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公开(公告)号：WO2018095214A1
公开(公告)日：2018-05-31
申请号：PCT/CN2017/109736
申请日：2017-11-07
Applicant: 深圳市道通智能航空技术有限公司
IPC: B64C25/12
Abstract: 一种无人飞行器（10）及其起落架装置（2），所述起落架装置（2）包括：起落架本体（21）；以及安装于机身（1）的动力组件（22），所述动力组件（22）包括驱动装置（23）、传动单元（29）和连接单元（24）；所述传动单元（29）包括由所述驱动装置（23）驱动的传动杆件（292）；所述连接单元（24）的一端与所述起落架本体（21）固定连接，另一端与所述传动杆件（292）相连，当所述传动杆件（292）在所述驱动装置（23）的驱动下转动时，带动所述起落架本体（21）收起或放下。该无人飞行器（10）及其起落架装置（2），既有利于改善无人飞行器（10）的飞行性能，也增加无人飞行器（10）的功能空间，对于具有影像获取装置的无人飞行器（10），能避免起落架装置（2）遮挡该影像获取装置的拍摄视角，从而改善无人飞行器（10）的拍摄性能，并且在不使用无人飞行器（10）时，也更便于携带和收纳。
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公开(公告)号：WO2017202222A1
公开(公告)日：2017-11-30
申请号：PCT/CN2017/084326
申请日：2017-05-15
Applicant: 亿航智能设备(广州)有限公司
Abstract: 一种飞行器及其折叠脚架，其包括：一第一支撑架设有一第一齿轮；一第二支撑架位于所述第一支撑架下方与所述第一支撑架枢接，所述第二支撑架设有一第二齿轮与所述第一齿轮啮合，所述第一齿轮转动以带动所述第二齿轮转动，使得所述第一支撑架相对于所述第二支撑架移动。
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3.发明申请REINFORCING FIBROUS STRUCTURE FOR A COMPOSITE MATERIAL AND A PART CONTAINING SAID STRUCTURE 审中-公开用于复合材料的增强纤维结构和包含结构的部件
公开(公告)号：WO2006136755A3
公开(公告)日：2007-06-21
申请号：PCT/FR2006050617
申请日：2006-06-21
Applicant: SNECMA , SNECMA PROPULSION SOLIDE , COUPE DOMINIQUE , DAMBRINE BRUNO , MAHIEU JEAN NOEL , BOUILLON ERIC , CHARLEUX FRANCOIS
Inventor： COUPE DOMINIQUE , DAMBRINE BRUNO , MAHIEU JEAN NOEL , BOUILLON ERIC , CHARLEUX FRANCOIS
CPC classification number: D03D25/005 , B29C70/24 , B29C70/48 , B29L2031/3076 , B29L2031/7488 , B64C25/12 , F16C7/026 , F16C2326/43 , Y10T74/2142 , Y10T442/3195 , Y10T442/3203 , Y10T442/3211
Abstract: A woven fibrous structure embodied in one piece, used for producing a composite material part and comprising an internal part or a core (72) and a part adjacent to the external surface thereof or a skin (74, 76), is formed by three-dimensional core weaving with at least one weave selected from interlock and multilayer weaves and by skin weaving with a weave which differs from the core weave and selected from a multilayer weave and a two-dimensional weave. It can be also formed by three-dimensional weaving with at least one core interlock weave (72) and weaving with a fabric-, satin or skin twill-type weave, wherein skin weaving is of a multilayer or two-dimensional type. .
Abstract translation: 用于制造复合材料部件并且包括内部部分或芯部（72）和邻近其外表面的部分或皮肤（74,76）的编织纤维结构通过三维形成， 具有选自互锁和多层织物的至少一个编织的三维芯编织，并且通过具有与芯编织不同的织造的皮肤编织，并从多层编织和二维编织中选择。 它也可以通过三维织造与至少一个芯互锁编织（72）和织造，缎纹或皮革斜纹织物编织，其中皮肤编织是多层或二维型。 。
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公开(公告)号：WO2014113458A1
公开(公告)日：2014-07-24
申请号：PCT/US2014/011658
申请日：2014-01-15
Applicant: OTTO, William M.
Inventor： OTTO, William M.
CPC classification number: B64C25/20 , B64C1/00 , B64C1/065 , B64C1/069 , B64C1/10 , B64C3/185 , B64C3/26 , B64C3/58 , B64C5/02 , B64C5/16 , B64C9/02 , B64C9/16 , B64C9/20 , B64C13/30 , B64C25/02 , B64C25/10 , B64C25/12 , B64C25/14 , B64C25/18 , B64C25/22 , B64C2025/125 , B64D33/10 , B64D37/04 , F02B37/001 , Y02T50/32 , Y02T50/44
Abstract: A support unit for a structure within a pressure vessel that includes an external load distribution plate, an internal load distribution plate, a standoff unit between the external load distribution plate and the internal load distribution plate that extends through an opening in a pressure vessel.
Abstract translation: 用于压力容器内的结构的支撑单元，其包括外部负载分配板，内部负载分配板，外部负载分配板和内部负载分配板之间的隔离单元，所述支架单元延伸穿过压力容器中的开口。
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5.发明申请
公开(公告)号：WO2011088991A1
公开(公告)日：2011-07-28
申请号：PCT/EP2011/000198
申请日：2011-01-19
Applicant: MESSIER-DOWTY SA , DUCOS, Dominique , LOCUFIER, Jean-François
Inventor： DUCOS, Dominique , LOCUFIER, Jean-François
IPC: B64C25/12
CPC classification number: B64C25/12 , B64C2025/125
Abstract: L'invention est relative à un atterrisseur d'aéronef de type à parallélogramme déformable, comportant : - une jambe comportant un caisson (1) avec une extrémité basse sur laquelle un balancier (3) portant au moins une roue est articulé, un amortisseur étant attelé entre le balancier et le caisson; - deux panneaux (10, 11) chacun articulés d'une part sur la structure de l'aéronef et d'autre part sur la jambe, selon des axes parallèles; Selon l'invention, l'un des panneaux (11) est articulé sur la jambe en étant broché à une extrémité d'un pivot (2) du balancier sur le caisson.
Abstract translation: 本发明涉及一种可变形 - 平行四边形类型的飞机起落架，其包括：腿部，其包括具有下端的壳体（1），其上铰接有至少一个车轮的摇臂（3）被铰接，减震器被连接 在摇臂和套管之间; 两个板（10,11）各自以平行轴线铰接在飞行器结构上并且在腿上。 根据本发明，其中一个面板（11）铰接在腿上，同时被销连接到壳体上的摇臂枢轴（2）的端部。
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Patent Agency Ranking
公开(公告)号：WO2010009289A2
公开(公告)日：2010-01-21
申请号：PCT/US2009/050796
申请日：2009-07-16
Applicant: HAMILTON SUNDSTRAND CORPORATION , COLLINS, Andrew, John
Inventor： COLLINS, Andrew, John
CPC classification number: B64C25/24 , B64C25/12 , B64C25/30 , F16H25/205 , F16H25/2454 , F16H2025/2071 , F16H2025/2081 , H02K7/06
Abstract: This disclosure relates to a landing gear system that includes a landing gear strut rotatable between stowed and deployed positions. An actuator is connected to the landing gear strut, and includes main and emergency drives housed within a common body and operable independently from one another. A controller in communication with the actuator is configured to command the actuator between the stowed and deployed positions in response to an input. The controller commands the main drive during a normal operating condition and commands the emergency drive in a failure condition of the main drive. The actuator includes a body supporting emergency and main leadscrews arranged coaxially with one another. Main and emergency motors respectively are coupled to the main and emergency leadscrews. An output rod is supported by and extends from the body. The output rod is threadingly coupled to and is coaxial with the main leadscrew and configured to move axially in response to rotation of the main leadscrew. A brake selectively enables and disables the emergency drive.
Abstract translation: 本公开涉及一种起落架系统，其包括可在收起位置和展开位置之间旋转的起落架支柱。 致动器连接到起落架支柱，并且包括容纳在共同体内并可彼此独立操作的主和应急驱动器。 与致动器通信的控制器被配置为响应于输入而在致动器和收起位置之间指令致动器。 控制器在正常运行状态下命令主驱动器，并在主驱动器的故障状态下命令紧急驱动器。 致动器包括支撑紧急的主体和彼此同轴布置的主导螺杆。 主电机和应急电动机分别连接到主和应急丝杠。 输出杆由主体支撑并延伸。 输出杆螺纹连接到主导螺杆上并且与主导螺杆同轴并且构造成响应于主丝杠的旋转而轴向移动。 制动器选择性地启用和禁用应急驱动器。
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公开(公告)号：WO2006071263A3
公开(公告)日：2007-03-22
申请号：PCT/US2005021633
申请日：2005-06-20
Applicant: GOODRICH CORP , LAVIGNE PAUL J , LEVOIR BARRY
Inventor： LAVIGNE PAUL J , LEVOIR BARRY
CPC classification number: B64C25/34 , B64C25/12 , B64C2025/345
Abstract: A landing gear for an aircraft, characterized by upper and lower pintle frame members (38, 40) being connected to a telescoping shock strut (14) in a non-rigid manner that tolerates twisting when reacting to torsional loads applied to the landing gear, and/or by a pitch trim actuator (30) that positions a landing gear truck (16) proportionally to the retraction angle of a shock strut (14) during retraction and extension.
Abstract translation: 用于飞机的起落架，其特征在于上和下枢轴架构件（38,40）以非刚性方式连接到伸缩式冲击支柱（14），当对施加到起落架的扭转载荷作出反应时，该起重装置允许扭转， 和/或通过间距调节致动器（30），其将起落架卡车（16）与缩回和延伸期间的冲击支柱（14）的缩回角成比例地定位。
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公开(公告)号：WO2007001353A2
公开(公告)日：2007-01-04
申请号：PCT/US2005/031205
申请日：2005-08-30
Applicant: MESSIER-DOWTY (USA), INC. , HINTON, Roland
Inventor： HINTON, Roland
Abstract: Disclosed is an arrangement in which the main landing gear assemblies of a large commercial airplane are each joined to the airplane at four attachement points. Two of the attachment points connect the landing gear side brace and drag brace to the airplane. The two remaining attachment points are aft and forward trunnions that are mounted to the airplane wing. The aft trunnion pivotally connects one side of the landing gear shock strut to the airplane and carries both vertical and torsional loading. The forward trunnion is pivotally connected to the other side of the shock strut by a trunnion link. An actuator is coupled between the shock strut and the trunnion link. When the landing gear is down and locked the actuator is not activated and the trunnion link does not have the rigidity and stiffness required to transfer vertical loads to the forward trunnion. When the actuator is activated, the combination of the actuator and trunnion links rigidly interconnects the shock strut with the forward trunnion so that four point mounting stabilization is present during landing gear retraction, extension and stowage.
Abstract translation: 本发明公开了一种大型商用飞机的主起落架组件在四个附着点处连接到飞机的布置。 两个连接点将起落架侧支架和拖曳支架连接到飞机。 剩余的两个附着点是安装在飞机机翼上的后方和前方耳轴。 尾座耳轴将起落架减震支柱的一侧枢转连接到飞机上，并承载垂直和扭转载荷。 前耳轴通过耳轴连杆枢转连接到冲击支柱的另一侧。 致动器耦合在冲击支柱和耳轴连杆之间。 当起落架向下并锁定时，执行器未被启动，而耳轴连杆不具有将垂直载荷传递到前轴耳轴所需的刚度和刚度。 当致动器被激活时，致动器和耳轴连杆的组合将冲击支柱与前耳轴刚性地相互连接，使得在起落架缩回，延伸和收起时存在四点安装稳定。
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公开(公告)号：WO1998024688A1
公开(公告)日：1998-06-11
申请号：PCT/GB1997003319
申请日：1997-12-02
Applicant: BRITISH AEROSPACE PUBLIC LIMITED COMPANY , HIGGINS, Nigel
Inventor： BRITISH AEROSPACE PUBLIC LIMITED COMPANY
IPC: B64C25/10
Abstract: An arrangement for an aircraft main landing gear is provided which includes a main oleo strut (7) having forward and aft trunnion bearings (8, 10), an aircraft wing rear spar (2) having a mounting (9) for the forward trunnion bearing (8) thereon, a gear beam (4) mounted at one end to the rear spar and at the other end to a fuselage. The gear beam (4) has a mounting (11) for the aft trunnion bearing (10) at a position intermediate its ends. The mounting for the forward trunnion bearing (8) includes a fusible element (12) adapted to fail upon the application of an excessive drag load. The mounting (11) for the aft trunnion bearing is integral with the structure of the gear beam (4) and is rotatable about the longitudinal axis of the gear beam to permit controlled detachment of the landing gear in an emergency.
Abstract translation: 提供了一种用于飞机主起落架的装置，其包括具有前和后耳轴承（8,10）的主液压支柱（7），具有用于前耳轴承轴承（9,10）的安装件（9）的飞机机翼后翼梁 （8），一端安装在后翼梁上的齿轮梁（4），另一端安装在机身上。 齿轮梁（4）在其尾端的中间位置具有用于后轴颈轴承（10）的安装件（11）。 用于前耳轴承（8）的安装件包括适于在施加过大阻力载荷时失效的可熔元件（12）。 用于后轴颈轴承的安装件（11）与齿轮梁（4）的结构成一体，并且能够围绕齿轮梁的纵向轴线旋转，以便在紧急情况下控制起落架的分离。
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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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