Patents by Inventor Akif O. Bolukbasi
Akif O. Bolukbasi 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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Publication number: 20230166842Abstract: An inversion-formed double-walled tube includes an outer tube having an outer wall thickness, an inner tube disposed inside the outer tube and having an inner wall thickness, and a transition portion connecting the inner tube and the outer tube. In this arrangement, at least one of the inner and outer wall thicknesses varies along a length of the double-walled tube. The inversion-formed double-walled tube may be configured as an inversion tube type energy absorber and as an energy absorbing inversion tube assembly.Type: ApplicationFiled: November 29, 2021Publication date: June 1, 2023Applicant: The Boeing CompanyInventors: Akif O. Bolukbasi, Timothy Gleason
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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: 10946979Abstract: Apparatus for controlling vehicle impact absorption systems and related methods are disclosed herein. An example apparatus includes a predictor to generate a prediction of an impact event for a vehicle based on data received from sensors of the vehicle. The example apparatus includes an energy absorption allocator to determine an amount of vehicle energy to be absorbed by a crash protection system of the vehicle upon the impact event. The example apparatus includes a communicator to generate an instruction to activate the crash protection system based on the prediction and the amount of vehicle energy to be absorbed by the crash protection system and transmit the instruction to a controller of the crash protection system.Type: GrantFiled: April 13, 2018Date of Patent: March 16, 2021Assignee: THE BOEING COMPANYInventor: Akif O. Bolukbasi
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Patent number: 10773821Abstract: Typical composite panels are brittle and unable to support transverse pressure loads that might be imposed on the panels. For example, the use of typical panels around fuel tanks of a vehicle are unable to support transverse pressure loads that might be imposed on the fuel tanks during a crash of the vehicle or a ballistic impact to the fuel tanks. In the embodiments described herein, panels include face sheets that are bonded to a foam core. The foam core includes a corrugated core sheet that is formed from a highly ductile material, such as Polyethylene or Aluminum. When a transverse pressure load is imposed on the panel, core crush of the foam occurs as the core sheet elongates from its original corrugated shape to a curve shape during deformation. This allows the panel to dissipate the energy of the transverse pressure load applied to the panel.Type: GrantFiled: March 27, 2018Date of Patent: September 15, 2020Assignee: The Boeing CompanyInventors: Akif O. Bolukbasi, Timothy R. Gleason, Peter Holemans
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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: 20190315485Abstract: Apparatus for controlling vehicle impact absorption systems and related methods are disclosed herein. An example apparatus includes a predictor to generate a prediction of an impact event for a vehicle based on data received from sensors of the vehicle. The example apparatus includes an energy absorption allocator to determine an amount of vehicle energy to be absorbed by a crash protection system of the vehicle upon the impact event. The example apparatus includes a communicator to generate an instruction to activate the crash protection system based on the prediction and the amount of vehicle energy to be absorbed by the crash protection system and transmit the instruction to a controller of the crash protection system.Type: ApplicationFiled: April 13, 2018Publication date: October 17, 2019Inventor: Akif O. Bolukbasi
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Publication number: 20190300195Abstract: Typical composite panels are brittle and unable to support transverse pressure loads that might be imposed on the panels. For example, the use of typical panels around fuel tanks of a vehicle are unable to support transverse pressure loads that might be imposed on the fuel tanks during a crash of the vehicle or a ballistic impact to the fuel tanks. In the embodiments described herein, panels include face sheets that are bonded to a foam core. The foam core includes a corrugated core sheet that is formed from a highly ductile material, such as Polyethylene or Aluminum. When a transverse pressure load is imposed on the panel, core crush of the foam occurs as the core sheet elongates from its original corrugated shape to a curve shape during deformation. This allows the panel to dissipate the energy of the transverse pressure load applied to the panel.Type: ApplicationFiled: March 27, 2018Publication date: October 3, 2019Inventors: Akif O. Bolukbasi, Timothy R. Gleason, Peter Holemans
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Patent number: 10370092Abstract: A vehicle load-limiting suspension apparatus comprises at least one shear tab for controlling an amount of impact load applied to a vehicle structure when a vehicle impact event occurs. The vehicle load-limiting suspension apparatus further comprises at least one crush tube for limiting the amount of impact load applied to the vehicle structure after the at least one shear tab shears in response to occurrence of the vehicle impact event.Type: GrantFiled: August 17, 2016Date of Patent: August 6, 2019Assignee: The Boeing CompanyInventors: Akif O. Bolukbasi, Timothy R. Gleason
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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: 20180050794Abstract: A vehicle load-limiting suspension apparatus comprises at least one shear tab for controlling an amount of impact load applied to a vehicle structure when a vehicle impact event occurs. The vehicle load-limiting suspension apparatus further comprises at least one crush tube for limiting the amount of impact load applied to the vehicle structure after the at least one shear tab shears in response to occurrence of the vehicle impact event.Type: ApplicationFiled: August 17, 2016Publication date: February 22, 2018Inventors: Akif O. Bolukbasi, Timothy R. Gleason
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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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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: 8376275Abstract: Energy absorbing structure disposed beneath the cargo area of an aircraft provides maximum energy absorption and structural strength using carbon fiber reinforced epoxy composites. The energy absorbing structure uses laminated stanchions having ply drop-offs to produce stable, progressive crushing of the stanchions during a wheels-up crash landing. Integrally formed flanges on the stanchions allow direct mounting of the stanchions on the structural members of the aircraft, without the need for specialized fittings.Type: GrantFiled: December 8, 2006Date of Patent: February 19, 2013Assignee: The Boeing CompanyInventors: Akif O. Bolukbasi, Thomas R. Baxter, Tuan A. Nguyen, Mostafa Rassaian, Kevin R. Davis, William J. Koch, Lee C. Firth
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Publication number: 20090206202Abstract: Energy absorbing structure disposed beneath the cargo area of an aircraft provides maximum energy absorption and structural strength using carbon fiber reinforced epoxy composites. The energy absorbing structure uses laminated stanchions having ply drop-offs to produce stable, progressive crushing of the stanchions during a wheels-up crash landing. Integrally formed flanges on the stanchions allow direct mounting of the stanchions on the structural members of the aircraft, without the need for specialized fittings.Type: ApplicationFiled: December 8, 2006Publication date: August 20, 2009Inventors: Akif O. Bolukbasi, Thomas R. Baxter, Tuan A. Nguyen, Mostafa Rassaian, Kevin R. Davis, William J. Koch, Lee C. Firth
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Patent number: 6620484Abstract: An energy absorbing stitched-composite structural element is provided having a glass thread stitched therethrough. The stitching pattern of the thread varies in density from a low-density portion at an initial impact portion of the panel to a high density portion at a final impact portion of the panel. Preferably, the stitch pattern includes a plurality of rows laterally spaced apart relative to the height of the panel. The spacing between adjacent rows progressively decreases from the initial impact portion of the panel to the final impact portion of the panel. Alternatively, or in combination therewith, the number of stitches per row varies from the fewest number of stitches proximate the initial impact portion of the panel to the final impact portion of the panel. In a highly preferred embodiment of the present invention, the stitched composite panel is incorporated into the subfloor structure of an aircraft fuselage.Type: GrantFiled: June 6, 2000Date of Patent: September 16, 2003Assignee: The Boeing CompanyInventors: Akif O. Bolukbasi, Joyanto Kumar Sen