公开(公告)号：US20130233964A1

公开(公告)日：2013-09-12

申请号：US13413696

申请日：2012-03-07

Applicant: Adam Woodworth ,  James Peverill

Inventor： Adam Woodworth ,  James Peverill

IPC: B64C37/02 ,  H02G11/00 ,  G05D1/00 ,  B64D25/00 ,  B64D17/80

CPC classification number: B64C39/022 ,  B64C9/00 ,  B64C25/58 ,  B64C27/006 ,  B64C27/20 ,  B64C37/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/143 ,  B64C2201/148 ,  B64D17/80 ,  B64F3/02 ,  G05D1/0866 ,  G05D1/104 ,  H02G11/00

Abstract: A tethered unmanned aerial vehicle (“UAV”) may be outfitted with a sensor payload for data gathering. The tethered UAV may be tethered to a ground station for constricting the flight space of the UAV while also providing the option for power delivery and/or bidirectional communications. The tethered UAV's flight path may be extended by introducing one or more secondary UAVs that cooperate to extend the horizontal flight path of a primary UAV. The ground station, which may be coupled with the tethered aerial vehicle, may comprise a listening switch configured to determine a condition of the tether such that the supply of power to the tether may be terminated when tether damage or a tether severance is detected.

Abstract translation: 系绳无人机（“UAV”）可以装备有用于数据采集的传感器有效载荷。 系缚的UAV可以被绑在地面站上，用于收缩无人机的飞行空间，同时还提供功率传送和/或双向通信的选项。 可以通过引入一个或多个辅助UAV以扩展主UAV的水平飞行路径来扩展系留的UAV的飞行路径。 可以与系留式航空器耦合的地面站可以包括侦听开关，其被配置为确定系绳的状况，使得当检测到系绳损伤或系绳断开时，可以终止对系绳的供电。

公开(公告)号：US20130214088A1

公开(公告)日：2013-08-22

申请号：US13814244

申请日：2011-11-10

Applicant: Gabriel Shachor ,  Shy Cohen ,  Ronen Keidar

Inventor： Gabriel Shachor ,  Shy Cohen ,  Ronen Keidar

IPC: B64C27/04

CPC classification number: B64F1/12 ,  B64C27/04 ,  B64C27/08 ,  B64C29/04 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/148 ,  B64F1/007 ,  B64F1/125

Abstract: An aerial unit includes a connecting element arranged to connect a ground unit to the aerial unit. The ground unit may include a connecting element manipulator, for altering an effective length of the connecting element and a ground unit controller for controlling the connecting element manipulator. A positioning unit is arranged to image the aerial unit and to generate metadata about a location of the aerial unit. An interfacing module is provided for coupling a payload to the aerial unit. At least one of the ground unit and the aerial unit may include a controller that is arranged to control, at least in response to the metadata, at least one of a first propeller motor and at least one steering element to affect at least one of the location of the aerial unit and the orientation of the aerial unit.

Abstract translation: 天线单元包括连接元件，该连接元件将接地单元连接到天线单元。 接地单元可以包括用于改变连接元件的有效长度的连接元件操纵器和用于控制连接元件操纵器的接地单元控制器。 定位单元布置成对天线单元进行成像并生成关于天线单元的位置的元数据。 提供了用于将有效载荷耦合到天线单元的接口模块。 地面单元和天线单元中的至少一个可以包括控制器，其被布置为至少响应于元数据来控制第一螺旋桨电动机和至少一个操纵元件中的至少一个，以影响至少一个 天线单元的位置和天线单元的方向。

公开(公告)号：US20130206919A1

公开(公告)日：2013-08-15

申请号：US13759087

申请日：2013-02-05

Applicant: Gabriel Shachor ,  Shy Cohen ,  Ronen Keidar

Inventor： Gabriel Shachor ,  Shy Cohen ,  Ronen Keidar

IPC: B64C29/04

CPC classification number: B64F1/12 ,  B64C27/04 ,  B64C27/08 ,  B64C29/04 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/148 ,  B64F1/007 ,  B64F1/125

Abstract: An aerial unit that includes a first propeller; a second propeller that is spaced apart from the first propeller and is below the first propeller; a propelling module that is configured to rotate the first propeller and the second propeller about a first axis; an apertured duct that comprises a first duct portion and a second duct portion. The first duct portion surrounds the first propeller. The second duct portion surrounds the second propeller. The apertured duct defines at least one aperture at an intermediate area that is positioned below the first propeller and is above the second propeller. The aggregate size of the at least one aperture is at least fifty percent of a size of the intermediate area; a frame; and at least one steering element; an interfacing module arranged to be connected to a connecting element that couples the aerial unit to a ground unit. The propelling module and the duct are connected to the frame.

Abstract translation: 包括第一螺旋桨的天线单元; 第二螺旋桨，其与第一螺旋桨间隔开并且在第一螺旋桨下方; 推进模块，其构造成围绕第一轴旋转所述第一螺旋桨和所述第二螺旋桨; 多孔管道，其包括第一管道部分和第二管道部分。 第一管道部分围绕第一螺旋桨。 第二管道部分围绕第二螺旋桨。 多孔管道在位于第一螺旋桨下方并在第二螺旋桨上方的中间区域处限定至少一个孔。 所述至少一个孔的聚集体尺寸为所述中间区域的尺寸的至少百分之五十; 一个框架; 和至少一个操纵元件; 连接模块被布置成连接到将天线单元耦合到接地单元的连接元件。 推进模块和管道连接到框架。

公开(公告)号：US08473125B2

公开(公告)日：2013-06-25

申请号：US13410229

申请日：2012-03-01

Applicant: Michael Rischmuller ,  Frederic D'haeyer

Inventor： Michael Rischmuller ,  Frederic D'haeyer

IPC: G06F13/00

CPC classification number: A63H27/12 ,  A63H30/04 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2203/00 ,  G05D1/0202 ,  G08C17/02 ,  G08C2201/93

Abstract: The respective motors of the drone (10) can be controlled to rotate at different speeds in order to pilot the drone both in attitude and speed. A remote control appliance produces a command to turn along a curvilinear path, this command comprising a left or right turning direction parameter and a parameter that defines the radius of curvature of the turn. The drone receives said command and acquires instantaneous measurements of linear velocity components, of angles of inclination, and of angular speeds of the drone. On the basis of the received command and the acquired measurements, setpoint values are generated for a control loop for controlling motors of the drone, these setpoint values controlling horizontal linear speed and inclination of the drone relative to a frame of reference associated with the ground so as to cause the drone to follow curvilinear path (C) at predetermined tangential speed (u).

Abstract translation: 无人机（10）的各个电机可以被控制为以不同的速度旋转，以便以姿态和速度引导无人机。 远程控制装置产生沿着曲线路径转动的命令，该命令包括左转或右转转方向参数和限定转弯曲率半径的参数。 无人机接收到所述命令，并获得无人机的线速度分量，倾角和角速度的瞬时测量值。 根据接收到的命令和采集的测量结果，产生用于控制无人机的电动机的控制回路的设定值，这些设定值控制无人机相对于与地面相关的参考系的水平线速度和倾角，因此 以使无人机以预定切向速度（u）跟随曲线路径（C）。

公开(公告)号：US20130105635A1

公开(公告)日：2013-05-02

申请号：US13285246

申请日：2011-10-31

Applicant: Hamzeh Mahmoud Abde Quader Alzu'bi ,  Imad Abd Allateef ,  Yahya Zweiri ,  Basim Alkhateeb ,  Ibrahem Mubarak Saleem Al-Masarwah

Inventor： Hamzeh Mahmoud Abde Quader Alzu'bi ,  Imad Abd Allateef ,  Yahya Zweiri ,  Basim Alkhateeb ,  Ibrahem Mubarak Saleem Al-Masarwah

IPC: B64C29/00

CPC classification number: B64C39/024 ,  B64C29/0033 ,  B64C2201/027 ,  B64C2201/108

Abstract: A system and method to control the stability and direction of a quad tilt vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV) by manipulating the rotational speed of propellers at each rotor while simultaneously tilting the rotors in a 45 degree configuration related to a central axis for directional control. Each rotor is attached to a tilting mechanism configured to be symmetrically aligned at a 45 degree angle from a central axis to manipulate a directional angle of each rotor along a first and second axis. The first and fourth rotors are aligned on the first axis while the second and third rotors are aligned on the second axis. A controller includes a first control loop for manipulating the rotational speed of the propellers to control the aircraft balance and a second control loop for controlling lateral movement by tilting the rotors along the first and second axis.

Abstract translation: 通过操纵每个转子上的螺旋桨的旋转速度同时使转子以与45度相关的45度配置倾斜来控制四倾斜垂直起飞和着陆（VTOL）无人机（UAV）的稳定性和方向的系统和方法 中心轴用于方向控制。 每个转子附接到倾斜机构，该倾斜机构构造成与中心轴成45度角对称地对准，以沿着第一和第二轴线操纵每个转子的方向角。 第一和第四转子在第一轴上对准，而第二和第三转子在第二轴上对准。 控制器包括用于操纵螺旋桨的旋转速度以控制飞行器平衡的第一控制回路和用于通过沿着第一和第二轴倾斜转子来控制横向运动的第二控制回路。

公开(公告)号：US20130068877A1

公开(公告)日：2013-03-21

申请号：US13700649

申请日：2011-05-03

Applicant: Key Dong Choi ,  Key Nam Choi

Inventor： Key Dong Choi ,  Key Nam Choi

IPC: B64C27/82

CPC classification number: B64C27/82 ,  A63H27/12 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/165

Abstract: An existing bottom-adjustable propeller-type flying object requires a device having a complex structure constructed through the combination of various components such as a servo, a control plate, and a hinge to control the rotor pitch at every moment and operate an adjustable blade for flight control. The bottom-adjustable propeller-type flying object of the disclosure includes a circular frame with a fixing plate and a protective plate installed at a lower portion of a shaft of a power propeller mounted to the central shaft, and an adjusting motor having an adjustable propeller. The flying object moves up or down by using force of the wind generated downward due to the rotation of the power propeller. The flying object makes a hovering flight, and leftward, rightward, forward, and backward flights by using the force of the wind generated due to the rotation of the adjustable propellers mounted on two adjusting motors.

Abstract translation: 现有的底部可调螺旋桨式飞行物体需要具有通过诸如伺服器，控制板和铰链的各种部件的组合构成的复杂结构的装置，以便在每一时刻控制转子节距并操作可调叶片 飞行控制。 本公开的底部可调螺旋桨式飞行物体包括具有固定板和安装在安装到中心轴的动力螺旋桨的轴的下部的保护板的圆形框架，以及具有可调螺旋桨的调节马达 。 飞行物体由于动力螺旋桨的旋转而产生向下的风的力而上下移动。 飞行物体通过使用由安装在两个调节马达上的可调螺旋桨的旋转而产生的风的力而产生悬停飞行，向左，向右，向前和向后飞行。

公开(公告)号：US08328130B2

公开(公告)日：2012-12-11

申请号：US12506052

申请日：2009-07-20

Applicant: Emray Goossen

Inventor： Emray Goossen

IPC: B64C29/00

CPC classification number: B64C27/20 ,  B33Y80/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  Y10T29/49336 ,  Y10T29/49826

Abstract: An unmanned aerial vehicle selectively formed of high strength composite structural part portions and lightweight aerodynamic foam portions to provide a low-cost and lightweight UAV that comports with export, civil airspace, and safety regulations. To further to reduce an overall weight of the UAV, mechanical elements are designed to provide multiple functionalities. Structural elements may be manufactured in same or similar non-specialized processes, and non-structural elements manufactured in same or similar non-specialized processes, reducing overall manufacturing costs. Materials and bonding elements are selected to provide frangibility and yet maintain normal flight structural integrity.

Abstract translation: 一种无人机选择性地由高强度复合结构部分部分和轻质的气动泡沫部分组成，以提供低成本和重量轻的无人机，符合出口，民用空域和安全规定。 为了进一步降低UAV的总体重量，机械元件设计为提供多种功能。 结构元件可以以相同或相似的非专门工艺制造，以及在相同或相似的非专业工艺中制造的非结构元件，降低总体制造成本。 选择材料和结合元件以提供易碎性​​并且仍然保持正常的飞行结构完整性。

公开(公告)号：US08272917B2

公开(公告)日：2012-09-25

申请号：US13024517

申请日：2011-02-10

Applicant: Steven Davis

Inventor： Steven Davis

IPC: A63H27/127

CPC classification number: B64C27/20 ,  A63H27/12 ,  A63H30/04 ,  A63H33/18 ,  B64C27/32 ,  B64C27/57 ,  B64C27/72 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  Y02T50/34

Abstract: A flying vehicle in accordance to an embodiment of the present invention includes a propeller control mechanism for flying the vehicle. The propeller control mechanism includes a propeller having a center shaft for connecting to the drive shaft; first and second propeller blades extending from the center shaft; and a control mechanism including a first linkage connecting the center shaft to the first propeller blade and a second linkage connecting the center shaft to a region defined on the propeller, wherein a change in a driving torque of the drive shaft causes the first linkage and the second linkage to change the pitch and height of the propeller blades while substantially unchanging the tip path plane of the propeller blades.

Abstract translation: 根据本发明的实施例的飞行器包括用于使车辆飞行的螺旋桨控制机构。 螺旋桨控制机构包括具有用于连接到驱动轴的中心轴的螺旋桨; 从中心轴延伸的第一和第二螺旋桨叶片; 以及控制机构，其包括将所述中心轴连接到所述第一螺旋桨叶片的第一连杆和将所述中心轴连接到所述螺旋桨上限定的区域的第二连杆，其中，所述驱动轴的驱动扭矩的变化导致所述第一连杆和 第二联动以改变螺旋桨叶片的桨距和高度，同时基本上不改变螺旋桨叶片的尖端路径平面。

公开(公告)号：US08256705B2

公开(公告)日：2012-09-04

申请号：US12612227

申请日：2009-11-04

Applicant: Timothy D. Smith

Inventor： Timothy D. Smith

IPC: B64C15/00

CPC classification number: B64C39/064 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/084 ,  B64C2201/205

Abstract: A torque production vehicle includes a plenum body having a wall with a central port and a radial port formed within the wall, an impeller disposed within the plenum body to move air through the central port, an engine coupled to the impeller to rotate the impeller about an axis, at least one arm coupled to the plenum body, and a plurality of foils disposed in the radial port to direct air about the plenum body to provide a torque force about the plenum body.

Abstract translation: 扭矩生产车辆包括具有中心端口和形成在壁内的径向端口的壁的增压室，设置在增压室内的叶轮以将空气移动通过中心端口，发动机联接到叶轮以使叶轮围绕 一个轴线，至少一个连接到集气室主体的臂，以及设置在该径向端口中的多个箔，以引导围绕该增压室的空气以提供围绕该增压室的转矩力。

公开(公告)号：US08251307B2

公开(公告)日：2012-08-28

申请号：US12104432

申请日：2008-04-16

Applicant: Emray R. Goossen

Inventor： Emray R. Goossen

IPC: B64C29/00 ,  B64C13/18

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/126 ,  B64C2201/128 ,  B64C2201/162 ,  B64D1/22

Abstract: A manipulator arm system on a ducted air-fan UAV is disclosed herein. The target site may be accurately located by the UAV, and the manipulator system may accurately locate the payload at the target site. The manipulator arm may select tools from a toolbox located on-board the UAV to assist in payload placement or the execution of remote operations. The system may handle the delivery of mission payloads, environmental sampling, and sensor placement and repair.

Abstract translation: 本文公开了一种管道式空气风扇UAV上的操纵臂系统。 目标站点可以由UAV精确定位，并且机械手系统可以准确地定位目标位置的有效载荷。 操纵臂可以从位于无人机上的工具箱中选择工具，以帮助有效载荷放置或执行远程操作。 该系统可以处理任务有效载荷的交付，环境取样以及传感器的放置和修理。