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公开(公告)号：US20170106981A1
公开(公告)日：2017-04-20
申请号：US14883912
申请日：2015-10-15
Applicant: The Boeing Company
Inventor： Akif O. Bolukbasi , Terrence S. Birchette , Justin Johnson Schaub
IPC: B64D11/06 , G01G19/44 , B60R21/015 , B64D25/04 , G01G19/08
Abstract: 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.
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公开(公告)号：US09500249B2
公开(公告)日：2016-11-22
申请号：US14641586
申请日：2015-03-09
Applicant: The Boeing Company
Inventor： Douglas R. Ludin , Matthew S. Stauffer , Akif O. Bolukbasi , Terrence S. Birchette
IPC: F16F7/12
CPC classification number: F16F7/12
Abstract: 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.
Abstract translation: 公开了一种具有整体能量吸收特征的复合结构飞行器传动支撑连杆的装置和方法。 该连杆是一个双力部件，可承受最大载荷的结构载荷。 当加载超过极限负载时，设计允许链路的部分以受控和渐进的方式失效，使得能量在规定的行程距离上被吸收。
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公开(公告)号：US20160265613A1
公开(公告)日：2016-09-15
申请号：US14641586
申请日：2015-03-09
Applicant: The Boeing Company
Inventor： Douglas R. Ludin , Matthew S. Stauffer , Akif O. Bolukbasi , Terrence S. Birchette
IPC: F16F7/12
CPC classification number: F16F7/12
Abstract: 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.
Abstract translation: 公开了一种具有整体能量吸收特征的复合结构飞行器传动支撑连杆的装置和方法。 该连杆是一个双力部件，可承受最大载荷的结构载荷。 当加载超过极限负载时，设计允许链路的部分以受控和渐进的方式失效，使得能量在规定的行程距离上被吸收。
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公开(公告)号：US11066172B2
公开(公告)日：2021-07-20
申请号：US14883912
申请日：2015-10-15
Applicant: The Boeing Company
Inventor： Akif O. Bolukbasi , Terrence S. Birchette , Justin Johnson Schaub
IPC: B64D25/02 , B64D11/06 , B60N2/42 , B60R21/015 , B64D25/04 , G01G19/08 , G01G19/44 , B64C25/58 , B64D45/00 , B64D45/06
Abstract: 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.
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公开(公告)号：US20180050794A1
公开(公告)日：2018-02-22
申请号：US15239294
申请日：2016-08-17
Applicant: The Boeing Company
Inventor： Akif O. Bolukbasi , Timothy R. Gleason
CPC classification number: B64C27/001 , B64C25/58 , B64C27/006 , B64C2027/002 , B64C2027/004 , B64D11/0619 , B64D45/00 , B64D2045/0085 , F16F7/003 , F16F7/12 , F16F7/125 , F16F2230/18
Abstract: 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.
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Patent Agency Ranking
公开(公告)号：US10773821B2
公开(公告)日：2020-09-15
申请号：US15937414
申请日：2018-03-27
Applicant: The Boeing Company
Inventor： Akif O. Bolukbasi , Timothy R. Gleason , Peter Holemans
IPC: B64D37/32 , B32B1/02 , B32B3/28 , B32B5/14 , B32B5/18 , B32B15/20 , B32B27/32 , B32B7/022 , B64C1/00 , B32B3/30 , B32B5/26 , B60K15/03 , B32B3/18 , B32B5/24 , B32B15/04 , B32B27/06 , B64D37/02 , B60K15/063
Abstract: 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.
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公开(公告)号：US20190300195A1
公开(公告)日：2019-10-03
申请号：US15937414
申请日：2018-03-27
Applicant: The Boeing Company
Inventor： Akif O. Bolukbasi , Timothy R. Gleason , Peter Holemans
Abstract: 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.
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公开(公告)号：US10053211B2
公开(公告)日：2018-08-21
申请号：US15637645
申请日：2017-06-29
Applicant: THE BOEING COMPANY
Inventor： Terrence S. Birchette , Akif O. Bolukbasi
Abstract: 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.
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公开(公告)号：US12240610B2
公开(公告)日：2025-03-04
申请号：US17536783
申请日：2021-11-29
Applicant: The Boeing Company
Inventor： Akif O. Bolukbasi , Timothy Gleason
Abstract: 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.
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公开(公告)号：US20230166842A1
公开(公告)日：2023-06-01
申请号：US17536783
申请日：2021-11-29
Applicant: The Boeing Company
Inventor： Akif O. Bolukbasi , Timothy Gleason
IPC: B64D11/06
CPC classification number: B64D11/0619 , B64D11/0649 , B64D11/0648
Abstract: 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.
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