Patents by Inventor Timothy Sanderson
Timothy Sanderson 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: 11811200Abstract: An apparatus and method for installing an aircraft bulkhead connector with a bulkhead is disclosed where access to only one side of the bulkhead is required. The disclosure is also applicable to installation of bulkhead connectors in aircraft fuel tanks. An aircraft bulkhead connector and installation tool is also disclosed. The bulkhead connector includes a female end portion and the installation tool includes a male end portion. The male end portion of the installation tool is removably engaged with the female end portion of the bulkhead connector, such that the installation tool protrudes beyond the female end portion of the bulkhead connector. The installation tool may be inserted through an aperture in a bulkhead and used to both position and hold the bulkhead connector during the installation process.Type: GrantFiled: March 28, 2019Date of Patent: November 7, 2023Assignee: AIRBUS OPERATIONS LIMITEDInventors: Timothy Sanderson, Stuart Quayle
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Patent number: 11597498Abstract: A seal for sealing an aircraft fuel tank, an aircraft wing rib and stringer sealing assembly, an aircraft wing fuel tank, an aircraft structural wing box, an aircraft wing, and a method of sealing an aperture are disclosed. The seal is for sealing a wing rib to a stringer passing through an aperture in the rib at a variable position in the aperture. The seal includes self-adjustment means to absorb any tolerance when forming the seal, upon the stringer being assembled into the aperture in the rib.Type: GrantFiled: July 15, 2022Date of Patent: March 7, 2023Assignee: AIRBUS OPERATIONS LIMITEDInventors: Paul Edwards, Antony Peacock, Timothy Sanderson
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Publication number: 20220348306Abstract: A seal for sealing an aircraft fuel tank, an aircraft wing rib and stringer sealing assembly, an aircraft wing fuel tank, an aircraft structural wing box, an aircraft wing, and a method of sealing an aperture are disclosed. The seal is for sealing a wing rib to a stringer passing through an aperture in the rib at a variable position in the aperture. The seal includes self-adjustment means to absorb any tolerance when forming the seal, upon the stringer being assembled into the aperture in the rib.Type: ApplicationFiled: July 15, 2022Publication date: November 3, 2022Inventors: Paul EDWARDS, Antony PEACOCK, Timothy SANDERSON
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Patent number: 11420722Abstract: A seal for sealing an aircraft fuel tank, an aircraft wing rib and stringer sealing assembly, an aircraft wing fuel tank, an aircraft structural wing box, an aircraft wing, and a method of sealing an aperture are disclosed. The seal is for sealing a wing rib to a stringer passing through an aperture in the rib at a variable position in the aperture. The seal includes self-adjustment means to absorb any tolerance when forming the seal, upon the stringer being assembled into the aperture in the rib.Type: GrantFiled: November 25, 2019Date of Patent: August 23, 2022Assignee: AIRBUS OPERATIONS LIMITEDInventors: Paul Edwards, Antony Peacock, Timothy Sanderson
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Patent number: 11054400Abstract: A method of inspecting a wing box of an aircraft. The wing box includes at least one rib partitioning the wing box in to two bays and at least one stringer attached along an inner surface of the wing box, generally perpendicular to the rib, and extending through an aperture of the rib. The method includes: providing an inspection device on the stringer such that it is movable along the stringer and controlling the inspection device to pass along the stringer, including through the aperture between bays, to perform an inspection of the wing box.Type: GrantFiled: September 27, 2018Date of Patent: July 6, 2021Assignee: Airbus Operations LimitedInventors: Timothy Sanderson, David Brawley
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Publication number: 20200164959Abstract: A seal for sealing an aircraft fuel tank, an aircraft wing rib and stringer sealing assembly, an aircraft wing fuel tank, an aircraft structural wing box, an aircraft wing, and a method of sealing an aperture are disclosed. The seal is for sealing a wing rib to a stringer passing through an aperture in the rib at a variable position in the aperture. The seal includes self-adjustment means to absorb any tolerance when forming the seal, upon the stringer being assembled into the aperture in the rib.Type: ApplicationFiled: November 25, 2019Publication date: May 28, 2020Inventors: Paul EDWARDS, Antony PEACOCK, Timothy SANDERSON
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Publication number: 20190305530Abstract: An apparatus and method for installing an aircraft bulkhead connector with a bulkhead is disclosed where access to only one side of the bulkhead is required. The disclosure is also applicable to installation of bulkhead connectors in aircraft fuel tanks. An aircraft bulkhead connector and installation tool is also disclosed. The bulkhead connector includes a female end portion and the installation tool includes a male end portion. The male end portion of the installation tool is removably engaged with the female end portion of the bulkhead connector, such that the installation tool protrudes beyond the female end portion of the bulkhead connector. The installation tool may be inserted through an aperture in a bulkhead and used to both position and hold the bulkhead connector during the installation process.Type: ApplicationFiled: March 28, 2019Publication date: October 3, 2019Inventors: Timothy SANDERSON, Stuart QUAYLE
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Publication number: 20190094188Abstract: A method of inspecting a wing box of an aircraft. The wing box includes at least one rib partitioning the wing box in to two bays and at least one stringer attached along an inner surface of the wing box, generally perpendicular to the rib, and extending through an aperture of the rib. The method includes: providing an inspection device on the stringer such that it is movable along the stringer and controlling the inspection device to pass along the stringer, including through the aperture between bays, to perform an inspection of the wing box.Type: ApplicationFiled: September 27, 2018Publication date: March 28, 2019Inventors: Timothy SANDERSON, David BRAWLEY
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Patent number: 9862478Abstract: A modular structural assembly to form part of an aircraft wing that has an outer skin and a plurality of stringers is disclosed. The assembly includes a plurality of panels, each panel having a portion that forms part of the outer skin and at least one stringer integrally formed with said portion.Type: GrantFiled: November 20, 2013Date of Patent: January 9, 2018Assignee: Airbus Operations LimitedInventors: Timothy Sanderson, Jonathan Price, Alexander Black
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Patent number: 9452588Abstract: An adjustable shim comprises a stack of plies comprising plastics material reinforced with a three-dimensional fiber layer, the plastics material being flowable under compressive force prior to cure for adjusting the thickness of the shim. The shim may be used to fill a void between two structural components joined together. Also, a method of filling a void between two structural components using the shim. The shim is easy to handle, can easily be laid up to a variety of thicknesses, and is quick to cure (depending on the plastics material used). The three-dimensional fiber layers make the shim highly compressible prior to cure, and provide significant reinforcement to the plastics material of the plies to support compressive stresses in the shim post cure.Type: GrantFiled: June 28, 2010Date of Patent: September 27, 2016Assignee: Airbus Operations LimitedInventors: Timothy Sanderson, Peter Burchell
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Patent number: 9409328Abstract: A method of curing a composite material. A tool is heated using microwaves. At least a part of the composite material is shielded by reflecting microwaves away from the composite material with a shield. Heat is transferred from the tool through the shield to the composite material. The tool comprises a material which is sensitive to microwaves so that, when microwaves are incident upon the tool, some of the microwaves are absorbed by the microwave-sensitive material, thereby heating the tool.Type: GrantFiled: April 10, 2013Date of Patent: August 9, 2016Assignee: Airbus Operations LimitedInventor: Timothy Sanderson
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Publication number: 20150283766Abstract: A method for forming a laminate component, the method comprising the steps of: a) providing a tool having a moulding surface; b) arranging a stack of ply layers on the moulding surface of the tool; and c) moulding the stack of ply layers over the moulding surface in a moulding process, wherein the tool has a wrinkle control feature in its moulding surface for managing the development of wrinkle in the ply layers during the moulding process, and wherein the wrinkle control feature cooperates with the stack of ply layers during the moulding process to produce a local surface undulation in a nominal surface of the laminate component nearest the tool to either prevent wrinkling in the ply layers or initiate wrinkling in one or more of the ply layers at a predetermined location. Also, a tool having a wrinkle control feature, and a laminate component so formed.Type: ApplicationFiled: June 17, 2015Publication date: October 8, 2015Inventors: Stephen WILLIAMS, Timothy SANDERSON
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Patent number: 9120558Abstract: A telescopic strut comprises a plurality of hollow members arranged to slide one within another between a retracted and an extended position. Adjacent hollow members are arranged to be electrically connected by one or more electrical connector assemblies as the hollow members move between the retracted and extended positions. Each electrical connector assembly includes an electrically conductive pad on one of the hollow members which is in sliding contact with an electrically conductive strip on the other of the hollow members. The telescopic strut may be used to electrically connect a moveable control surface to a fixed aerofoil structure in an aircraft.Type: GrantFiled: November 13, 2014Date of Patent: September 1, 2015Assignee: Airbus Operations LimitedInventor: Timothy Sanderson
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Patent number: 9067371Abstract: A method for forming a laminate component, the method comprising the steps of: a) providing a tool having a molding surface; b) arranging a stack of ply layers on the molding surface of the tool; and c) molding the stack of ply layers over the molding surface in a molding process, wherein the tool has a wrinkle control feature in its molding surface for managing the development of wrinkle in the ply layers during the molding process, and wherein the wrinkle control feature cooperates with the stack of ply layers during the molding process to produce a local surface undulation in a nominal surface of the laminate component nearest the tool to either prevent wrinkling in the ply layers or initiate wrinkling in one or more of the ply layers at a predetermined location. Also, a tool having a wrinkle control feature, and a laminate component so formed.Type: GrantFiled: November 8, 2012Date of Patent: June 30, 2015Assignee: AIRBUS OPERATIONS LIMITEDInventors: Stephen Williams, Timothy Sanderson
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Publication number: 20150069177Abstract: A telescopic strut comprises a plurality of hollow members arranged to slide one within another between a retracted and an extended position. Adjacent hollow members are arranged to be electrically connected by one or more electrical connector assemblies as the hollow members move between the retracted and extended positions. Each electrical connector assembly includes an electrically conductive pad on one of the hollow members which is in sliding contact with an electrically conductive strip on the other of the hollow members. The telescopic strut may be used to electrically connect a moveable control surface to a fixed aerofoil structure in an aircraft.Type: ApplicationFiled: November 13, 2014Publication date: March 12, 2015Inventor: Timothy SANDERSON
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Patent number: 8899529Abstract: A telescopic strut comprises a plurality of hollow members arranged to slide one within another between a retracted and an extended position. Adjacent hollow members are arranged to be electrically connected by one or more electrical connector assemblies as the hollow members move between the retracted and extended positions. Each electrical connector assembly includes an electrically conductive pad on one of the hollow members which is in sliding contact with an electrically conductive strip on the other of the hollow members. The telescopic strut may be used to electrically connect a moveable control surface to a fixed aerofoil structure in an aircraft.Type: GrantFiled: June 16, 2010Date of Patent: December 2, 2014Assignee: Airbus Operations LimitedInventor: Timothy Sanderson
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Publication number: 20140138485Abstract: A modular structural assembly to form part of an aircraft wing that has an outer skin and a plurality of stringers is disclosed. The assembly includes a plurality of panels, each panel having a portion that forms part of the outer skin and at least one stringer integrally formed with said portion.Type: ApplicationFiled: November 20, 2013Publication date: May 22, 2014Applicant: AIRBUS OPERATIONS LIMITEDInventors: Timothy SANDERSON, Jonathan PRICE, Alexander BLACK
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Publication number: 20140084516Abstract: The invention provides a cure tool 10, the tool having a working face 11 for placing a component 20 to be cured upon, wherein the tool is provided with a channel 12 along a length of the working face of the tool. The tool may be further provided with an inflatable member 15 in a length of the channel. The invention also provides a method for curing a component, a component that has been cured by the method and an aircraft comprising one or more components that have been cured by the method.Type: ApplicationFiled: September 19, 2013Publication date: March 27, 2014Applicant: AIRBUS OPERATIONS LIMITEDInventors: Timothy SANDERSON, Stephen WILLIAMS, Jonathan PRICE
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Patent number: 8616499Abstract: A wing structure is provided, wherein the wing structure comprises; an upper covering, a lower covering, and a spar, the spar comprising; a spar web, an upper spar cap attached to the upper covering, and a lower spar cap attached to the lower covering, the wing structure also comprising a face spaced apart from the spar web extending between the upper and lower spar caps. The wing structure is arranged to contain fuel in a fuel containment area between the upper and lower coverings on one side of the spar web. The upper and lower spar caps extend from the spar web only on the other side of the spar web to the fuel containment area.Type: GrantFiled: March 31, 2010Date of Patent: December 31, 2013Assignee: Airbus Operations LimitedInventors: Michael Tucker, Timothy Sanderson
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Publication number: 20130285292Abstract: A method of curing a composite material. A tool is heated using microwaves. At least a part of the composite material is shielded by reflecting microwaves away from the composite material with a shield. Heat is transferred from the tool through the shield to the composite material. The tool comprises a material which is sensitive to microwaves so that, when microwaves are incident upon the tool, some of the microwaves are absorbed by the microwave-sensitive material, thereby heating the tool.Type: ApplicationFiled: April 10, 2013Publication date: October 31, 2013Applicant: Airbus Operations LimitedInventor: Timothy SANDERSON