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公开(公告)号：US08820680B2
公开(公告)日：2014-09-02
申请号：US13001976
申请日：2009-06-30
IPC分类号： B64C25/10
CPC分类号： B64C25/34 , B64C25/14 , B64C2025/125
摘要： Landing gear mechanism for aircraft are provided which include first and second connecting arms and front and rear wheels operatively associated with the first and second connecting arms, respectively. A balance beam element is indirectly linked to the front and rear wheels through each one of the connecting arms and shock absorber elements, respectively, so that the front portion of the balance beam element is associated with the first portion of the first shock absorber element. A positioning damper element is hingedly connected to the aircraft structure and also connected, directly or indirectly, to a portion of the body of the balance beam element.
摘要翻译： 提供了用于飞机的起落架机构，其包括分别与第一和第二连接臂可操作地相关联的第一和第二连接臂以及前后轮。 平衡梁元件分别通过连接臂和减震器元件中的每一个间接连接到前轮和后轮，使得平衡梁元件的前部与第一减震器元件的第一部分相关联。 定位阻尼器元件铰接地连接到飞行器结构，并且还直接或间接地连接到平衡梁元件的主体的一部分。
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公开(公告)号：US20100219295A1
公开(公告)日：2010-09-02
申请号：US12594276
申请日：2008-03-27
CPC分类号： B64D47/08 , G03B15/006
摘要： The invention discloses a retractable optical sensor (1) composed of an EO/IR (Electro-Optical/Infrared Remote) sensor (2) which is fastened to an articulated structure (3) that is actuated by an actuator (4); the structure (3) accomplishes angular movement whose turning point is located in an end that is mounted to an articulation support (5); the articulation support (5) is fastened to the support (6) which is fastened to the aircraft structure (7); the actuator (4) is electrically or hydraulically actuated and it has an end united to a support (8) which is fastened to the aircraft structure (7); the opposite end of the actuator (4) is articulated to the structure (3) and it promotes angular movement of the structure (3); the EO/IR sensor (2) presents a cylindrical shape having a spherical end; an articulated door (9) solidary to the movement of the structure (3) is mounted close to said spherical end; the movement of the door (9) is limited by the rods (10) for actuating the door, and the rods (10) are also fastened to the structure (3).
摘要翻译： 本发明公开了一种由EO / IR（电光/红外遥控）传感器（2）构成的伸缩式光学传感器（1），其被紧固到由致动器（4）致动的铰接结构（3）; 结构（3）实现角运动，其转向点位于安装到关节支撑件（5）的端部中; 铰接支撑件（5）固定到固定到飞行器结构（7）上的支撑件（6）上。 致动器（4）是电动或液压致动的，并且其一端结合到紧固到飞机结构（7）的支撑件（8）上; 致动器（4）的相对端被铰接到结构（3）上并促进结构（3）的角运动。 EO / IR传感器（2）具有球形端的圆柱形状; 靠近结构（3）的运动的铰接门（9）靠近所述球形端安装; 门（9）的移动被用于致动门的杆（10）限制，并且杆（10）也被紧固到结构（3）。
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公开(公告)号：US08453968B2
公开(公告)日：2013-06-04
申请号：US12594276
申请日：2008-03-27
IPC分类号： B64C1/22
CPC分类号： B64D47/08 , G03B15/006
摘要： A retractable optical sensor system includes a sensor body (e.g., an electro-optical/infrared (EO/IR) remote sensor) connected to a sensor support structure that is actuated by an actuator. The sensor support structure accomplishes angular movement whose turning point is located in an end that is mounted to an articulation support. A bulkhead support is fastened to the aircraft structure. The actuator is electrically or hydraulically actuated and has an end united to a support member which is fastened to the aircraft structure. The opposite end of the actuator is connected for articulation to the sensor support structure so as to cause angular movement thereof. Articulation of the sensor support structure causes the sensor body to extend/retract while simultaneously causing the fairing door to be raised/lowered, respectively.
摘要翻译： 可伸缩光学传感器系统包括连接到由致动器致动的传感器支撑结构的传感器体（例如，电光/红外（EO / IR）远程传感器）。 传感器支撑结构实现角运动，其转动点位于安装到铰接支撑件的端部。 舱壁支架固定在飞机结构上。 致动器是电动或液压致动的，并且其端部与固定到飞行器结构的支撑构件结合。 致动器的相对端被连接用于铰接到传感器支撑结构，以便引起其角度运动。 传感器支撑结构的接合使得传感器主体能够延伸/缩回，同时使整流罩门分别升高/降低。
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公开(公告)号：US20110174924A1
公开(公告)日：2011-07-21
申请号：US13001976
申请日：2009-06-30
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）。
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