Patents by Inventor Terrence S. Birchette
Terrence S. Birchette 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: 11066172Abstract: Controlled energy absorption of seats for impact is described herein. One disclosed example method includes determining a weight of an occupant of a seat of an aircraft, and calculating, using a processor, a stroke load of a seat energy absorber operatively coupled to the seat based on the weight of the occupant. The example method also includes setting the seat energy absorber to the calculated stroke load.Type: GrantFiled: October 15, 2015Date of Patent: July 20, 2021Assignee: The Boeing CompanyInventors: Akif O. Bolukbasi, Terrence S. Birchette, Justin Johnson Schaub
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Patent number: 10569865Abstract: An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.Type: GrantFiled: August 17, 2018Date of Patent: February 25, 2020Assignee: THE BOEING COMPANYInventors: Terrence S. Birchette, Akif O. Bolukbasi
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Publication number: 20190071169Abstract: An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.Type: ApplicationFiled: August 17, 2018Publication date: March 7, 2019Inventors: Terrence S. BIRCHETTE, Akif O. BOLUKBASI
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Patent number: 10053211Abstract: An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.Type: GrantFiled: June 29, 2017Date of Patent: August 21, 2018Assignee: THE BOEING COMPANYInventors: Terrence S. Birchette, Akif O. Bolukbasi
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Publication number: 20170297684Abstract: An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.Type: ApplicationFiled: June 29, 2017Publication date: October 19, 2017Inventors: Terrence S. BIRCHETTE, Akif O. BOLUKBASI
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Patent number: 9708057Abstract: An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.Type: GrantFiled: February 24, 2014Date of Patent: July 18, 2017Assignee: THE BOEING COMPANYInventors: Terrence S. Birchette, Akif O. Bolukbasi
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Publication number: 20170106981Abstract: Controlled energy absorption of seats for impact is described herein. One disclosed example method includes determining a weight of an occupant of a seat of an aircraft, and calculating, using a processor, a stroke load of a seat energy absorber operatively coupled to the seat based on the weight of the occupant. The example method also includes setting the seat energy absorber to the calculated stroke load.Type: ApplicationFiled: October 15, 2015Publication date: April 20, 2017Inventors: Akif O. Bolukbasi, Terrence S. Birchette, Justin Johnson Schaub
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Patent number: 9500249Abstract: An apparatus and method for a composite structural aircraft transmission support link having an integral energy-absorbing feature is disclosed. The link is a two-force member that can carry structural loads up an ultimate load. When loaded beyond ultimate load the design allows sections of the link to fail in a controlled and progressive manner, so that energy is absorbed over a defined stroking distance.Type: GrantFiled: March 9, 2015Date of Patent: November 22, 2016Assignee: THE BOEING COMPANYInventors: Douglas R. Ludin, Matthew S. Stauffer, Akif O. Bolukbasi, Terrence S. Birchette
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Patent number: 9487291Abstract: A method and apparatus for moving a blade of a rotorcraft. The method comprises operating the rotorcraft and applying a torque to an elongate member connected to a tip portion of the blade during operation of the rotorcraft using a tip actuation mechanism that is external to the blade and associated with the elongate member such that the tip portion of the blade rotates about an axis through the blade.Type: GrantFiled: December 5, 2012Date of Patent: November 8, 2016Assignee: THE BOEING COMPANYInventors: Thomas A. Zientek, Terrence S. Birchette, Friedrich K. Straub
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Publication number: 20160265613Abstract: An apparatus and method for a composite structural aircraft transmission support link having an integral energy-absorbing feature is disclosed. The link is a two-force member that can carry structural loads up an ultimate load. When loaded beyond ultimate load the design allows sections of the link to fail in a controlled and progressive manner, so that energy is absorbed over a defined stroking distance.Type: ApplicationFiled: March 9, 2015Publication date: September 15, 2016Inventors: Douglas R. Ludin, Matthew S. Stauffer, Akif O. Bolukbasi, Terrence S. Birchette
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Publication number: 20150239554Abstract: An active landing gear damping system and method for decelerating a vehicle during a terrain impact event, such as an aircraft landing or crash. The system monitors aircraft state data and terrain information to predict an impact of the vehicle with the terrain. The system can then determine a target damper force for each landing gear of the vehicle and a predicted damper velocity at the time of impact. Each landing gear can include an adjustable damper valve, wherein adjustment of the damper valves varies the damping coefficient of the respective dampers. The system can adjust valves of the respective dampers to provide the target force based on the predicted damper velocity. After an impact begins, the system can continuously monitor and adjust the valve to maintain the target force.Type: ApplicationFiled: February 24, 2014Publication date: August 27, 2015Inventors: Terrence S. Birchette, Akif O. Bolukbasi
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Patent number: 8714945Abstract: An air pump positioned within a hollow space in an aerodynamic structure for controlling the flow over an aerodynamic surface thereof, includes a movable member linearly displaced by a very low friction piston mechanism and a compression chamber open to the exterior of the aerodynamic surface through an orifice. Reciprocal displacement of the very low friction movable member changes the volume of the compression chamber to alternately expel fluid (e.g., air) from and pull fluid into the compression chamber through the orifice. The movable member includes a piston oscillating within a piston housing each having an ultra-low friction coating for improved thermal performance and reduced maintenance. Fluid intake to the compression chamber may be increased through the use of a one-way valve located either in the aerodynamic surface, or in the piston. Multiple flapper valves may surround the orifice in the aerodynamic surface for increased fluid control.Type: GrantFiled: July 8, 2011Date of Patent: May 6, 2014Assignee: The Boeing CompanyInventor: Terrence S. Birchette
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Patent number: 8083179Abstract: An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.Type: GrantFiled: September 16, 2010Date of Patent: December 27, 2011Assignee: The Boeing CompanyInventors: Brian K. Hamilton, Ahmed Hassan, Terrence S. Birchette, Robert R. Murrill
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Publication number: 20110280740Abstract: An air pump positioned within a hollow space in an aerodynamic structure for controlling the flow over an aerodynamic surface thereof, includes a movable member linearly displaced by a very low friction piston mechanism and a compression chamber open to the exterior of the aerodynamic surface through an orifice. Reciprocal displacement of the very low friction movable member changes the volume of the compression chamber to alternately expel fluid (e.g., air) from and pull fluid into the compression chamber through the orifice. The movable member includes a piston oscillating within a piston housing each having an ultra-low friction coating for improved thermal performance and reduced maintenance. Fluid intake to the compression chamber may be increased through the use of a one-way valve located either in the aerodynamic surface, or in the piston. Multiple flapper valves may surround the orifice in the aerodynamic surface for increased fluid control.Type: ApplicationFiled: July 8, 2011Publication date: November 17, 2011Applicant: THE BOEING COMPANYInventor: Terrence S. Birchette
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Patent number: 7980516Abstract: An air pump positioned within a hollow space in an aerodynamic structure for controlling the flow over an aerodynamic surface thereof, includes a movable member linearly displaced by a very low friction piston mechanism and a compression chamber open to the exterior of the aerodynamic surface through an orifice. Reciprocal displacement of the very low friction movable member changes the volume of the compression chamber to alternately expel fluid (e.g., air) from and pull fluid into the compression chamber through the orifice. The movable member includes a piston oscillating within a piston housing each having an ultra-low friction coating for improved thermal performance and reduced maintenance. Fluid intake to the compression chamber may be increased through the use of a one-way valve located either in the aerodynamic surface, or in the piston. Multiple flapper valves may surround the orifice in the aerodynamic surface for increased fluid control.Type: GrantFiled: December 20, 2006Date of Patent: July 19, 2011Assignee: The Boeing CompanyInventor: Terrence S. Birchette
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Publication number: 20110001018Abstract: An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.Type: ApplicationFiled: September 16, 2010Publication date: January 6, 2011Applicant: THE BOEING COMPANYInventors: Brian K. Hamilton, Ahmed Hassan, Terrence S. Birchette, Robert R. Murrill
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Patent number: 7798443Abstract: An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.Type: GrantFiled: December 18, 2006Date of Patent: September 21, 2010Assignee: The Boeing CompanyInventors: Brian K. Hamilton, Ahmed Hassan, Terrence S. Birchette, Robert R. Murrill
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Publication number: 20100025538Abstract: An airfoil member and an airfoil member altering system are provided for significantly modifying the shape and size of the airfoil member while simultaneously providing an airfoil member with increased adaptability to various flight conditions throughout a flight envelope. The airfoil member comprises at least one motor or actuator, a system controller, a plurality of vehicle performance sensors, at least one temperature controller and airfoil member comprising at least one geometric morphing device that is adjustable in both size and shape and one or more rigid members.Type: ApplicationFiled: December 18, 2006Publication date: February 4, 2010Inventors: Brian K. Hamilton, Ahmed Hassan, Terrence S. Birchette, Robert R. Murrill
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Publication number: 20080152521Abstract: An air pump positioned within a hollow space in an aerodynamic structure for controlling the flow over an aerodynamic surface thereof, includes a movable member linearly displaced by a very low friction piston mechanism and a compression chamber open to the exterior of the aerodynamic surface through an orifice. Reciprocal displacement of the very low friction movable member changes the volume of the compression chamber to alternately expel fluid (e.g., air) from and pull fluid into the compression chamber through the orifice. The movable member includes a piston oscillating within a piston housing each having an ultra-low friction coating for improved thermal performance and reduced maintenance. Fluid intake to the compression chamber may be increased through the use of a one-way valve located either in the aerodynamic surface, or in the piston. Multiple flapper valves may surround the orifice in the aerodynamic surface for increased fluid control.Type: ApplicationFiled: December 20, 2006Publication date: June 26, 2008Inventor: Terrence S. Birchette