公开(公告)号：WO2009109771A3

公开(公告)日：2009-09-11

申请号：PCT/GB2009/050181

申请日：2009-02-24

Applicant: AIRBUS UK LIMITED ,  THOMPSON, Robert, Ian

Inventor： THOMPSON, Robert, Ian

IPC: B64C25/12 ,  B64C25/18 ,  B64C25/62 ,  B64C25/14

Abstract: An aircraft landing gear comprising: an arm (17) mounted to a pivot (18) and carrying one or more wheel assemblies (19); and a composite leaf spring (20) 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 ofbending 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.

公开(公告)号：WO2021221958A2

公开(公告)日：2021-11-04

申请号：PCT/US2021/028213

申请日：2021-04-20

Applicant: LUCCI, Adam ,  LEE, Randy ,  EGGERS, Gregory ,  PASIC, Zoran

Inventor： LEE, Randy ,  EGGERS, Gregory ,  PASIC, Zoran

IPC: B64C25/36 ,  B64C25/02 ,  B64C25/00 ,  B64C25/04 ,  B64C25/08 ,  B64C25/10 ,  B64C25/58 ,  B64C25/18 ,  B64C25/42 ,  B64C25/44 ,  B64C25/60

Abstract: A truck beam for an aircraft landing gear assembly is provided. The truck beam includes an elongate hub having first and second ends. The hub is rotatably mountable a shock strut of the landing gear assembly. A first leg extends radially in a first direction from the first end of the hub. The first leg has an inner side facing the second end of the hub and is configured to have a first wheel rotatably mounted to the inner side about a first wheel axis. A second leg extends radially in a second direction from the second end of the hub and has an inner side facing the first end of the hub. The second leg is configured to have a second wheel rotatably mounted to the inner side of the second leg about a second wheel axis.

公开(公告)号：WO2010063110A1

公开(公告)日：2010-06-10

申请号：PCT/CA2009/001754

申请日：2009-12-03

Applicant: MESSIER-DOWTY INC. ,  AMBERG, Steve

Inventor： AMBERG, Steve

IPC: B64C25/16 ,  B64C25/18

CPC classification number: B64C25/16 ,  B64C25/20

Abstract: The present invention provides a double hook door mechanism for use in opening and closing aircraft landing gear bay doors.

Abstract translation: 本发明提供一种用于打开和关闭飞机起落架舱门的双钩门机构。

公开(公告)号：WO2006094145A1

公开(公告)日：2006-09-08

申请号：PCT/US2006007477

申请日：2006-03-02

Applicant: GOODRICH CORP ,  BARR ANTHONY J

Inventor： BARR ANTHONY J

IPC: B64C25/18

CPC classification number: B64C25/34 ,  B64C2025/008

Abstract: A landing gear (10) is equipped with a mechanism (66) that isolates a hydraulic pitch trimmer (72) outside of the landing loop thereby eliminating the need for complex hydraulics normally associated with articulated landing gear designs equipped with pitch or trimmers or other articulating actuators. The mechanism comprises an articulated strut (68) connected between a bogie beam (18) and a shock strut cylinder (24) for controlling the pitch of the bogie beam, an over-center linkage (70) connected between the articulated strut and the shock strut cylinder, and an externally powered actuator (72) connected to the over-center linkage for moving the over-center linkage between the over-center locked position and other another position articulating the bogie beam from an end of take-off position to a stowage position, whereby the bogie beam can be properly angularly positioned relative to the shock strut for retraction into an aircraft landing gear bay.

Abstract translation: 起落架（10）装备有一个机构（66），其将液压俯仰修剪器（72）隔离在着陆回路外部，从而消除了通常与配备有俯仰或微调器或其他铰接的铰接起落架设计相关联的复杂液压的需要 执行器。 该机构包括连接在转向架梁（18）和用于控制转向架的俯仰之间的减震支柱（24）之间的铰接支柱（68），连接在铰接支柱和冲击之间的过中心连杆 支撑缸和外部驱动的致动器（72），其连接到超中心连杆机构，用于将超中心连杆件在超中心锁定位置和将转向架梁从起飞位置的端部铰接到另一个位置之间移动 从而转向架梁可以相对于冲击支柱适当地定位，以便缩回飞机起落架舱。

公开(公告)号：WO2022016256A1

公开(公告)日：2022-01-27

申请号：PCT/CA2021/050987

申请日：2021-07-16

Applicant: SAFRAN LANDING SYSTEMS ,  SAFRAN LANDING SYSTEMS CANADA INC.

Inventor： ELLIS, Andrew Michael ,  KLIM, Graeme Peter Arthur ,  MAZOUE, Thibaud ,  TOFFLEMIRE, Cole

IPC: B64C25/18 ,  B64C19/00

Abstract: A method for extending a landing gear system for a vehicle is disclosed. The landing gear system includes a first landing gear assembly and a second landing gear assembly. The method includes the steps of sensing a first load on the first landing gear assembly after the first landing gear assembly has reached a wheels-on-ground state and comparing the first load to a first target value. The method further includes the step of controlling an extension speed of the first landing gear assembly according to a difference between the first load and the first target value.

公开(公告)号：WO2021087260A1

公开(公告)日：2021-05-06

申请号：PCT/US2020/058216

申请日：2020-10-30

Applicant: FRION, Stéphane

Inventor： FRION, Stéphane

IPC: B64C25/14 ,  B64C25/02 ,  B64C25/16 ,  B64C7/00 ,  B64C25/12 ,  B64C25/10 ,  B64C25/34 ,  B64C25/00 ,  B64C25/60 ,  B64C25/04 ,  B64C25/18

Abstract: Shield assemblies for an aircraft landing gear include an aerodynamic shield, a first support bracket assembly, and a second support bracket assembly. The first support bracket assembly is configured to couple with a structural member of the aircraft landing gear, to support a first end of the aerodynamic shield, and to have a first position that is fixed relative to the structural member in an x-direction, a y-direction, and a z-direction. The first support bracket assembly has a first clamp that is configured to fix the first support bracket assembly relative to the structural member in the x-direction. The second support bracket assembly is configured to support a second end of the aerodynamic shield and to have a second position that is fixed relative to the structural member in the y-direction and the z-direction.

公开(公告)号：WO2020142434A1

公开(公告)日：2020-07-09

申请号：PCT/US2019/068949

申请日：2019-12-30

Applicant: DZYNE TECHNOLOGIES INCORPORATED

Inventor： SCHUSTER, Ewald ,  WHITLOCK, Jennifer ,  LONG, Joshua, B. ,  DONASTORG, Cristina ,  KENNELLY, Brendan ,  PAGE, Mark, A.

IPC: B64C25/10 ,  B64C25/00 ,  B64C25/14 ,  B64C25/18 ,  B64C25/20 ,  B64C25/22

Abstract: Systems and methods for mechanically rotating an aircraft about its center-of-gravity (C G ) are disclosed. The system can enable the rear, or main, landing gear to squat, while the nose landing gear raises to generate a positive pitch angle for the aircraft for takeoff or landing. The system can also enable the nose gear and main gear to return to a relatively level fuselage attitude for ground operations. The system can include one or more hydraulically linked hydraulic cylinders to control the overall height of the nose gear and the main gear. Because the hydraulic cylinders are linked, a change on the length of the nose cylinder generates a proportional, and opposite, change in the length of the main cylinder, and vice-versa. A method and control system for monitoring and controlling the relative positions of the nose gear and main gear is also disclosed.

公开(公告)号：WO2019067873A1

公开(公告)日：2019-04-04

申请号：PCT/US2018/053385

申请日：2018-09-28

Applicant: GEORGIA TECH RESEARCH CORPORATION ,  DI LEO, Claudio ,  COSTELLO, Mark ,  LEON, Benjamin ,  RIMOLI, Julian ,  WARD, Michael

Inventor： DI LEO, Claudio

IPC: B64C25/58 ,  B64C25/18 ,  B64C25/20 ,  B64C25/60 ,  B64C29/00

Abstract: A leg mechanism includes an articulated leg system (100), a passive device (130) and a cable (134). The articulated leg system (100) has a leg portion (128). The passive device (130) is coupled to the articulated leg system and is configured to apply a first force to a portion thereof. The cable (134) is coupled to the articulated leg system (100) and is configured to apply a second force, in opposition to the first force, to a portion thereof. When the cable (134) is drawn away from the articulated leg system (100), the second force moves the leg portion (128) in a first direction. When tension is released from the cable (134), the passive device (130) exerts the first force so as to move the leg portion (128) a second direction that is opposite the first direction.

公开(公告)号：WO2010129960A1

公开(公告)日：2010-11-11

申请号：PCT/US2010/034261

申请日：2010-05-10

Applicant: SPECTRUM AERONAUTICAL, LLC

Inventor： MASON, Garth, L.

IPC: B64C25/18

CPC classification number: B64C25/18 ,  B64C25/22 ,  B64C25/30 ,  Y10T74/18592

Abstract: 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.

Abstract translation: 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接收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：WO2005077757A1

公开(公告)日：2005-08-25

申请号：PCT/US2005/002728

申请日：2005-01-28

Applicant: THE BOEING COMPANY ,  LINDAHL, Gary, M. ,  TROTTER, Steven, J.

Inventor： LINDAHL, Gary, M. ,  TROTTER, Steven, J.

IPC: B64C25/18

CPC classification number: B64C25/18 ,  B64C25/16 ,  B64C25/22 ,  B64C25/28

Abstract: Methods and systems for performing landing gear operations. In one embodiment, a method for retracting a landing gear is useable with an aircraft having a gear door (128) that at least partially covers a gear well when the landing gear (120) is extended. The method can include receiving a first signal during movement of the aircraft down a runway for takeoff. The first signal can correspond to at least a first aspect of motion of the aircraft, such as upward rotation of the aircraft for liftoff. The gear door (128) can be opened in response to receiving the first signal. The method can further include receiving a second signal after the aircraft has lifted off of the runway. The second signal can correspond to a second aspect of motion of the aircraft, such as the aircraft achieving a positive rate of climb. In response to receiving the second signal, the landing gear (120) can be retracted into the gear well.

Abstract translation: 进行起落架作业的方法和系统。 在一个实施例中，用于缩回起落架的方法可用于具有齿轮门（128）的飞行器，当起落架（120）延伸时至少部分地覆盖齿轮井。 该方法可以包括在飞行器在跑道下运行期间接收第一信号以起飞。 第一信号可以对应于飞行器的运动的至少第一方面，例如飞机向上旋转以用于提升。 响应于接收到第一信号，可以打开齿轮门（128）。 该方法还可以包括在飞行器从跑道上升起之后接收第二信号。 第二信号可以对应于飞行器的运动的第二方面，例如飞行器达到正的爬升速率。 响应于接收到第二信号，起落架（120）可以缩回到齿轮井中。