公开(公告)号：US08991753B2

公开(公告)日：2015-03-31

申请号：US13900071

申请日：2013-05-22

申请人： The Boeing Company

发明人： Mitchell L. Mellor ,  Michael A. Long ,  Richard B. Odell

IPC分类号： B64C25/34 ,  B64C25/10 ,  B64C25/04 ,  B64C25/20 ,  B64C25/00

CPC分类号： B64C25/04 ,  B64C25/20 ,  B64C25/34 ,  B64C2025/008

摘要： A method of positioning landing gear of an airplane is provided that includes providing the landing gear including a shock strut, a truck beam operatively pivotally connected to the shock strut, first and second interconnected links operatively connected to the truck beam and a third link extending between the shock strut and the first and second links with the third link pivotally connected to the second link at a third pivot. When the landing gear is commanded to a lowered position, the third pivot is positioned in a first position to support a taxi mode, a take-off mode and a landing mode if the landing gear is operational and in a second position to support an alternate landing mode if the landing gear is not fully operational. When the landing gear is commanded to a raised position, the third pivot is in the second position to support a stow mode.

公开(公告)号：US08317130B1

公开(公告)日：2012-11-27

申请号：US12200318

申请日：2008-08-28

申请人： Aaron L. Westman

发明人： Aaron L. Westman

IPC分类号： B64C25/10 ,  B64C25/14 ,  B64C25/20

CPC分类号： B64C25/04 ,  B64C39/024 ,  B64C2001/0072 ,  Y02T50/43

摘要： Landing gear mount techniques for aircraft are described. The landing gear is mounted to composite structures of the aircraft in a manner that distributes landing loads, including out-of-plane loads, adequately so that the landing gear and its mounting to the aircraft is tough and can withstand variable landing loads. The landing gear is disposed between and fastened on each side to composite bulkheads. The composite bulkheads are also bonded to the outer skins of the aircraft. The described mounting distributes the loads into the composite bulkheads and from there into the outer skins. This distribution of the loading helps the landing gear withstand variable landing loads and helps maintain the integrity of the composite materials.

摘要翻译： 描述了飞机的起落架安装技术。 起落架以以分布着陆载荷（包括平面外载荷）的方式安装在飞行器的复合结构上，使得起落架及其对飞行器的安装是坚固的并且能承受可变的着陆载荷。 起落架设置在每个侧面并固定在复合隔板之间。 复合隔板也结合在飞机的外表面上。 所描述的安装将负载分配到复合隔板中并从那里分配到外壳中。 负载分配有助于起落架承受可变着陆载荷，有助于保持复合材料的完整性。

公开(公告)号：US20080237396A1

公开(公告)日：2008-10-02

申请号：US11492857

申请日：2006-07-26

申请人： Claude Bietenhader

发明人： Claude Bietenhader

IPC分类号： B64C25/10

CPC分类号： B64C25/00 ,  B64C25/04 ,  B64C25/14

摘要： A steerable auxiliary nose undercarriage (2) for a rotary wing aircraft (1); the undercarriage (2) being retractable substantially rearwards. In the undercarriage (2), an oscillating system (13) presents a elevation stroke (58) about its hinged front end (52) that is greater than a shock absorbing stroke (59), and a shock-absorbing actuator (9) possesses retraction means for going beyond a high abutment position of the oscillating system (13) so that the oscillating system (13) and the shock-absorbing actuator (9) provide both a shock-absorption function and an undercarriage retraction function.

摘要翻译： 用于旋翼飞机（1）的可操纵的辅助鼻架（2）; 起落架（2）可大体向后伸缩。 在起落架（2）中，摆动系统（13）围绕其铰接的前端（52）提供大于冲击吸收冲程（59）的升降冲程（58），并且减震致动器（9）具有 用于超越摆动系统（13）的较高邻接位置的回缩装置，使得摆动系统（13）和减震致动器（9）同时提供减震功能和起落架缩回功能。

公开(公告)号：US07413140B2

公开(公告)日：2008-08-19

申请号：US11408170

申请日：2006-04-21

申请人： Claude Bietenhader

发明人： Claude Bietenhader

IPC分类号： B64C25/00 ,  B64C27/00 ,  B64C1/00 ,  B64C30/00 ,  B64C1/20 ,  B64C1/22 ,  B64C25/10 ,  B64C25/14 ,  B64C25/20 ,  B64D47/00 ,  B64D11/00 ,  B64D13/00 ,  B64D11/06

CPC分类号： B64C1/062 ,  B64C1/06 ,  B64C25/04 ,  B64C25/14 ,  B64C27/04 ,  B64C2001/0072 ,  B64C2025/325 ,  Y02T50/43

摘要： A rotary wing aircraft (1) such as a helicopter comprises a force-transmission structure (5) for transmitting forces, in particular those coming from an undercarriage (2), and that, in longitudinal elevation view, presents an L-shape in which the arrangement (6, 19-21) forms a transversely centered box (6), such that the structure (5) transfers the forces, at least in part, to top and bottom working covering segments of the fuselage.

摘要翻译： 诸如直升机的旋转翼飞机（1）包括用于传递力的力传递结构（5），特别是来自起落架（2）的力传递结构（5），并且在纵向正视图中呈现L形，其中 该布置（6,19-21）形成横向中心的箱体（6），使得结构（5）至少部分地将力传递到机身的顶部和底部工作覆盖段。

公开(公告)号：US20070095976A1

公开(公告)日：2007-05-03

申请号：US11408171

申请日：2006-04-21

申请人： Claude Bietenhader

发明人： Claude Bietenhader

IPC分类号： B64C25/10

CPC分类号： B64C25/00 ,  B64C25/04 ,  B64C25/14

摘要： A steerable auxiliary nose undercarriage (2) for a rotary wing aircraft (1); the undercarriage (2) being retractable substantially rearwards. In the undercarriage (2), an oscillating system (13) presents a elevation stroke (58) about its hinged front end (52) that is greater than a shock absorbing stroke (59), and a shock-absorbing actuator (9) possesses retraction elements for going beyond a high abutment position of the oscillating system (13) so that the oscillating system (13) and the shock-absorbing actuator (9) provide both a shock-absorption function and an undercarriage retraction function.

摘要翻译： 用于旋翼飞机（1）的可操纵的辅助鼻架（2）; 起落架（2）可大体向后伸缩。 在起落架（2）中，摆动系统（13）围绕其铰接的前端（52）提供大于冲击吸收冲程（59）的升降冲程（58），并且减震致动器（9）具有 用于超越摆动系统（13）的高度邻接位置的回缩元件，使得摆动系统（13）和减震致动器（9）同时提供减震功能和起落架缩回功能。

公开(公告)号：US06811117B2

公开(公告)日：2004-11-02

申请号：US10318858

申请日：2002-12-12

申请人： Grégory Reniau

发明人： Grégory Reniau

IPC分类号： B64C2510

CPC分类号： F16C23/10 ,  B64C25/04 ,  B64C25/10 ,  B64F5/10 ,  F16C23/045 ,  F16C2326/43

摘要： A landing gear hinge shaft is installed on an aircraft structure using at least two ball joints (22), at least one of which is adjustable. The differences between the theoretical and real positions of the centers of the balls are measured, and the adjustments that have to be made to bring the centers of the balls back to their theoretical positions is deduced. This is done by making a first adjustment in the axial direction using a shim (30) and a second adjustment in the radial direction by adjusting the rotation of an inner cage (34) and an outer cage (36) of the ball joint. The inner and outer cages have eccentric axes that facilitate the adjustment.

摘要翻译： 起落架铰链轴使用至少两个球接头（22）安装在飞机结构上，其中至少一个是可调节的。 测量球的中心的理论位置和实际位置之间的差异，推导出必须进行将球的中心回到理论位置的调整。 这是通过使用垫片（30）在轴向上进行第一调整，并且通过调节球窝接头的内保持架（34）和外保持架（36）的旋转而在径向上进行第二调整。 内外笼具有便于调节的偏心轴。

公开(公告)号：US20040144889A1

公开(公告)日：2004-07-29

申请号：US10703191

申请日：2003-11-06

发明人： Victor K. Stuhr

IPC分类号： B64C027/22

CPC分类号： B64D29/02 ,  B64C3/32 ,  B64C7/02 ,  B64C25/04 ,  B64C25/10 ,  B64D27/18 ,  B64D33/02 ,  Y02T50/44

摘要： Engine nacelles for use with aircraft. In one embodiment, an engine nacelle includes an inlet having an inlet aperture and an outlet having an outlet aperture. In one aspect of this embodiment, the engine nacelle further includes a first side portion, a second side portion, and a third side portion. The first side portion can extend at least generally between a first edge portion of the inlet aperture and a third edge portion of the outlet aperture. The second side portion can be offset from the first side portion and extend at least generally between a second edge portion of the inlet aperture and a fourth edge portion of the outlet aperture to define a first interior portion. The third side portion can be offset from the second side portion and extend at least generally from the second edge portion of the inlet aperture toward the fourth edge portion of the outlet aperture to define a second interior portion. In another aspect of this embodiment, the first interior portion is configured to house an engine, and the second interior portion is configured to house a landing gear assembly.

摘要翻译： 发动机舱用于飞机。 在一个实施例中，发动机机舱包括具有入口孔的入口和具有出口孔的出口。 在该实施例的一个方面，发动机舱还包括第一侧部分，第二侧部分和第三侧部分。 第一侧部分可以至少大体上在入口孔的第一边缘部分和出口孔的第三边缘部分之间延伸。 第二侧部分可以从第一侧部偏移并且至少大体上在入口孔的第二边缘部分和出口孔的第四边缘部分之间延伸以限定第一内部部分。 第三侧部分可以从第二侧部偏移并且至少大体上从入口孔的第二边缘部分延伸到出口孔的第四边缘部分以限定第二内部部分。 在该实施例的另一方面，第一内部部分构造成容纳发动机，并且第二内部部分构造成容纳起落架组件。

公开(公告)号：US06651928B1

公开(公告)日：2003-11-25

申请号：US10235411

申请日：2002-09-05

申请人： Victor K. Stuhr

发明人： Victor K. Stuhr

IPC分类号： B64B124

CPC分类号： B64D29/02 ,  B64C3/32 ,  B64C7/02 ,  B64C25/04 ,  B64C25/10 ,  B64D27/18 ,  B64D33/02 ,  Y02T50/44

摘要： Engine nacelles for use with aircraft. In one embodiment, an engine nacelle includes an inlet having an inlet aperture and an outlet having an outlet aperture. In one aspect of this embodiment, the engine nacelle further includes a first side portion, a second side portion, and a third side portion. The first side portion can extend at least generally between a first edge portion of the inlet aperture and a third edge portion of the outlet aperture. The second side portion can be offset from the first side portion and extend at least generally between a second edge portion of the inlet aperture and a fourth edge portion of the outlet aperture to define a first interior portion. The third side portion can be offset from the second side portion and extend at least generally from the second edge portion of the inlet aperture toward the fourth edge portion of the outlet aperture to define a second interior portion. In another aspect of this embodiment, the first interior portion is configured to house an engine, and the second interior portion is configured to house a landing gear assembly.

摘要翻译： 发动机舱用于飞机。 在一个实施例中，发动机机舱包括具有入口孔的入口和具有出口孔的出口。 在该实施例的一个方面，发动机舱还包括第一侧部分，第二侧部分和第三侧部分。 第一侧部分可以至少大体上在入口孔的第一边缘部分和出口孔的第三边缘部分之间延伸。 第二侧部分可以从第一侧部偏移并且至少大体上在入口孔的第二边缘部分和出口孔的第四边缘部分之间延伸以限定第一内部部分。 第三侧部分可以从第二侧部偏移并且至少大体上从入口孔的第二边缘部分延伸到出口孔的第四边缘部分以限定第二内部部分。 在该实施例的另一方面，第一内部部分构造成容纳发动机，并且第二内部部分构造成容纳起落架组件。

公开(公告)号：US5062587A

公开(公告)日：1991-11-05

申请号：US558602

申请日：1990-07-27

申请人： Kenneth G. Wernicke

发明人： Kenneth G. Wernicke

IPC分类号： B64C25/04 ,  B64C29/02

CPC分类号： B64C29/02 ,  B64C25/04

摘要： A tail sitter aircraft of a type that takes off and lands on its tail section with the fuselage pointed vertically upward has landing gears located on its rearward end. Each of the landing gears is mounted on a support axis which is offset from the fuselage axis and which intersects a wheel axle at a 90 degree angle. The landing gears are located on the tail section and spaced around the fuselage axis. Two of the landing gears which are opposite each other will be locked so that they can roll only along a single straight line. The other two landing gears, which are also spaced opposite each other, are locked so that they can roll only on a single straight line. The straight lines are perpendicular to each other.

摘要翻译： 具有垂直向上指示的机身起飞并落在其尾部上的类型的尾部飞行器具有位于其后端的起落架。 每个起落架安装在从机身轴线偏移并且以90度角与轮轴相交的支撑轴上。 起落架位于尾部并且围绕机身轴线间隔开。 彼此相对的两个起落架将被锁定，使得它们只能沿着一条直线滚动。 另外两个彼此相对间隔的起落架被锁定，使得它们只能在单个直线上滚动。 直线彼此垂直。

公开(公告)号：US2577385A

公开(公告)日：1951-12-04

申请号：US77492947

申请日：1947-09-19

申请人： TROENDLE JEAN A

发明人： TROENDLE JEAN A

IPC分类号： B64C25/00

CPC分类号： B64C25/06 ,  B64C25/04 ,  B64C25/14 ,  B64C25/22 ,  B64C25/66