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    HIGH-ALTITUDE DRONE
    4.
    发明申请
    HIGH-ALTITUDE DRONE 审中-公开
    高海拔度

    公开(公告)号：US20160167775A1

    公开(公告)日：2016-06-16

    申请号：US14891153

    申请日：2014-05-09

    Applicant: RIDENGINEERING

    Inventor： Jaques JONIOT

    IPC: B64C27/22 ,  B64B1/40 ,  B64C39/02 ,  B64C17/04

    CPC classification number: B64C27/22 ,  B64B1/40 ,  B64B1/44 ,  B64C17/04 ,  B64C27/20 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/101 ,  B64C2201/108 ,  B64C2201/122 ,  B64C2201/123 ,  B64D2211/00

    Abstract: The invention relates to a drone comprising: two contra-rotating annular propellers (2, 4) defining a plane therebetween which is referred to as an equatorial plane and is assumed to be horizontal, means for driving the propellers, a load arranged below the equatorial plane, and means (20) for moving the load relative to the equatorial plane, an enclosure referred to as an upper enclosure (6) filled with a gas or a gaseous mixture having a density of less than 1 and arranged essentially above the equatorial plane, and an enclosure referred to as a lower enclosure (8) filled with a gas or a gaseous mixture having a density of less than 1 and arranged essentially below the equatorial plane, the load being placed inside the lower enclosure.

    Abstract translation: 无人机技术领域本发明涉及一种无人机，包括：两个反向旋转的环形螺旋桨（2,4），在其间限定一个平面，被称为赤道平面，并被假设为水平的，用于驱动螺旋桨的装置，设置在赤道 平面和用于相对于赤道平面移动负载的装置（20），被称为上部外壳（6）的外壳，其填充有密度小于1且基本上位于赤道平面上方的气体或气体混合物 ，以及被称为下部外壳（8）的外壳，其中填充有密度小于1且基本上位于赤道平面下方的气体或气体混合物，所述负载被放置在下部外壳内。

    AERIAL VEHICLE AND METHOD OF FLIGHT
    5.
    发明申请
    AERIAL VEHICLE AND METHOD OF FLIGHT 有权
    空中客车和飞行方法

    公开(公告)号：US20140339356A1

    公开(公告)日：2014-11-20

    申请号：US14324306

    申请日：2014-07-07

    Applicant: Athene Works Limited

    Inventor： Nicholas James DEAKIN

    IPC: B64B1/02 ,  B64B1/64

    CPC classification number: B64B1/02 ,  B64B1/08 ,  B64B1/10 ,  B64B1/12 ,  B64B1/14 ,  B64B1/20 ,  B64B1/38 ,  B64B1/64 ,  B64B2201/00 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/167 ,  H01Q1/36 ,  H01Q9/27

    Abstract: An aerial vehicle comprises an elongate envelope within which are at least one first compartment for holding a lighter than air gas and at least one second compartment for holding atmospheric air and said at least one second compartment having an inlet and an outlet and at least one pair of wings extending laterally from the envelope; said wings being planar units with a leading and trailing edge, the width of the wings from their leading edges to their trailing edges being substantially less than the length of the envelope with airfoil portions fitted between the leading and trailing edges of the wing: the top and bottom of the wings are mirror images of one another; in which forward motion of the vehicle is obtainable without trust through alternate diving and climbing motion.

    Abstract translation: 一种空中飞行器包括一个细长的外壳，其中至少有一个用于保持比空气气体轻的第一隔间和至少一个用于保持大气空气的第二隔室，并且所述至少一个第二隔室具有入口和出口以及至少一对 的翼从信封横向延伸; 所述翼是具有前缘和后缘的平面单元，翼从其前缘到其后缘的宽度基本上小于具有机翼部分装配在翼的前缘和后缘之间的封套的长度：顶部 翅膀的底部是彼此的镜像; 其中车辆的向前运动通过交替的潜水和爬坡运动而不被信任地获得。

    SYSTEM FOR PROVIDING A RAPIDLY ELEVATED AEROSTAT PLATFORM
    7.
    发明申请
    SYSTEM FOR PROVIDING A RAPIDLY ELEVATED AEROSTAT PLATFORM 审中-公开
    提供快速高空作战平台的系统

    公开(公告)号：US20120181380A1

    公开(公告)日：2012-07-19

    申请号：US13009207

    申请日：2011-01-19

    Applicant: Peter K. Van Staagen ,  William Douglas McDaniel ,  James H. Boschma, JR.

    Inventor： Peter K. Van Staagen ,  William Douglas McDaniel ,  James H. Boschma, JR.

    IPC: B64B1/50 ,  B64B1/40

    CPC classification number: B64B1/50 ,  B64B1/58 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/123 ,  B64C2201/201 ,  B64C2201/208 ,  B64F1/14

    Abstract: A system and method for deploying a payload with an aerostat uses a mobile transporter for moving the system to a deployment site. Structurally, the system includes a base unit with a rotation head mounted thereon. An envelope container for holding a deflated aerostat is mounted on the rotation head and a rotation of the container on the rotation head positions the aerostat for optimal compliance with the existing wind condition. Also included in the system is an inflator that is mounted on the base unit to inflate the aerostat with a Helium gas. And, the system includes a tether control unit for maintaining a connection with the aerostat during its deployment, in-flight use, and recovery. Preferably, a deployment computer is used for a coordinated control of the rotation head, inflator and tether.

    Abstract translation: 用空气净化器部署有效载荷的系统和方法使用移动运输装置将系统移动到部署现场。 在结构上，该系统包括其上安装有旋转头的基座单元。 用于保持放气式放气器的信封容器安装在旋转头上，并且旋转头上的容器的旋转定位了空气调节器，以最佳地符合现有的风况。 还包括在系统中的是充气机，其安装在基座单元上以用氦气对空气净化器进行充气。 而且，该系统包括一个系绳控制单元，用于在其部署，飞行中使用和恢复期间维持与浮空器的连接。 优选地，部署计算机用于旋转头，充气机和系绳的协调控制。

    Airship and method of operation
    9.
    发明授权
    Airship and method of operation 失效
    飞艇及作战方法

    公开(公告)号：US07055777B2

    公开(公告)日：2006-06-06

    申请号：US10178345

    申请日：2002-06-25

    Applicant: Hokan S. Colting

    Inventor： Hokan S. Colting

    IPC: B64B1/02 ,  B64B1/24

    CPC classification number: B64B1/34 ,  B64B1/02 ,  B64B1/32 ,  B64C21/02 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  Y02T50/166

    Abstract: An airship has a generally spherical shape and has an internal envelope for containing a lifting gas such as Helium or Hydrogen. The airship has a propulsion and control system that permits it to be flown to a desired loitering location, and to be maintained in that location for a period of time. In one embodiment the airship may achieve neutral buoyancy when the internal envelope is as little as 7% full of lifting gas, and may have a service ceiling of about 60,000 ft. The airship has an equipment module that can include either communications equipment, or monitoring equipment, or both. The airship can be remotely controlled from a ground station. The airship has a solar cell array and electric motors of the propulsion and control system are driven by power obtained from the array. The airship also has an auxiliary power unit that can be used to drive the electric motors. The airship can have a pusher propeller that assists in driving the airship and also moves the point of flow separation of the spherical airship further aft. In one embodiment the airship can be refuelled at altitude to permit extended loitering.

    Abstract translation: 飞艇具有大致球形并且具有用于容纳诸如氦气或氢气的提升气体的内部信封。 飞艇有一个推进和控制系统，允许飞行到所需的游荡地点，并在该地点保持一段时间。 在一个实施例中，当内部信封充满提升气体的时间少至7％时，飞艇可以达到中性浮力，并且可以具有大约6万英尺的服务天花板。飞艇具有可以包括通信设备或监视的设备模块 设备，或两者兼而有之。 飞艇可以从地面站遥控。 飞艇具有太阳能电池阵列，推进和控制系统的电动机由阵列获得的功率驱动。 飞艇还具有可用于驱动电动机的辅助动力单元。 飞艇可以有一个推动螺旋桨，有助于驾驶飞艇，还可以使球形飞艇进一步向后流动。 在一个实施例中，飞艇可以在高度加油以允许延长的游荡。

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