Patents by Inventor Stephen J. Fox
Stephen J. Fox 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: 11932802Abstract: Various shaped abrasive particles are disclosed. Each shaped abrasive particle includes a body having at least one major surface and a side surface extending from the major surface.Type: GrantFiled: December 2, 2022Date of Patent: March 19, 2024Assignee: SAINT-GOBAIN CERAMICS & PLASTICS, INC.Inventors: Todd M. Cotter, Francois Wagner, Rene G. Demers, Richard J. Klok, Alexandra Marazano, Adam D. Lior, James A. Salvatore, Sujatha K. Iyengar, David F Louapre, Sidath S. Wijesooriya, Ronald Christopher Motta, Gary A. Guertin, Michael D. Kavanaugh, Doruk O. Yener, Jennifer H. Czerepinski, Jun Jia, Frederic Josseaux, Ralph Bauer, Frank J. Csillag, Yang Zhong, James P. Stewart, Mark P. Dombrowski, Sandhya Jayaraman Rukmani, Amandine Martin, Stephen E. Fox, Nilanjan Sarangi, Dean S. Matsumoto
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Patent number: 10538307Abstract: A wing assembly comprises a raked wing tip having an outboard portion hinged to one of a main wing having at least one moveable control surface and an inboard raked wing tip portion. The outboard portion of the raked wing tip does not carry any moveable flight control surfaces.Type: GrantFiled: October 30, 2012Date of Patent: January 21, 2020Assignee: The Boeing CompanyInventors: Paul W. Dees, Mark S. Good, Seiya Sakurai, Jan A. Kordel, Stephen J. Fox, Matthew A. Lassen, Bruce Robert Fox, Steven Paul Walker, Gregory M. Santini
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Patent number: 9783284Abstract: A rotary drive assembly is provided. The assembly includes a tip hinge box, a body hinge box pivotably coupled to the tip hinge box, a rotary actuator positioned within the body hinge box, and a linkage mechanism coupled between the rotary actuator and the tip hinge box, the linkage mechanism including a first linkage fixedly coupled to the rotary actuator, and a second linkage coupled between the first linkage and the tip hinge box, wherein rotation of the rotary actuator causes the tip hinge box to rotate relative to the body hinge box.Type: GrantFiled: May 20, 2014Date of Patent: October 10, 2017Assignee: THE BOEING COMPANYInventors: Keith Townsend, Stephen J. Fox
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Patent number: 9688386Abstract: A variable camber Krueger flap deployment linkage mechanism is presented. A first linkage assembly couples a flap assembly and an airfoil, and comprising a first drive arm, a first drive link, and a support arm. A second linkage assembly couples the flap assembly and the first drive arm, and comprises a drive transfer arm, a middle connection segment, and a bullnose link.Type: GrantFiled: June 13, 2016Date of Patent: June 27, 2017Assignee: The Boeing CompanyInventors: Seiya Sakurai, Stephen J. Fox, Victor H. Reyes
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Publication number: 20160297513Abstract: A variable camber Krueger flap deployment linkage mechanism is presented. A first linkage assembly couples a flap assembly and an airfoil, and comprising a first drive arm, a first drive link, and a support arm. A second linkage assembly couples the flap assembly and the first drive arm, and comprises a drive transfer arm, a middle connection segment, and a bullnose link.Type: ApplicationFiled: June 13, 2016Publication date: October 13, 2016Inventors: Seiya Sakurai, Stephen J. Fox, Victor H. Reyes
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Patent number: 9365284Abstract: A variable camber Krueger flap deployment linkage mechanism is presented. A first linkage assembly couples a flap assembly and an airfoil, and comprising a first drive arm, a first drive link, and a support arm. A second linkage assembly couples the flap assembly and the first drive arm, and comprises a drive transfer arm, a middle connection segment, and a bullnose link.Type: GrantFiled: April 22, 2013Date of Patent: June 14, 2016Assignee: The Boeing CompanyInventors: Seiya Sakurai, Stephen J. Fox, Victor H. Reyes
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Publication number: 20150336657Abstract: A rotary drive assembly is provided. The assembly includes a tip hinge box, a body hinge box pivotably coupled to the tip hinge box, a rotary actuator positioned within the body hinge box, and a linkage mechanism coupled between the rotary actuator and the tip hinge box, the linkage mechanism including a first linkage fixedly coupled to the rotary actuator, and a second linkage coupled between the first linkage and the tip hinge box, wherein rotation of the rotary actuator causes the tip hinge box to rotate relative to the body hinge box.Type: ApplicationFiled: May 20, 2014Publication date: November 26, 2015Applicant: THE BOEING COMPANYInventors: Keith Townsend, Stephen J. Fox
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Patent number: 9016637Abstract: A system and method to enable natural laminar flow over a fluid-dynamic body using a variable camber Krueger flap is disclosed. A sequence of flap positions is deployed where the variable camber Krueger flap is below and aft of the wing leading edge before reaching a configured takeoff and landing position. The variable camber Krueger flap is positioned in a high position relative to a wing leading edge when the variable camber Krueger flap is fully deployed.Type: GrantFiled: February 10, 2012Date of Patent: April 28, 2015Assignee: The Boeing CompanyInventors: Seiya Sakurai, Stephen J. Fox, Victor Reyes, Kara Marie Charles
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Publication number: 20140312175Abstract: A variable camber Krueger flap deployment linkage mechanism is presented. A first linkage assembly couples a flap assembly and an airfoil, and comprising a first drive arm, a first drive link, and a support arm. A second linkage assembly couples the flap assembly and the first drive arm, and comprises a drive transfer arm, a middle connection segment, and a bullnose link.Type: ApplicationFiled: April 22, 2013Publication date: October 23, 2014Applicant: The Boeing CompanyInventors: Seiya Sakurai, Stephen J. Fox, Victor H. Reyes
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Patent number: 8763953Abstract: An aircraft flap actuator assembly includes at least one fixed support, at least one track having a curvilinear track surface connected to the fixed support, at least one flap support adapted to traverse the curvilinear track surface, a trailing edge flap connected to the at least one flap support and a flap actuator engaging the at least one flap support.Type: GrantFiled: July 14, 2010Date of Patent: July 1, 2014Assignee: The Boeing CompanyInventors: Seiya Sakurai, James M. Wheaton, Stephen J. Fox
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Patent number: 8708286Abstract: A rotation joint and methods for rotationally coupling a swing tip assembly to a fluid-dynamic body are presented. A rotation plate configured to couple to the swing tip assembly comprises a slide ring comprising an open center, an upper slide surface, an inner slide surface, and a lower slide surface. An upper joint plate is slidably coupled to the upper slide surface and the inner slide surface is configured to couple the fluid-dynamic body. A lower joint plate is slidably coupled to the lower slide surface and the inner slide surface, and is coupled to the upper joint plate through the open center. The lower joint plate is configured to couple to the fluid-dynamic body.Type: GrantFiled: June 21, 2012Date of Patent: April 29, 2014Assignee: The Boeing CompanyInventors: Seiya Sakurai, Kelly T. Jones, Stephen J. Fox, Bruce R. Fox, Nicholas I. Bennett, Mark S. Good
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Patent number: 8684316Abstract: A trailing edge flap mechanism incorporates a support beam, a flap carrier beam supporting an aerodynamic flap, a first link interconnecting a first and second rotation points and a second link interconnecting third and fourth rotation points. The support beam has a ground connection on a first fixed axis of rotation. A connecting link has a ground connection on a second fixed axis of rotation and is connected to the first link intermediate the first and second rotation points. An actuator is connected with a drive link pivotally engaged to the first link for initial forward and aft movement of a nose profile of the Fowler flap substantially parallel to the wing lower surface with extending aft movement providing a rapidly changing angle of the flap with respect to the wing upper surface.Type: GrantFiled: September 23, 2011Date of Patent: April 1, 2014Assignee: The Boeing CompanyInventors: Seiya Sakurai, James M. Wheaton, Stephen J. Fox, Sharon Xiangdong Che
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Patent number: 8657238Abstract: A device and methods for low speed performance improvement of a lifting surface assembly are disclosed. At least one vortex generator is coupled to the lifting surface assembly, and the vortex generator is extended through the lifting surface assembly by drooping a hinged leading coupled to the lifting surface assembly to increase lift. The vortex generator is retracted inside the lifting surface assembly to decrease drag.Type: GrantFiled: July 5, 2011Date of Patent: February 25, 2014Assignee: The Boeing CompanyInventors: Bruce R. Fox, Stephen J. Fox
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Publication number: 20130341467Abstract: A rotation joint and methods for rotationally coupling a swing tip assembly to a fluid-dynamic body are presented. A rotation plate configured to couple to the swing tip assembly comprises a slide ring comprising an open center, an upper slide surface, an inner slide surface, and a lower slide surface. An upper joint plate is slidably coupled to the upper slide surface and the inner slide surface is configured to couple the fluid-dynamic body. A lower joint plate is slidably coupled to the lower slide surface and the inner slide surface, and is coupled to the upper joint plate through the open center. The lower joint plate is configured to couple to the fluid-dynamic body.Type: ApplicationFiled: June 21, 2012Publication date: December 26, 2013Inventors: Seiya Sakurai, Kelly T. Jones, Stephen J. Fox, Bruce R. Fox, Nicholas I. Bennett, Mark S. Good
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Publication number: 20130206917Abstract: A system and method to enable natural laminar flow over a fluid-dynamic body using a variable camber Krueger flap is disclosed. A sequence of flap positions is deployed where the variable camber Krueger flap is below and aft of the wing leading edge before reaching a configured takeoff and landing position. The variable camber Krueger flap is positioned in a high position relative to a wing leading edge when the variable camber Krueger flap is fully deployed.Type: ApplicationFiled: February 10, 2012Publication date: August 15, 2013Inventors: Seiya Sakurai, Stephen J. Fox, Victor Reyes, Kara Marie Charles
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Publication number: 20130075537Abstract: A trailing edge flap mechanism incorporates a support beam, a flap carrier beam supporting an aerodynamic flap, a first link interconnecting a first and second rotation points and a second link interconnecting third and fourth rotation points. The support beam has a ground connection on a first fixed axis of rotation. A connecting link has a ground connection on a second fixed axis of rotation and is connected to the first link intermediate the first and second rotation points. An actuator is connected with a drive link pivotally engaged to the first link for initial forward and aft movement of a nose profile of the Fowler flap substantially parallel to the wing lower surface with extending aft movement providing a rapidly changing angle of the flap with respect to the wing upper surface.Type: ApplicationFiled: September 23, 2011Publication date: March 28, 2013Applicant: THE BOEING COMPANYInventors: Seiya Sakurai, James M. Wheaton, Stephen J. Fox, Sharon Xiangdong Che
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Publication number: 20130009016Abstract: A device and methods for low speed performance improvement of a lifting surface assembly are disclosed. At least one vortex generator is coupled to the lifting surface assembly, and the vortex generator is extended through the lifting surface assembly by drooping a hinged leading coupled to the lifting surface assembly to increase lift. The vortex generator is retracted inside the lifting surface assembly to decrease drag.Type: ApplicationFiled: July 5, 2011Publication date: January 10, 2013Inventors: Bruce R. Fox, Stephen J. Fox
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Publication number: 20120012696Abstract: An aircraft flap actuator assembly includes at least one fixed support, at least one track having a curvilinear track surface connected to the fixed support, at least one flap support adapted to traverse the curvilinear track surface, a trailing edge flap connected to the at least one flap support and a flap actuator engaging the at least one flap support.Type: ApplicationFiled: July 14, 2010Publication date: January 19, 2012Inventors: Seiya Sakurai, James M. Wheaton, Stephen J. Fox
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Patent number: 7578484Abstract: Link mechanisms for gapped rigid Krueger flaps, and associated methods and systems are disclosed. A system in accordance with one embodiment includes a deployable leading edge assembly that in turn includes a deployable leading edge panel having a generally fixed-shape flow surface, a bullnose coupled to the panel, and a link mechanism coupled to the panel and the bullnose to move the panel between a stowed position and a deployed position. The mechanism can include a first support link, a second support link, and first, second, and third positioning links. The positioning links can be pivotably connected among the leading edge panel, the bullnose, the first support link and the second support link so that the leading edge panel forms a gap with the airfoil when in the deployed position. The positioning links can be the only positioning links coupled between the support links, the leading edge panel, and the bullnose at a particular wing span location.Type: GrantFiled: June 14, 2006Date of Patent: August 25, 2009Assignee: The Boeing CompanyInventors: Stephen J. Fox, Seiya Sakurai
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Publication number: 20090072093Abstract: Link mechanisms for gapped rigid Krueger flaps, and associated methods and systems are disclosed. A system in accordance with one embodiment includes a deployable leading edge assembly that in turn includes a deployable leading edge panel having a generally fixed-shape flow surface, a bullnose coupled to the panel, and a link mechanism coupled to the panel and the bullnose to move the panel between a stowed position and a deployed position. The mechanism can include a first support link, a second support link, and first, second, and third positioning links. The positioning links can be pivotably connected among the leading edge panel, the bullnose, the first support link and the second support link so that the leading edge panel forms a gap with the airfoil when in the deployed position. The positioning links can be the only positioning links coupled between the support links, the leading edge panel, and the bullnose at a particular wing span location.Type: ApplicationFiled: June 14, 2006Publication date: March 19, 2009Applicant: The Boeing CompanyInventors: Stephen J. Fox, Seiya Sakurai