Patents by Inventor Wesley L. Holman
Wesley L. Holman 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: 20230014027Abstract: A seal assembly includes a first wall extending from a compression side to a fastened side of the seal assembly, a stiffening member embedded within the first wall adjacent to the compression side of the seal assembly, and a second wall exterior of the first wall and extending from the compression side to the fastened side of the seal assembly. When the seal assembly is pressurized, the first wall and the second wall define an insulated pocket.Type: ApplicationFiled: July 19, 2021Publication date: January 19, 2023Applicant: The Boeing CompanyInventors: Jessica Marie-Meyer Ribble, Wesley L. Holman, Stephen R. Byrne, Amy Everson, Huilin Xie, Daniel Freeman, Genesis Marvin S. Pilarca
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Patent number: 10539473Abstract: Methods and systems for monitoring an environment history of a component using an indicator array that includes energy exposure indicator pads direct-printed onto a surface of the component in a geometric pattern. Each of the plurality of energy exposure indicator pads in the geometric pattern may include a mechanochromic material, a first thermochromic indicator responsive within a first temperature range, a second thermochromic indicator responsive within a second temperature range, and a third thermochromic indicator responsive within a third temperature range, provided that the first, second, and third temperature ranges are distinct from one another.Type: GrantFiled: August 8, 2016Date of Patent: January 21, 2020Assignee: The Boeing CompanyInventors: Eric Winter, Gregory Robert Gleason, Wesley L. Holman, Gary Georgeson, Scott Robert Johnston
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Patent number: 10024792Abstract: There is provided a removable chromatic witness assembly, system, and method to monitor thermal events and impact events on a surface of a composite structure. The removable chromatic witness assembly has a plurality of chromatic witness geometric configurations separately coupled in an arrangement to one or more portions of a polymeric film layer. Each chromatic witness geometric configuration has a plurality of chromatic probes of a same type incorporated into an adhesive material. At least two of the geometric configurations have a different type of chromatic probes with a different sensing capability for thermal events and impact events on the composite structure. The polymeric film layer and the geometric configurations form the removable chromatic witness assembly in a form of a removable chromatic witness applique configured to be removably applied directly and continuously to the surface of the composite structure, and configured to monitor the thermal and impact events.Type: GrantFiled: August 8, 2016Date of Patent: July 17, 2018Assignee: The Boeing CompanyInventors: Ryan E. Toivola, Alex Kwan-Yue Jen, Sei-Hum Jang, Brian D. Flinn, Eric G. Winter, Gary E. Georgeson, Wesley L. Holman, Gregory R. Gleason, Scott R. Johnston
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Patent number: 9945735Abstract: There is provided a system, a method, and a thermochromatic witness assembly to monitor a thermal environment of a composite structure. The thermochromatic witness assembly has a polymeric material and one or more thermochromatic probes mixed into the polymeric material to form a thermochromatic probe mixture. The thermochromatic probe mixture is applied to a transparent polymeric film, or is formed into the transparent polymeric film with a pressure sensitive adhesive (PSA) applied thereto, thus forming the thermochromatic witness assembly in a form of a thermochromatic applique. The thermochromatic applique is configured to be applied directly and continuously to a surface of the composite structure. The thermochromatic applique is further configured to monitor the thermal environment of the composite structure by detecting one or more temperatures and one or more times the surface of the composite structure is exposed to the thermal environment.Type: GrantFiled: September 16, 2015Date of Patent: April 17, 2018Assignee: The Boeing CompanyInventors: Gary E. Georgeson, Wesley L. Holman, Jr., Brandon P. Jamison, Randy J. Grove
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Publication number: 20180038744Abstract: Methods and systems for monitoring an environment history of a component using an indicator array that includes energy exposure indicator pads direct-printed onto a surface of the component in a geometric pattern. Each of the plurality of energy exposure indicator pads in the geometric pattern may include a mechanochromic material, a first thermochromic indicator responsive within a first temperature range, a second thermochromic indicator responsive within a second temperature range, and a third thermochromic indicator responsive within a third temperature range, provided that the first, second, and third temperature ranges are distinct from one another.Type: ApplicationFiled: August 8, 2016Publication date: February 8, 2018Applicant: The Boeing CompanyInventors: Eric Winter, Gregory Robert Gleason, Wesley L. Holman, Gary Georgeson, Scott Robert Johnston
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Publication number: 20180038792Abstract: There is provided a removable chromatic witness assembly, system, and method to monitor thermal events and impact events on a surface of a composite structure. The removable chromatic witness assembly has a plurality of chromatic witness geometric configurations separately coupled in an arrangement to one or more portions of a polymeric film layer. Each chromatic witness geometric configuration has a plurality of chromatic probes of a same type incorporated into an adhesive material. At least two of the geometric configurations have a different type of chromatic probes with a different sensing capability for thermal events and impact events on the composite structure. The polymeric film layer and the geometric configurations form the removable chromatic witness assembly in a form of a removable chromatic witness applique configured to be removably applied directly and continuously to the surface of the composite structure, and configured to monitor the thermal and impact events.Type: ApplicationFiled: August 8, 2016Publication date: February 8, 2018Inventors: Ryan E. Toivola, Alex Kwan-Yue Jen, Sei-Hum Jang, Brian D. Flinn, Eric G. Winter, Gary E. Georgeson, Wesley L. Holman, Gregory R. Gleason, Scott R. Johnston
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Publication number: 20160282198Abstract: There is provided a system, a method, and a thermochromatic witness assembly to monitor a thermal environment of a composite structure. The thermochromatic witness assembly has a polymeric material and one or more thermochromatic probes mixed into the polymeric material to form a thermochromatic probe mixture. The thermochromatic probe mixture is applied to a transparent polymeric film, or is formed into the transparent polymeric film with a pressure sensitive adhesive (PSA) applied thereto, thus forming the thermochromatic witness assembly in a form of a thermochromatic applique. The thermochromatic applique is configured to be applied directly and continuously to a surface of the composite structure. The thermochromatic applique is further configured to monitor the thermal environment of the composite structure by detecting one or more temperatures and one or more times the surface of the composite structure is exposed to the thermal environment.Type: ApplicationFiled: September 16, 2015Publication date: September 29, 2016Inventors: Gary E. Georgeson, Wesley L. Holman, JR., Brandon P. Jamison, Randy J. Grove
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Patent number: 8713895Abstract: A structural member such as a strut includes a composite material tube having metal end fittings that are attached to the tube by co-bonded, double shear joints. The double shear bond joint construction reduces the residual stress on the bonds that result from mismatch of the coefficients of thermal expansion of the composite tube and the metal end fittings. The ends of the fittings that are bonded to the tube may include a stepped profile that functions to limit the peak stresses in the bonds.Type: GrantFiled: January 3, 2013Date of Patent: May 6, 2014Assignee: The Boeing CompanyInventors: Christopher T. Allen, Patrick D. Bertrand, Derek J. Fox, William B. Grace, Kenneth M. Harrison, Wesley L. Holman, Menelaos S. Kafkalidis, James R. Schnelz, Edward M. Fisher
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Patent number: 8414992Abstract: In one step of a method of fabricating a composite tube, layers of uncured composite material may be laid over a surface. In another step, spaced-apart strips of at least one of uncured, partially cured, and completely cured composite material may be laid lengthwise over the laid layers of composite material. In still another step, the spaced-apart strips may be compacted against the layers of uncured composite material. In an additional step, the compacted spaced-apart strips and the layers of uncured composite material may be further consolidated and/or cured to form a composite tube.Type: GrantFiled: January 13, 2012Date of Patent: April 9, 2013Assignee: The Boeing CompanyInventors: Garry A. Booker, Wesley L. Holman
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Patent number: 8365502Abstract: A structural member such as a strut includes a composite material tube having metal end fittings that are attached to the tube by co-bonded, double shear joints. The double shear bond joint construction reduces the residual stress on the bonds that result from mismatch of the coefficients of thermal expansion of the composite tube and the metal end fittings. The ends of the fittings that are bonded to the tube may include a stepped profile that functions to limit the peak stresses in the bonds.Type: GrantFiled: May 11, 2007Date of Patent: February 5, 2013Assignee: The Boeing CompanyInventors: Christopher T. Allen, Patrick D. Bertrand, Derek J. Fox, William B. H. Grace, Kenneth M. Harrison, Wesley L. Holman, Menelaos S. Kafkalidis, James R. Schnelz, Edward M. Fisher
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Publication number: 20120141705Abstract: In one step of a method of fabricating a composite tube, layers of uncured composite material may be laid over a surface. In another step, spaced-apart strips of at least one of uncured, partially cured, and completely cured composite material may be laid lengthwise over the laid layers of composite material. In still another step, the spaced-apart strips may be compacted against the layers of uncured composite material. In an additional step, the compacted spaced-apart strips and the layers of uncured composite material may be further consolidated and/or cured to form a composite tube.Type: ApplicationFiled: January 13, 2012Publication date: June 7, 2012Applicant: THE BOEING COMPANYInventors: Garry A. Booker, Wesley L. Holman
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Patent number: 8123996Abstract: In one step of a method of fabricating a composite tube, layers of uncured composite material may be laid over a surface. In another step, spaced-apart strips of at least one of uncured, partially cured, and completely cured composite material may be laid lengthwise over the laid layers of composite material. In still another step, the spaced-apart strips may be compacted against the layers of uncured composite material. In an additional step, the compacted spaced-apart strips and the layers of uncured composite material may be further consolidated and/or cured to form a composite tube.Type: GrantFiled: February 7, 2008Date of Patent: February 28, 2012Assignee: The Boeing CompanyInventors: Garry A. Booker, Wesley L. Holman
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Publication number: 20090202767Abstract: In one step of a method of fabricating a composite tube, layers of uncured composite material may be laid over a surface. In another step, spaced-apart strips of at least one of uncured, partially cured, and completely cured composite material may be laid lengthwise over the laid layers of composite material. In still another step, the spaced-apart strips may be compacted against the layers of uncured composite material. In an additional step, the compacted spaced-apart strips and the layers of uncured composite material may be further consolidated and/or cured to form a composite tube.Type: ApplicationFiled: February 7, 2008Publication date: August 13, 2009Applicant: THE BOEING COMPANYInventors: GARRY A. BOOKER, WESLEY L. HOLMAN
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Publication number: 20080129041Abstract: A structural member such as a strut includes a composite material tube having metal end fittings that are attached to the tube by co-bonded, double shear joints. The double shear bond joint construction reduces the residual stress on the bonds that result from mismatch of the coefficients of thermal expansion of the composite tube and the metal end fittings. The ends of the fittings that are bonded to the tube may include a stepped profile that functions to limit the peak stresses in the bonds.Type: ApplicationFiled: May 11, 2007Publication date: June 5, 2008Inventors: Christopher T. Allen, Patrick D. Bertrand, Derek J. Fox, William B.H. Grace, Kenneth M. Harrison, Wesley L. Holman, Menelaso S. Kafkalidis, James R. Schnelz, Edward M. Fisher
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Patent number: 5654060Abstract: An insulating blanket for a bulkhead in an engine nacelle comprises a fabric backing layer, a central insulating core, a ceramic precursor-impregnated hot-side fabric layer and, as required, erosion-preventing wire mesh. The backing layer comprises a fiberglass fabric. The insulating core comprises a ceramic felt. The hot side layer comprises one or more layers of resin-impregnated fiber glass fabric. The blanket is precured to provide a predetermined geometric shape.Type: GrantFiled: June 16, 1995Date of Patent: August 5, 1997Assignee: The Boeing CompanyInventors: Wesley L. Holman, Frederick L. Knoll