公开(公告)号：US06450445B1

公开(公告)日：2002-09-17

申请号：US09868008

申请日：2001-10-12

Applicant: Paul S. Moller

Inventor： Paul S. Moller

IPC: B64C2900

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/162

Abstract: A robotic or remotely controlled flying platform (10) with reduced drag stabilizing control apparatus constructed having an air duct (12) with an air intake (14) on the top and an exhaust (16) at the bottom, containing supported therein a clockwise rotating fan (22) and a counter-clockwise rotating fan (24). Directly below the perimeter of the air duct exhaust are mounted a plurality of trough shaped air deflection assemblies (32) each including a rotatably adjustable half trough (44) for selectively scooping a portion of the drive air, and a stationary adjacent half trough (36) for receiving the scooped drive air and redirecting it outward and upward from the air duct. A centrally positioned plate (112) has a plurality of rods (106), each pivotably connected between the plate (74) and a corresponding lever associated with each of the adjustable half troughs (44) so as to couple the adjustable half trough (44) in or out of the drive air steam according to the position of the plate (74), thereby providing control over the pitch and roll of the flying platform. The plate is driven by first and second motors responding to input control signals. The control signals also direct the yaw of the flying platform by selectively providing independent speed control to each of the clockwise and counter clockwise fan motors resulting in duct rotation in a clockwise or counter clockwise direction accordingly.

Abstract translation: 一种机器人或远程控制的飞行平台（10），其具有减少的阻力稳定控制装置，其构造为具有在顶部具有进气口（14）的空气管道（12）和底部的排气（16），其包含支撑在其中的顺时针旋转 风扇（22）和逆时针旋转的风扇（24）。 安装有多个槽形的空气偏转组件（32），每个包括可旋转的可调节的半槽（44），用于选择性地舀取驱动空气的一部分，以及固定的相邻半槽（36） ），用于接收舀取的驱动空气并将其从空气管道向外和向上引导。 中心定位的板（112）具有多个杆（106），每个杆（106）可枢转地连接在板（74）和与可调节半槽（44）中的每一个相关联的相应杆，以便联接可调节半槽（44） ）根据板（74）的位置进入或离开驱动空气蒸汽，从而提供对飞行平台的俯仰和滚动的控制。 该板由响应于输入控制信号的第一和第二电动机驱动。 控制信号还通过选择性地为每个顺时针和逆时针风扇电动机提供独立的速度控制来引导飞行平台的偏转，从而导致管道沿顺时针或逆时针方向旋转。

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：US20190217952A1

公开(公告)日：2019-07-18

申请号：US16324656

申请日：2016-08-19

Applicant: MOTOROLA SOLUTIONS, INC.

Inventor： Artur ZAWADZKI ,  Rafal Leszek ADAMSKI ,  Michal SLUSARCZYK

IPC: B64C39/02 ,  B64D47/08 ,  B64D1/22 ,  B64D1/02 ,  B64F3/02 ,  H02G11/02

CPC classification number: B64C39/022 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/143 ,  B64C2201/148 ,  B64C2201/162 ,  B64D1/02 ,  B64D1/22 ,  B64D47/08 ,  B64F3/02 ,  G05D1/0866 ,  G05D1/104 ,  H02G11/00 ,  H02G11/02

Abstract: Methods and systems are described for an aerial drone system including a drone system controller, at least one working drone (101), and a plurality of support drones (103). The working drone (101) is operated by the drone system controller (125) to adjust a position of the working drone (101). A tether line (105) coupled to the working drone (101) provides electrical power to the working drone (101). The support drones (103) are each coupled to the tether line (105) at a different location along the tether line (105) forming a tethered aerial drone system. Each support (drone 103) supports a portion of the weight of the tether line (105) and is operated by the drone system controller (125) to adjust the position of the tether line (105) by adjusting the position of one or more of the support drones (103).

公开(公告)号：US20180273170A1

公开(公告)日：2018-09-27

申请号：US15927847

申请日：2018-03-21

Applicant: Regents of the University of Minnesota

Inventor： Ruben Raphael D'Sa ,  Nikolaos Papanikolopoulos ,  Devon Jenson ,  Travis Henderson ,  John Kilian

IPC: B64C29/02 ,  B64C39/02 ,  B64C3/56 ,  B64C3/32 ,  B64D27/24 ,  B64C11/30 ,  B64C13/18

CPC classification number: B64C29/02 ,  B64C3/32 ,  B64C3/56 ,  B64C11/30 ,  B64C13/18 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/102 ,  B64C2201/162 ,  B64C2201/165 ,  B64D27/24 ,  B64D2211/00

Abstract: An unmanned aerial vehicle (UAV) including wing sections and hinge assemblies. Each wing section includes an airfoil and a propulsion unit. The wing sections are arranged side-by-side, pivotably connected by the hinge assemblies to define an airframe module. The airframe module is transitionable between a fixed-wing state and a rotor state. In the fixed-wing state, the airframe module has an elongated shape extending between opposing, first and second ends. In the rotor state, the first end is immediately proximate the second end. With this construction, the UAV provides two distinct modes of flight (fixed-wing for low power flight, and rotor for high maneuverability flight (including hover)). The wing sections can carry solar cells and a battery. A maximum power point tracker (MPPT) can be provided for optimizing the match between the solar array and the battery. The propulsion unit can include a variable pitch propeller.

公开(公告)号：US20180269587A1

公开(公告)日：2018-09-20

申请号：US15463167

申请日：2017-03-20

Applicant: Lockheed Martin Corporation

Inventor： Mike I. Jones

IPC: H01Q15/14 ,  B64C39/02 ,  B64C11/20

CPC classification number: H01Q15/14 ,  B64C1/36 ,  B64C11/00 ,  B64C11/20 ,  B64C39/024 ,  B64C2201/162 ,  H01Q1/28 ,  H01Q1/44 ,  H01Q15/165

Abstract: In one embodiment, a system includes an aircraft body and a propeller coupled to the aircraft body. The propeller includes a plurality of blades forming a rearward-facing curvature with respect to an axis running longitudinally with the aircraft body. The system further includes a surface coupled to a first blade of the propeller that is operable to reflect radio frequency (RF) waves.

公开(公告)号：US20180218617A1

公开(公告)日：2018-08-02

申请号：US15927900

申请日：2018-03-21

Applicant: AT&T Intellectual Property I, L.P.

Inventor： Venson Shaw ,  Zhi Cui ,  Sangar Dowlatkhah

IPC: G08G5/00 ,  H04W28/02 ,  B64C39/02

CPC classification number: G08G5/0043 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/146 ,  B64C2201/162 ,  G08G5/0013 ,  G08G5/0034 ,  G08G5/0069 ,  G08G5/0082 ,  H04W28/0247

Abstract: Concepts and technologies disclosed herein are directed to intelligent drone traffic management via a radio access network (“RAN”). As disclosed herein, a RAN node, such as an eNodeB, can receive, from a drone, a flight configuration. The flight configuration can include a drone ID and a drone route. The RAN node can determine whether capacity is available in an airspace associated with the RAN node. In response to determining that capacity is available in the airspace associated with the RAN node, the RAN node can add the drone ID to a queue of drones awaiting use of the airspace associated with the RAN node. When the drone ID is next in the queue of drones awaiting use of the airspace associated with the RAN node, the RAN node can instruct the drone to fly through at least a portion of the airspace in accordance with the drone route.