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公开(公告)号：US09033275B2
公开(公告)日：2015-05-19
申请号：US13240817
申请日：2011-09-22
申请人： André Barbieri , Bruno Cacciaguerra
发明人： André Barbieri , Bruno Cacciaguerra
CPC分类号： B64C25/00 , B64C25/14 , B64C2025/125 , B64C2025/325
摘要： An undercarriage (6) provided with an undercarriage leg (10) and a shock absorber (20), said undercarriage (6) including an actuator-shock absorber (30), said undercarriage leg (10) comprising both a first element (11) carrying contact means (13) and a second element (12), which elements are hinged to each other. The undercarriage (6) includes pivot means (40) enabling said undercarriage leg (10) to pivot firstly in a first direction (S1) in order to retract said undercarriage leg (10) into said housing (4) under drive from said actuator-shock absorber (30), and secondly, during an emergency landing, in a second direction (S2) opposite to the first direction (S1) in order to move said undercarriage leg (10) away from said housing (4) while stressing said actuator-shock absorber (30).
摘要翻译： 一种具有起落架脚架（10）和减震器（20）的起落架（6），所述起落架（6）包括致动器减振器（30），所述起落架腿部（10）包括第一元件（11） 承载接触装置（13）和第二元件（12），所述元件彼此铰接。 起落架（6）包括枢转装置（40），其使得所述起落架腿（10）首先在第一方向（S1）枢转，以便在所述致动器（10）的驱动下将所述起落架腿（10）缩回到所述壳体（4） 减震器（30），其次，在紧急着陆期间，在与所述第一方向（S1）相反的第二方向（S2）上移动所述起落架腿（10）以远离所述壳体（4），同时将所述致动器 - 减震器（30）。
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公开(公告)号：US08850950B2
公开(公告)日：2014-10-07
申请号：US13559973
申请日：2012-07-27
申请人： Aaron Deckard , James Buechler , Michael Holzmeyer , Glen Dick , Paul Danesha
发明人： Aaron Deckard , James Buechler , Michael Holzmeyer , Glen Dick , Paul Danesha
IPC分类号： F41A23/00 , F41A27/14 , F41A19/10 , F41A9/60 , B64D7/06 , F41A9/00 , F41A19/08 , F41A27/06 , B64C25/14
摘要： A weapon mounting system for a vehicle, such as a helicopter. The weapon mounting system illustratively includes a weapon cradle supporting a machine gun for pivoting movement about a generally horizontal elevational axis. A carriage supports the weapon cradle and is supported by a pintle for rotation about a generally vertical azimuth axis. An ejection collection device is supported by the carriage and collects spent shell casings and links ejected from the machine gun for discharge through the pintle. A trigger assembly illustratively provides for manual operation by a gunner and for remote electrical operation by a pilot.
摘要翻译： 用于车辆的武器安装系统，例如直升机。 武器安装系统示例性地包括支撑机枪的武器支架，用于围绕大致水平的仰角枢转运动。 托架支撑武器支架，并由枢轴支撑，以围绕大致垂直的方位轴线旋转。 喷射收集装置由托架支撑并收集从机枪喷出的用过的壳壳和链节，以通过枢轴排放。 触发器组件示意性地提供了枪手的手动操作和飞行员的远程电气操作。
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113.发明授权公开(公告)号：US08820679B2
公开(公告)日：2014-09-02
申请号：US12990648
申请日：2009-03-12
IPC分类号： B64C25/26
摘要： The invention relates to landing gear mounted on an aircraft in such a way as to be movable between a stowed position and a deployed position, the landing gear incorporating: a barrel mounted in a hinged way on the aircraft; a folding strut with two arms; a stabilizing member to stabilize the strut in an aligned position, having two rods hinged to each other; a telescopic unlocking member having one end coupled to one of the rods, the telescopic member being selectively activatable to break an alignment of the rods. According to the invention, said rod has an aperture in which the end of the telescopic unlocking member engages and which is arranged in such a way that, when the telescopic member is activated, said end interacts with an end of the aperture to move the associated rod toward a non-aligned position which said rod reaches when the telescopic member reaches an internal stop, the aperture allowing any hinged movement of the rod beyond the non-aligned position.
摘要翻译： 本发明涉及安装在飞机上的起落架，以便在收起位置和展开位置之间移动，起落架包括：以铰接方式安装在飞行器上的筒体; 带双臂的折叠支柱 稳定构件，用于将支柱稳定在对准位置，具有彼此铰接的两个杆; 伸缩解锁构件，其一端联接到所述杆之一，所述伸缩构件可选择性地激活以破坏所述杆的对准。 根据本发明，所述杆具有孔，其中伸缩解锁构件的端部接合并且以这样的方式布置，使得当伸缩构件被启动时，所述端部与孔的端部相互作用以移动相关联的 杆朝向不对准位置，当伸缩构件到达内部止动件时，所述杆到达，所述孔允许杆的任何铰接运动超过非对准位置。
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公开(公告)号：US20140197277A1
公开(公告)日：2014-07-17
申请号：US14154702
申请日：2014-01-14
申请人： William M. OTTO
发明人： William M. OTTO
IPC分类号： B64C1/00
CPC分类号： B64C25/20 , B64C1/00 , B64C1/065 , B64C1/069 , B64C1/10 , B64C3/185 , B64C3/26 , B64C3/58 , B64C5/02 , B64C5/16 , B64C9/02 , B64C9/16 , B64C9/20 , B64C13/30 , B64C25/02 , B64C25/10 , B64C25/12 , B64C25/14 , B64C25/18 , B64C25/22 , B64C2025/125 , B64D33/10 , B64D37/04 , F02B37/001 , Y02T50/32 , Y02T50/44
摘要： A support unit for a structure within a pressure vessel that includes an external load distribution plate, an internal load distribution plate, a standoff unit between the external load distribution plate and the internal load distribution plate that extends through an opening in a pressure vessel.
摘要翻译： 用于压力容器内的结构的支撑单元，其包括外部负载分配板，内部负载分配板，外部负载分配板和内部负载分配板之间的隔离单元，所述支架单元延伸穿过压力容器中的开口。
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公开(公告)号：US20140131514A1
公开(公告)日：2014-05-15
申请号：US13674303
申请日：2012-11-12
发明人： Brian G. Cook , John Louis , Thomas Van de Ven , Robert M. Vieito
IPC分类号： B64C25/34
CPC分类号： B64C25/001 , B64C25/14 , B64C25/16 , B64C2025/003 , B64C2025/006 , Y10T29/49826
摘要： A nose landing gear arrangement for an aircraft and a method of assembling the nose landing gear arrangement are disclosed herein. The nose landing gear arrangement includes, but is not limited to, a wheel assembly, a shock strut extending upwards from the wheel assembly towards a fuselage of the aircraft, and a torque arm assembly coupled to the wheel assembly and to the shock strut. The torque arm assembly is configured to transmit torque to the wheel assembly. The torque arm assembly is disposed forward of the shock strut with respect to a direction of travel of the aircraft.
摘要翻译： 本文公开了一种用于飞行器的前起落架装置和组装前起落架装置的方法。 前起落架装置包括但不限于轮组件，从车轮组件向上延伸到飞行器的机身的冲击支柱，以及联接到车轮组件和冲击支柱的扭矩臂组件。 扭矩臂组件构造成将扭矩传递到车轮组件。 扭矩臂组件相对于飞行器的行进方向设置在冲击支柱的前方。
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公开(公告)号：US20140060309A1
公开(公告)日：2014-03-06
申请号：US13559973
申请日：2012-07-27
申请人： Aaron Deckard , James Buechler , Michael Holzmeyer , Glen Dick , Paul Danesha
发明人： Aaron Deckard , James Buechler , Michael Holzmeyer , Glen Dick , Paul Danesha
摘要： A weapon mounting system for a vehicle, such as a helicopter. The weapon mounting system illustratively includes a weapon cradle supporting a machine gun for pivoting movement about a generally horizontal elevational axis. A carriage supports the weapon cradle and is supported by a pintle for rotation about a generally vertical azimuth axis. An ejection collection device is supported by the carriage and collects spent shell casings and links ejected from the machine gun for discharge through the pintle. A trigger assembly illustratively provides for manual operation by a gunner and for remote electrical operation by a pilot.
摘要翻译： 用于车辆的武器安装系统，例如直升机。 武器安装系统示例性地包括支撑机枪的武器支架，用于围绕大致水平的仰角枢转运动。 托架支撑武器支架，并由枢轴支撑，以围绕大致垂直的方位轴线旋转。 喷射收集装置由托架支撑并收集从机枪喷出的用过的壳壳和链节，以通过枢轴排放。 触发器组件示意性地提供了枪手的手动操作和飞行员的远程电气操作。
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公开(公告)号：US08640988B2
公开(公告)日：2014-02-04
申请号：US12918492
申请日：2009-02-24
申请人： Robert Ian Thompson
发明人： Robert Ian Thompson
摘要： An aircraft landing gear comprising: an arm mounted to a pivot and carrying one or more wheel assemblies; and a composite leaf spring which is coupled to the arm and arranged to provide a resilient biasing force which opposes rotation of the arm about the pivot. The arm can be made relatively stiff in comparison with the leaf spring, so that load is transferred directly into the pivot without a large amount of bending of the leg. The leaf spring shock absorber typically has a reduced part count compared with a conventional oleo-pneumatic shock absorber. By forming the leaf spring from a composite material, its weight is significantly reduced in comparison with a conventional metal spring, making it suitable for use on a relatively large aircraft.
摘要翻译： 一种飞机起落架，包括：安装到枢轴并承载一个或多个车轮组件的臂; 以及复合板簧，其联接到所述臂并布置成提供与所述臂围绕所述枢轴旋转的弹性偏压力。 与板簧相比，臂可以制成相对刚性，使得负载直接转移到枢轴中，而不会有大量的腿的弯曲。 与常规的油气减震器相比，板簧减震器通常具有减少的部件数量。 通过从复合材料形成板簧，与传统的金属弹簧相比，其重量显着降低，使其适用于较大的飞机。
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公开(公告)号：US20130341457A1
公开(公告)日：2013-12-26
申请号：US13531650
申请日：2012-06-25
申请人： Phillip K. Wilson
发明人： Phillip K. Wilson
IPC分类号： B64C25/60
摘要： The landing gear system for an aircraft includes a shock strut assembly that is coupled to the airframe with a universal joint. A tire member is mounted to the shock strut assembly. The landing gear system also includes a drag brace assembly coupled to an airframe of the aircraft with a spindle, the spindle being rotatable about a spindle axis. A radius rod is rotatably coupled to the airframe of the aircraft. The radius rod and the shock strut assembly are retractable about a retraction rotation axis. Further, the spindle axis has a common intersection point with the centerline axis and the retraction rotation axis. The orientation of the spindle axis causes a translation of the tire member to have a longitudinal component during a compression of the shock strut assembly.
摘要翻译： 用于飞机的起落架系统包括用万向接头联接到机身的冲击支柱组件。 轮胎构件安装在冲击支柱组件上。 起落架系统还包括与主轴联接到飞行器的机身的牵引支架组件，所述主轴可围绕主轴轴线旋转。 半径杆可旋转地联接到飞行器的机身。 半径杆和冲击支柱组件围绕收回旋转轴线可收缩。 此外，主轴具有与中心线轴和缩回旋转轴线的共同交点。 在冲击支柱组件的压缩过程中，主轴的方位导致轮胎构件的平移，以具有纵向分量。
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公开(公告)号：US08602352B2
公开(公告)日：2013-12-10
申请号：US13376160
申请日：2010-06-03
摘要： A method of operating an aircraft landing gear between a deployed position and a retracted position. The landing gear comprises a leg hinged to the aircraft, the leg being stabilized in the deployed position by a folding strut comprising two hinged-together links, the strut being held in an aligned position by a stabilizer member comprising two hinged-together links themselves held in alignment by a locking member. The method comprises the steps of arranging the strut (2; 102) and the stabilizer member (4; 104) in such a manner that at least one of the links (4a; 104a) of the stabilizer member moves continuously during a movement of the leg from the deployed position to the retracted position, and of attaching an operating actuator (10; 110) to the link in order to cause the link to pivot against the locking member and to exert thereon a force tending to move the leg.
摘要翻译： 一种在展开位置和缩回位置之间操作飞机起落架的方法。 起落架包括铰接到飞行器的腿部，腿部由包括两个铰接在一起的连杆的折叠支柱稳定在展开位置，该支柱由稳定器构件保持在对准位置，稳定器构件包括两个铰接在一起的链节， 通过锁定构件对齐。 该方法包括以下步骤：将支柱（2; 102）和稳定器构件（4; 104）布置成使得稳定器构件的至少一个连杆（4a; 104a）在移动过程中连续地移动 从展开位置到缩回位置，并且将操作致动器（10; 110）连接到连杆上，以便使连杆枢转抵靠锁定件并在其上施加倾向于移动腿部的力。
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公开(公告)号：US20130134259A1
公开(公告)日：2013-05-30
申请号：US13689324
申请日：2012-11-29
发明人： Patrick Lieven , Pascal Chaumel
IPC分类号： B64C25/20
摘要： A front structure of an aircraft fuselage comprising landing gear pivoting about a main shaft and a stay shaft. The front structure also comprises a first reinforcing frame and a second reinforcing frame, the main shaft and the stay shaft being respectively connected to the first and second frames, and a device for the mechanical connection and transfer of forces connecting the stay shaft and the main shaft and transferring to the main shaft a portion of the forces induced by the wheels of the landing gear onto the stay shaft, the second frame and said device being perpendicular to one another.
摘要翻译： 飞机机身的前部结构，包括围绕主轴和支撑轴枢转的起落架。 前部结构还包括第一加强框架和第二加强框架，主轴和支撑轴分别连接到第一和第二框架，以及用于机械连接和传递连接支撑轴和主体的力的装置 并且将起落架的车轮所引起的力的一部分传递到主轴上，并将第二框架和所述装置彼此垂直。
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