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公开(公告)号：WO2023031035A1
公开(公告)日：2023-03-09
申请号：PCT/EP2022/073770
申请日：2022-08-26
Applicant: SAFRAN LANDING SYSTEMS UK LIMITED
Inventor： BENNETT, Ian Robert
Abstract: An aircraft landing gear assembly (50) comprising: a first structural member (52); a second structural member (54) pivotally coupled to the first structural member at an apex pivot point so as to be movable between a first angular condition and a second angular condition; a down-lock spring having a first end region pivotally coupled to a mounting structure and being arranged under tension to bias the first and second structural members to assume the first angular condition; and a linkage assembly, the linkage assembly comprising: an arm member (58) pivotally coupled to one of the first and second structural members at an arm pivot point, the arm having an first end region pivotally coupled to a second end region of the down-lock spring; and a control link (56) pivotally coupled to one of the first and second structural members at a first control link pivot point and pivotally coupled to the arm member at a second control link pivot point the such that, as the first and second structural members move relative to one another from the first angular condition towards the second angular condition, the first control link pivot point moves over centre, though an axis or plane bisecting the apex pivot point and the second control link pivot point.
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公开(公告)号：WO2022249181A1
公开(公告)日：2022-12-01
申请号：PCT/IL2022/050554
申请日：2022-05-25
Applicant: HEVENDRONES LTD.
Inventor： PARPARA, David
Abstract: A drone configured for landing on uneven terrain, comprising a drone body comprising a plurality of propellers; a plurality of multi-sectional landing legs, each landing leg comprising at least one joint and a servo motor for operating the joint to adjust the orientation of said each landing leg; an image sensor configured on an underside of the drone; a processor configured to: analyze images of a landing area topography captured by the image sensor; extrapolate topographic information from the images; based on the topographic information, determine an appropriate landing orientation for each leg, whereby the drone body and plurality of propellers are horizontally balanced; instruct each servo motor to operate a respective joint so as to cause each leg to reach its appropriate landing orientation.
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公开(公告)号：WO2021208139A1
公开(公告)日：2021-10-21
申请号：PCT/CN2020/087248
申请日：2020-04-27
Applicant: 南京祖航航空科技有限公司
Inventor： 杨思强
Abstract: 一种无人机用起落架减振结构，包括：固定安装在无人机底部的连接板（1），固定安装在连接板（1）一侧的一级减振板（2），对称安装在一级减振板（2）两端的连接弯管（3），固定连接在连接弯管（3）另一端的液压阻尼管（4），以及固定安装在液压阻尼管（4）另一端的气囊支架（5）；在降落时气囊支架（5）触地，因无人机重力产生的反作用力直接作用气囊足（51），气囊足（51）向上弹起作用弧形减振片（54），经过弧形减振片（54）的限位和抵消后振动力经过弹性连接架向上传递至液压阻尼管（4）上，使经过两次递减的垂直方向的反作用力经过一级减振板（2）进行三级减振，减少垂直方向上的反作用力对无人机上各元件的伤害。
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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.
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公开(公告)号：WO2021047980A1
公开(公告)日：2021-03-18
申请号：PCT/EP2020/074507
申请日：2020-09-02
Applicant: AIRBUS OPERATIONS LIMITED
Inventor： SHARPE, Peter
Abstract: Retraction of a landing gear assembly (4) on an aircraft (1) is actuated by a hydraulic actuator (12). The actuator (12) includes a piston (28) that travels within a cylinder (26) along a stroke length between a first position corresponding to the landing gear assembly when extended and a second position corresponding to the landing gear assembly when retracted. Movement of the piston (28) along its stroke length is snubbed at one end by a different amount according to the direction of travel, for example by use of an orifice plate (Fig 10; Fig 11) that has a discharge coefficient that is greater in one direction (Fig 13) than in the opposite direction (Fig 12). Asymmetric snubbing is thus provided, which enables the landing gear to retract faster.
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Patent Agency Ranking
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.
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.
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公开(公告)号：WO2018228033A1
公开(公告)日：2018-12-20
申请号：PCT/CN2018/082219
申请日：2018-04-08
Applicant: 深圳市道通智能航空技术有限公司
IPC: B64C25/10
Abstract: 一种无人机起落架（20），包括设于机身（10）内的动力组件（200）和与动力组件（200）相连的起落架本体（201）。动力组件（200）包括第一连接件（22）和用于驱动第一连接件（22）做往复直线运动的驱动装置（21）；起落架本体（201）包括与第一连接件（22）铰接的第一连杆（24），以及一端与动力组件（200）铰接、另一端与第一连杆（24）铰接的第二连杆（26）。第一连接件（22）做往复直线运动时，带动起落架本体（201）展开或折叠入机身（10）内部。还公开了一种包括上述起落架（20）的无人机。上述无人机在进行航拍时，可将起落架本体（201）至少部分折叠进机身（10）内，以避免对无人机上的航拍设备造成遮挡。
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公开(公告)号：WO2018213190A1
公开(公告)日：2018-11-22
申请号：PCT/US2018/032568
申请日：2018-05-14
Applicant: MOMBRINIE, Bruno
Inventor： MOMBRINIE, Bruno
IPC: B64C25/10
Abstract: An electrically powered STOL aircraft having dedicated motors energized to deploy movable landing gear driven to propel short takeoffs and to actively rotate downwardly to engage the runway surface as the aircraft approaches touchdown on landing. The front and rear landing gear, or both, may be powered and actuated in the landing process with braking to shorten the landing distance, each driven landing gear wheel having a dedicated electric motor and coaxial brake.
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公开(公告)号：WO2018182883A1
公开(公告)日：2018-10-04
申请号：PCT/US2018/019136
申请日：2018-02-22
Applicant: QUALCOMM INCORPORATED
Inventor： DAVIS, Jonathan Paul , HUTSON, Donald , FERRELL, Paul , DUMSTORFF, Clayton , VAN SCHOYCK, Travis , KESSLER, Ross Eric
CPC classification number: B64C25/12 , B64C25/04 , B64C27/37 , B64C39/024 , B64C2025/125 , B64C2201/027 , B64C2201/088 , B64C2201/108 , B64C2201/165 , B64C2201/18
Abstract: Methods, devices, and systems of various embodiments are disclosed for operating a propeller assembly for use with a UAV. Various embodiments include a propeller assembly including a pivotal arm, a propeller mounted on the pivotal arm, and pivotal leg coupled to the pivotal arm. The pivotal leg may be folded into the pivotal arm and the pivotal arm may be folded into a body of the UAV. A processor may be coupled to the propeller assembly and configured with processor-executable instructions to perform operations of the propeller assembly.
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公开(公告)号：WO2018005302A1
公开(公告)日：2018-01-04
申请号：PCT/US2017/039148
申请日：2017-06-23
Applicant: DZYNE TECHNOLOGIES, INC.
Inventor： PAGE, Mark A.
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 angle of attack 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.
Abstract translation: 公开了用于机械地旋转飞机关于其重心（C G ）的系统和方法。 该系统可以使后起落架或主起落架蹲下，同时前起落架升起，为飞机起飞或着陆产生正迎角。 该系统还可以使前起落架和主起落架返回到相对较高的机身姿态，以便进行地面作业。 该系统可以包括一个或多个液压连接的液压缸以控制前起落架和主起落架的整体高度。 由于液压缸是连接的，所以前端液压缸长度的变化会产生与主液压缸长度成正比和相反的变化，反之亦然。 还公开了一种用于监测和控制前起落架和主起落架的相对位置的方法和控制系统。
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