Patents by Inventor Gregory B. Doty
Gregory B. Doty 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: 10308344Abstract: The disclosure herein provides for disbond resistant stringer runouts. Various aspects may be used independently or in combination to mitigate disbonding associated with the stiffener runout under operational loads. Aspects include a stiffener runout having rounded base flange corners. A recessed notch may be incorporated within the base flange to provide a flange termination point that is forward of the web termination point, allowing the web to terminate prior to the base flange. The web may be trimmed from a full height to a reduced height at the web termination point. The base flange may be co-bonded to the underlying composite structure via a scarf joint. Perimeter clamp radius fillers may be used to concentrate a clamping force around the perimeter of the base flange.Type: GrantFiled: May 11, 2017Date of Patent: June 4, 2019Assignee: The Boeing CompanyInventors: Lyle R. Deobald, Kenneth L. Brook, Timothy D. Jackson, Kenneth J. Duffie, Gregory B. Doty
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Publication number: 20170246830Abstract: The disclosure herein provides for disbond resistant stringer runouts. Various aspects may be used independently or in combination to mitigate disbonding associated with the stiffener runout under operational loads. Aspects include a stiffener runout having rounded base flange corners. A recessed notch may be incorporated within the base flange to provide a flange termination point that is forward of the web termination point, allowing the web to terminate prior to the base flange. The web may be trimmed from a full height to a reduced height at the web termination point. The base flange may be co-bonded to the underlying composite structure via a scarf joint. Perimeter clamp radius fillers may be used to concentrate a clamping force around the perimeter of the base flange.Type: ApplicationFiled: May 11, 2017Publication date: August 31, 2017Applicant: The Boeing CompanyInventors: Lyle R. Deobald, Kenneth L. Brook, Timothy D. Jackson, Kenneth J. Duffie, Gregory B. Doty
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Patent number: 9676470Abstract: The disclosure herein provides for disbond resistant stringer runouts. Various aspects may be used independently or in combination to mitigate disbonding associated with the stiffener runout under operational loads. Aspects include a stiffener runout having rounded base flange corners. A recessed notch may be incorporated within the base flange to provide a flange termination point that is forward of the web termination point, allowing the web to terminate prior to the base flange. The web may be trimmed from a full height to a reduced height at the web termination point. The base flange may be co-bonded to the underlying composite structure via a scarf joint. Perimeter clamp radius fillers may be used to concentrate a clamping force around the perimeter of the base flange.Type: GrantFiled: March 9, 2015Date of Patent: June 13, 2017Assignee: The Boeing CompanyInventors: Lyle R. Deobald, Kenneth L. Brook, Timothy D. Jackson, Kenneth J. Duffie, Gregory B. Doty
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Publication number: 20150175250Abstract: The disclosure herein provides for disbond resistant stringer runouts. Various aspects may be used independently or in combination to mitigate disbonding associated with the stiffener runout under operational loads. Aspects include a stiffener runout having rounded base flange corners. A recessed notch may be incorporated within the base flange to provide a flange termination point that is forward of the web termination point, allowing the web to terminate prior to the base flange. The web may be trimmed from a full height to a reduced height at the web termination point. The base flange may be co-bonded to the underlying composite structure via a scarf joint. Perimeter clamp radius fillers may be used to concentrate a clamping force around the perimeter of the base flange.Type: ApplicationFiled: March 9, 2015Publication date: June 25, 2015Inventors: Lyle R. Deobald, Kenneth L. Brook, Timothy D. Jackson, Kenneth J. Duffie, Gregory B. Doty
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Patent number: 8974886Abstract: The disclosure herein provides for disbond resistant stringer runouts. Various aspects may be used independently or in combination to mitigate disbonding associated with the stiffener runout under operational loads. Aspects include a stiffener runout having rounded base flange corners. A recessed notch may be incorporated within the base flange to provide a flange termination point that is forward of the web termination point, allowing the web to terminate prior to the base flange. The web may be trimmed from a full height to a reduced height at the web termination point. The base flange may be co-bonded to the underlying composite structure via a scarf joint. Perimeter clamp radius fillers may be used to concentrate a clamping force around the perimeter of the base flange.Type: GrantFiled: April 25, 2012Date of Patent: March 10, 2015Assignee: The Boeing CompanyInventors: Lyle Ray Deobald, Kenneth L. Brook, Timothy D. Jackson, Kenneth John Duffié, Gregory B. Doty
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Publication number: 20130287995Abstract: The disclosure herein provides for disbond resistant stringer runouts. Various aspects may be used independently or in combination to mitigate disbonding associated with the stiffener runout under operational loads. Aspects include a stiffener runout having rounded base flange corners. A recessed notch may be incorporated within the base flange to provide a flange termination point that is forward of the web termination point, allowing the web to terminate prior to the base flange. The web may be trimmed from a full height to a reduced height at the web termination point. The base flange may be co-bonded to the underlying composite structure via a scarf joint. Perimeter clamp radius fillers may be used to concentrate a clamping force around the perimeter of the base flange.Type: ApplicationFiled: April 25, 2012Publication date: October 31, 2013Inventors: Lyle Ray Deobald, Kenneth L. Brook, Timothy D. Jackson, Kenneth John Duffié, Gregory B. Doty
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Patent number: 7721995Abstract: An innovative wing structure provides fibs to support skin panels without an attachment between the rib and the stringer free flange or the web. The support is provided by rib shear ties installed directly to the stringer skin flange. The rib incorporates a cut away to allow the stringer to pass through the rib. The composite stringer is an ‘I’ section and is stable under compression, not requiring mechanical methods to prevent rolling over.Type: GrantFiled: December 13, 2006Date of Patent: May 25, 2010Assignee: The Boeing CompanyInventors: Richard B. Tanner, Ian C. Burford, Thomas V. Gendzwill, Gregory B. Doty, James R. Huck, Dean E. Wilson, Brian H. Korenaga
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Patent number: 7686251Abstract: A method and apparatus for an aircraft structure. In one advantageous embodiment, the aircraft structure may have a rib, a plurality of stringers, and a set of shear ties. The plurality of stringers may have skin flanges at ends of the plurality of stringers capable of being fastened to skin for the aircraft structure. The set of shear ties may extend from the rib and have a set of elongate members in which the set of elongate members are attached to the plurality of stringers.Type: GrantFiled: October 4, 2007Date of Patent: March 30, 2010Assignee: The Boeing CompanyInventors: Richard B. Tanner, Ian C. Burford, Thomas V. Gendzwill, Gregory B. Doty, James R. Huck, Dean E. Wilson, Brian H. Korenaga
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Publication number: 20080210821Abstract: An innovative wing structure provides ribs to support skin panels without an attachment between the rib and the stringer free flange or the web. The support is provided by rib shear ties installed directly to the stringer skin flange. The rib incorporates a cut away to allow the stringer to pass through the rib. The composite stringer is an ‘I’ section and is stable under compression, not requiring mechanical methods to prevent rolling over.Type: ApplicationFiled: December 13, 2006Publication date: September 4, 2008Applicant: THE BOEING COMPANYInventors: Richard B. Tanner, Ian C. Burford, Thomas V. Gendzwill, Gregory B. Doty, James R. Huck, Dean E. Wilson, Brian H. Korenaga
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Publication number: 20080173757Abstract: A method and apparatus for an aircraft structure. In one advantageous embodiment, the aircraft structure may have a rib, a plurality of stringers, and a set of shear ties. The plurality of stringers may have skin flanges at ends of the plurality of stringers capable of being fastened to skin for the aircraft structure. The set of shear ties may extend from the rib and have a set of elongate members in which the set of elongate members are attached to the plurality of stringers.Type: ApplicationFiled: October 4, 2007Publication date: July 24, 2008Inventors: Richard B. Tanner, Ian C. Burford, Thomas V. Gendzwill, Gregory B. Doty, James R. Huck, Dean E. Wilson, Brian H. Korenaga