公开(公告)号：US07984873B2

公开(公告)日：2011-07-26

申请号：US12248410

申请日：2008-10-09

申请人： Vincent Lassus ,  Benjamin Talon

发明人： Vincent Lassus ,  Benjamin Talon

IPC分类号： B64C25/22

CPC分类号： B64C25/14 ,  B64C25/22 ,  B64C25/60 ,  B64C2025/325 ,  F15B15/204

摘要： A retraction cylinder (20) makes it possible to retract a leg (10) of a rotorcraft landing gear, the retraction cylinder (20) comprising a retraction chamber (33) and an extension chamber (34) separated by a head (26) of a piston (25), the piston (25) sliding in a cylindrical sheath (35). In addition, the retraction cylinder (20) comprises a return element (23) and a control chamber (22) furnished with a first fluid, this control chamber (22) being separated from the return element (23) by a movable release member (24), the movable release member (24) sliding so that the retraction cylinder (20) fulfils a damping function when a control pressure exerted by the first fluid on the movable release member (24) is greater than a return pressure exerted by the return element (23).

摘要翻译： 缩回气缸（20）使得可以缩回旋翼飞机起落架的腿部（10），缩回气缸（20）包括收缩室（33）和由头部（26）分开的延伸室（34） 活塞（25），所述活塞（25）在圆柱形护套（35）中滑动。 此外，回缩缸（20）包括具有第一流体的返回元件（23）和控制室（22），该控制室（22）通过可移动释放构件与返回元件（23）分离 24），当由第一流体施加在可移动释放构件（24）上的控制压力大于由返回件施加的返回压力时，可移动释放构件（24）滑动使得缩回缸（20）履行阻尼功能 元件（23）。

公开(公告)号：US20110174924A1

公开(公告)日：2011-07-21

申请号：US13001976

申请日：2009-06-30

申请人： Mario Sergio Dias Ferraz

发明人： Mario Sergio Dias Ferraz

IPC分类号： B64C25/10 ,  B64C25/18 ,  B64C25/26

CPC分类号： B64C25/34 ,  B64C25/14 ,  B64C2025/125

摘要： Landing gear mechanism for aircraft comprising at least a first connecting arm (2′) and a second connecting arm (2), at least a front wheel (3′) and rear wheels (3) each associated with one of the connecting arms (2′, 2) with a balance beam element (4), which is indirectly linked to said front and rear wheels (3′, 3) through each one of the connecting arms (2′, 2) and each one of the shock absorber elements (1′, 1), respectively, so that the front portion of the balance beam element (4) is associated with the first portion of the first shock absorber element (1′), which in turn has a second portion associated with a first portion of the first connecting arm (2′), which in turn has a second portion associated with the aircraft structure (10), and said rear portion of the balance beam element (4) is associated with a first portion of the second shock absorber element (1), which in turn has a second portion associated with a first portion of the second connecting arm (2), which in turn has a second portion associated with the aircraft structure (10), further comprising the positioning damper element (9) hingedly connected to the aircraft structure (10) and also connected, directly or indirectly, to a portion of the body of the balance beam element (4).

摘要翻译： 至少包括第一连接臂（2'）和第二连接臂（2）的飞行器起落架机构，至少前轮（3'）和后轮（3），每个与所述连接臂（2）中的一个相关联 '，2）与通过每个连接臂（2'，2）间接连接到所述前轮和后轮（3'，3）的平衡梁元件（4）和每个减震器元件 （1'），使得所述平衡梁元件（4）的前部与所述第一减震器元件（1'）的第一部分相关联，所述第一部分又具有与第一部分相关联的第二部分 所述第一连接臂（2'）的部分又具有与所述飞机结构（10）相关联的第二部分，所述平衡梁元件（4）的所述后部与所述第二减震器 元件（1），其又具有与第二连接臂（2）的第一部分相关联的第二部分， 其又具有与飞行器结构（10）相关联的第二部分，还包括铰接地连接到飞行器结构（10）的定位阻尼元件（9），并且还直接或间接地连接到飞行器结构（10）的主体的一部分 平衡梁单元（4）。

公开(公告)号：US20110163202A1

公开(公告)日：2011-07-07

申请号：US12990648

申请日：2009-03-12

申请人： Laurent Martinez ,  François Boilley ,  Gérard Balducci

发明人： Laurent Martinez ,  François Boilley ,  Gérard Balducci

IPC分类号： B64C25/26 ,  B64C25/10

CPC分类号： B64C25/20 ,  B64C25/10 ,  B64C25/14 ,  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，其中可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。

公开(公告)号：US20110155845A1

公开(公告)日：2011-06-30

申请号：US12980967

申请日：2010-12-29

申请人： Fabio NANNONI ,  Dante Ballerio

发明人： Fabio NANNONI ,  Dante Ballerio

IPC分类号： B64C25/10 ,  B64C25/34 ,  B64C25/52

CPC分类号： B64C25/14 ,  B64C25/66 ,  B64C2025/325

摘要： A retractable helicopter landing gear has a suspension structure supporting one wheel, and is movable between a withdrawn position, to reduce drag on the helicopter, and a lowered position for landing and takeoff of the helicopter. The landing gear also has a skid, which is located between the axis of rotation of the wheel and the periphery of the wheel, is diametrically opposite the suspension structure, and is connected to the suspension structure by a connecting device having a torsion bar.

摘要翻译： 可伸缩直升机起落架具有支撑一个车轮的悬挂结构，并且可以在撤回位置之间移动，以减少直升机上的阻力，以及用于降落和起飞直升机的降低位置。 起落架还具有位于车轮的旋转轴线和车轮周边之间的滑动件，与悬架结构径向相对，并且通过具有扭杆的连接装置连接到悬架结构。

公开(公告)号：US20100001129A1

公开(公告)日：2010-01-07

申请号：US12373055

申请日：2007-06-28

申请人： Bernard Guering

发明人： Bernard Guering

IPC分类号： B64C25/10

CPC分类号： B64C1/068 ,  B64C25/04 ,  B64C25/14 ,  B64C2001/0027

摘要： A front landing gear storage compartment configured for an airplane including a set of retractable landing gears including a front gear centered on a longitudinal median plane of the fuselage. The storage compartment forms an impervious partition between a pressurized zone and the housing for the front gear in its retracted position, and includes a reinforced upper face including a more or less flat zone, more or less horizontal when the airplane is on the ground, so as to form a floor of a pressurized area of the airplane.

摘要翻译： 一种前起落架储存室，其构造成用于飞机，包括一组可缩回的起落架，包括以机身纵向中心平面为中心的前齿轮。 存储隔间在加压区域和壳体之间形成不可渗透的分隔物，用于前端齿轮处于其缩回位置，并且包括加强的上表面，其包括或多或少的平坦区域，当飞机在地面上时，该区域或多或少是水平的，因此 以形成飞机加压区域的地板。

公开(公告)号：US20090321560A1

公开(公告)日：2009-12-31

申请号：US12491021

申请日：2009-06-24

申请人： William E. Luce ,  Phillip K. Wilson ,  Jonathon R. Davis

发明人： William E. Luce ,  Phillip K. Wilson ,  Jonathon R. Davis

IPC分类号： B64C25/10

CPC分类号： B64C25/14 ,  B64C2025/008

摘要： A landing gear system includes a shock strut assembly and a linkage member coupled to an aircraft. Preferably, the shock strut assembly and linkage member are oriented or angled relative to one another in a non-parallel relationship. Actuation of the linkage member moves the shock strut from a de-hiked to a hiked configuration or vice-versa. In addition, the orientation of the linkage member relative to the shock strut assembly permits it to automatically move the shock strut assembly to the de-hiked position during retraction of the landing gear system and prevents the shock strut assembly from exceeding a desired length during retraction. The linkage member may take the form of a hydraulic actuator having a lower end portion coupled to an inner cylinder of the shock strut assembly and an upper end portion coupled to the aircraft aft of where the shock strut assembly is coupled to the aircraft.

摘要翻译： 起落架系统包括冲击支柱组件和联接到飞行器的联动构件。 优选地，冲击支柱组件和连接构件以非平行关系相对于彼此定向或成角度。 联动构件的致动将冲击支柱从脱轨装置移动到高架配置，反之亦然。 此外，联动构件相对于冲击支柱组件的取向允许其在起落架系统缩回期间自动地将冲击支柱组件移动到脱离位置，并且在缩回期间防止冲击支柱组件超过所需长度 。 连杆构件可以采取液压致动器的形式，其具有联接到减震支柱组件的内圆筒的下端部分，以及联接到飞行器后部的上端部分，其中冲击支柱组件联接到飞行器。

公开(公告)号：US07575193B2

公开(公告)日：2009-08-18

申请号：US11429255

申请日：2006-05-08

申请人： Herve Payen ,  Vincent Malfuson

发明人： Herve Payen ,  Vincent Malfuson

IPC分类号： B64C25/00 ,  B64C25/52 ,  B64C25/60

CPC分类号： B64C25/14 ,  B64C25/00 ,  B64C25/10 ,  B64C2025/325

摘要： An undercarriage (2) for an aircraft (1) includes anti-crash elements that are specific to a second stage of a crash after the end of a first stage. The undercarriage includes: a device for blocking a retraction actuator (6); a device for retaining the actuator (6) functionally separated from a landing gear leg (9); and a device for applying controlled braking to the pivoting of the leg (9) by irreversible lengthening of a deformable member (25).

摘要翻译： 用于飞机（1）的起落架（2）包括特定于第一阶段结束后的第二阶段的碰撞元件。 起落架包括：用于阻挡回缩致动器（6）的装置; 用于保持与起落架脚（9）功能分离的致动器（6）的装置; 以及用于通过可变形构件（25）的不可逆延长来对腿部（9）的枢转施加受控制动的装置。

公开(公告)号：US07429019B1

公开(公告)日：2008-09-30

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 ,  B64C25/14 ,  B64C25/60 ,  B64C25/00 ,  B64C27/00 ,  B64C1/00 ,  B64C25/50

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：US20070205326A1

公开(公告)日：2007-09-06

申请号：US11473977

申请日：2006-06-23

申请人： William Waide

发明人： William Waide

IPC分类号： B64C25/00

CPC分类号： B64C25/14 ,  B64C29/0033 ,  B64C2025/008 ,  B64C2025/125

摘要： Electrically controlled and/or actuated landing gear mechanisms are presented that allow for adjustment of aircraft attitude on the ground as well as for retraction and extension of the landing gear in a single unit. Most preferably, the electric actuator is positioned within the diameter of the strut to thereby form a compact and load bearing structure.

摘要翻译： 提出了电控和/或致动的起落架机构，其允许调整飞机在地面上的姿态以及起落架在单个单元中的缩回和延伸。 最优选地，电致动器定位在支柱的直径内，从而形成紧凑的承载结构。

公开(公告)号：US20070057117A1

公开(公告)日：2007-03-15

申请号：US11429255

申请日：2006-05-08

申请人： Herve Payen ,  Vincent Malfuson

发明人： Herve Payen ,  Vincent Malfuson

IPC分类号： B64C25/00

CPC分类号： B64C25/14 ,  B64C25/00 ,  B64C25/10 ,  B64C2025/325

摘要： An undercarriage (2) for an aircraft (1) includes anti-crash elements that are specific to a second stage of a crash after the end of a first stage. The undercarriage includes: a device for blocking a retraction actuator (6); a device for retaining the actuator (6) functionally separated from a landing gear leg (9); and a device for applying controlled braking to the pivoting of the leg (9) by irreversible lengthening of a deformable member (25).

摘要翻译： 用于飞机（1）的起落架（2）包括特定于第一阶段结束后的第二阶段的碰撞元件。 起落架包括：用于阻挡回缩致动器（6）的装置; 用于保持与起落架脚（9）功能分离的致动器（6）的装置; 以及用于通过可变形构件（25）的不可逆延长来对腿部（9）的枢转施加受控制动的装置。