Patents by Inventor Russell L. Keller
Russell L. Keller 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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Publication number: 20220268663Abstract: Non-destructive testing apparatuses, systems, and methods for assessing strain in structural components are disclosed. Structural components include induced predetermined regions having materials of varying density, including induced geometric patterns of differing densities within the structural component that can be a composite material structural component. The method includes projecting waves of energy, that can be beams of electromagnetic (EM) energy and/or waves of ultrasonic (UT) energy, into or through the structural component to evaluate the predetermined induced pattern region of varying density and determining existing strain within a structural component based on the detected energy response.Type: ApplicationFiled: January 19, 2022Publication date: August 25, 2022Inventors: Russell L. Keller, Gary E. Georgeson, Kenneth H. Griess
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Patent number: 11243071Abstract: Systems and methods for assessing strain in structural components are disclosed. Structural components may have geometric patterns of diffraction cavities within the structural component, with the diffraction cavities in the geometric pattern each having a cavity width and being spaced from each other by a cavity spacing distance. The method may include projecting beams of electromagnetic (EM) energy through the structural component to the geometric pattern of diffraction cavities to create diffracted beams of EM energy that are reflected from or transmitted through the geometric pattern of diffraction cavities and have diffracted wavelengths indicating changes in the cavity spacing distances due to strain caused when the structural component is exposed to environmental conditions, detecting the diffracted wavelength of the diffracted beams, and correlating the diffracted wavelengths of the diffracted beams to the strain in the structural components.Type: GrantFiled: February 3, 2020Date of Patent: February 8, 2022Assignee: The Boeing CompanyInventors: Gary E. Georgeson, Kenneth H. Griess, Russell L. Keller
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Publication number: 20210239460Abstract: Systems and methods for assessing strain in structural components are disclosed. Structural components may have geometric patterns of diffraction cavities within the structural component, with the diffraction cavities in the geometric pattern each having a cavity width and being spaced from each other by a cavity spacing distance. The method may include projecting beams of electromagnetic (EM) energy through the structural component to the geometric pattern of diffraction cavities to create diffracted beams of EM energy that are reflected from or transmitted through the geometric pattern of diffraction cavities and have diffracted wavelengths indicating changes in the cavity spacing distances due to strain caused when the structural component is exposed to environmental conditions, detecting the diffracted wavelength of the diffracted beams, and correlating the diffracted wavelengths of the diffracted beams to the strain in the structural components.Type: ApplicationFiled: February 3, 2020Publication date: August 5, 2021Applicant: The Boeing CompanyInventors: Gary E. Georgeson, Kenneth H. Griess, Russell L. Keller
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Patent number: 10989523Abstract: Systems and methods for assessing strain in structural components are disclosed. Structural components may have geometric patterns of grooves within the structural component, with the grooves in the geometric pattern each having a groove width. The method may include projecting beams of electromagnetic (EM) energy through the structural component to the geometric pattern of grooves to create diffracted beams of EM energy that are reflected from or transmitted through the geometric pattern of grooves and have diffracted wavelengths indicating changes in the groove widths due to strain caused when the structural component is exposed to environmental conditions, detecting the diffracted wavelength of the diffracted beams, and correlating the diffracted wavelengths of the diffracted beams to the strain in the structural components.Type: GrantFiled: March 14, 2019Date of Patent: April 27, 2021Assignee: The Boeing CompanyInventors: Gary E. Georgeson, Kenneth H. Griess, Russell L. Keller
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Patent number: 10801833Abstract: Systems and methods for assessing strain in structural components are disclosed. Structural component may have geometric patterns of grooves, with the grooves in the geometric pattern each having a groove width. The method may include illuminating the geometric pattern of grooves with a first light at a first wavelength that corresponds to the groove width to create diffraction when the first light hits the geometric pattern of grooves and corresponding changes in the wavelength of the light reflected from the geometric pattern of grooves indicating changes in the groove widths due to strain caused when the structural component is exposed to environmental conditions, detecting the wavelength of the light reflected from the geometric pattern of grooves, and correlating the detected wavelength of the light reflected from the geometric pattern of grooves to the strain in the structural components.Type: GrantFiled: April 9, 2018Date of Patent: October 13, 2020Assignee: The Boeing CompanyInventors: Gary E. Georgeson, Kenneth H. Griess, Russell L. Keller
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Publication number: 20200292302Abstract: Systems and methods for assessing strain in structural components are disclosed. Structural components may have geometric patterns of grooves within the structural component, with the grooves in the geometric pattern each having a groove width. The method may include projecting beams of electromagnetic (EM) energy through the structural component to the geometric pattern of grooves to create diffracted beams of EM energy that are reflected from or transmitted through the geometric pattern of grooves and have diffracted wavelengths indicating changes in the groove widths due to strain caused when the structural component is exposed to environmental conditions, detecting the diffracted wavelength of the diffracted beams, and correlating the diffracted wavelengths of the diffracted beams to the strain in the structural components.Type: ApplicationFiled: March 14, 2019Publication date: September 17, 2020Applicant: The Boeing CompanyInventors: Gary E. Georgeson, Kenneth H. Griess, Russell L. Keller
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Publication number: 20190310076Abstract: Systems and methods for assessing strain in structural components are disclosed. Structural component may have geometric patterns of grooves, with the grooves in the geometric pattern each having a groove width. The method may include illuminating the geometric pattern of grooves with a first light at a first wavelength that corresponds to the groove width to create diffraction when the first light hits the geometric pattern of grooves and corresponding changes in the wavelength of the light reflected from the geometric pattern of grooves indicating changes in the groove widths due to strain caused when the structural component is exposed to environmental conditions, detecting the wavelength of the light reflected from the geometric pattern of grooves, and correlating the detected wavelength of the light reflected from the geometric pattern of grooves to the strain in the structural components.Type: ApplicationFiled: April 9, 2018Publication date: October 10, 2019Applicant: The Boeing CompanyInventors: Gary E. Georgeson, Kenneth H. Griess, Russell L. Keller
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Patent number: 10000019Abstract: An installation assembly and an associated method for forming a bonded join are provided to permit the adhesive attachment of a first workpiece, such as a patch, to a portion of a second workpiece. The installation assembly and the associated method provide for at least partial debulking of the adhesive prior to curing of the adhesive such that the resulting bondline may have improved mechanical properties as a result of having fewer voids and/or porosity. The installation assembly may include an installation stand and a carrier plate supported by the installation stand and including an attachment surface configured to carry the first workpiece. The installation stand also includes an adjustment mechanism for positioning a carrier plate to a first predefined position to define a gap between the first and second workpieces and also to a second predefined position such that a predetermined bondline thickness is defined between the first and second workpieces.Type: GrantFiled: April 8, 2016Date of Patent: June 19, 2018Assignee: The Boeing CompanyInventors: Michael W. Evens, Megan Nicole Watson, Russell L. Keller, Nicholas H. Room, John F. Spalding, Mary Helen Vargas, James D. Chanes, Kathy Lynn Ferguson, Joseph Lawrence Hafenrichter
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Publication number: 20160221257Abstract: An installation assembly and an associated method for forming a bonded join are provided to permit the adhesive attachment of a first workpiece, such as a patch, to a portion of a second workpiece. The installation assembly and the associated method provide for at least partial debulking of the adhesive prior to curing of the adhesive such that the resulting bondline may have improved mechanical properties as a result of having fewer voids and/or porosity. The installation assembly may include an installation stand and a carrier plate supported by the installation stand and including an attachment surface configured to carry the first workpiece. The installation stand also includes an adjustment mechanism for positioning a carrier plate to a first predefined position to define a gap between the first and second workpieces and also to a second predefined position such that a predetermined bondline thickness is defined between the first and second workpieces.Type: ApplicationFiled: April 8, 2016Publication date: August 4, 2016Inventors: Michael W. Evens, Megan Nicole Watson, Russell L. Keller, Nicholas H. Room, John F. Spalding, Mary Helen Vargas, James D. Chanes, Kathy Lynn Ferguson, Joesph Lawrence Hafenrichter
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Patent number: 9393768Abstract: A repair patch for reworking an inconsistent area of a composite structure includes a patch body adapted to cover the inconsistent area and having a first patch region, a second patch region outside the first patch region and a first separation zone between the first patch region and the second patch region, with the first patch region, the first separation zone and the second patch region having increasing interlaminar fracture toughness from a center to an edge of the patch body; and a layer of adhesive for bonding the patch body to the composite structure.Type: GrantFiled: November 20, 2013Date of Patent: July 19, 2016Assignee: The Boeing CompanyInventors: Eugene A. Dan-Jumbo, Russell L. Keller, Everett A. Westerman
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Patent number: 9393651Abstract: A composite laminate patch for reworking an inconsistent area in a structure has inner and outer control regions possessing differing interlaminar fracture toughnesses for controlling the advance of a disbond in the patch. One or more separation zones in the patch between the control regions aids in diffusing the fracture energy of the disbond as the disbond advances from the inner region to the outer region.Type: GrantFiled: July 18, 2013Date of Patent: July 19, 2016Assignee: The Boeing CompanyInventors: Eugene A. Dan-Jumbo, Russell L. Keller, Everett A. Westerman
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Patent number: 9308688Abstract: An installation assembly and an associated method for forming a bonded join are provided to permit the adhesive attachment of a first workpiece, such as a patch, to a portion of a second workpiece. The installation assembly and the associated method provide for at least partial debulking of the adhesive prior to curing of the adhesive such that the resulting bondline may have improved mechanical properties as a result of having fewer voids and/or porosity. The installation assembly may include an installation stand and a carrier plate supported by the installation stand and including an attachment surface configured to carry the first workpiece. The installation stand also includes an adjustment mechanism for positioning a carrier plate to a first predefined position to define a gap between the first and second workpieces and also to a second predefined position such that a predetermined bondline thickness is defined between the first and second workpieces.Type: GrantFiled: March 20, 2013Date of Patent: April 12, 2016Assignee: The Boeing CompanyInventors: Michael W. Evens, Megan Nicole Watson, Russell L. Keller, Nicholas H. Room, John F. Spalding, Mary Helen Vargas, James D. Chanes, Kathy Lynn Ferguson, Joesph Lawrence Hafenrichter
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Patent number: 8828515Abstract: A patch for reworking an inconsistent area in a composite structure includes a composite laminate patch and a layer of adhesive for bonding the laminate patch to the composite structure. The laminate patch has at least first and second regions for releasing strain energy around the inconsistent area respectively at different rates.Type: GrantFiled: May 26, 2013Date of Patent: September 9, 2014Assignee: The Boeing CompanyInventors: Eugene A. Dan-Jumbo, Russell L. Keller, Everett A. Westerman
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Patent number: 8802213Abstract: A patch for reworking an inconsistent area in a composite structure includes a composite laminate patch adapted to cover the inconsistent area and bonded to the structure by a layer of adhesive. The patch includes a plurality of composite plies having a tapered cross section, and at least first and second regions respectively having differing fracture toughnesses.Type: GrantFiled: May 27, 2013Date of Patent: August 12, 2014Assignee: The Boeing CompanyInventors: Eugene A. Dan-Jumbo, Russell L. Keller, Everett A. Westerman
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Publication number: 20140076481Abstract: A repair patch for reworking an inconsistent area of a composite structure includes a patch body adapted to cover the inconsistent area and having a first patch region, a second patch region outside the first patch region and a first separation zone between the first patch region and the second patch region, with the first patch region, the first separation zone and the second patch region having increasing interlaminar fracture toughness from a center to an edge of the patch body; and a layer of adhesive for bonding the patch body to the composite structure.Type: ApplicationFiled: November 20, 2013Publication date: March 20, 2014Applicant: The Boeing CompanyInventors: Eugene A. Dan-Jumbo, Russell L. Keller, Everett A. Westerman
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Publication number: 20140020221Abstract: A composite laminate patch for reworking an inconsistent area in a structure has inner and outer control regions possessing differing interlaminar fracture toughnesses for controlling the advance of a disbond in the patch. One or more separation zones in the patch between the control regions aids in diffusing the fracture energy of the disbond as the disbond advances from the inner region to the outer region.Type: ApplicationFiled: July 18, 2013Publication date: January 23, 2014Inventors: Eugene A. Dan-Jumbo, Russell L. Keller, Everett A. Westerman
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Patent number: 8617694Abstract: A repair patch for reworking an inconsistent area of a composite structure includes a patch body adapted to cover the inconsistent area and having a first patch region, a second patch region outside the first patch region and a first separation zone between the first patch region and the second patch region, with the first patch region, the first separation zone and the second patch region having increasing interlaminar fracture toughness from a center to an edge of the patch body; and a layer of adhesive for bonding the patch body to the composite structure.Type: GrantFiled: October 13, 2010Date of Patent: December 31, 2013Assignee: The Boeing CompanyInventors: Eugene A. Dan-Jumbo, Russell L Keller, Everett A. Westerman
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Publication number: 20130337214Abstract: A patch for reworking an inconsistent area in a composite structure includes a composite laminate patch and a layer of adhesive for bonding the laminate patch to the composite structure. The laminate patch has at least first and second regions for releasing strain energy around the inconsistent area respectively at different rates.Type: ApplicationFiled: May 26, 2013Publication date: December 19, 2013Applicant: The Boeing CompanyInventors: Eugene A. Dan-Jumbo, Russell L. Keller, Everett A. Westerman
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Patent number: 8581736Abstract: A strain measurement device to assess the integrity of a structural repair to a surface comprises a detector, a processor, and a memory module coupled to the processor. The memory module comprises logic instructions stored in a computer readable medium which, when executed by the processor, configure the processor to use the detector to obtain a first strain measurement from an external strain indicator, use the detector to obtain a second strain measurement from the measurement sensor after at least one stress test is applied to the structural repair, and generate a signal when a difference between the first strain measurement and the second strain measurement exceeds a threshold.Type: GrantFiled: June 24, 2010Date of Patent: November 12, 2013Assignee: The Boeing CompanyInventors: Keith L. McIver, Aristidis Sidiropoulos, Russell L. Keller, Cong N. Duong
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Publication number: 20130260077Abstract: A patch for reworking an inconsistent area in a composite structure includes a composite laminate patch adapted to cover the inconsistent area and bonded to the structure by a layer of adhesive. The patch includes a plurality of composite plies having a tapered cross section, and at least first and second regions respectively having differing fracture toughnesses.Type: ApplicationFiled: May 27, 2013Publication date: October 3, 2013Inventors: Eugene A. Dan-Jumbo, Russell L. Keller, Everett A. Westerman