Patents by Inventor Mark J. Gardner
Mark J. Gardner 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: 11440640Abstract: Methods and systems according to one or more examples are provided for reducing chatter in a no-back brake during aiding load operations. In one example, an apparatus comprises a no-back brake, disposed within an actuator coupled to an aircraft, including a shaft, and a ball ramp plate, coupled to the shaft, to receive a force comprising an air loading force and is displaced responsive to the force. The apparatus further comprises a brake, coupled to the shaft and coupled to the ball ramp plate, and displaced by the ball ramp plate corresponding to a distance the ball ramp plate is displaced. The apparatus further comprises a modulating spring, coupled to the shaft and coupled to the brake, configured to compress in response to the brake being displaced, and the modulating spring is configured to apply a selective compressive force at the brake corresponding to a distance the brake is displaced.Type: GrantFiled: December 18, 2018Date of Patent: September 13, 2022Assignee: The Boeing CompanyInventors: Kwan-Ho Bae, Mark J. Gardner, Jen-Shen Liu
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Publication number: 20200189723Abstract: Methods and systems according to one or more examples are provided for reducing chatter in a no-back brake during aiding load operations. In one example, an apparatus comprises a no-back brake, disposed within an actuator coupled to an aircraft, including a shaft, and a ball ramp plate, coupled to the shaft, to receive a force comprising an air loading force and is displaced responsive to the force. The apparatus further comprises a brake, coupled to the shaft and coupled to the ball ramp plate, and displaced by the ball ramp plate corresponding to a distance the ball ramp plate is displaced. The apparatus further comprises a modulating spring, coupled to the shaft and coupled to the brake, configured to compress in response to the brake being displaced, and the modulating spring is configured to apply a selective compressive force at the brake corresponding to a distance the brake is displaced.Type: ApplicationFiled: December 18, 2018Publication date: June 18, 2020Inventors: Kwan-Ho Bae, Mark J. Gardner, Jen-Shen Liu
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Patent number: 10457379Abstract: A system and method for a number of backup systems in an aircraft. The apparatus comprises a movement system; a latch system; a lock system; and at least one of a backup valve, a backup actuator, or a backup power source connected to at least one of the movement system, the latch system, or the lock system. The movement system has a first number of actuators and is connected to a hydraulic power source. The latch system has a second number of actuators and is connected to the hydraulic power source. The lock system has a third number of actuators and is connected to the hydraulic power source.Type: GrantFiled: July 6, 2018Date of Patent: October 29, 2019Assignee: The Boeing CompanyInventors: Mark Steven Good, Matthew August Lassen, Michael E. Renzelmann, Mark J. Gardner, Mark William Lesyna, Brian Curtis Hill, Nicholas Seth Tyler
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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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Patent number: 10118712Abstract: The disclosure provides in one embodiment an electrical conductor pathway system for diverting an electric charge. The electrical conductor pathway system includes a substrate having a first surface to be printed on and having one or more grounding points. The electrical conductor pathway system further includes a direct write conductive material pattern printed directly onto the first surface via a direct write printing process. The direct write conductive material pattern forms one or more electrical pathways interconnected with the one or more grounding points. The one or more electrical pathways interconnected with the one or more grounding points divert the electric charge from the first surface to the one or more grounding points.Type: GrantFiled: March 31, 2016Date of Patent: November 6, 2018Assignee: The Boeing CompanyInventors: Victoria L. Garcia, Mark J. Gardner, Otis F. Layton, Jeffrey Lynn Duce, Joseph A. Marshall, IV
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Publication number: 20180312240Abstract: A system and method for a number of backup systems in an aircraft. The apparatus comprises a movement system; a latch system; a lock system; and at least one of a backup valve, a backup actuator, or a backup power source connected to at least one of the movement system, the latch system, or the lock system. The movement system has a first number of actuators and is connected to a hydraulic power source. The latch system has a second number of actuators and is connected to the hydraulic power source. The lock system has a third number of actuators and is connected to the hydraulic power source.Type: ApplicationFiled: July 6, 2018Publication date: November 1, 2018Inventors: Mark Steven Good, Matthew August Lassen, Michael E. Renzelmann, Mark J. Gardner, Mark William Lesyna, Brian Curtis Hill, Nicholas Seth Tyler
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Patent number: 10106244Abstract: A system and method for a number of backup systems in an aircraft. The apparatus comprises a movement system; a latch system; a lock system; and at least one of a backup valve, a backup actuator, or a backup power source connected to at least one of the movement system, the latch system, or the lock system. The movement system has a first number of actuators and is connected to a hydraulic power source. The latch system has a second number of actuators and is connected to the hydraulic power source. The lock system has a third number of actuators and is connected to the hydraulic power source.Type: GrantFiled: November 7, 2014Date of Patent: October 23, 2018Assignee: THE BOEING COMPANYInventors: Mark Steven Good, Matthew August Lassen, Michael E. Renzelmann, Mark J. Gardner, Mark William Lesyna, Brian Curtis Hill, Nicholas Seth Tyler
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Publication number: 20160251073Abstract: A system and method for a number of backup systems in an aircraft. The apparatus comprises a movement system; a latch system; a lock system; and at least one of a backup valve, a backup actuator, or a backup power source connected to at least one of the movement system, the latch system, or the lock system. The movement system has a first number of actuators and is connected to a hydraulic power source. The latch system has a second number of actuators and is connected to the hydraulic power source. The lock system has a third number of actuators and is connected to the hydraulic power source.Type: ApplicationFiled: November 7, 2014Publication date: September 1, 2016Inventors: Mark Steven Good, Matthew August Lassen, Michael E. Renzelmann, Mark J. Gardner, Mark William Lesyna, Brian Curtis Hill, Nicholas Seth Tyler
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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: 20160214735Abstract: The disclosure provides in one embodiment an electrical conductor pathway system for diverting an electric charge. The electrical conductor pathway system includes a substrate having a first surface to be printed on and having one or more grounding points. The electrical conductor pathway system further includes a direct write conductive material pattern printed directly onto the first surface via a direct write printing process. The direct write conductive material pattern forms one or more electrical pathways interconnected with the one or more grounding points. The one or more electrical pathways interconnected with the one or more grounding points divert the electric charge from the first surface to the one or more grounding points.Type: ApplicationFiled: March 31, 2016Publication date: July 28, 2016Inventors: Victoria L. Garcia, Mark J. Gardner, Otis F. Layton, Jeffrey Lynn Duce, Joseph A. Marshall, IV
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Patent number: 9359065Abstract: A system for optimizing performance of an aircraft may include a flight control computer for computing an optimum flap setting based on aircraft data. The system may further include a flap control system having a flap control device. The system may additionally include a flap actuation system coupled to the flap control system for positioning the trailing edge device at the optimum flap setting.Type: GrantFiled: September 24, 2013Date of Patent: June 7, 2016Assignee: The Boeing CompanyInventors: Matthew A. Moser, Michael R. Finn, Mark J. Gardner, Robert M. Murphy, Adam Thoreen
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Patent number: 9193440Abstract: A variable camber system for an aircraft may include a variable camber trim unit (VCTU) positioned between an inboard device and an outboard device. The inboard device and the outboard device may be mounted to at least one of a leading edge and a trailing edge of a wing. The VCTU may include a speed sum gearbox having an inboard shaft coupled to the inboard device and an outboard shaft coupled to the outboard device. The VCTU may additionally include a VCTU electric motor engaged to the speed sum gearbox. The VCTU electric motor may be selectively operable in conjunction with the speed sum gearbox to rotate the outboard shaft independent of the inboard shaft in a manner causing the outboard device to be actuated independent of the inboard device.Type: GrantFiled: September 24, 2013Date of Patent: November 24, 2015Assignee: The Boeing CompanyInventors: Matthew A. Moser, Michael R. Finn, Mark J. Gardner, Mark S. Good, Sarah A. Jones
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Patent number: 9180962Abstract: A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.Type: GrantFiled: September 24, 2013Date of Patent: November 10, 2015Assignee: The Boeing CompanyInventors: Matthew A. Moser, Mark J. Gardner, Michael R. Finn, Mark S. Good, Adam P. Malachowski, Monica E. Thommen, Stephen R. Amorosi, Dan Onu
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Publication number: 20150083852Abstract: A variable camber system for an aircraft may include a variable camber trim unit (VCTU) positioned between an inboard device and an outboard device. The inboard device and the outboard device may be mounted to at least one of a leading edge and a trailing edge of a wing. The VCTU may include a speed sum gearbox having an inboard shaft coupled to the inboard device and an outboard shaft coupled to the outboard device. The VCTU may additionally include a VCTU electric motor engaged to the speed sum gearbox. The VCTU electric motor may be selectively operable in conjunction with the speed sum gearbox to rotate the outboard shaft independent of the inboard shaft in a manner causing the outboard device to be actuated independent of the inboard device.Type: ApplicationFiled: September 24, 2013Publication date: March 26, 2015Applicant: The Boeing CompanyInventors: Matthew A. Moser, Michael R. Finn, Mark J. Gardner, Mark S. Good, Sarah A. Jones
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Publication number: 20150083850Abstract: A system for optimizing performance of an aircraft may include a flight control computer for computing an optimum flap setting based on aircraft data. The system may further include a flap control system having a flap control device. The system may additionally include a flap actuation system coupled to the flap control system for positioning the trailing edge device at the optimum flap setting.Type: ApplicationFiled: September 24, 2013Publication date: March 26, 2015Applicant: The Boeing CompanyInventors: Matthew A. Moser, Michael R. Finn, Mark J. Gardner, Robert M. Murphy, Adam Thoreen
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Publication number: 20150083867Abstract: A system for varying a wing camber of an aircraft wing may include a leading edge device coupled to the wing. The leading edge device may be configured to be actuated in an upward direction and a downward direction relative to a retracted position of the leading edge device.Type: ApplicationFiled: September 24, 2013Publication date: March 26, 2015Applicant: The Boeing CompanyInventors: Matthew A. Moser, Mark J. Gardner, Michael R. Finn, Mark S. Good, Adam P. Malachowski, Monica E. Thommen, Stephen R. Amorosi, Dan Onu
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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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Patent number: 8115649Abstract: An apparatus comprises a sensor system, a flexible line, and a sensor. The sensor system is capable of detecting skew in at least some of a plurality of control surfaces for a vehicle. The flexible line extends across a number of interfaces for a portion of the plurality of control surfaces. The sensor is connected to the flexible line and is capable of detecting the skew in the portion of the plurality of control surfaces in response to a selected amount of movement of the flexible line.Type: GrantFiled: April 30, 2009Date of Patent: February 14, 2012Assignee: The Boeing CompanyInventors: George Moy, Peter Angel Padilla, Michael Edward Renzelmann, Mark J. Gardner, Charles E. Jokisch, William Suhail Hanna, Eric J. Selby, Mark A. Barr, Stephen Roger Amorosi
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Patent number: 7945425Abstract: A method for detecting freewheeling skew failures in the wing flaps of an aircraft includes measuring the outputs of flap skew sensors when the aircraft is in flight (IF) and the flaps are extended to a selected position, and when the aircraft is next on the ground (OG) and the flaps are extended to the selected position. The respective differences between the IF and OG outputs of symmetrical pairs of the flap skew sensors are computed, and then the respective difference between the computed IF output difference and the computed OG output difference of each symmetrical pair of the sensors is computed. The computed IF and OG difference of each symmetrical pair of the sensors is then compared with each of predetermined maximum and minimum threshold value to determine whether a freewheeling skew failure exists in any of the flaps of the aircraft.Type: GrantFiled: October 17, 2008Date of Patent: May 17, 2011Assignee: The Boeing CompanyInventors: Alan D. Marx, Gary A. Emch, Mark J. Gardner, Richard I. Apfel, Michael E. Renzelmann, Christopher D. Feet, Michael R. Finn, Mark S. Good, Gregory J. Seehusen
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Publication number: 20100277346Abstract: An apparatus comprises a sensor system, a flexible line, and a sensor. The sensor system is capable of detecting skew in at least some of a plurality of control surfaces for a vehicle. The flexible line extends across a number of interfaces for a portion of the plurality of control surfaces. The sensor is connected to the flexible line and is capable of detecting the skew in the portion of the plurality of control surfaces in response to a selected amount of movement of the flexible line.Type: ApplicationFiled: April 30, 2009Publication date: November 4, 2010Applicant: THE BOEING COMPANYInventors: George Moy, Peter Angel Padilla, Michael Edward Renzelmann, Mark J. Gardner, Charles E. Jokisch, William Suhail Hanna, Eric J. Selby, Mark A. Barr, Stephen Roger Amorosi