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    METHODS AND SYSTEMS FOR TRANSITIONING AN AERIAL VEHICLE BETWEEN HOVER FLIGHT AND CROSSWIND FLIGHT
    2.
    发明公开
    METHODS AND SYSTEMS FOR TRANSITIONING AN AERIAL VEHICLE BETWEEN HOVER FLIGHT AND CROSSWIND FLIGHT 审中-公开
    方法和系统之间的悬停和交叉出发飞机过渡

    公开(公告)号：EP3046835A4

    公开(公告)日：2017-05-24

    申请号：EP14843632

    申请日：2014-09-15

    申请人： X DEV LLC

    发明人： CHUBB ERIK CHRISTOPHER ,  LIND DAMON VANDER

    IPC分类号： B64C31/06 ,  B64B1/66

    CPC分类号： B64C39/022 ,  B64C2201/021 ,  B64C2201/148 ,  F03D1/00 ,  F03D5/00 ,  F05B2240/917 ,  F05B2240/921 ,  Y02E10/70 ,  Y02E10/728

    摘要： A method involves operating an aerial vehicle in a hover-flight orientation. The aerial vehicle is connected to a tether that defines a tether sphere having a radius based on a length of the tether, and the tether is connected to a ground station. The method involves positioning the aerial vehicle at a first location that is substantially on the tether sphere. The method involves transitioning the aerial vehicle from the hover-flight orientation to a forward-flight orientation, such that the aerial vehicle moves from the tether sphere. And the method involves operating the aerial vehicle in the forward-flight orientation to ascend at an angle of ascent to a second location that is substantially on the tether sphere. The first and second locations are substantially downwind of the ground station.

    摘要翻译： 一种方法涉及悬停飞行方向上的飞行器运行。 飞行器被连接到系链那样定义具有基于所述系绳的长度为半径的系绳球体，并且系绳连接到地面站。 该方法包括在第一位置处定位所述飞行器所做的是基本上在系绳球体。 该方法包括从悬停飞行方向的飞行器过渡到向前飞行方向，寻求做与拴系领域的飞行器移动。 并且该方法涉及在该系绳球体操作在向前飞行取向处上升的角度来提升到第二位置飞行器并基本上。 所述第一和第二位置是基本上顺风地面站。

    FLIGHT CONTROL UNIT FOR TIED UNMANNED AERIAL VEHICLE MODELS
    6.
    发明公开
    FLIGHT CONTROL UNIT FOR TIED UNMANNED AERIAL VEHICLE MODELS 审中-公开
    FLUGSTEUERUNGSEINHEITFÜRUNBEMANNTE ANGEBUNDENE LUFTFAHRZEUGE

    公开(公告)号：EP3020633A1

    公开(公告)日：2016-05-18

    申请号：EP15466013.8

    申请日：2015-11-11

    申请人： Vyzkumny utav melioraci a ochrany pudy, v.v.l. ,  ADCIS s.r.o.

    发明人： Kulhavý, Zbynek ,  Krejzek, Pavel ,  Kulhavý, Martin

    IPC分类号： B64C39/02 ,  G05D1/08

    CPC分类号： G05D1/0866 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/148

    摘要： The solution proposed refers to a flight control unit (6) for tied models (1) (copters; UAV - Unmanned Aerial Vehicle) that provides for direct flight control using mechanical or electronic guiding link (2) between the guiding point (3) and the model (1). The mechanical execution of the guiding point (3) and the guiding link (2) can consist of a whipcord, wire, electrical cable etc.; the electronic type of guiding link (2) is then representing the line with an acoustic or electromagnetic signal, a light beam etc. The unit may be completed with data communication to specify the position coordinates of the guiding point (3) and the model (1) in more detail. The solution proposed provides for fully automated navigation of the model (1) to a required position in reference of the guiding point (3), without imposing higher level of skills on the pilot (4) or the necessity to know the movement path trajectory in advance as it is the case in wireless remote control of the model (1), or its flight programming.

    摘要翻译： 所提出的解决方案是指用于绑定型号（1）（直升机;无人机 - 无人机）的飞行控制单元（6），其使用机械或电子引导连杆（2）在引导点（3）和 模型（1）。 引导点（3）和引导连杆（2）的机械执行可以由拨号，电线，电缆等组成; 引导连杆（2）的电子式表示具有声或电信号，光束等的线。该单元可以用数据通信完成，以指定引导点（3）和模型（3）的位置坐标 1）更详细。 所提出的解决方案提供了将模型（1）的全自动导航参考引导点（3）到所需位置，而不对飞行员施加更高水平的技能（4）或者知道运动轨迹轨迹的必要性 如同在模型（1）的无线遥控器或其飞行编程中一样。

    STABILIZING CONTROL APPARATUS FOR ROBOTIC OR REMOTELY CONTROLLED FLYING PLATFORM
    8.
    发明公开
    STABILIZING CONTROL APPARATUS FOR ROBOTIC OR REMOTELY CONTROLLED FLYING PLATFORM 有权
    稳定装置用于机器人或遥控飞行平台

    公开(公告)号：EP1144249A4

    公开(公告)日：2002-12-18

    申请号：EP99972834

    申请日：1999-12-10

    申请人： MOLLER INT INC

    发明人： MOLLER PAUL S

    IPC分类号： B64C29/00 ,  B64C15/02 ,  B64C27/10 ,  B64C27/20 ,  B64C29/02 ,  B64C39/02

    CPC分类号： B64C39/024 ,  B64C29/02 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/162

    摘要： 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.

    Robotic or remotely controlled flying platform
    9.
    发明公开
    Robotic or remotely controlled flying platform 失效
    Fattesteuerte fliegende Plattform。

    公开(公告)号：EP0279391A2

    公开(公告)日：1988-08-24

    申请号：EP88102150.5

    申请日：1988-02-13

    申请人： MOLLER INTERNATIONAL, INC.

    发明人： Moller, Paul S.

    IPC分类号： B64C39/02 ,  B64C27/00 ,  B64C27/20

    CPC分类号： B64C39/024 ,  B64C27/00 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/162

    摘要： A flying platform (10), propelled by at least one ducted fan (11) causing a vertically downwardly directed airstream in and through a cylindrical duct (12). A vane system in the duct (12) has two mutually perpendicular pairs (31-34) of diametrically opposite first vanes, each extending in from the duct rim toward the center of the duct. Each pair of first vanes provides a pair of generally vertical walls parallel to a diametral line across the duct, and they define duct passages between the pairs of vanes and define quadrants between adjacent pairs. Each first vane has an upper, fixed, rigid portion and a variable camber flap (45, 46) depending therefrom. A first servomotor with linkages vary the camber of each pair of flaps (45, 46), so that the camber of the flaps (45, 46) of each pair is at all times the same amount but in opposite directions. Preferably, there are also four second vanes (41-44), one bisecting each quadrant, and a symmetric pair of spoilers (75-82) is mounted on each second vane (41-44). Each pair of spoilers (75-82) is independently movable, as a pair continuously between a position substantially blocking airflow through the outer portion of said quadrant and a position permitting substantially full airflow therethrough. A second servomotor with linkages symmetrically varies the position of its spoilers (75-82). There may be a radio receiver responsive to remote control signals for actuating each servo­motor and its linkages.

    摘要翻译： 一个由至少一个风扇（11）推动的飞行平台（10），引起垂直向下定向的气流穿过圆柱形导管（12）。 管道（12）中的叶片系统具有直径相对的第一叶片的两个相互垂直的对（31-34），每个叶片从管道边缘朝向管道的中心延伸。 每对第一叶片提供一对平行于穿过管道的直径线的大致垂直的壁，并且它们在两对叶片之间限定了通道，并在相邻的对之间限定了象限。 每个第一叶片具有从其垂直的上部固定的刚性部分和可变的外倾板（45,46）。 具有连接的第一伺服电机改变每对翼片（45,46）的弯度，使得每对翼片（45,46）的外倾角总是相同的量但是在相反的方向上。 优选地，还有四个第二叶片（41-44），一个二等分每个象限，并且对称的一对扰流器（75-82）安装在每个第二叶片（41-44）上。 每对扰流器（75-82）可独立地可移动，作为一对连续地在基本上阻挡通过所述象限的外部部分的气流的位置和允许基本上完全通过气流的位置之间。 具有连杆的第二个伺服电机对称地改变其扰流板的位置（75-82）。 可以存在响应于用于致动每个伺服电机及其连接的遥控信号的无线电接收器。

    MULTI-ROTOR AERIAL VEHICLE
    10.
    发明公开
    MULTI-ROTOR AERIAL VEHICLE 审中-公开
    多旋翼空中车辆

    公开(公告)号：EP3212502A1

    公开(公告)日：2017-09-06

    申请号：EP15854629.1

    申请日：2015-10-28

    申请人： ACC Innovation AB

    发明人： LJUNG, Anders

    IPC分类号： B64D35/04 ,  B64C27/08 ,  B64C27/12

    CPC分类号： B64D35/04 ,  A63H27/12 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/04 ,  B64C2201/06 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148 ,  B64D37/00

    摘要： Multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) comprising, at least a first, second and third rotor 10, 20, 30, each rotatable by a dedicated first second and third hydraulic motor 11, 21, 31, a power unit 2, at least a first, second and third hydraulic pump 12, 22, 32 dedicated to the respective first, second and third hydraulic motor 11, 21, 31, wherein each hydraulic pump 12, 22, 32 is arranged to provide pressurized fluid to each hydraulic motor 11, 21, 31 for powering the hydraulic motor 11, 21, 31 and thereby rotating the respective rotor 10, 20, 30, a control unit 6 for controlling the operation of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″), wherein the control of the multi-rotor aerial vehicle (1, 1′, 1″, 1′″, 1″″, 1″″′, 1″″″) is arranged to be performed by altering the flow of pressurized fluid distributed to each respective hydraulic motor 11, 21, 31, wherein, wherein the flow of pressurized fluid provided to each hydraulic motor 11, 21, 31 is individually controllable by means of at least one control valve 13, 23, 33 configured to control the flow of pressurized fluid from each hydraulic pump 12, 22, 32 to its dedicated hydraulic motor 11, 21, 31.

    摘要翻译： 多旋翼飞行器（1,1'，1“，1”'，1“'，1”'，1“'）包括至少第一，第二和 第三转子10,20,30，每个转子通过专用的第一第二和第三液压马达11,21,31，动力单元2，至少第一，第二和第三液压泵12,22,32可旋转，所述第一，第二和第三液压泵12,22,32专用于相应的第一， 第二和第三液压马达11,21,31，其中每个液压泵12,22,32被布置成向每个液压马达11,21,31提供加压流体，用于给液压马达11,21,31供能并由此旋转相应的 转子10,20,30，用于控制多旋翼飞行器（1,1'，1“，1”'，1“，1”''）的操作的控制单元6， 其中多旋翼飞行器（1,1'，1“，1”'，1“'，1”'，1“ ）被布置成通过改变分配给每个相应液压马达11,21,31的加压流体的流动来执行，其中，向每个液压马达提供加压流体的流动 液压马达11,21,31可通过至少一个控制阀13,23,33单独控制，所述至少一个控制阀13,23,33构造成控制从每个液压泵12,22,32到其专用液压马达11,21,31的加压流体的流动 。