公开(公告)号：US09731818B2

公开(公告)日：2017-08-15

申请号：US14372060

申请日：2013-01-10

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： Guy Dekel ,  Lior Zivan ,  Yoav Efraty ,  Amit Wolff ,  Avner Volovick

IPC: B64C27/26 ,  B64C29/00 ,  B64C39/02 ,  B64C19/00 ,  G05D1/06 ,  G05D1/08

CPC classification number: B64C27/26 ,  B64C19/00 ,  B64C29/00 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/187 ,  G05D1/0676 ,  G05D1/0858

Abstract: A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle.

公开(公告)号：US20170166304A1

公开(公告)日：2017-06-15

申请号：US14967070

申请日：2015-12-11

Applicant: Amazon Technologies, Inc.

Inventor： Jack Erdozain, JR. ,  Louis LeRoi LeGrand, III ,  Joshua White Traube

IPC: B64C27/58 ,  H02K49/10 ,  H02K7/114 ,  B64C27/12 ,  B64C39/02

CPC classification number: B64C27/58 ,  B64C11/02 ,  B64C27/12 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/165 ,  H02K7/106 ,  H02K7/114 ,  H02K7/14 ,  H02K49/10

Abstract: A propeller alignment device is described. The propeller alignment device can include a second retainer attached to a propeller and a motor. The propeller alignment device can also include a first retainer that does not rotate, but that is aligned with the second retainer. The first retainer can include two or more magnets oppositely orientated relative to each other. The second retainer can also include two or more magnets oppositely orientated relative to each other. As the second retainer rotates relative to the first retainer, the magnets may alternatingly align with each other. In the absence of a current applied to the motor, the magnets may magnetically bias the second retainer into a predetermined orientation relative to the first retainer. The predetermined orientation can be predetermined to correspond to an alignment of the propeller that is desirable (e.g., that minimizes aerodynamic drag on the propeller).

公开(公告)号：US20170124884A1

公开(公告)日：2017-05-04

申请号：US14929858

申请日：2015-11-02

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 ,  B64C2201/027 ,  B64C2201/14 ,  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.

公开(公告)号：US20170088205A1

公开(公告)日：2017-03-30

申请号：US15272239

申请日：2016-09-21

Applicant: CALIFORNIA INSTITUTE OF TECHNOLOGY

Inventor： Jaakko T. KARRAS ,  Christine FULLER ,  Kalind C. CARPENTER ,  Alessandro BUSCICCHIO ,  Carolyn E. PARCHETA

IPC: B62D57/02 ,  B64C27/08

CPC classification number: B62D57/02 ,  B64C27/08 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/162

Abstract: A repeatably reconfigurable robot, comprising at least two printed circuit board (PCB) rigid sections, at least one PCB flexible section coupled to the at least two PCB rigid sections, at least one wheel, hybrid wheel propeller, wheel and propeller, or hybrid wheel screw propeller rotatably coupled to at least one of the at least two PCB rigid sections and at least one actuator coupled to the at least two PCB rigid sections, wherein the at least one actuator folds and unfolds the repeatably reconfigurable robot.

公开(公告)号：US20170081045A1

公开(公告)日：2017-03-23

申请号：US15364852

申请日：2016-11-30

Applicant: Cisco Technology, Inc.

Inventor： Charles Calvin Byers ,  Gonzalo Salgueiro

IPC: B64F5/60 ,  B64F1/00 ,  B64C39/02

CPC classification number: B64F5/60 ,  A47G29/14 ,  B64C39/024 ,  B64C2201/00 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/08 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2201/18 ,  B64D1/00 ,  B64F1/00 ,  B64F1/04 ,  B64F1/12 ,  G06Q10/0832

Abstract: In one embodiment, a controller instructs an unmanned aerial vehicle (UAV) docked to a landing perch to perform a pre-flight test operation of a pre-flight test routine. The controller receives sensor data associated with the pre-flight test operation from one or more force sensors of the landing perch, in response to the UAV performing the pre-flight test operation. The controller determines whether the sensor data associated with the pre-flight test operation is within an acceptable range. The controller causes the UAV to launch from the landing perch based in part on a determination that UAV has passed the pre-flight test routine.

公开(公告)号：US09567071B1

公开(公告)日：2017-02-14

申请号：US15152416

申请日：2016-05-11

Applicant: MARTIN UAV, LLC

Inventor： Stephen Morris

IPC: B64C29/00 ,  B64C29/02 ,  G05D1/08 ,  G05D1/10 ,  B64C11/00

CPC classification number: B64C29/02 ,  B64C11/001 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/162 ,  G05D1/0858 ,  G05D1/102

Abstract: An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight more, and transition the aircraft from the vertical flight mode to the horizontal flight mode.

Abstract translation: 飞机包括机身，机翼，风扇和控制器。 机翼和管道风扇耦合到机身。 控制器可操作以以垂直飞行模式，水平飞行更多地控制飞行器，并且将飞行器从垂直飞行模式转换到水平飞行模式。

公开(公告)号：US20160311529A1

公开(公告)日：2016-10-27

申请号：US15104614

申请日：2014-12-17

Applicant: Neva Aerospace, Ltd.

Inventor： David Brotherton-Ratcliffe ,  Laurent Martin

IPC: B64C29/00 ,  B64C27/20 ,  B64C37/02 ,  B64C39/02 ,  B64D35/06 ,  G05D1/00 ,  G08G5/00 ,  B64D27/10 ,  B64D35/04 ,  B64D27/24 ,  B64C27/30 ,  G01C21/16

CPC classification number: B64C29/0033 ,  B64C27/20 ,  B64C27/30 ,  B64C37/02 ,  B64C39/024 ,  B64C2027/8227 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2211/00 ,  B64D27/10 ,  B64D27/24 ,  B64D35/04 ,  B64D35/06 ,  B64D2041/002 ,  G01C21/16 ,  G05D1/0088 ,  G08G5/0034

Abstract: A VTOL aircraft is disclosed comprising a plurality of autonomous lifting modules wherein each autonomous lifting module is composed of a physical structure in which are mounted one or more electric ducted fans, an electrical energy storage system to drive the electric ducted fans, a charging and energy storage monitoring system to charge and monitor the electrical energy storage system, an inertial navigation system, electronic speed controllers to control the electric ducted fans and one or more microcomputers assuring (a) module flight stability by control of the electric ducted fans given the input of the inertial navigation system, (b) flight planning and (c) inter-module communication.

Abstract translation: 公开了一种VTOL飞机，其包括多个自主提升模块，其中每个自动提升模块由物理结构组成，其中安装有一个或多个电风扇，用于驱动电风扇的电能存储系统，充电和能量 存储监控系统，用于对电能存储系统进行充电和监测，惯性导航系统，电子速度控制器，用于控制电风扇和一个或多个微型计算机，确保（a）通过控制电风扇的模块飞行稳定性， 惯性导航系统，（b）飞行计划和（c）模块间通信。

公开(公告)号：US20160159458A1

公开(公告)日：2016-06-09

申请号：US14560964

申请日：2014-12-04

Applicant: JONATHON J. LINCH ,  Kyle M. Rahrig

Inventor： JONATHON J. LINCH ,  Kyle M. Rahrig

IPC: B64C11/00 ,  B64C11/08 ,  B64C11/18

CPC classification number: B64C11/001 ,  B64C11/08 ,  B64C11/18 ,  B64C39/024 ,  B64C39/10 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/162 ,  B64C2220/00 ,  Y02T50/12

Abstract: A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. At least one propeller blade is fixedly attached to both the hub and ring shroud and extends radially therebetween for mutual rotation therewith. At least one stub blade has a first stub end radially spaced from a second stub end. The first stub end is fixedly attached to a selected one of the hub and ring shroud. The second stub end is cantilevered from the first stub end and is radially interposed between the first stub end and the selected one of the hub and ring shroud.

Abstract translation: 螺旋桨包括同轴地围绕纵向轴线的轮毂。 环形护罩同轴地围绕纵向轴线并与轮毂径向间隔开。 至少一个螺旋桨叶片固定地附接到轮毂和环形护罩上并且在其间径向延伸以与其相互旋转。 至少一个短刀片具有与第二短截线径向间隔开的第一短截线端。 第一短截线端部固定地连接到轮毂和环形护罩中的所选择的一个。 第二短截线端部从第一短截线端部悬臂，并且径向插入在第一短截线端与轮毂和环形护罩中选定的一个之间。

公开(公告)号：US20160114887A1

公开(公告)日：2016-04-28

申请号：US14940379

申请日：2015-11-13

Applicant: Dylan T X Zhou ,  Andrew H B Zhou ,  Tiger T G Zhou

Inventor： Dylan T X Zhou ,  Andrew H B Zhou ,  Tiger T G Zhou

IPC: B64C39/02 ,  G05D1/00 ,  B63G8/00 ,  G05D1/04 ,  H04N5/265 ,  G01S19/39 ,  G08G3/02 ,  G08G5/04 ,  H04N7/18 ,  H04N5/232 ,  B60F3/00 ,  B63G8/14

CPC classification number: B64C35/008 ,  B60F5/02 ,  B63G8/001 ,  B63G8/16 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/145 ,  B64C2201/162 ,  B64C2201/165 ,  G05D1/102 ,  H04N5/2252 ,  H04N5/23206 ,  H04N5/2328 ,  H04N5/23296

Abstract: Provided is an amphibious vertical takeoff and landing unmanned device comprising a modular and expandable waterproof body, a chassis, an outer body shell, a propulsion system, a propeller protection system, a surface skidding material platform, a landing system, control surfaces, a ballast, an onboard air compressor, an onboard electrolysis system, a waterproof through-body wire or antenna feed-through, a single- or multiple-axis tilt-motor device, a tilt fuselage device, a tilt wing device, a battery, a power distribution board, a Global Positioning System module, a lost model alert, a cooling device, a detachable impact absorbing skin or shell, vision aiding and orientative lights, hatches, quick connect payloads, a lap counter for racing, a flat or inclined launch platform or footing, claws, an apparatus for externally attaching and internally housing the cargo, a charging station, a partial vacuum device, a manually or automatically deployable parachute, and an onboard or ground station electricity generator.

Abstract translation: 提供一种水陆两用垂直起降无人装置，其包括模块化和可扩展防水体，底盘，外壳体，推进系统，螺旋桨保护系统，表面打滑材料平台，着陆系统，控制面，镇流器 ，车载空气压缩机，车载电解系统，防水通体线或天线馈通，单轴或多轴倾斜电机装置，倾斜机身装置，倾斜翼装置，电池，电力 配电板，全球定位系统模块，丢失的模型警报，冷却装置，可拆卸的冲击吸收皮肤或壳体，视觉辅助和定向灯，舱口，快速连接有效载荷，赛车搭档，平坦或倾斜发射平台 或脚，爪，用于外部附接和内部容纳货物的装置，充电站，部分真空装置，手动或可自动展开的降落伞，以及船上或地面 发电机。

公开(公告)号：US09096314B2

公开(公告)日：2015-08-04

申请号：US13257810

申请日：2010-03-22

Applicant: David Brotherton-Ratcliffe ,  Jerzy Lelusz

Inventor： David Brotherton-Ratcliffe ,  Jerzy Lelusz

IPC: B64C29/02 ,  B64C27/20 ,  B64C29/00 ,  B64C39/02 ,  B64D27/24

CPC classification number: B64C29/0016 ,  B64C11/001 ,  B64C27/08 ,  B64C27/20 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/10 ,  B64D27/24 ,  B64D47/08 ,  G05D1/042 ,  Y02T50/64

Abstract: An electric and hybrid Vertical-Take Off and Landing (“VTOL”) aircraft is disclosed comprising a plurality of small Electric Ducted Fans (“EDFs”) of various sizes and orientations. The thrust of each fixed EDF is individually controlled by modulation of motor power by one or more onboard microcomputers connected to a plurality of onboard laser distance measuring sensors, at least three onboard three-axis accelerometers and at least one GPS thereby allowing extremely precise and safe VTOL operation. The aircraft may be employed to allow robotic and passenger vehicles to transition extremely quickly between normal linear flight and VTOL and to operate in extreme and gusty conditions.

Abstract translation: 公开了一种具有各种尺寸和方向的多个小型电风扇（“EDF”）的电动和混合垂直起飞和着陆（“垂直起落架”）飞机。 每个固定EDF的推力通过一个或多个连接到多个机载激光距离测量传感器，至少三个板载三轴加速度计和至少一个GPS的机载微型计算机调节电机功率来单独控制，从而允许非常精确和安全 VTOL操作。 飞机可能被允许机器人和乘客车辆在正常线性飞行和垂直起降之间非常快速地转变并且在极端和阵风的条件下操作。