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1. 发明授权

US06328259B1 Variable-load shear collar for helicopter landing gear shock struts 有权
标题翻译：直升机起落架减震支架的可变载荷剪切环
公开(公告)号：US06328259B1
公开(公告)日：2001-12-11
申请号：US09587954
申请日：2000-06-06
申请人： Akif O. Bolukbasi
发明人： Akif O. Bolukbasi
IPC分类号： B64C2520
CPC分类号： B64C25/60
摘要： A shock strut is provided for a landing gear assembly in an aircraft including a variable load shear collar. The shock strut includes a housing having first and second pistons axially disposed therein. An annular shear collar is rotatably coupled about the housing and includes an inner radial wall, an outer radial wall and a plurality of axially spaced apart shear flanges radially extending from the inner radial wall. The second piston includes a plurality of axially spaced apart force transmitting flanges radially extending therefrom which abuttingly engage the plurality of shear flanges. The degree to which the force transmitting flanges engage the shear flanges corresponds to a circumferential orientation of the shear collar relative to the second piston. The amount of abutting engagement dictates the amount of force required to shear the shear flanges, thereby allowing the second piston to stroke.
摘要翻译：为包括可变负载剪切环的飞行器中的起落架组件提供冲击支柱。冲击支柱包括具有轴向设置在其中的第一和第二活塞的壳体。环形剪切环围绕壳体可旋转地联接并且包括内径向壁，外径向壁和从内径向径向径向延伸的多个轴向隔开的剪切凸缘。第二活塞包括从其径向延伸的多个轴向隔开的力传递凸缘，其邻接地与多个剪切凸缘接合。力传递凸缘接合剪切凸缘的程度对应于剪切环相对于第二活塞的周向取向。抵接接合量决定了剪切剪切凸缘所需的力量，从而允许第二活塞行程。

2. 发明授权

US08376275B2 Energy absorbing structure for aircraft 有权
公开(公告)号：US08376275B2
公开(公告)日：2013-02-19
申请号：US11636056
申请日：2006-12-08
申请人： Akif O. Bolukbasi , Thomas R. Baxter , Tuan A. Nguyen , Mostafa Rassaian , Kevin R. Davis , William J. Koch , Lee C. Firth
发明人： Akif O. Bolukbasi , Thomas R. Baxter , Tuan A. Nguyen , Mostafa Rassaian , Kevin R. Davis , William J. Koch , Lee C. Firth
IPC分类号： B64C1/00
CPC分类号： B64C1/062
摘要： 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.

3. 发明授权

US06168142A Hydraulic damper with elastomeric spring assembly 失效
标题翻译：带弹性弹簧组件的液压阻尼器
公开(公告)号：US06168142A
公开(公告)日：2001-01-02
申请号：US09047961
申请日：1998-03-25
申请人： Akif O. Bolukbasi , Paul Saliba , Lowell Pester
发明人： Akif O. Bolukbasi , Paul Saliba , Lowell Pester
IPC分类号： F16F500
CPC分类号： F16F9/585 , F16F9/0218
摘要： A hydraulic damper assembly has a barrel-piston assembly and a spring assembly. The barrel-piston assembly has a barrel with a top portion having an open end, and a piston extending through the open end. The piston has a bottom portion that is located inside the barrel. The piston and the barrel also define an annular space in which is a barrel shoulder and a piston shoulder. The barrel shoulder radially extends into the annular space from the barrel top portion. The piston shoulder radially extends into the annular space from the piston bottom portion. The spring assembly is disposed in the annular space between the barrel shoulder and the piston shoulder. When the piston is extended from the barrel, the shoulders compress the spring assembly and, thereby, reduce the amount of force required to compress the piston which enables the damper to be charged to a higher nitrogen pressure. An object of the invention is to provide a damper assembly for aircraft landing gears that permit high nitrogen pressures to increase ground resonance clearance at high aircraft gross weight and not be fully extended at low aircraft gross weights to avoid ground resonance problems. Another object of the invention is to provide a cost effective damper assembly that is easily retrofitted into current designs of helicopter landing gears.
摘要翻译：液压阻尼器组件具有桶 - 活塞组件和弹簧组件。桶 - 活塞组件具有一个具有开口端的顶部的桶，以及延伸穿过开口端的活塞。活塞具有位于筒内的底部。活塞和筒体还限定一个环形空间，其中是桶肩和活塞肩。筒肩从筒顶部径向延伸到环形空间中。活塞肩从活塞底部向径向延伸进入环形空间。弹簧组件设置在筒肩和活塞肩之间的环形空间中。当活塞从筒体延伸时，肩部压缩弹簧组件，从而减小压缩活塞所需的力量，使阻尼器能够被充入较高的氮气压力。本发明的目的是提供一种用于飞机起落架的阻尼器组件，其允许高氮压力在高飞机总重量下增加地面共振间隙，并且不能在低飞机总重量下完全延伸以避免地面共振问题。本发明的另一个目的是提供一种成本有效的阻尼器组件，其易于改装成直升机起落架的当前设计。

4. 发明授权

US09708057B2 Active landing gear damper 有权
公开(公告)号：US09708057B2
公开(公告)日：2017-07-18
申请号：US14188589
申请日：2014-02-24
申请人： Terrence S. Birchette , Akif O. Bolukbasi
发明人： Terrence S. Birchette , Akif O. Bolukbasi
IPC分类号： B64C25/50 , B64C25/60 , B64C25/58 , B64D45/00
CPC分类号： B64C25/60 , B64C25/58 , B64D45/00
摘要： 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.

5. 发明申请

US20090206202A1 Energy absorbing structure for aircraft 有权
标题翻译：飞机能量吸收结构
公开(公告)号：US20090206202A1
公开(公告)日：2009-08-20
申请号：US11636056
申请日：2006-12-08
申请人： Akif O. Bolukbasi , Thomas R. Baxter , Tuan A. Nguyen , Mostafa Rassaian , Kevin R. Davis , William J. Koch , Lee C. Firth
发明人： Akif O. Bolukbasi , Thomas R. Baxter , Tuan A. Nguyen , Mostafa Rassaian , Kevin R. Davis , William J. Koch , Lee C. Firth
IPC分类号： B64C1/06 , B64C1/18
CPC分类号： B64C1/062
摘要： 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.
摘要翻译：设置在飞机货物区域下方的能量吸收结构使用碳纤维增强的环氧复合材料提供最大的能量吸收和结构强度。能量吸收结构使用具有帘布层落下的层叠支柱，以在轮式碰撞着陆期间产生稳定的，渐进式的破碎的支柱。支柱上的整体成形法兰允许将支柱直接安装在飞机的结构构件上，而不需要专门的配件。

6. 发明授权

US06620484B1 Variable density stitched-composite structural elements for energy absorption 失效
标题翻译：用于能量吸收的可变密度缝合 - 复合结构元件
公开(公告)号：US06620484B1
公开(公告)日：2003-09-16
申请号：US09587796
申请日：2000-06-06
申请人： Akif O. Bolukbasi , Joyanto Kumar Sen
发明人： Akif O. Bolukbasi , Joyanto Kumar Sen
IPC分类号： B32B306
CPC分类号： B64C1/062 , B64C2001/0072 , Y02T50/43 , Y10T428/24033
摘要： 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.
摘要翻译：提供了一种能量吸收缝合复合结构元件，其具有穿过其中的玻璃线。螺纹的缝合图案的密度从面板的初始冲击部分处的低密度部分到面板的最终冲击部分处的高密度部分的密度变化。优选地，针迹图案包括相对于面板的高度横向间隔开的多个行。相邻行之间的间隔从面板的初始冲击部分逐渐减小到面板的最终冲击部分。可替换地或与其组合，每排的针数从接近面板的初始冲击部分到面板的最终冲击部分的最少的线数变化。在本发明的高度优选的实施例中，缝合的复合面板被结合到飞行器机身的底层地板结构中。

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