Patents by Inventor Chetan Korya
Chetan Korya 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: 10227128Abstract: The invention provides an aircraft wing, comprising a fixed wing and a wing tip device at the tip. The wing tip device is configurable between: (i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations. The wing further comprises a locking mechanism for locking the folding wing tip device in the locked flight configuration. A rotatable locking member is associated with one of the folding wing tip device and the fixed wing, and a locking pin associated with the other. The rotatable locking member comprises a guide surface to guide the locking pin to a locked configuration, in which the guide surface is shaped such that the locking pin is urged toward the rotation axis of the rotatable locking member by a camming action of the guide surface on the locking pin, thereby preloading the locking mechanism.Type: GrantFiled: May 12, 2016Date of Patent: March 12, 2019Assignee: AIRBUS OPERATIONS LIMITEDInventors: Chetan Korya, Anthony Bryant, Matt Harding, David Brakes
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Patent number: 10118348Abstract: A method of manufacturing an aircraft component, the component comprising a pair of covers joined by a pair of spars. The covers and spars form a closed box structure with four corners, each corner providing a transition between one of the covers and one of the spars. The method comprises: laying up a laminated sheet of fiber plies; and after the sheet has been laid up, folding the sheet to form the four corners and then joining the sheet to itself to provide the closed box structure.Type: GrantFiled: May 12, 2016Date of Patent: November 6, 2018Assignee: AIRBUS OPERATIONS LIMITEDInventors: Jonathan Price, Chetan Korya, Peter Baker, Stephen Williams
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Patent number: 10087968Abstract: The invention provides a method of manufacturing a metallic-composite joint comprising a metallic component having one hole in a surface thereof, and a metallic fastener having a head portion for attaching to the metallic component and a tail portion for attaching to a composite component, comprising the steps of positioning the metallic fastener such that the head portion of the metallic fastener is retained in the hole, and the tail portion of the metallic fastener extends out of the hole, arranging layered fibers of an uncured composite component on the surface of the metallic component such that the tail portion extends through a gap between adjacent fibers in each fiber layer, and curing the composite component. The invention also provides a metallic-composite joint, a structure, an aircraft structure, an aircraft, a method of manufacturing a fastener assembly, a fastener assembly and a metallic fastener.Type: GrantFiled: December 11, 2015Date of Patent: October 2, 2018Assignee: AIRBUS OPERATIONS LIMITEDInventors: Chetan Korya, David Brakes
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Patent number: 9957036Abstract: The present invention provides an aircraft structure comprising a first sub-structure, having a first box cross-section, a second sub-structure, having a second box cross-section, and a joint joining a first end region of the first sub-structure to second end region of the second sub-structure, wherein the joint comprises an overlap region where the end regions of the first and the second sub-structures overlap such that the first sub-structure is inside the second sub-structure. The present invention also provides an aircraft comprising such an aircraft structure and a method of manufacturing an aircraft structure.Type: GrantFiled: September 30, 2013Date of Patent: May 1, 2018Assignee: AIRBUS OPERATIONS LIMITEDInventors: Timothy J. Sanderson, Jonathan Price, James Eden, Chetan Korya, Robert James Heath, Peter Baker, Richard Smith, Graham Morgan
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Publication number: 20160332723Abstract: The invention provides an aircraft wing, comprising a fixed wing and a wing tip device at the tip. The wing tip device is configurable between: (i) a locked flight configuration for use during flight and (ii) a ground configuration for use during ground-based operations. The wing further comprises a locking mechanism for locking the folding wing tip device in the locked flight configuration. A rotatable locking member is associated with one of the folding wing tip device and the fixed wing, and a locking pin associated with the other. The rotatable locking member comprises a guide surface to guide the locking pin to a locked configuration, in which the guide surface is shaped such that the locking pin is urged toward the rotation axis of the rotatable locking member by a camming action of the guide surface on the locking pin, thereby preloading the locking mechanism.Type: ApplicationFiled: May 12, 2016Publication date: November 17, 2016Inventors: Chetan KORYA, Anthony BRYANT, Matt HARDING, David BRAKES
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Publication number: 20160332409Abstract: A method of manufacturing an aircraft component, the component comprising a pair of covers joined by a pair of spars. The covers and spars form a closed box structure with four corners, each corner providing a transition between one of the covers and one of the spars. The method comprises: laying up a laminated sheet of fibre plies; and after the sheet has been laid up, folding the sheet to form the four corners and then joining the sheet to itself to provide the closed box structure.Type: ApplicationFiled: May 12, 2016Publication date: November 17, 2016Inventors: Jonathan PRICE, Chetan KORYA, Peter BAKER, Stephen WILLIAMS
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Publication number: 20160185457Abstract: A device for removing debris, such as insects and ice, from an aerodynamic structure of an aircraft and in which the aerodynamic structure has upper and lower surfaces separated by a leading edge extending along the length of the aerodynamic structure. The device includes a spine positionable so as to extend between the upper and lower surfaces over the leading edge of the aerodynamic structure, a scraping edge carried by the spine facing a direction that extends along the length, and a drive mechanism configured to move the spine in the direction so that the scraping edge scrapes debris from along the length of the aerodynamic structure. The spine is configured to bias the scraping edge against the aerodynamic structure.Type: ApplicationFiled: December 29, 2015Publication date: June 30, 2016Inventors: Chetan Korya, Andrew McVey
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Publication number: 20160177995Abstract: The invention provides a method of manufacturing a metallic-composite joint comprising a metallic component having one hole in a surface thereof, and a metallic fastener having a head portion for attaching to the metallic component and a tail portion for attaching to a composite component, comprising the steps of positioning the metallic fastener such that the head portion of the metallic fastener is retained in the hole, and the tail portion of the metallic fastener extends out of the hole, arranging layered fibres of an uncured composite component on the surface of the metallic component such that the tail portion extends through a gap between adjacent fibres in each fibre layer, and curing the composite component. The invention also provides a metallic-composite joint, a structure, an aircraft structure, an aircraft, a method of manufacturing a fastener assembly, a fastener assembly and a metallic fastener.Type: ApplicationFiled: December 11, 2015Publication date: June 23, 2016Inventors: Chetan KORYA, David BRAKES
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Patent number: 9193470Abstract: An aircraft fuel tank access cover comprises an inner door, an outer door and a clamping arrangement for clamping the doors together about an access aperture in the skin of the fuel tank. The clamping arrangement comprises a bolt in-molded in a generally central part of the inner door and or external nut. The doors have reinforcing rib arrangements to spread the clamping load to the peripheral edges thereof.Type: GrantFiled: February 22, 2012Date of Patent: November 24, 2015Assignee: AIRBUS OPERATIONS LIMITEDInventors: Chetan Korya, Timothy J. Sanderson
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Publication number: 20150217852Abstract: The present invention provides an aircraft structure comprising a first sub-structure, having a first box cross-section, a second sub-structure, having a second box cross-section, and a joint joining a first end region of the first sub-structure to second end region of the second sub-structure, wherein the joint comprises an overlap region where the end regions of the first and the second sub-structures overlap such that the first sub-structure is inside the second sub-structure. The present invention also provides an aircraft comprising such an aircraft structure and a method of manufacturing an aircraft structure.Type: ApplicationFiled: September 30, 2013Publication date: August 6, 2015Inventors: Timothy J. Sanderson, Jonathan Price, James Eden, Chetan Korya, Robert James Heath, Peter Baker, Richard Smith, Graham Morgan
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Patent number: 8506746Abstract: A method of forming a joint between a first component and a second component, the first component comprising a plurality of layers of fibers impregnated with a thermosetting matrix. A welding interface element is provided with an array of pointed prongs. One or more of the layers of fibers are penetrated with the prongs, either before or after the fibers have been impregnated with the thermosetting matrix. The first component is cured by heating the thermosetting matrix after the prongs have been embedded. A thermoplastic weld is formed between the second component and the welding interface element.Type: GrantFiled: March 28, 2011Date of Patent: August 13, 2013Assignee: Airbus Operations LimitedInventors: Chetan Korya, Timothy Sanderson
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Publication number: 20120217347Abstract: An aircraft fuel tank access cover comprises an inner door, an outer door and a clamping arrangement for clamping the doors together about an access aperture in the skin of the fuel tank. The clamping arrangement comprises a bolt in-moulded in a generally central part of the inner door and or external nut. The doors have reinforcing rib arrangements to spread the clamping load to the peripheral edges thereof.Type: ApplicationFiled: February 22, 2012Publication date: August 30, 2012Applicant: AIRBUS OPERATIONS LIMITEDInventors: Chetan KORYA, Timothy J. SANDERSON
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Publication number: 20110240200Abstract: A method of forming a joint between a first component and a second component, the first component comprising a plurality of layers of fibres impregnated with a thermosetting matrix. A welding interface element is provided with an array of pointed prongs. One or more of the layers of fibres are penetrated with the prongs, either before or after the fibres have been impregnated with the thermosetting matrix. The first component is cured by heating the thermosetting matrix after the prongs have been embedded. A thermoplastic weld is formed between the second component and the welding interface element.Type: ApplicationFiled: March 28, 2011Publication date: October 6, 2011Applicant: AIRBUS OPERATIONS LIMITEDInventors: Chetan Korya, Timothy Sanderson