公开(公告)号：US5340279A

公开(公告)日：1994-08-23

申请号：US903063

申请日：1992-06-22

Applicant: James P. Cycon ,  David H. Hunter ,  Timothy A. Krauss

Inventor： James P. Cycon ,  David H. Hunter ,  Timothy A. Krauss

IPC: B64C27/10 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C29/00 ,  B64C39/02 ,  B64C39/06 ,  F02B75/02 ,  B64C27/38

CPC classification number: B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025

Abstract: A snubber assembly for a rotor assembly having ducted, coaxial counter-rotating rotors that is design optimized to facilitate utilization of a self-aligning bearing and for installation inboard of the corresponding flexbeam-to-rotor hub attachment joint, thereby enhancing accessibility and reducing maintenance costs. The rotor hub of the rotor assembly is design optimized for securing the snubber assembly in combination therewith and includes a plurality of arms, each arm forming an outboard clevis for attaching the rotor assembly flexbeam to the rotor hub. Inboard of the clevis, each rotor hub arm includes an outboard internal bulkhead having a bolt hole therethrough and an inboard internal bulkhead having a bolt hole therethrough. The inboard and outboard internal bulkheads in combination define a bearing cavity and an internal cavity for securing the snubber assembly in combination with the rotor hub. The snubber assembly includes a spherical self-aligning bearing, a bearing bolt, a locking nut, a snubber bracket secured in combination with the spherical bearing, and securing bolts. The spherical bearing, snubber bracket combination is rotatably mounted within the bearing cavity utilizing the bearing bolt. The bearing bolt is secured in combination with the rotor hub utilizing the locking nut, which is threaded onto the bearing bolt in the internal cavity to jam against the inboard internal bulkhead. The securing bolts are utilized to secure the snubber bracket in combination with the corresponding integrated torque tube/spar member of the rotor assembly.

Abstract translation: 一种用于转子组件的缓冲组件，其具有导管同轴的反向旋转转子，其设计优化以便于利用自对准轴承并安装在对应的挠性梁至转子轮毂附接接头的内侧，从而增强可接近性并减少维护 费用 转子组件的转子轮毂被设计为优化用于将缓冲器组件与其组合固定并且包括多个臂，每个臂形成用于将转子组件挠性束附接到转子毂的外侧U形夹。 在U形夹的内侧，每个转子轮毂臂包括具有穿过其中的螺栓孔的外侧内部隔板和具有穿过其中的螺栓孔的内侧内部隔板。 内侧和外侧的内部舱壁组合地限定了轴承腔和用于将缓冲器组件与转子毂组合固定的内部空腔。 缓冲组件包括球形自调心轴承，轴承螺栓，锁紧螺母，与球面轴承组合固定的缓冲支架和固定螺栓。 球轴承，缓冲支架组合使用轴承螺栓可旋转地安装在轴承腔内。 轴承螺栓利用锁定螺母与转子毂组合固定，该锁定螺母被拧到内部空腔中的轴承螺栓上以卡在内侧内部舱壁上。 紧固螺栓用于将缓冲支架与转子组件的相应的集成扭矩管/翼梁构件组合固定。

公开(公告)号：US5295643A

公开(公告)日：1994-03-22

申请号：US997007

申请日：1992-12-28

Applicant: Marvin D. Ebbert ,  Russell G. Gustin ,  Edward G. Horbett ,  Jack J. Edwards ,  Clifton L. Adcock

Inventor： Marvin D. Ebbert ,  Russell G. Gustin ,  Edward G. Horbett ,  Jack J. Edwards ,  Clifton L. Adcock

IPC: B64C29/00 ,  B64C27/22 ,  B64C29/02 ,  B64C39/02 ,  B64C39/06

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162 ,  Y10T428/24157

Abstract: An unmanned air vehicle capable of vertical take-off and landing, hovering and high-speed horizontal cruise flight. A forward centerbody houses an engine and carries a single rotor assembly having a plurality of propellers lying in a plane substantially perpendicular to the centerline of the forward centerbody. A coaxial aft centerbody is secured to the aft end of the forward centerbody and typically houses the vehicle avionics. A plurality of stators extend outwardly of the aft centerbody, in a plane substantially parallel to the propellers. A single toroidal duct surrounds the rotor assembly and the stators and is secured to the stators. A plurality of movable control vanes are secured between the duct and aft centerbody aft of the stators. A flight control system, typically housed in the aft centerbody, controls the engine and the vanes to cause the vehicle to selectively move upwardly, downwardly, hover or translate to forward, horizontal, motion with the rotor in a plane within 80.degree. of vertical. A sensor, cargo, or other payload may be carried at the forward end of the forward centerbody, extending well in front of the duct. The vehicle is highly maneuverable, light weight and safe for operation from a small area due to the ducted rotor.

Abstract translation: 一种能够垂直起飞和着陆，无人驾驶和高速水平巡航飞行的无人机。 前向中心体容纳发动机并且承载具有多个螺旋桨的单个转子组件，所述多个螺旋桨位于基本上垂直于前方中心体的中心线的平面中。 同轴尾座中心体被固定到前方中心体的后端，并且通常容纳车辆航空电子设备。 多个定子在基本上平行于螺旋桨的平面中从后中心体向外延伸。 单个环形管道围绕转子组件和定子并固定到定子。 多个可动控制叶片固定在定子后的导管和后中心体之间。 通常安装在后中心体内的飞行控制系统控制发动机和叶片，以使车辆选择性地向上，向下，向上悬停或平移，以使转子在垂直于80度的平面内向前，水平运动。 传感器，货物或其他有效载荷可以在前方中心体的前端承载，并且在管道前方延伸。 该车辆高度机动，重量轻，安全可靠，由于导管的转子而在小范围内进行操作。

公开(公告)号：US5281099A

公开(公告)日：1994-01-25

申请号：US903064

申请日：1992-06-22

Applicant: David H. Hunter ,  Timothy A. Krauss ,  Vincent F. Millea

Inventor： David H. Hunter ,  Timothy A. Krauss ,  Vincent F. Millea

IPC: B64C11/02 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/02 ,  F02B75/02

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025 ,  Y10T403/7035

Abstract: An integrated spline/cone seat subassembly for a rotor assembly that is design optimized to minimize the radial dimensions of the rotor shafts, the rotor shaft bearings, the transmission housing, and the swashplate subassemblies thereof. The integrated subassembly includes a rotor hub having a shaft aperture with a plurality of hub splines extend radially inwardly therefrom. The lower portion of each hub spline has an outwardly tapered portion that makes a predetermined angle with respect to the hub centerline. The integrated subassembly further includes a rotor shaft having a primary shaft portion of a first diameter, an end shaft portion having an intermediate second diameter less than the first diameter, and a conic transition portion that makes a predetermined angle with respect to the rotor shaft axis. The end shaft portion has a plurality of shaft splines extending radially outwardly therefrom that defines a third diameter that is equal to the first diameter. The hub and shaft splines are sized to accommodate the torque required by the rotor assembly and interleaved to provide a rotational interlock between the rotor hub and rotor shaft. The tapered portions of the hub splines abuttingly engage and are mechanically supported by the conic transition portion of the rotor shaft. The first diameter of the rotor shaft defines the radial dimensions of the rotor shafts, the rotor shaft bearings, the transmission housing, and the swashplate subassemblies of the rotor assembly.

Abstract translation: 用于转子组件的集成花键/锥座组件，其设计优化以使转子轴，转子轴轴承，变速器壳体和其斜盘组件的径向尺寸最小化。 集成子组件包括具有轴孔的转子轮毂，其具有从其径向向内延伸的多个轮毂花键。 每个毂花键的下部具有相对于轮毂中心线形成预定角度的向外的锥形部分。 集成子组件还包括具有第一直径的主轴部分的转子轴，具有小于第一直径的中间第二直径的端轴部分和相对于转子轴轴线形成预定角度的圆锥过渡部分 。 端轴部分具有从其径向向外延伸的多个轴花键，其限定等于第一直径的第三直径。 轮毂和轴花键的尺寸适于容纳转子组件所需的扭矩并交错以在转子毂和转子轴之间提供旋转互锁。 轮毂花键的锥形部分邻接地接合并由转子轴的锥形过渡部分机械地支撑。 转子轴的第一直径限定了转子轴，转子轴承，变速器壳体和转子组件的斜盘组件的径向尺寸。

公开(公告)号：US3703998A

公开(公告)日：1972-11-28

申请号：US3703998D

申请日：1970-12-28

Applicant: TELEDYNE RYAN AERONAUTICAL CO

Inventor： GIRARD PETER F

IPC: B64C1/00 ,  B64C39/02 ,  B64C1/28 ,  B64C3/56

CPC classification number: B64C39/024 ,  B64C1/00 ,  B64C2001/0045 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/167

Abstract: A drone type aircraft having a telescopic fuselage and folding aerodynamic surfaces to facilitate installation in a limited capacity bomb bay or storage compartment of a launch aircraft. Prior to launch, the drone is lowered from the aircraft on a supporting frame, the aerodynamic surfaces are extended, and the nose section of the fuselage is extended. The added fuselage capacity is used as fuel tankage, which is filled from the launch aircraft to increase the operating range of the drone.

Abstract translation: 具有伸缩机身和折叠空气动力学表面的无人机型飞机，以便于安装在发射飞机的有限容量的炸弹舱或储藏室中。 在发射之前，无人机在支架上从飞机上下降，空气动力学表面延伸，机身的鼻部延伸。 增加的机身容量用作燃油箱，由发射机充满，以增加无人机的运行范围。

公开(公告)号：US3302908A

公开(公告)日：1967-02-07

申请号：US42180164

申请日：1964-12-29

Applicant: NORD AVIATION

Inventor： MICHEL LAZAREFF

IPC: B64C29/00 ,  B64C29/02 ,  B64C39/06

CPC classification number: B64C39/024 ,  B64C29/0091 ,  B64C29/02 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/162

公开(公告)号：NO20025705A

公开(公告)日：2002-11-27

申请号：NO20025705

申请日：2002-11-27

Applicant: BAE SYSTEMS PLC

Inventor： WARSOP CLYDE ,  WOODS MIKE ,  HENDERSON JAMES ,  LOCK GARY

IPC: B64C39/02 ,  B64C39/06

CPC classification number: B64C39/062 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/162

公开(公告)号：NO934831A

公开(公告)日：1994-06-29

申请号：NO934831

申请日：1993-12-27

Applicant: HUGHES MISSILE SYSTEMS

Inventor： EBBERT MARVIN D ,  GUSTIN RUSSELL G ,  HORBETT EDWARD C ,  EDWARDS JACK J ,  ADCOCK CLIFTON L

IPC: B64C29/00 ,  B64C27/22 ,  B64C29/02 ,  B64C39/02 ,  B64C39/06 ,  B64C27/20

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162 ,  Y10T428/24157

公开(公告)号：EP3354566A1

公开(公告)日：2018-08-01

申请号：EP17400002.6

申请日：2017-01-26

Applicant: AIRBUS HELICOPTERS DEUTSCHLAND GmbH

Inventor： Mores, Sebastian ,  D'Alascio, Alessandro ,  Kneisch, Thomas ,  Kicker, Klaus ,  Link, Stefanie ,  Kiesewetter, Uwe ,  Bebesel, Marius

IPC: B64C27/20 ,  B64C11/00 ,  B64C11/48 ,  B64D25/00

CPC classification number: B64C11/001 ,  B64C11/48 ,  B64C27/08 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/162 ,  B64D25/00

Abstract: The invention is related to a thrust producing unit 3d for producing thrust in a predetermined direction 23, comprising at least two rotor assemblies 7d, 8d and a shrouding 6d, each one of the at least two rotor assemblies 7d, 8d defining an associated rotor plane 21, 22, wherein a first rotor assembly 7d of the at least two rotor assemblies 7d, 8d is provided for operating in a failure-free operating mode of the thrust producing unit 3d and a second rotor assembly 8d of the at least two rotor assemblies 7d, 8d is provided for operating at least in case of a failure of the first rotor assembly 7d, and wherein the shrouding 6d accommodates at most one of the at least two rotor assemblies 7d, 8d.

公开(公告)号：EP3305658A1

公开(公告)日：2018-04-11

申请号：EP16803675.4

申请日：2016-05-26

Applicant: Won, Gi Yeon ,  Choi, Dae Kyu ,  KIM, Kyung Wha

Inventor： Won, Gi Yeon ,  Choi, Dae Kyu ,  KIM, Kyung Wha

IPC: B64C39/02 ,  B64C37/00 ,  B60F5/02 ,  A62C3/00 ,  A62C31/02 ,  A62C99/00

CPC classification number: A62C3/0242 ,  A62C3/00 ,  A62C3/025 ,  A62C27/00 ,  A62C31/02 ,  A62C31/28 ,  A62C37/40 ,  A62C99/00 ,  B60F5/02 ,  B64C25/405 ,  B64C37/00 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64D1/02 ,  B64D1/18

Abstract: The present invention relates to a fire extinguishing firefighting drone which, in case of a fire in a house, a structure, a building, or the like, can be rapidly introduced and extinguish a fire in an early stage of the fire, and can be remotely operated in an unmanned manner through connection with a central control system. The fire extinguishing firefighting drone includes a flight unit configured to include propeller units, a disaster prevention turret unit configured to spray a fire-extinguishing chemical, a plurality of movement units configured to move a body unit, and a disaster prevention means unit configured to be provided with items adapted to spray a fire-extinguishing chemical, to launch a fire-extinguishing bomb, or to save lives.

Abstract translation: 灭火消防无人机本发明涉及一种灭火消防无人机，其在住宅内发生火灾时，建筑物或建筑物等可在火灾早期快速引入并扑灭火灾， 通过与中央控制系统连接以无人操作的方式进行远程操作。 灭火消防无人机包括：飞行单元，其构造成包括螺旋桨单元;防灾转台单元，其构造成喷射灭火药剂;多个移动单元，其构造成移动本体单元;以及防灾单元单元， 提供适合喷洒灭火剂的物品，发射灭火弹或拯救生命。

公开(公告)号：EP3290334A1

公开(公告)日：2018-03-07

申请号：EP17188895.1

申请日：2017-08-31

Applicant: Sunlight Photonics Inc.

Inventor： Frolov, Sergey V. ,  Cyrus, Michael ,  Moussouris, John Peter

IPC: B64C27/28 ,  B64C29/00 ,  B64C11/00 ,  B64D27/24 ,  B64C39/02 ,  B64C27/24

CPC classification number: B64D27/24 ,  B64C11/001 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/208 ,  Y02T50/64

Abstract: Embodiments of the present invention provide an aircraft (200) for vertical take-off and landing. In various embodiments, an aircraft assembly includes at least one first wing portion (210) providing a lift force during a horizontal flight, at least one wing opening disposed on a vertical axis of the at least one first wing portion (210) and at least one thruster (240) positioned inside the at least one wing opening to provide vertical thrust during a vertical flight. The aircraft assembly can further include air vents (2030) positioned inside at least one of the wing openings. The air vents can further include louvres (2040) positioned over or under the air vents (2030) to open and close the wing openings. The thruster can further be used to provide flight control for the aircraft.

Abstract translation: 本发明的实施例提供用于垂直起飞和降落的飞行器（200）。 在各种实施例中，飞机组件包括在水平飞行期间提供升力的至少一个第一机翼部分（210），设置在至少一个第一机翼部分（210）的竖直轴线上的至少一个机翼开口以及至少一个 一个推进器（240）位于所述至少一个翼开口内以在垂直飞行期间提供垂直推力。 飞机组件还可以包括定位在至少一个翼开口内的通气孔（2030）。 通风口还可以包括位于通风口（2030）上方或下方的百叶窗（2040）以打开和关闭翼部开口。 推进器可以进一步用于为飞机提供飞行控制。