplicationFiled: August 13, 2008Publication date: February 19, 2009Applicant: Rohr, Inc.Inventors: Song Chiou, Jia Yu, Claude Hubert, Michael Layland, Hwa-Wan Kwan
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Publication number: 20080179448Abstract: An engine nacelle inlet lip includes both acoustic treatment and electric heating for ice protection. The inlet lip has a composite outer skin and a composite inner skin, with the composite outer skin having at least one integrated heater element embedded in the composite material. An acoustic cellular core positioned between the outer and inner skin acts to attenuate fan noise from the engine. Covering the outer skin and overlying the acoustic core is a perforated erosion shield having a first set of openings that pass entirely thorough its thickness. The composite outer skin includes a second set of openings such that sound waves can pass from an inner barrel portion of the inlet lip through the erosion shield, outer skin, and heater element to the underlying acoustic cellular core.Type: ApplicationFiled: April 10, 2007Publication date: July 31, 2008Applicant: Rohr, Inc.Inventors: Michael Layland, Keith Brown, Claude Hubert, Daniel Christy
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Publication number: 20070210073Abstract: The invention includes a composite ice protection heater for an aircraft. The composite heater includes at least one electrically insulating layer, and at least one electric heater element comprising an electrically conductive layer bonded to the insulating layer. The conductive layer may include a pre-impregnated woven fabric that includes a plurality of threads that include an electrically conductive material, such as carbon or graphite fibers. The composite heater can be incorporated into a composite surface structure of an aircraft. The conductive layer and insulating layer may include a plurality of spaced openings through the layers that cooperate with an underlying open-cell matrix to attenuate noise at the associated surface of an aircraft. A desired electrical resistance of the conductive layer may be obtained by introducing a plurality of discontinuities in the layer, such as spaced holes or slits.Type: ApplicationFiled: February 24, 2006Publication date: September 13, 2007Applicants: GOODRICH CORPORATION, ROHR, INC.Inventors: Claude Hubert, Daniel Christy
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Patent number: 7205066Abstract: A structural element for use in aerospace applications such as a structural element suitable as an aircraft component is described. In one embodiment of the invention, the composite structure comprises: (a) at least one member having an inner surface and an outer surface; (b) a rib having a first end and a second end; (c) a rib-receiving member integral to the inner surface of the at least one member, wherein the rib-receiving member comprises a plurality of rib-receiving elements and openings therein for receiving the first end of the rib and at least one cover sheet having an opening therein for receiving the first end of the rib; and (d) at least one anchoring element interconnecting the rib-receiving elements.Type: GrantFiled: May 23, 2002Date of Patent: April 17, 2007Assignee: Rohr, Inc.Inventors: Basil Hammi, Claude Hubert
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Publication number: 20060186013Abstract: The invention relates to a container (1) for containing foodstuff (F), which container comprises: a bottom (2); a peripheral wall (3) integral with the bottom (2) and extending upwardly from the bottom (2) and defining a mouth opening; a closing foil (5) arranged onto the mouth opening; at least one support element (4) arranged on the bottom (2) at a position corresponding to the edge (7) of the mouth opening, such that in a stacked position of at least two identical containers, the support element (4) of the first container rests on the edge (7) of the mouth opening of the second container. Furthermore the invention relates to a stack of containers, comprising at least a first and a second container according to any of the preceding claims, wherein the first container is stacked on top of the second container, and wherein the support element (4) of the first container rests on the edge (7) of the mouth opening of the second container.Type: ApplicationFiled: July 13, 2004Publication date: August 24, 2006Inventor: Jean-Claude Hubert
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Patent number: 6680272Abstract: Co-precipitated CoCuMn and CoCuMg catalysts are used in Fischer-Tropsch synthesis.Type: GrantFiled: December 11, 2001Date of Patent: January 20, 2004Assignee: ExxonMobil Chemical Patents Inc.Inventors: Philippe Buess, Raphael Frans Ivo Caers, Alfred Frennet, Eric Ghenne, Claude Hubert, Norbert Kruse
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Patent number: 6523241Abstract: The method provides for molding the rear end portion 4 of a tubular body 2 made of plastic material on an end portion 5 of a cable adaptor 6. The tubular body 2 has windows 10 formed in a front end portion 3 thereof. A coil spring 21 and a ferrule holder 13 having wings 19 are inserted through the front end portion 3 of the tubular body 2 and forced therethrough so that the wings 19 expand radially the the front end portion 3 and the end walls 11 of the windows 10. When the wings 19 arrive in the windows 10, the end walls 11 and the front end portion 3 may re-contract radially so that the wings 19 may catch the end walls 11 under the bias of the coil spring 21.Type: GrantFiled: August 23, 2000Date of Patent: February 25, 2003Assignee: Interlemo Holding S.A.Inventors: Jean-Claude Hubert, Jean-Philippe Barbey, Alan Brooks
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Patent number: D562154Type: GrantFiled: December 29, 2004Date of Patent: February 19, 2008Assignee: Impress Group B.V.Inventors: Yves Pelletier, Jean Claude Hubert
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Patent number: D588937Type: GrantFiled: January 3, 2008Date of Patent: March 24, 2009Assignee: Impress Group B.V.Inventors: Yves Pelletier, Jean Claude Hubert