Patents by Inventor Wei-Yueh Lee
Wei-Yueh Lee 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: 11566984Abstract: A method of offset load testing a tubular composite specimen with two pairs of aligned holes and having at least one defect, the method comprising: providing a testing apparatus having a pair of arms including a fixed arm and a mobile arm; securing the pair of arms using a fastener assembly in each of the two pairs of aligned holes; and moving the mobile arm to impart an offset load force to the tubular specimen. One aspect includes a method of offset load testing comprising: providing a testing apparatus having a pair of arms including a fixed arm and a mobile arm; providing a tubular composite specimen with a top portion and a bottom portion; securing the pair of arms to the top and bottom portions of the tubular composite specimen; and moving the mobile arm to impart an offset load force to the tubular composite specimen.Type: GrantFiled: July 8, 2020Date of Patent: January 31, 2023Assignee: Textron Innovations, Inc.Inventors: Wei-Yueh Lee, Michael Burnett, Michael Dearman
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Patent number: 11440276Abstract: In an aspect, there is a method of determining allowable defects for a composite component comprising identifying at least one wrinkle characteristic of a composite component wrinkle defect; making a first plurality of specimens each having a predetermined wrinkle defect representative of the composite component wrinkle defect; measuring each of the predetermined wrinkle defects in the first plurality of specimens for at least one performance metric to generate performance data; and generating an allowable wrinkle defect profile based on the performance data from the first plurality of specimens. In other aspects, there are methods of making a specimen with a predetermined wrinkle defect.Type: GrantFiled: July 7, 2020Date of Patent: September 13, 2022Assignee: Textron Innovations Inc.Inventors: Michael Burnett, Wei-Yueh Lee, Michael Dearman
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Patent number: 11020910Abstract: The present invention includes methods of preparing a composite structure comprising: placing a first ply of a fibrous material with a curable material on a layup tool; adding one or more additional plies on the first ply, wherein each of the one or more additional plies has a perimeter that is different in size around the perimeter than a previous ply to form a taper; and curing the composite structure, wherein the curable material is selected to minimize, limit, control, or eliminate the outflow of the curable material along the perimeter of the composite structure during the curing step.Type: GrantFiled: May 13, 2016Date of Patent: June 1, 2021Assignee: BELL HELICOPTER TEXTRON INC.Inventors: Amarjit Olenchery Kizhakkepat, Tyler Wayne Baldwin, Edward Wei-Yueh Lee
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Publication number: 20200340894Abstract: A method of offset load testing a tubular composite specimen with two pairs of aligned holes and having at least one defect, the method comprising: providing a testing apparatus having a pair of arms including a fixed arm and a mobile arm; securing the pair of arms using a fastener assembly in each of the two pairs of aligned holes; and moving the mobile arm to impart an offset load force to the tubular specimen. One aspect includes a method of offset load testing comprising: providing a testing apparatus having a pair of arms including a fixed arm and a mobile arm; providing a tubular composite specimen with a top portion and a bottom portion; securing the pair of arms to the top and bottom portions of the tubular composite specimen; and moving the mobile arm to impart an offset load force to the tubular composite specimen.Type: ApplicationFiled: July 8, 2020Publication date: October 29, 2020Applicant: Bell Textron Inc.Inventors: Wei-Yueh Lee, Michael Burnett, Michael Dearman
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Publication number: 20200331216Abstract: In an aspect, there is a method of determining allowable defects for a composite component comprising identifying at least one wrinkle characteristic of a composite component wrinkle defect; making a first plurality of specimens each having a predetermined wrinkle defect representative of the composite component wrinkle defect; measuring each of the predetermined wrinkle defects in the first plurality of specimens for at least one performance metric to generate performance data; and generating an allowable wrinkle defect profile based on the performance data from the first plurality of specimens. In other aspects, there are methods of making a specimen with a predetermined wrinkle defect.Type: ApplicationFiled: July 7, 2020Publication date: October 22, 2020Applicant: Bell Textron Inc.Inventors: Michael Burnett, Wei-Yueh Lee, Michael Dearman
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Patent number: 10744727Abstract: In a first aspect, there is a method of making a specimen with a predetermined wrinkle defect, the steps including orienting a composite material around a layup tool at a wrap angle to form a closed loop; and generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of determining allowable defects for a composite component.Type: GrantFiled: March 21, 2017Date of Patent: August 18, 2020Assignee: Textron Innovations Inc.Inventors: Michael Burnett, Wei-Yueh Lee, Michael Dearman
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Patent number: 10746640Abstract: There is a method of making a tubular specimen with a predetermined wrinkle defect including providing a layup tool with a cavity forming member having a cavity which resembles a desired shape of the at least one wrinkle; orienting a composite material around the mandrel at a wrap angle to form a closed loop; positioning a wrinkle tool on the closed loop; and/or generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a tubular specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of offset load testing a tubular composite specimen. In a third aspect, there is a method of determining allowable defects for a composite component.Type: GrantFiled: March 21, 2017Date of Patent: August 18, 2020Assignee: Textron Innovations Inc.Inventors: Wei-Yueh Lee, Michael Burnett, Michael Dearman
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Patent number: 10669021Abstract: An airfoil member can have a root end, a tip end, a leading edge, and a trailing edge. The airfoil member can include an upper skin, a lower skin, and a composite core member having a plurality of cells, an upper surface network of the cells can be bonded to the upper skin, a lower surface network of the cells can be bonded to the lower skin. The composite core can have a septum layer embedded in the cells that form the composite core, the septum layer being configured to provide tailored characteristics of the airfoil member.Type: GrantFiled: September 10, 2013Date of Patent: June 2, 2020Assignee: Textron Innovations Inc.Inventors: Paul K. Oldroyd, Wei-Yueh Lee, James D. Hethcock, Jr., John R. McCullough, Patrick R. Tisdale
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Publication number: 20190240876Abstract: A method is provided in one example embodiment and may include forming a ply stack on a tool, the ply stack comprising a plurality of plies; compacting the ply stack; and heating the ply stack during the compacting to form a composite structure, wherein the heating is caused by an electromagnetic inductive device or a radiative device. Compacting the ply stack can include encapsulating the ply stack within a bag and increasing a vacuum within the bag to increase external pressure on the bag and the ply stack.Type: ApplicationFiled: February 7, 2018Publication date: August 8, 2019Inventors: Wei-Yueh Lee, Paul K. Oldroyd
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Publication number: 20180272629Abstract: In a first aspect, there is a method of making a specimen with a predetermined wrinkle defect, the steps including orienting a composite material around a layup tool at a wrap angle to form a closed loop; and generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of determining allowable defects for a composite component.Type: ApplicationFiled: March 21, 2017Publication date: September 27, 2018Applicant: Bell Helicopter Textron Inc.Inventors: Michael Burnett, Wei-Yueh Lee, Michael Dearman
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Publication number: 20180275030Abstract: There is a method of making a tubular specimen with a predetermined wrinkle defect including providing a layup tool with a cavity forming member having a cavity which resembles a desired shape of the at least one wrinkle; orienting a composite material around the mandrel at a wrap angle to form a closed loop; positioning a wrinkle tool on the closed loop; and/or generating at least one wrinkle with a predetermined characteristic in a portion of the closed loop to form a tubular specimen. The predetermined characteristic is at least one of the following: wrinkle location, an outward wrinkle, an inward wrinkle, a wrinkle width, a wrinkle height, and a wrinkle length. In another aspect, there is a method of offset load testing a tubular composite specimen. In a third aspect, there is a method of determining allowable defects for a composite component.Type: ApplicationFiled: March 21, 2017Publication date: September 27, 2018Applicant: Bell Helicopter Textron Inc.Inventors: Wei-Yueh Lee, Michael Burnett, Michael Dearman
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Publication number: 20170326808Abstract: The present invention includes methods of preparing a composite structure comprising: placing a first ply of a fibrous material with a curable material on a layup tool; adding one or more additional plies on the first ply, wherein each of the one or more additional plies has a perimeter that is different in size around the perimeter than a previous ply to form a taper; and curing the composite structure, wherein the curable material is selected to minimize, limit, control, or eliminate the outflow of the curable material along the perimeter of the composite structure during the curing step.Type: ApplicationFiled: May 13, 2016Publication date: November 16, 2017Inventors: Amarjit Olenchery Kizhakkepat, Tyler Wayne Baldwin, Edward Wei-Yueh Lee
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Patent number: 9783289Abstract: The present application relates a core member for a core-stiffened structural assembly. The core member includes a plurality of cell members oriented a direction to provide a tailored stiffness in a certain direction. The core member can further include one or more planar members that can aid in shear transfer between cell members. The cell members can be made from bonding a plurality of corrugated layers together. The core-stiffened structure can be a rotor blade for an aircraft. In such an embodiment, the torsional stiffness of the rotor blade can be tailored in at least one of the chordwise and spanwise directions to provide tailor a torsional stiffness at any give location in the rotor blade.Type: GrantFiled: July 31, 2015Date of Patent: October 10, 2017Assignee: Textron Innovations Inc.Inventors: Wei-Yueh Lee, Paul Oldroyd
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Publication number: 20150367936Abstract: The present application relates a core member for a core-stiffened structural assembly. The core member includes a plurality of cell members oriented a direction to provide a tailored stiffness in a certain direction. The core member can further include one or more planar members that can aid in shear transfer between cell members. The cell members can be made from bonding a plurality of corrugated layers together. The core-stiffened structure can be a rotor blade for an aircraft. In such an embodiment, the torsional stiffness of the rotor blade can be tailored in at least one of the chordwise and spanwise directions to provide tailor a torsional stiffness at any give location in the rotor blade.Type: ApplicationFiled: July 31, 2015Publication date: December 24, 2015Applicant: TEXTRON INNOVATIONS INC.Inventors: Wei-Yueh Lee, Paul Oldroyd
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Patent number: 9205605Abstract: A multi-function detection liner is applied to a non-cured composite material at the point of manufacturing for building a composite part. The detection liner includes a first insulative layer and a first conductive layer. The detection liner is configured to be detectable from a plurality of non-destructive inspection tests. The first insulative layer is detectable by ultrasound and radiograph within the composite part. The first conductive layer is configured to provide an eddy current signal and to enhance ultrasound attenuation of the detection liner within the composite part. Alternatively, the detection liner may include an integrated layer that combines the functions of an insulative layer and a conductive layer. The detection liner is releasably bonded to a surface of the non-cured composite material.Type: GrantFiled: April 25, 2012Date of Patent: December 8, 2015Assignee: Textron Innovations Inc.Inventor: Wei-Yueh Lee
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Patent number: 9096316Abstract: The present application relates a core member for a core-stiffened structural assembly. The core member includes a plurality of cell members oriented a direction to provide a tailored stiffness in a certain direction. The core member can further include one or more planar members that can aid in shear transfer between cell members. The cell members can be made from bonding a plurality of corrugated layers together. The core-stiffened structure can be a rotor blade for an aircraft. In such an embodiment, the torsional stiffness of the rotor blade can be tailored in at least one of the chordwise and spanwise directions to provide tailor a torsional stiffness at any give location in the rotor blade.Type: GrantFiled: February 1, 2012Date of Patent: August 4, 2015Assignee: Textron Innovations Inc.Inventors: Wei-Yueh Lee, Paul Oldroyd
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Publication number: 20140301856Abstract: An airfoil member can have a root end, a tip end, a leading edge, and a trailing edge. The airfoil member can include an upper skin, a lower skin, and a composite core member having a plurality of cells, an upper surface network of the cells can be bonded to the upper skin, a lower surface network of the cells can be bonded to the lower skin. The composite core can have a septum layer embedded in the cells that form the composite core, the septum layer being configured to provide tailored characteristics of the airfoil member.Type: ApplicationFiled: September 10, 2013Publication date: October 9, 2014Applicant: Bell Helicopter Textron Inc.Inventors: Paul K. Oldroyd, Wei-Yueh Lee, James D. Hethcock, JR., John R. McCullough, Patrick R. Tisdale
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Publication number: 20130283920Abstract: A multi-function detection liner is applied to a non-cured composite material at the point of manufacturing for building a composite part. The detection liner includes a first insulative layer and a first conductive layer. The detection liner is configured to be detectable from a plurality of non-destructive inspection tests. The first insulative layer is detectable by ultrasound and radiograph within the composite part. The first conductive layer is configured to provide an eddy current signal and to enhance ultrasound attenuation of the detection liner within the composite part. Alternatively, the detection liner may include an integrated layer that combines the functions of an insulative layer and a conductive layer. The detection liner is releasably bonded to a surface of the non-cured composite material.Type: ApplicationFiled: April 25, 2012Publication date: October 31, 2013Applicant: BELL HELICOPTER TEXTRON INC.Inventor: Wei-Yueh Lee
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Publication number: 20130195672Abstract: The present application relates a core member for a core-stiffened structural assembly. The core member includes a plurality of cell members oriented a direction to provide a tailored stiffness in a certain direction. The core member can further include one or more planar members that can aid in shear transfer between cell members. The cell members can be made from bonding a plurality of corrugated layers together. The core-stiffened structure can be a rotor blade for an aircraft. In such an embodiment, the torsional stiffness of the rotor blade can be tailored in at least one of the chordwise and spanwise directions to provide tailor a torsional stiffness at any give location in the rotor blade.Type: ApplicationFiled: February 1, 2012Publication date: August 1, 2013Applicant: BELL HICOPTER TEXTRON INC.Inventors: Wei-Yueh Lee, Paul Oldroyd