Patents by Inventor Kelly T. Jones
Kelly T. Jones 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: 10766602Abstract: A system for mechanical operation of an aircraft wing includes a torque tube rotatable at a first rate of rotation to cause a downward rotation of a control surface relative to the aircraft wing. A gearing assembly including an output shaft is coupled to the torque tube. The torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation less than the first rate of rotation. A rotational member is coupled to the output shaft, and the output shaft is configured to drive a rotation of the rotational member. A first end of a linear actuator is coupled to the rotational member at a forward attach point, which is eccentric to a rotational center of the rotational member. The rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing.Type: GrantFiled: November 1, 2017Date of Patent: September 8, 2020Assignee: The Boeing CompanyInventors: Seiya Sakurai, Mark S. Good, Lisa Schleuter, Kelly T. Jones, Gregory M. Santini
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Patent number: 10309431Abstract: Methods and apparatus to control movement of a component are disclosed herein. An example apparatus includes a housing defining a bore and a piston disposed inside the bore. The piston is to be coupled to a movable component disposed outside of the bore. The example apparatus further includes a fluid flowline in fluid communication with a first chamber of the bore and a second chamber of the bore. The first chamber is on a first side of the piston, and the second chamber on a second side of the piston. The example apparatus also includes a valve to control fluid flow through the fluid flowline. The valve is to be in a first state to enable the piston to dampen movement of the component, and the valve is to be in a second state to enable the piston to hold the component substantially stationary.Type: GrantFiled: April 12, 2016Date of Patent: June 4, 2019Assignee: THE BOEING COMPANYInventors: Robert M. Murphy, Kelly T. Jones, Robert E. Fisher, Mark J. Gardner
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Publication number: 20190127044Abstract: A system for mechanical operation of an aircraft wing includes a torque tube rotatable at a first rate of rotation to cause a downward rotation of a control surface relative to the aircraft wing. A gearing assembly including an output shaft is coupled to the torque tube. The torque tube is configured to rotate the output shaft, via the gearing assembly, at a second rate of rotation less than the first rate of rotation. A rotational member is coupled to the output shaft, and the output shaft is configured to drive a rotation of the rotational member. A first end of a linear actuator is coupled to the rotational member at a forward attach point, which is eccentric to a rotational center of the rotational member. The rotational member is rotatable to cause a translation of the forward attach point relative to the aircraft wing.Type: ApplicationFiled: November 1, 2017Publication date: May 2, 2019Inventors: Seiya Sakurai, Mark S. Good, Lisa Schleuter, Kelly T. Jones, Gregory M. Santini
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Patent number: 10053237Abstract: Systems and methods are provided for a track roller failure detection system. The system may include a main aerodynamic device and a secondary aerodynamic device including a track supported by one or more rollers and a marker. Failure of the one or more rollers may result in the track contacting the marker. Operation of the secondary aerodynamic device when one or more of the rollers have failed may result in the marker leaving a mark and/or a trail on a portion of the main aerodynamic device and/or a portion of the secondary aerodynamic device. Failure of the one or more rollers may then be determined from the mark and/or trail.Type: GrantFiled: May 20, 2016Date of Patent: August 21, 2018Assignee: The Boeing CompanyInventors: Sam X. Huang, Kelly T. Jones
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Publication number: 20170334582Abstract: Systems and methods are provided for a track roller failure detection system. The system may include a main aerodynamic device and a secondary aerodynamic device including a track supported by one or more rollers and a marker. Failure of the one or more rollers may result in the track contacting the marker. Operation of the secondary aerodynamic device when one or more of the rollers have failed may result in the marker leaving a mark and/or a trail on a portion of the main aerodynamic device and/or a portion of the secondary aerodynamic device. Failure of the one or more rollers may then be determined from the mark and/or trail.Type: ApplicationFiled: May 20, 2016Publication date: November 23, 2017Inventors: Sam X. Huang, Kelly T. Jones
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Patent number: 9731812Abstract: An airfoil, a flap mechanism and an associated method are provided to controllably actuate a flap positioned proximate the trailing edge of an airfoil body. The flap mechanism includes a carrier beam hingedly connected to an airfoil body and also pivotally connected to a flap proximate the trailing edge of the airfoil body. The flap mechanism further includes an actuator, a first plurality of links and a second plurality of links. The first plurality of links is operably connected to the airfoil body, the actuator and the carrier beam. The first plurality of links causes the carrier beam to be rotated with respect to the airfoil body in response to actuation by the actuator. The second plurality of links is responsive to rotation of the carrier beam with respect to the airfoil body. The second plurality of links causes the flap to be rotated with respect to the carrier beam.Type: GrantFiled: January 26, 2015Date of Patent: August 15, 2017Assignee: The Boeing CompanyInventors: Steven Paul Walker, Flint Matthew Jamison, Kelly T. Jones
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Patent number: 9614209Abstract: An aircraft comprises a rechargeable battery including an array of battery cells, and means for mitigating consequences of failure of the rechargeable battery due to aircraft operating cycles.Type: GrantFiled: February 24, 2014Date of Patent: April 4, 2017Assignee: The Boeing CompanyInventors: Kelly T. Jones, Alfred R. Carlo, Alan D. Amort, Daniel F. Lewinski, Daniel J. Murray, Douglas D. Maben, Harry H. Ayubi, Craig G. Robotham, Julie K. Plessner, Kevin S. Callahan, Michael L. Trent, Michael R. Madden, Mohammad M. Malik, Richard K. Johnson, Royal E. Boggs, Mehdy Barekatein, Frederic P. Lacaux, Bruce L. Drolen, James C. Russell, John R. Lowell, Thomas P. Barrera, Timothy R. North, Richard P. Lorenz, Matthew J. O'Brien, Nels A. Olson, David C. Shangraw, Mark E. Smith, Jean-Philippe Belieres, George A. McEachen
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Patent number: 9508970Abstract: An apparatus comprises a rechargeable battery susceptible to thermal runaway, and a metal enclosure for the battery. The enclosure is configured to mitigate battery failure consequences resulting from thermal runaway.Type: GrantFiled: February 24, 2014Date of Patent: November 29, 2016Assignee: The Boeing CompanyInventors: Kelly T. Jones, Al R. Carlo, Alan D. Amort, Daniel F. Lewinski, Daniel J. Murray, Douglas D. Maben, Harry H. Ayubi, Howard E. McKenzie, Julie K. Plessner, Kevin S. Callahan, Michael L. Trent, Mike R. Madden, Mohammad M. Malik, Richard K. Johnson, Royal E. Boggs
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Publication number: 20160222994Abstract: Methods and apparatus to control movement of a component are disclosed herein. An example apparatus includes a housing defining a bore and a piston disposed inside the bore. The piston is to be coupled to a movable component disposed outside of the bore. The example apparatus further includes a fluid flowline in fluid communication with a first chamber of the bore and a second chamber of the bore. The first chamber is on a first side of the piston, and the second chamber on a second side of the piston. The example apparatus also includes a valve to control fluid flow through the fluid flowline. The valve is to be in a first state to enable the piston to dampen movement of the component, and the valve is to be in a second state to enable the piston to hold the component substantially stationary.Type: ApplicationFiled: April 12, 2016Publication date: August 4, 2016Inventors: Robert M. Murphy, Kelly T. Jones, Robert E. Fisher, Mark J. Gardner
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Publication number: 20160214705Abstract: An airfoil, a flap mechanism and an associated method are provided to controllably actuate a flap positioned proximate the trailing edge of an airfoil body. The flap mechanism includes a carrier beam hingedly connected to an airfoil body and also pivotally connected to a flap proximate the trailing edge of the airfoil body. The flap mechanism further includes an actuator, a first plurality of links and a second plurality of links. The first plurality of links is operably connected to the airfoil body, the actuator and the carrier beam. The first plurality of links causes the carrier beam to be rotated with respect to the airfoil body in response to actuation by the actuator. The second plurality of links is responsive to rotation of the carrier beam with respect to the airfoil body. The second plurality of links causes the flap to be rotated with respect to the carrier beam.Type: ApplicationFiled: January 26, 2015Publication date: July 28, 2016Inventors: Steven Paul Walker, Flint Matthew Jamison, Kelly T. Jones
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Publication number: 20140242424Abstract: An aircraft comprises a rechargeable battery including an array of battery cells, and means for mitigating consequences of failure of the rechargeable battery due to aircraft operating cycles.Type: ApplicationFiled: February 24, 2014Publication date: August 28, 2014Applicant: THE BOEING COMPANYInventor: Kelly T. Jones
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Publication number: 20140242423Abstract: An apparatus comprises a rechargeable battery susceptible to thermal runaway, and a metal enclosure for the battery.Type: ApplicationFiled: February 24, 2014Publication date: August 28, 2014Applicant: The Boeing CompanyInventor: Kelly T. Jones
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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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Publication number: 20140033909Abstract: Methods and apparatus to control movement of a component are disclosed herein. An example apparatus includes a housing defining a bore and a piston disposed inside the bore. The piston is to be coupled to a movable component disposed outside of the bore. The example apparatus further includes a fluid flowline in fluid communication with a first chamber of the bore and a second chamber of the bore. The first chamber is on a first side of the piston, and the second chamber on a second side of the piston. The example apparatus also includes a valve to control fluid flow through the fluid flowline. The valve is to be in a first state to enable the piston to dampen movement of the component, and the valve is to be in a second state to enable the piston to hold the component substantially stationary.Type: ApplicationFiled: August 3, 2012Publication date: February 6, 2014Inventors: Robert M. Murphy, Kelly T. Jones, Robert E. Fisher, Mark J. Gardner
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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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Patent number: 8226049Abstract: A control surface drive system having a plurality of actuator assemblies are coupled to first and second supply lines and to a return line. The first and second supply lines are connected to a source of hydraulic fluid. At least one of the actuator assemblies has a hydraulic actuator movably connectable to an aircraft control surface. A flow control assembly is connected to the return line and to at least one of the first and second supply lines. A bypass line is in fluid communication with the first and second supply lines and positioned to recycle the hydraulic fluid from one of the first and second supply lines back into the other one of the first and second supply lines when the hydraulic actuator moves toward the first position. A computer controller operatively interconnects the plurality of actuator assemblies and the flow control assembly. It is emphasized that this abstract is provided to comply with the rules requiring an abstract.Type: GrantFiled: February 25, 2011Date of Patent: July 24, 2012Assignee: The Boeing CompanyInventor: Kelly T. Jones
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Publication number: 20110215195Abstract: A control surface drive system having a plurality of actuator assemblies are coupled to first and second supply lines and to a return line. The first and second supply lines are connected to a source of hydraulic fluid. At least one of the actuator assemblies has a hydraulic actuator movably connectable to an aircraft control surface. A flow control assembly is connected to the return line and to at least one of the first and second supply lines. A bypass line is in fluid communication with the first and second supply lines and positioned to recycle the hydraulic fluid from one of the first and second supply lines back into the other one of the first and second supply lines when the hydraulic actuator moves toward the first position. A computer controller operatively interconnects the plurality of actuator assemblies and the flow control assembly. It is emphasized that this abstract is provided to comply with the rules requiring an abstract.Type: ApplicationFiled: February 25, 2011Publication date: September 8, 2011Inventor: Kelly T. Jones
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Patent number: 7913955Abstract: A control surface drive system having a plurality of actuator assemblies are coupled to first and second supply lines and to a return line. The first and second supply lines are connected to a source of hydraulic fluid. At least one of the actuator assemblies has a hydraulic actuator movably connectable to an aircraft control surface. A flow control assembly is connected to the return line and to at least one of the first and second supply lines. A bypass line is in fluid communication with the first and second supply lines and positioned to recycle the hydraulic fluid from one of the first and second supply lines back into the other one of the first and second supply lines when the hydraulic actuator moves toward the first position. A computer controller operatively interconnects the plurality of actuator assemblies and the flow control assembly. It is emphasized that this abstract is provided to comply with the rules requiring an abstract.Type: GrantFiled: March 23, 2009Date of Patent: March 29, 2011Assignee: The Boeing CompanyInventor: Kelly T. Jones
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Publication number: 20090308983Abstract: A control surface drive system having a plurality of actuator assemblies are coupled to first and second supply lines and to a return line. The first and second supply lines are connected to a source of hydraulic fluid. At least one of the actuator assemblies has a hydraulic actuator movably connectable to an aircraft control surface. A flow control assembly is connected to the return line and to at least one of the first and second supply lines. A bypass line is in fluid communication with the first and second supply lines and positioned to recycle the hydraulic fluid from one of the first and second supply lines back into the other one of the first and second supply lines when the hydraulic actuator moves toward the first position. A computer controller operatively interconnects the plurality of actuator assemblies and the flow control assembly. It is emphasized that this abstract is provided to comply with the rules requiring an abstract.Type: ApplicationFiled: March 23, 2009Publication date: December 17, 2009Applicant: The Boeing CompanyInventor: Kelly T. Jones
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Patent number: 7506842Abstract: A control surface drive system having a plurality of actuator assemblies are coupled to first and second supply lines and to a return line. The first and second supply lines are connected to a source of hydraulic fluid. At least one of the actuator assemblies has a hydraulic actuator movably connectable to an aircraft control surface. A flow control assembly is connected to the return line and to at least one of the first and second supply lines. A bypass line is in fluid communication with the first and second supply lines and positioned to recycle the hydraulic fluid from one of the first and second supply lines back into the other one of the first and second supply lines when the hydraulic actuator moves toward the first position. A computer controller operatively interconnects the plurality of actuator assemblies and the flow control assembly. It is emphasized that this abstract is provided to comply with the rules requiring an abstract.Type: GrantFiled: October 5, 2004Date of Patent: March 24, 2009Assignee: The Boeing CompanyInventor: Kelly T. Jones