公开(公告)号：KR20180026280A

公开(公告)日：2018-03-12

申请号：KR20160113454

申请日：2016-09-02

Applicant: FDCREAT CO LTD ,  IND ACADEMIC COOPERATION FOUNDATION OF DAEDUK COLLEGE

Inventor： CHOI HYO SEON

IPC: G09B9/48 ,  B64C27/08 ,  B64C27/12 ,  B64C39/02 ,  G09B19/16

CPC classification number: G09B9/48 ,  B64C27/08 ,  B64C27/12 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/165 ,  B64C2201/201 ,  G09B19/165

Abstract: 본발명은드론의실제비행에앞서드론의각 구성품에대한학습및 조립, 드론제어방법을실습할수 있도록함으로써체계적인드론교육이이루어질수 있도록하는드론실습장치에관한것이다. 본발명에따른드론실습장치는드론의각 구성부를 PCB 보드에장착하여각 구성부의출력값과성능을테스트할수 있는드론실습장치로서, 배터리(70)부터전원을공급받아분배하는전원분배회로(25)가구비된 PCB 보드(20)와; 중앙플레이트(31)를중심으로외측으로연장형성되는복수의드론암(32)이구비되어상기 PCB 보드(20)의상부에체결되는드론몸체(30)와; 상기드론몸체(30)의드론암(32) 단부에형성되는드론모터홀드지그(33)에각각체결되는모터(50) 및상기모터(50)의상부에체결되는프로펠러(55)와; 상기드론몸체(30)의드론암(32) 중간부에체결되어모터(50)의구동의제어하는모터컨트롤러(60)와; 상기드론몸체(30)의중앙플레이트(31) 상부에체결되어상기모터컨트롤러(60)를통하여모터(50)의구동을제어하여드론의비행동작을제어하는메인제어모듈(40);을포함하여이루어지되, 상기 PCB 보드(20)는전원분배회로(25)를통하여배터리(70)로부터공급되는전원을분배하여, 상기드론몸체(30)에체결되는메인제어모듈(40)과모터(50) 및모터컨트롤러(60)에동작전원으로공급하는것을특징으로한다.

Abstract translation: 本发明涉及使得一个系统的实践雄蜂雄蜂教育可以通过无人驾驶飞机的实际飞行之前提供学习实验室和组件，无人驾驶飞机控制方法，用于无人驾驶飞机的各组分来实现的装置。 根据本发明雄蜂练习装置被附接到所述PCB板的部分，无人驾驶飞机作为可以测试输出值和性能，配电电路25的各构成部件，用于从电池70与动力分配供给的雄蜂锻炼装置的各结构 无纺布PCB板（20）; 一个无人机主体（30），具有多个围绕中心板（31）向外延伸并固定在PCB板（20）上部的无人驾驶臂（32）; 紧固在无人驾驶飞机本体30的无人驾驶臂32的端部形成的无人驾驶电动机保持夹具33上的电动机50和紧固到电动机50上部的螺旋桨55; 电机控制器60，其连接到无人机主体30的无人机臂32的中间部分以控制电动机50的运动; 并且主控制模块40耦合到无人机主体30的中心板31的上部以通过马达控制器60控制马达50的驱动以控制无人机的飞行操作 PCB板20通过配电电路25分配从电池70供应的电力并且向主控制模块40和电动机50供应电力， 并且马达控制器（60）作为操作动力。

公开(公告)号：KR101831119B1

公开(公告)日：2018-02-21

申请号：KR1020177017487

申请日：2010-09-09

Applicant: 에어로바이론먼트, 인크.

Inventor： 미랄레스,카로스토마스 ,  수,구안에이치. ,  앤드류코브,오렉산드르 ,  맥네일,존

IPC: B64F1/06 ,  B64C39/02 ,  F42B39/14 ,  F41A21/02 ,  F41F3/042 ,  B64F1/04 ,  B64C13/20

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/201 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F41F3/042 ,  F42B39/14

Abstract: 무인항공기(UAV) 발사관(100)은, 직육면체개구(305) 둘레에배치된적어도하나의내부프리프레그기재층(370); 직육면체개구(305) 둘레에배치된적어도하나의외부프리프레그기재층(380); 및적어도하나의내부프리프레그기재층(340)과적어도하나의외부프리프레그기재층(380) 사이에배치된하나이상의구조판(structural panel, 341~344)을포함한다. UAV 발사관(100)은, 내벽으로정의된발사장치체적내에서무인항공기(UAV)에맞물리도록구성되고, 내벽에서압력밀봉을제공하도록치수가정해지며내벽에테더링된테더링이탈피(700, 740)를포함하며, 이때 테더링이탈피(700, 740)는고압체적을향해배향된개방단및 이탈피(700)의중공(910) 내에서부착된테더(740)를구비하여중공으로이루어지며, 내벽에부착되어고압체적을유지하거나기저내벽(1013)에부착된다. 시스템은, 통신노드(1500~1505); 및발사전 상태에서통신노드(1500~1505)로부터명령입력을수신하고이에응답하도록구성된 UAV를포함하는발사장치(1520)를포함한다.

Abstract translation: 无人飞行器（UAV）发射管100包括至少一个围绕矩形平行六面体开口305设置的内部预浸料坯基层370; 至少一个布置在长方体开口（305）周围的外部预浸料坯基层（380）; 以及设置在至少一个内部预浸料坯基层340和至少一个外部预浸料坯基层380之间的至少一个结构面板341-344。 无人飞行器发射管100被配置为接合定义为内壁的发射器体积中的无人飞行器，并且其尺寸被设计为在内壁处提供压力密封并且系住到内壁的系绳被剥离700， 其中系链700,740包括朝向高压容积定向的开放端和附接在释放凹坑700的中空部910内的中空的系绳740， 并且附接到内壁以保持高压容积或附接到基部内壁1013。 该系统包括：通信节点（1500-1505）; 并且发射装置1520包括UAV，其被配置为接收并响应于处于抢先状态的通信节点1500-1505的指令输入。

公开(公告)号：KR1020170078847A

公开(公告)日：2017-07-07

申请号：KR1020177017487

申请日：2010-09-09

Applicant: 에어로바이론먼트, 인크.

Inventor： 미랄레스,카로스토마스 ,  수,구안에이치. ,  앤드류코브,오렉산드르 ,  맥네일,존

IPC: B64F1/06 ,  B64C39/02 ,  F42B39/14 ,  F41A21/02 ,  F41F3/042 ,  B64F1/04 ,  B64C13/20

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/201 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F41F3/042 ,  F42B39/14 ,  B64C13/20 ,  B64C2201/084

Abstract: 무인항공기(UAV) 발사관(100)은, 직육면체개구(305) 둘레에배치된적어도하나의내부프리프레그기재층(370); 직육면체개구(305) 둘레에배치된적어도하나의외부프리프레그기재층(380); 및적어도하나의내부프리프레그기재층(340)과적어도하나의외부프리프레그기재층(380) 사이에배치된하나이상의구조판(structural panel, 341~344)을포함한다. UAV 발사관(100)은, 내벽으로정의된발사장치체적내에서무인항공기(UAV)에맞물리도록구성되고, 내벽에서압력밀봉을제공하도록치수가정해지며내벽에테더링된테더링이탈피(700, 740)를포함하며, 이때 테더링이탈피(700, 740)는고압체적을향해배향된개방단및 이탈피(700)의중공(910) 내에서부착된테더(740)를구비하여중공으로이루어지며, 내벽에부착되어고압체적을유지하거나기저내벽(1013)에부착된다. 시스템은, 통신노드(1500~1505); 및발사전 상태에서통신노드(1500~1505)로부터명령입력을수신하고이에응답하도록구성된 UAV를포함하는발사장치(1520)를포함한다.

公开(公告)号：KR1020070112819A

公开(公告)日：2007-11-27

申请号：KR1020077021876

申请日：2006-02-09

Applicant: 허니웰 인터내셔널 인코포레이티드

Inventor： 구센엠레이알.

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

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C29/0016 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/201

Abstract: A dual ducted fan arrangement in which the duct components (203), engine (10), and avionics/payload pods (300, 302) are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan (201), stator (102), and control vane design. Assembly connections between ducted fans (203) and electronic modules are also identical. An engine (10) or APU drives the dual ducted fans (203) through a splined shaft (601) to a differential (600) or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator (102) hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms (603) on each of the splined shafts (601) between the differential (600) and ducted fans (203). In the electric motor case relative speed is through electronic speed control. The fans (201) are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

Abstract translation: 一种双管道风扇装置，其中管道部件（203），发动机（10）和航空电子设备/有效载荷容器（300,302）能够快速拆卸以适合普通的背包系统。 风扇（201），定子（102）和控制叶片设计中的每个管道相同。 管道风扇（203）和电子模块之间的组装连接也是相同的。 发动机（10）或APU通过花键轴（601）驱动双管道风扇（203）到差速器（600）或通过电动机驱动。 通过安装到定子（102）毂的单个齿轮将能量传递到管道风扇。 单个管道风扇的相对速度通过在差速器（600）和管道风扇（203）之间的每个花键轴（601）上的分开的摩擦或发电机负载控制制动机构（603）来控制。 在电动机壳体中，相对速度是通过电子速度控制。 风扇（201）反向旋转以进行扭矩平衡。 电子模块位置对于纵向重心是垂直可变的，用于有效载荷的变化。

公开(公告)号：KR1019890000530B1

公开(公告)日：1989-03-20

申请号：KR1019820003604

申请日：1982-08-11

Applicant: 레이테온 이-시스템즈 인코포레이티드

Inventor： 찰스에이취.터버주니어 ,  프레데릭에이.베렌스 ,  존에이취.헌튼

IPC: B64C39/02

CPC classification number: F41G7/22 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208 ,  B64F1/06 ,  F41G7/007

Abstract: The remotely piloted aircraft has control surfaces asymmetrical in the pitch and yaw planes, a sensor, and a guidance system operative in the terminal portions of the flight of the aircraft in a yaw-to- turn mode with a zero roll rate. The system has a directional sensor for providing azimuth and elevation error signals. A device provides guidance signals indicative of the rate of change of the azimuth and elevation signals. A guidance programmer responds to the guidance signals for providing pitch control and yaw control signals. An altitude sensor provides an altitude control signal. Roll, pitch and yaw rate gyros provide a rate control signal and a three axis autopilot.

Abstract translation: 遥控飞行器具有在俯仰和偏航平面中不对称的控制表面，传感器和在零滚动速率的偏航 - 转弯模式下在飞行器的飞行的终端部分中操作的引导系统。 该系统具有用于提供方位角和仰角误差信号的方向传感器。 装置提供指示方位角和仰角信号变化率的指导信号。 指导程序员响应用于提供俯仰控制和偏航控制信号的引导信号。 高度传感器提供高度控制信号。 滚动，俯仰和偏航率陀螺仪提供速率控制信号和三轴自动驾驶仪。

公开(公告)号：EP3483071A2

公开(公告)日：2019-05-15

申请号：EP18201352.4

申请日：2010-09-09

Applicant: AeroVironment, Inc.

Inventor： MIRALLES, Carlos Thomas ,  SU, Guan H. ,  ANDRYUKOV, Alexander ,  MCNEIL, John

IPC: B64F1/04 ,  F41F3/04 ,  B64C13/20 ,  F42B39/14 ,  F41F1/00 ,  B64C39/02 ,  B64F1/06 ,  F41A21/02

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/201 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F41F3/042 ,  F42B39/14

Abstract: An unmanned aerial vehicle (UAV) launch tube (100) that comprises at least one inner layer of prepreg substrate (370) disposed about a right parallelepiped aperture (305), at least one outer layer of prepreg substrate (380) disposed about the right parallelepiped aperture (305), and one or more structural panels (341-344) disposed between the at least one inner layer of prepreg substrate (340) and the at least one outer layer of prepreg substrate (380). An unmanned aerial vehicle (UAV) launch tube (100) that comprises a tethered sabot (700,740) configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot (700,740) dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot (700,740) is hollow having an open end oriented toward a high pressure volume and a tether (740) attached within a hollow (910) of the sabot (700) and attached to the inner wall retaining the high pressure volume or attach to the inner base wall (1013). A system comprising a communication node (1500-1505) and a launcher (1520) comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node (1500-1505).

公开(公告)号：EP3393911A1

公开(公告)日：2018-10-31

申请号：EP16877900.7

申请日：2016-12-21

Applicant: Airscort Ltd.

Inventor： STRAUS, Itai ,  TAL, Yitzhak

IPC: B64F1/12 ,  B64F1/00

CPC classification number: B64F1/12 ,  B64C39/024 ,  B64C2201/201 ,  B64F1/007

Abstract: A solution to the problem of short battery life of drones and operation in isolated or distant areas of service, by means of docking station/stations that allow for the autonomous landing/takeoff, storage, recharging and/or battery swapping for the drone/drones. The station is multi-cell station for drones with one or more landing/takeoff cells; at least two docking/storage cells; a transitioning closed-loop system configured for transporting the drones within the landing/takeoff cells and docking/storage cells; and control means configured for autonomous control, operation and management of the multi-cell station, where each one of the one or more landing/takeoff cells and at least two docking/storage cells shares at least two sides with neighbouring cells. Recharging mechanism for recharging the stored drones and transitioning mechanism for circulating the drones within the cells of the station are also provided.

公开(公告)号：EP3337724A1

公开(公告)日：2018-06-27

申请号：EP16836725.8

申请日：2016-08-17

Applicant: H3 Dynamics Holdings Pte. Ltd.

Inventor： WANKEWYCZ, Taras

IPC: B64F1/22 ,  B64F1/20 ,  E04H6/44 ,  H02J7/00

CPC classification number: E04H6/44 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/148 ,  B64C2201/201 ,  E04H6/04 ,  H02J7/00 ,  H02J7/0042 ,  H02J7/025

Abstract: The application provides a storage unit for an Unmanned Aerial Vehicle (UAV). The storage unit includes a container, a UAV landing platform, and a receptacle. The container is provided for enclosing the UAV. The receptacle is positioned above the UAV landing platform and it includes at least one inclined surface for guiding a landing UAV to a predetermined UAV landing position on the UAV landing platform.

公开(公告)号：EP3241741A4

公开(公告)日：2018-01-24

申请号：EP15875204

申请日：2015-12-29

Applicant: BEIJING ZERO ZERO INFINITY TECH CO LTD

Inventor： ZHANG TONG ,  WANG MENGQIU ,  WANG ZHAOZHE ,  ZHANG XUYANG ,  ZHANG GUANQUN ,  GONG SHUANG ,  ZHANG YALIN ,  WANG JINGLONG ,  LIU LIXIN

IPC: B64C39/02

CPC classification number: B64C27/006 ,  B64C1/30 ,  B64C27/08 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/20 ,  B64C2201/201

Abstract: A fully-protected unmanned aerial vehicle comprises an unmanned aerial vehicle body (1) and a rotor (2) connected to the unmanned aerial vehicle body (1), and further comprises a protection housing (3) connected to the unmanned aerial vehicle body (1). The protection housing (3) is a hollowed-out closed housing and has a hollow cavity (31), and the rotor (2) is installed in the hollow cavity (31). Because the rotor is installed in the hollow cavity of the protection housing, the rotor cannot make contact with a human body, so that the unmanned aerial vehicle can be released or reclaimed by an operator with the hand, and the operation portability and safety of the rotor are improved. The hollowed-out structure provides a forming space of lift for the rotor and normal flight of the unmanned aerial vehicle is ensured. The rotor is installed in the protection housing that is connected to the unmanned aerial vehicle body, so that the overall height of the unmanned aerial vehicle is reduced, and the portability of the unmanned aerial vehicle is further improved.

公开(公告)号：EP3201088A1

公开(公告)日：2017-08-09

申请号：EP15847916.2

申请日：2015-09-24

Applicant: Swift Engineering, Inc.

Inventor： STREETT, Andrew

IPC: B64C39/02 ,  B64D41/00

CPC classification number: B60L11/182 ,  B64C39/024 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/222 ,  G05D1/0011 ,  G05D1/0088 ,  H02J7/35

Abstract: A transportable ground station for a UAV includes a container in which the UAV may be transported and housed. The container includes a wireless or contact-based recharging station that recharges the UAV's batteries or other power sources after the UAV returns from a mission. The recharging station may be directly or indirectly connected to one or more solar panels that generate energy to power the recharging station. The ground station may be deployed virtually anywhere, from any vehicle (e.g., plane, train, boat, truck, etc.), and may operate over an extended period of time without human intervention.

Abstract translation: 用于无人飞行器的可移动地面站包括其中可以运输和容纳无人飞行器的容器。 该集装箱包括无线或基于接触的充电站，在无人机返回任务后，该无线充电站可为无人机的电池或其他电源充电。 再充电站可以直接或间接地连接到一个或多个太阳能电池板，这些太阳能电池板产生能量以给再充电站供电。 地面站几乎可以从任何车辆（例如飞机，火车，船，卡车等）的任何地方部署，并且可以在延长的时间段内运行而无需人工干预。