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    회전하는 하방날개형 비행체
    81.
    发明授权
    회전하는 하방날개형 비행체 有权
    旋转底刀型车

    公开(公告)号：KR101344777B1

    公开(公告)日：2014-01-15

    申请号：KR1020080065306

    申请日：2008-07-07

    Applicant: (주)선택이앤티

    Inventor： 최기남

    IPC: B64C27/54 ,  B64C27/32

    CPC classification number: B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127

    Abstract: 종래의 하방날개형 비행체는 프로펠러의 회전으로 발생하는 비행체의 반토크를 제거하고 비행체의 비행을 위해, 여러 쌍의 고정판과 전후진 조정날개 및 좌우회전 조정날개를 각각 장착하여 조정함으로 비행체의 구조와 조정이 복잡하며 비행체의 무게와 부피가 대형화하게 되어 협소한 공간에서 정찰 및 감시에 어려운 문제점이 있었다.
    그러나, 본 발명은 비행체의 반토크를 제거하지 않고 1개의 조정날개로 비행체가 계속하여 회전하면서 정지, 전후진, 좌우회전, 좌측진, 우측진 등의 비행을 가능하게 한 것을 특징으로 하는 비행체로서, 비행체의 구조와 조정을 간단하게 하여 무게와 크기를 줄일 수 있어 협소한 장소에서의 비행 뿐 만아니라, 실내에서의 정찰과 감시 등을 가능하게 하고, 동력효율을 높일 수 있는 회전하는 하방날개형 비행체를 제공한다.
    고정피치, 가변피치, 프로펠러, 고정판, 조정날개, 카메라

    삼엽 하방날개형 비행체
    82.
    发明公开
    삼엽 하방날개형 비행체 有权
    3底部叶片式车辆

    公开(公告)号：KR1020100005315A

    公开(公告)日：2010-01-15

    申请号：KR1020080065298

    申请日：2008-07-07

    Applicant: (주)선택이앤티

    Inventor： 최기남

    IPC: B64C27/54 ,  B64C27/32

    CPC classification number: B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127

    Abstract: PURPOSE: A three bottom-blade vehicle is provided to improve power efficiency and length the flying duration, and to reduce the affects of wind by securing enough distance between the rudders. CONSTITUTION: A fixed-pitch propeller(2) is horizontally installed around a central shaft(1). A power unit(3) is installed on the top of the central shaft of the propeller. A control unit(4) is installed on the bottom of the central shaft of the propeller. One end of each of first to third attachment plates(11~13) is successively attached to the control unit at the angle of 120 degrees. The other end of each attachment plate is attached to a round frame(5) and leg plates(32,33).

    Abstract translation: 目的：提供三个底刀车辆，以提高飞行时间的功率效率和长度，并通过确保方向舵之间足够的距离来减少风的影响。 构成：固定螺距螺旋桨（2）围绕中心轴（1）水平安装。 动力单元（3）安装在螺旋桨中心轴的顶部。 控制单元（4）安装在螺旋桨中心轴的底部。 每个第一至第三安装板（11〜13）的一端以120度的角度连续地附接到控制单元。 每个附接板的另一端附接到圆形框架（5）和腿板（32,33）。

    공중부상형 비행체, 모듈형 듀얼 덕트 비행체의 조립 방법, 및 듀얼 덕트형 비행체의 팩키징 방법
    83.
    发明公开
    공중부상형 비행체, 모듈형 듀얼 덕트 비행체의 조립 방법, 및 듀얼 덕트형 비행체의 팩키징 방법 失效
    双排气罩空气动力车

    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。

    UNMANNED AERIAL VEHICLE TAKE-OFF AND LANDING CONTROL SYSTEM AND CONTROL METHOD
    86.
    发明公开
    UNMANNED AERIAL VEHICLE TAKE-OFF AND LANDING CONTROL SYSTEM AND CONTROL METHOD 审中-公开

    公开(公告)号：EP3372492A1

    公开(公告)日：2018-09-12

    申请号：EP16881084.4

    申请日：2016-12-22

    Applicant: Goertek Technology Co., Ltd.

    Inventor： HU, Tengfei

    IPC: B64C19/00 ,  B64F1/00

    CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/18 ,  B64C2201/208 ,  B64F1/02 ,  B64F1/362 ,  H01F7/202 ,  H02J7/025 ,  H02N15/00

    Abstract: Disclosed is an unmanned aerial vehicle take-off and landing control system and a control method. The control system comprises a magnet assembly provided at the side of an unmanned aerial vehicle (1) and a magnetic field assembly provided at the side of a parking platform. An electrified coil (2) is provided in the magnetic field assembly. A current is supplied into the electrified coil (2). A supporting magnetic field is generated by the magnetic field assembly at the side of the parking platform, so that a thrust force acting on the unmanned aerial vehicle (1) is formed. A resultant force is formed by the thrust force and a lift force or resistance force in the process of take-off or landing of the unmanned aerial vehicle (1) to supplement the lift force or the resistance. In the process of take-off or landing of the unmanned aerial vehicle (1), the current in the electrified coil (2) is changed to form a uniform magnetic field, the thrust force acting on the unmanned aerial vehicle (1) is generated to supplement the lift force or the resistance in the process of take-off and landing , thereby improving the safety performance of the unmanned aerial vehicle (1), reducing the energy consumption of the unmanned aerial vehicle (1) when it is used, and prolonging the service life of the unmanned aerial vehicle (1).

    AN UNMANNED AERIAL VEHICLE
    89.
    发明公开
    AN UNMANNED AERIAL VEHICLE 有权
    UNBEMANNTES LUFTFAHRZEUG

    公开(公告)号：EP3087003A4

    公开(公告)日：2017-09-13

    申请号：EP13900333

    申请日：2013-12-24

    Applicant: SINGAPORE TECH AEROSPACE LTD

    Inventor： CHAN KEEN IAN

    IPC: B64C29/02 ,  A63H27/127 ,  A63H27/133 ,  A63H27/18 ,  B64C11/48 ,  B64C39/02

    CPC classification number: B64C29/02 ,  A63H27/12 ,  B64C11/48 ,  B64C27/08 ,  B64C27/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/122 ,  B64C2201/141

    Abstract: An unmanned aerial vehicle (UAV) capable of vertical and horizontal flight modes, a method of assembling a UAV, and a kit of parts for assembling a UAV. The UAV comprises an elongated wing structure having an elongated axis along the longest dimension of the elongated wing structure, the elongated wing structure having a middle location at a substantially halfway point; a connecting structure extending substantially perpendicularly from the elongated wing structure, the connecting structure being offset from the middle location of the elongated wing structure at a first position along the elongated axis; and at least three sets of propellers, wherein at least two sets of propellers are mounted on the connecting structure, and wherein at least one set of propellers is mounted at a second position offset from the middle location in an opposite direction away from the connecting structure.

    Abstract translation: 一种能够纵向和横向飞行模式的无人驾驶飞行器（UAV），一种组装无人飞行器的方法和一套用于组装无人飞行器的部件。 无人飞行器包括细长机翼结构，细长机翼结构具有沿着细长机翼结构的最长尺寸的细长轴线，细长机翼结构具有在大体中途点处的中间位置; 连接结构，所述连接结构从所述细长机翼结构大致垂直地延伸，所述连接结构在所述细长机翼结构的中间位置沿着所述细长轴线在第一位置处偏移; 以及至少三组螺旋桨，其中至少两组螺旋桨安装在所述连接结构上，并且其中至少一组螺旋桨安装在第二位置，所述第二位置偏离所述中间位置在远离所述连接结构的相反方向上 。

    AIRCRAFT WITH WING-BORNE FLIGHT MODE AND HOVER FLIGHT MODE
    90.
    发明公开
    AIRCRAFT WITH WING-BORNE FLIGHT MODE AND HOVER FLIGHT MODE 审中-公开
    飞翼飞行模式和HOVER飞行模式

    公开(公告)号：EP3172130A1

    公开(公告)日：2017-05-31

    申请号：EP15747241.6

    申请日：2015-07-21

    Applicant: Atmos Uav B.V.

    Inventor： HULSMAN, Sander ,  DE GROOT, Jurjen ,  MILIS, Maarten ,  DOKTER, Dirk Lucas Eduard ,  BOUMAN, Joost Leon ,  KNOOPS, Ruud

    IPC: B64C39/02

    CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165

    Abstract: An aircraft, in particular an unmanned aerial vehicle with wing-borne flight mode and hover flight mode, comprises a wing structure (4) having a left (6), middle (7), and right wing section (8). A support structure extends from the wing structure (4), and has an upper and lower support section. Each one of the left and right wing section (6, 8), and upper and lower support section (18, 20) has a thrust unit (10, 12, 22, 24). Left and right wingtip sections are rotatable relative to a left and right wing base section, respectively, around an axis extending substantially in a lengthwise direction of the wing structure. The thrust units (10,12) of the left and right wing sections(6, 8) are provided at the respective wingtip sections, in particular at the extremities thereof.

    Abstract translation: 一种飞机，特别是具有机翼飞行模式和悬停飞行模式的无人驾驶飞行器，包括具有左（6），中（7）和右翼部分（8）的机翼结构（4）。 支撑结构从机翼结构（4）延伸，并具有上支撑部分和下支撑部分。 左右翼部（6,8）和上下支承部（18,20）中的每一个具有推力单元（10,12,22,24）。 左翼尖部分和右翼尖部分可以分别围绕基本上在翼结构的纵向方向上延伸的轴线相对于左翼基部部分和右翼基部部分旋转。 左翼部分（6）和右翼部分（8）的推力单元（10，12）设置在相应的翼尖部分处，特别是在其末端。

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