公开(公告)号：US20150367933A1

公开(公告)日：2015-12-24

申请号：US14308162

申请日：2014-06-18

申请人： Goodrich Corporation

发明人： Chi Shing Li ,  Marco Perrella

IPC分类号： B64C25/62 ,  B64C25/22 ,  F16F9/02

CPC分类号： B64C25/62 ,  B64C25/22 ,  B64C25/60 ,  F16F9/0209 ,  F16F9/0245

摘要： A strut length and pressure regulation system is disclosed. The system may regulate the length of a strut by controlling the amount of gas in the strut. The system may monitor the length of the strut and/or pressure of gas in the strut and may change the amount of gas in the strut in response to the length of the strut and/or pressure of gas in the strut. In this manner, the effects of temperature changes may be compensated.

摘要翻译： 公开了支柱长度和压力调节系统。 该系统可以通过控制支柱中的气体量来调节支柱的长度。 系统可以监测支柱的长度和/或支柱中的气体的压力，并且可以响应于支柱的长度和/或支柱中的气体的压力而改变支柱中的气体量。 以这种方式，可以补偿温度变化的影响。

公开(公告)号：US08998133B2

公开(公告)日：2015-04-07

申请号：US13078075

申请日：2011-04-01

申请人： Justin Duane Cottet

发明人： Justin Duane Cottet

IPC分类号： B64C25/22 ,  B64C25/60 ,  B64C25/00

CPC分类号： B64C25/60 ,  B64C25/22 ,  B64C2025/008

摘要： A method and apparatus for changing a length of a landing gear system. A first cylinder and a second cylinder are moved relative to each other along an axis extending centrally through the first cylinder and the second cylinder such that the first cylinder and the second cylinder are in an extended position. In response to the first cylinder and the second cylinder being in the extended position, a flow of a fluid is substantially prevented between a first chamber formed between the first cylinder and the second cylinder and a second chamber within the first cylinder and the second cylinder. In response to a pressure applied to the first chamber, the first cylinder and the second cylinder are moved relative to each other along the axis such that a length of the first cylinder and the second cylinder is reduced.

摘要翻译： 一种用于改变起落架系统的长度的方法和装置。 第一气缸和第二气缸沿着通过第一气缸和第二气缸中心延伸的轴相对于彼此移动，使得第一气缸和第二气缸处于伸出位置。 响应于第一气缸和第二气缸处于伸展位置，在形成在第一气缸和第二气缸之间的第一腔室和第一气缸和第二气缸内的第二腔室之间基本上防止了流体的流动。 响应于施加到第一室的压力，第一气缸和第二气缸沿轴线相对于彼此移动，使得第一气缸和第二气缸的长度减小。

公开(公告)号：US08827205B2

公开(公告)日：2014-09-09

申请号：US12463207

申请日：2009-05-08

申请人： Garth L. Mason

发明人： Garth L. Mason

IPC分类号： B64C25/58 ,  B64C25/30 ,  B64C25/18 ,  B64C25/22

CPC分类号： B64C25/18 ,  B64C25/22 ,  B64C25/30 ,  Y10T74/18592

摘要： An electromechanical linear actuator includes a pneumomechanical back-up system to ensure extension of retractable landing gear for landing an aircraft. Structurally, the linear actuator includes a stator forming a channel for receiving a ball screw. Further, the actuator includes a ball screw housing forming a chamber for receiving the ball screw. Specifically, the ball screw and the housing are in threaded engagement to translate rotation of the ball screw into axial extension of the housing. To power electromechanical extension of the actuator, the ball screw is selectively engaged to a motor with a gear train. Importantly, fluid communication between the ball screw housing and a pressurized fluid is selectively provided by a valve. If electromechanical extension of the actuator fails, the gear train is disconnected from the ball screw and the pressurized fluid is introduced into the chamber to drive pneumomechanical extension.

摘要翻译： 机电线性致动器包括气动机械备用系统，以确保用于着陆飞机的可伸缩起落架的延伸。 在结构上，线性致动器包括形成用于接收滚珠丝杠的通道的定子。 此外，致动器包括形成用于容纳滚珠丝杠的腔室的滚珠丝杠壳体。 具体地，滚珠丝杠和壳体是螺纹接合的，以将滚珠丝杠的旋转转移到壳体的轴向延伸。 为了对致动器的机电延伸进行动力，滚珠丝杠选择性地与具有齿轮系的马达接合。 重要的是，滚珠丝杠壳体和加压流体之间的流体连通由阀选择性地提供。 如果执行机构的机电延伸器故障，齿轮系与滚珠丝杠断开，加压流体被引入腔室，以驱动气力机械延伸。

公开(公告)号：US20120112001A1

公开(公告)日：2012-05-10

申请号：US13332680

申请日：2011-12-21

申请人： Ian Bennett ,  Richard C. Lang ,  Robert A. Menezes

发明人： Ian Bennett ,  Richard C. Lang ,  Robert A. Menezes

IPC分类号： B64C25/22 ,  B64C25/10

CPC分类号： B64C25/60 ,  B64C25/22 ,  B64C25/34 ,  B64C25/58

摘要： An auxiliary mechanism includes a lever unit, a spring unit and a positioning unit. One of the units pivotally connects to the upper portion of a main shock absorber strut so as to pivot between a predetermined lower position for take-off and landing and an upper position. Another unit pivotally connects at an upper end to the upper portion of the main shock absorber strut and pivotally connects at a lower end to the first unit. A third unit pivotally connects at a lower end to the bogie beam at an auxiliary pivot and connects at an upper end to the lever. The positioning unit assumes either a contracted state or extended state for taxiing, take-off and landing, and assumes the other state for stowing the landing gear after take-off. The spring unit provides spring resistance to pivotal movements of the bogie beam about the main pivot during taxiing.

摘要翻译： 辅助机构包括杠杆单元，弹簧单元和定位单元。 其中一个单元枢转地连接到主减震器支柱的上部，以便在用于起飞和着陆的预定下部位置和上部位置之间枢转。 另一个单元在上端枢转地连接到主减震器支柱的上部，并且在下端枢转地连接到第一单元。 第三单元在下端处以辅助枢轴枢转地连接到转向架梁，并且在上端连接到杠杆。 定位单元承担滑行，起飞和着陆的承包状态或延长状态，并在起飞后采取起落架的另一种状态。 弹簧单元在滑行期间提供弹簧抵抗转向架梁绕主枢轴的枢转运动。

公开(公告)号：US20120097792A1

公开(公告)日：2012-04-26

申请号：US13273607

申请日：2011-10-14

申请人： Sébastien ERNIS ,  Xavier JUBERT ,  David LEUTARD

发明人： Sébastien ERNIS ,  Xavier JUBERT ,  David LEUTARD

IPC分类号： B64C25/22 ,  B64C25/10

CPC分类号： B64C25/22

摘要： A hydraulic circuit for actuating an undercarriage, the circuit comprising: a feed line for feeding fluid and a return line; at least one door selector connected to the feed and return lines, the selector feeding door service lines, including an opening line and a closing line for opening and closing the doors; at least one undercarriage selector connected to the feed and return lines, feeding undercarriage service lines including a deployment line and a raising line for deploying and raising the undercarriage; and a door unhooking line and an undercarriage unhooking line. The door unhooking line is connected to at least one undercarriage service line while the undercarriage unhooking line is connected to at least one door service line, the circuit also including means for connecting the door service lines together during a door opening stage, and means for connecting the undercarriage service lines together during an undercarriage deployment stage.

摘要翻译： 一种用于致动起落架的液压回路，所述回路包括：用于供给流体的进给管线和回流管线; 至少一个门选择器，连接到馈送和返回线路，选择器馈送门服务线路，包括用于打开和关闭门的开口线和闭合线; 至少一个起落架选择器连接到进给和返回线路，提供包括用于部署和升起起落架的展开线和升起线的底盘服务线; 和一个门脱钩线和一个起落架的脱钩线。 门起吊线路连接到至少一个起落架服务线，而起落架脱钩线连接到至少一个门服务线，该电路还包括用于在门打开阶段将门服务线连接在一起的装置，以及用于连接的装置 在起落架部署阶段，起落架服务线在一起。

公开(公告)号：US20110127376A1

公开(公告)日：2011-06-02

申请号：US13002158

申请日：2009-07-06

申请人： Gilbert Gleyse

发明人： Gilbert Gleyse

IPC分类号： B64C25/22 ,  B64C25/16

CPC分类号： B64C25/16 ,  B64C25/22

摘要： The invention concerns a system for opening and closing a door (50) for a landing gear (30) compartment (20) of an aircraft (10) having great positioning freedom.According to the invention, the connecting means (60, 70, 81, 82) between the landing gear (30) and the door (50) include a first system forming an actuator (60) mounted on the landing gear (30) and a second system forming an actuator (70) mounted on the door (50), the two systems forming actuators (60, 70) being connected to each other by at least one fluid communication means (81, 82) such that actuating the first system forming an actuator (60) causes the actuation of the second system forming an actuator (70).

摘要翻译： 本发明涉及一种用于打开和关闭具有很大定位自由度的飞机（10）的起落架（30）隔间（20）的门（50）的系统。 根据本发明，起落架（30）和门（50）之间的连接装置（60,70,81,82）包括形成安装在起落架（30）上的致动器（60）的第一系统和 形成安装在门（50）上的致动器（70）的第二系统，形成致动器（60,70）的两个系统通过至少一个流体连通装置（81,82）彼此连接，使得致动第一系统形成 致动器（60）使得形成致动器（70）的第二系统的致动。

公开(公告)号：US20100264265A1

公开(公告)日：2010-10-21

申请号：US12729290

申请日：2010-03-23

申请人： Royston Alan EVANS

发明人： Royston Alan EVANS

IPC分类号： B64C25/22

CPC分类号： B64C25/22 ,  B64C25/30

摘要： A hydraulic control system for an aircraft landing gear system comprises a hydraulic pressure source connected to a hydraulic fluid pressure transmission line, and at least one hydraulic actuator for extending and/or retracting a landing gear, wherein first and second valves are provided in series along the hydraulic fluid pressure transmission line, the first and second valves being adjustable to control the hydraulic pressure supplied to the at least one hydraulic actuator. The control system also controls uplock actuators.

摘要翻译： 一种用于飞机起落架系统的液压控制系统包括连接到液压流体压力传输线的液压源和用于延伸和/或缩回起落架的至少一个液压致动器，其中第一和第二阀串联地设置 所述液压流体压力传输线，所述第一和第二阀是可调节的，以控制供应至所述至少一个液压致动器的液压。 控制系统还控制上锁致动器。

公开(公告)号：US20100133379A1

公开(公告)日：2010-06-03

申请号：US11717904

申请日：2007-03-13

申请人： Garrett H. DeVlieg

发明人： Garrett H. DeVlieg

IPC分类号： B64C25/22 ,  B64C25/58

CPC分类号： B64C25/001 ,  B64C2025/008

摘要： A mechanism for increasing the ride height of aircraft by selectively increasing the hydraulic fluid content within landing gear struts. By increasing the hydraulic fluid volume within a strut, the strut is lengthened without adversely affecting its spring rate while the ability to withdraw fluid from a strut maintains the ability of the strut to absorb the impact of landing. The mechanism is readily retrofitable to existing landing gear systems to accommodate more efficient under the wing intake designs and to reduce the likelihood of FOD during taxiing at minimal cost and with very a minimal increase in the aircraft weight.

摘要翻译： 通过选择性地增加起落架支柱内的液压流体含量来增加飞行器的行驶高度的机构。 通过增加支柱内的液压流体体积，支柱延长而不会对其弹簧刚度造成不利影响，而从支柱中抽出液体的能力保持支柱吸收着陆冲击的能力。 该机构对于现有的起落架系统来说容易可逆，以适应机翼进气设计下的更有效率，并且以最小的成本减少滑行期间的FOD的可能性并且飞机重量的增加非常小。

公开(公告)号：US20050207910A1

公开(公告)日：2005-09-22

申请号：US11062442

申请日：2005-02-23

申请人： Hiroshi Yamanouchi ,  Katsutoshi Tada ,  Masaru Oono ,  Tetsuji Sato

发明人： Hiroshi Yamanouchi ,  Katsutoshi Tada ,  Masaru Oono ,  Tetsuji Sato

IPC分类号： B64C25/16 ,  B64C25/22 ,  B64C25/26 ,  F15B15/26 ,  F04B9/08 ,  F04B35/02

CPC分类号： B64C25/22 ,  B64C25/16 ,  F15B15/261

摘要： A groove is provided to the rear of an inner wall of a cylinder. A locking ram capable of freely sliding in a radial direction and a cam rod having a profile changing with a transition from the rear to the front from a small diameter part to a large diameter part that are provided relative to a piston. The inner end of the locking ram makes contact with the profile, and the cam rod is urged to the rear by the spring, so that the cam rod can be pushed to the front by a push rod. The piston can therefore be locked with a simple structure, and it is possible to provide a linear actuator where locking can be released with a straightforward operation even when a pressurized oil source fails.

摘要翻译： 在气缸的内壁的后部设有凹槽。 能够沿径向方向自由滑动的锁定拉杆和具有从后部到前部从相对于活塞设置的小直径部分到大直径部分的过渡部分的轮廓的凸轮杆。 锁定柱塞的内端与型材接触，凸轮杆通过弹簧向后推动，使得凸轮杆可以通过推杆向前推动。 因此，活塞可以以简单的结构锁定，并且可以提供线性致动器，即使当加压油源故障时，可以直接操作释放锁定。

公开(公告)号：US5743491A

公开(公告)日：1998-04-28

申请号：US352337

申请日：1994-12-08

申请人： Michael J. Meneghetti

发明人： Michael J. Meneghetti

IPC分类号： B64C25/34 ,  B64C25/22 ,  B64C25/58

CPC分类号： B64C25/34 ,  B64C2025/345

摘要： Very large aircraft landing gear using single mounted eight wheel bogie on dual shock struts. A primary or main two-stage shock absorber and a semi-articulating secondary or auxiliary single-stage shock absorber, each of which are mounted using the second and third axles as pivot joints in a four axle, eight wheel truck beam.

摘要翻译： 非常大的飞机起落架使用单个安装的八轮转向架在双冲击支柱上。 一个主要或主要的两级减震器和一个半关节的二次或辅助单级减震器，每个减震器都使用第二和第三轴作为枢轴接头安装在四轴八轮车梁上。