Patents by Inventor Lyle R. Deobald
Lyle R. Deobald 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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Patent number: 10220935Abstract: An open-channel stiffener for stiffening a panel has a bonding flange for bonding the stiffener to the panel through a bondline formed between the bonding flange and the panel to form a stiffened panel. The open-channel stiffener has a cross-sectional shape that aligns, or substantially aligns, a shear center of the stiffener with a centroid of the stiffener and aligns the shear center proximate an edge of the bondline, and removes the need for a radius filler noodle. A plurality of perforations may be formed through the bonding flange to permit an adhesive to wick into the perforations and create a mechanical interlock between the bonding flange and the panel.Type: GrantFiled: September 13, 2016Date of Patent: March 5, 2019Assignee: The Boeing CompanyInventors: Lyle R. Deobald, Matthew A. Dilligan, Aaron N. Rinn, Madhavadas Ramnath
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Patent number: 9981444Abstract: A composite stiffener is fabricated using preforms of laminated, unidirectional composite tape. The stiffener includes a void that is reinforced by a filler wrapped with a structural adhesive. The surfaces of the preforms surrounding the void include a layer of composite fabric which is bonded to the filler by the adhesive, thereby increasing the toughness of stiffeners around the void and improving pull-off strength of the stiffener.Type: GrantFiled: June 27, 2013Date of Patent: May 29, 2018Assignee: THE BOEING COMPANYInventors: Lyle R. Deobald, John D. Morris, Karl B. Lee, Jeffery L. Marcoe, Mark C. Iden, Christopher G. Harris
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Publication number: 20180072400Abstract: An open-channel stiffener for stiffening a panel has a bonding flange for bonding the stiffener to the panel through a bondline formed between the bonding flange and the panel to form a stiffened panel. The open-channel stiffener has a cross-sectional shape that aligns, or substantially aligns, a shear center of the stiffener with a centroid of the stiffener and aligns the shear center proximate an edge of the bondline, and removes the need for a radius filler noodle. A plurality of perforations may be formed through the bonding flange to permit an adhesive to wick into the perforations and create a mechanical interlock between the bonding flange and the panel.Type: ApplicationFiled: September 13, 2016Publication date: March 15, 2018Applicant: The Boeing CompanyInventors: Lyle R. Deobald, Matthew A. Dilligan, Aaron N. Rinn, Madhavadas Ramnath
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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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Patent number: 9592651Abstract: A composite structure having a base charge and an outer channel charge is provided. The outer channel charge has an inner radius and an outer radius. A charge of plies adjacent to the inner radius reduces the inner radius.Type: GrantFiled: September 30, 2014Date of Patent: March 14, 2017Assignee: The Boeing CompanyInventors: Lyle R. Deobald, Aaron N. Rinn, Ying Shan, Madhavadas Ramnath, Derek P. Vetter, Kenneth H. Griess, Michael J. Graves
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Publication number: 20160089856Abstract: A composite structure having a base charge and an outer channel charge is provided. The outer channel charge has an inner radius and an outer radius. A charge of plies adjacent to the inner radius reduces the inner radius.Type: ApplicationFiled: September 30, 2014Publication date: March 31, 2016Inventors: Lyle R. Deobald, Aaron N. Rinn, Ying Shan, Madhavadas Ramnath, Derek P. Vetter, Kenneth H. Griess, Michael J. Graves
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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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Publication number: 20130309443Abstract: A composite stiffener is fabricated using preforms of laminated, unidirectional composite tape. The stiffener includes a void that is reinforced by a filler wrapped with a structural adhesive. The surfaces of the preforms surrounding the void include a layer of composite fabric which is bonded to the filler by the adhesive, thereby increasing the toughness of stiffeners around the void and improving pull-off strength of the stiffener.Type: ApplicationFiled: June 27, 2013Publication date: November 21, 2013Inventors: Lyle R. Deobald, John D. Morris, Karl B. Lee, Jeffrey L. Marcoe, Mark C. Iden, Christopher G. Harris
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Patent number: 8540833Abstract: A composite stiffener is fabricated using preforms of laminated, unidirectional composite tape. The stiffener includes a void that is reinforced by a filler wrapped with a structural adhesive. The surfaces of the preforms surrounding the void include a layer of composite fabric which is bonded to the filler by the adhesive, thereby increasing the toughness of stiffeners around the void and improving pull-off strength of the stiffener.Type: GrantFiled: May 16, 2008Date of Patent: September 24, 2013Assignee: The Boeing CompanyInventors: Lyle R. Deobald, John D. Morris, Karl B. Lee, Jeffery L. Marcoe, Mark C. Iden, Christopher G. Harris
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Patent number: 7900346Abstract: In non-limiting, exemplary embodiments a mount assembly is provided for mounting an inspection sensor to a surface of a workpiece. The mount assembly includes a mount having an attachment portion and an engagement portion. The attachment portion is arranged to attach the mount to the surface of the workpiece. The engagement portion is arranged to engage the inspection sensor with the mount. Exemplary mount assemblies may be arranged to mount pulse echo ultrasonic testing transducers, focused ultrasonic testing transducers, through transmission ultrasonic testing transducers, eddy current inspection sensors, or any type of inspection sensor as desired.Type: GrantFiled: June 15, 2007Date of Patent: March 8, 2011Assignee: The Boeing CompanyInventors: Michael D. Fogarty, Gary E. Georgeson, Daniel J. Wright, Lyle R. Deobald
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Publication number: 20090317587Abstract: A composite stiffener is fabricated using preforms of laminated, unidirectional composite tape. The stiffener includes a void that is reinforced by a filler wrapped with a structural adhesive. The surfaces of the preforms surrounding the void include a layer of composite fabric which is bonded to the filler by the adhesive, thereby increasing the toughness of stiffeners around the void and improving pull-off strength of the stiffener.Type: ApplicationFiled: May 16, 2008Publication date: December 24, 2009Inventors: Lyle R. Deobald, John D. Morris, Karl B. Lee, Jeffery L. Marcoe, Mark C. Iden, Christopher G. Harris
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Patent number: 7505885Abstract: A finite element method for predicting crack opening and propagation entails defining a succession of overlapping interface elements at a potential crack plane, each element having a bound node pair and side node pairs spaced from the bound node pair to sense approach of a crack. An energy-based fracture mechanics criterion determines whether release occurs at the bound nodes and, if so, the displacement between the bound nodes is calculated based on a strain softening law. The process is repeated for each element in sequence.Type: GrantFiled: January 24, 2003Date of Patent: March 17, 2009Assignee: The Boeing CompanyInventors: Lyle R. Deobald, Bernhard Dopker, Gerald E. Mabson
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Publication number: 20080307637Abstract: In non-limiting, exemplary embodiments a mount assembly is provided for mounting an inspection sensor to a surface of a workpiece. The mount assembly includes a mount having an attachment portion and an engagement portion. The attachment portion is arranged to attach the mount to the surface of the workpiece. The engagement portion is arranged to engage the inspection sensor with the mount. Exemplary mount assemblies may be arranged to mount pulse echo ultrasonic testing transducers, focused ultrasonic testing transducers, through transmission ultrasonic testing transducers, eddy current inspection sensors, or any type of inspection sensor as desired.Type: ApplicationFiled: June 15, 2007Publication date: December 18, 2008Inventors: Michael D. Fogarty, Gary E. Georgeson, Daniel J. Wright, Lyle R. Deobald
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Publication number: 20040148143Abstract: A finite element method for predicting crack opening and propagation entails defining a succession of overlapping interface elements at a potential crack plane, each element having a bound node pair and side node pairs spaced from the bound node pair to sense approach of a crack. An energy-based fracture mechanics criterion determines whether release occurs at the bound nodes and, if so, the displacement between the bound nodes is calculated based on a strain softening law. The process is repeated for each element in sequence.Type: ApplicationFiled: January 24, 2003Publication date: July 29, 2004Applicant: The Boeing CompanyInventors: Lyle R. Deobald, Bernhard Dopker, Gerald E. Mabson