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    Flyer assembly
    232.
    发明授权
    Flyer assembly 有权
    传单装配

    公开(公告)号：US06392213B1

    公开(公告)日：2002-05-21

    申请号：US09690000

    申请日：2000-10-12

    Applicant: Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland, Jr.

    Inventor： Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland, Jr.

    IPC: B64C351

    CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

    Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load and high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.

    Abstract translation: 飞行器组件适用于从具有沿弹道壳轴线延伸的中心空隙区域的炮弹发射，转移和展开。 传单组件包括可喷射的护罩和传单​​。 护罩沿护罩轴线延伸，并且可定位在中心空隙区域内，护罩轴线基本上平行于外壳轴线。 飞行器适于在处于第一状态时承受沿飞行器轴的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单可定位在护罩内，飞翼轴线平行于护罩轴线和外壳轴线。 传单包括围绕飞翼轴设置的主体部件和安装到主体部件的可折叠翼组件。 翼组件可配置成折叠状态，其特征在于当传单处于第一状态时由多个嵌套翼片段组成。 机翼组件可配置为展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件适于从诸如炮兵炮的弹道传送系统发射，并且因此可以快速到达目标，而不会消耗存储在飞行物内的系统能量。 在发射期间，传单联接到护罩上，以便在飞行物沿着由发射引起的飞翼轴的加速期间，使传单的一部分保持张紧。 飞行器组件适于承受大炮发射的高负载和高温环境，并且可以容忍约16,000g的安装载荷。

    Variable geometry RPV
    233.
    发明授权
    Variable geometry RPV 失效
    可变几何RPV

    公开(公告)号：US5118052A

    公开(公告)日：1992-06-02

    申请号：US115333

    申请日：1987-11-02

    Applicant: Albert Alvarez Calderon F

    Inventor： Albert Alvarez Calderon F

    IPC: B64C1/30 ,  B64C3/56 ,  B64C39/02

    CPC classification number: B64C3/56 ,  B64C1/30 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  Y02T50/145

    Abstract: A Variable Geometry Remotely Piloted Vehicle (VG-RPV) has a main fuselage portion supporting at one end main wing panels and a forward fuselage portion. In the stowed position, the main wings and forward fuselage portion are laterally adjacent the main fuselage. This provides compact volume of small dimensions for stowage inside a canister. When deployed for flight, the wings are inclined at a large angle to the main fuselage, and a fuselage forebody is positioned upstream of the main fuselage, to establish a vehicle center of gravity adjacent to the deployed wings. Folding panels are mounted on chordwise hinges at the tip of the main wing panels. These panels overlap the main wing panels in the stowed configuration, inside the canister or on deck, and extend the span and area of the deployed main panels in the flight configuration. In-flight deployment is provided to launch the VG-RPV with a reduced span and area with the folding panels placed under the main panels. After launch, but prior to slow speed flight, aerodynamic in-flight deployment of the folding panels is aided with trailing tabs on the folding panels.

    Abstract translation: 可变几何遥控牵引车（VG-RPV）具有主机架主体部分，主机翼部分和前机身部分支撑。 在收起位置上，主翼和前机身部分横向邻近主机身。 这提供了小尺寸的小尺寸用于在罐内的装载。 当部署为飞行时，机翼与主机身倾斜大角度，并且机身前体位于主机身的上游，以建立与展开机翼相邻的车辆重心。 折叠板安装在主翼板顶端的弦向铰链上。 这些面板与收起的结构中的主翼板重叠，在罐内或甲板上，并且在飞行配置中延伸部署的主面板的跨度和面积。 提供飞行部署以发射具有减小的跨度和面积的VG-RPV，折叠面板放置在主面板下方。 在发射后，但在慢速飞行之前，折叠板的空气动力学飞行中部署有助于折叠板上的拖尾。

    DRONE BOX
    234.
    发明申请
    DRONE BOX 审中-公开

    公开(公告)号：WO2017029611A1

    公开(公告)日：2017-02-23

    申请号：PCT/IB2016/054916

    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: H02J7/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/148 ,  B64C2201/201 ,  E04H6/04 ,  E04H6/44

    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 land- ing position on the UAV landing platform.

    Abstract translation: 该应用提供了无人机（UAV）的存储单元。 存储单元包括容器，UAV着陆平台和容器。 该容器用于封闭无人机。 该容器位于UAV着陆平台的上方，并且其包括至少一个倾斜表面，用于将无人机的着陆UAV引导到无人机登陆平台上的预定无人机定位位置。

    UNMANNED AERIAL VEHICLE MANAGEMENT
    235.
    发明申请
    UNMANNED AERIAL VEHICLE MANAGEMENT 审中-公开
    不定期的空中客车管理

    公开(公告)号：WO2016205415A1

    公开(公告)日：2016-12-22

    申请号：PCT/US2016/037694

    申请日：2016-06-15

    Applicant: IMAGEKEEPER LLC

    Inventor： SPEASL, Jerry ,  PATTERSON, Mike ,  ROBERTS, Mark

    IPC: B65F9/00 ,  G01C23/00 ,  B65G67/00

    CPC classification number: G08G5/0034 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/08 ,  B64C2201/082 ,  B64C2201/121 ,  B64C2201/126 ,  B64C2201/128 ,  B64C2201/145 ,  B64C2201/20 ,  B64C2201/201 ,  B64C2201/205 ,  B64C2201/206 ,  B64C2201/208 ,  B64F1/222 ,  G06Q10/08 ,  G08G5/0069 ,  G08G5/0082 ,  G08G5/0091

    Abstract: A base module may be used to receive and house one or more unmanned aerial vehicles (UAVs) via one or more cavities. The base module receives commands from a manager device and identifies a flight plan that allows a UAV to execute the received commands. The base module transfers the flight plan to the UAV and frees the UAV. Once the UAV returns, the base module once again receives it. The base module then receives sensor data from the UAV from one or more sensors onboard the UAV, and optionally receives additional information describing its flight and identifying success or failure of the flight plan. The base module transmits the sensor data and optionally the additional information to a storage medium locally or remotely accessible by the manager device.

    Abstract translation: 基座模块可以用于经由一个或多个空腔接收和容纳一个或多个无人机（UAV）。 基本模块从管理器设备接收命令，并识别允许UAV执行接收到的命令的飞行计划。 基地模块将飞行计划转移到无人机，并释放无人机。 一旦UAV返回，基本模块再次接收它。 然后，基本模块从UAV上的一个或多个传感器接收来自UAV的传感器数据，并且可选地接收描述其飞行并识别飞行计划的成功或失败的附加信息。 基本模块将传感器数据和可选的附加信息传输到本地或由管理器设备远程访问的存储介质。

    SYSTEMS AND METHODS FOR FOLDABLE ARMS
    236.
    发明申请
    SYSTEMS AND METHODS FOR FOLDABLE ARMS 审中-公开
    可折叠系统的系统和方法

    公开(公告)号：WO2016192021A1

    公开(公告)日：2016-12-08

    申请号：PCT/CN2015/080528

    申请日：2015-06-01

    Applicant: SZ DJI TECHNOLOGY CO., LTD.

    Inventor： WU, Xumin ,  WU, Xiaolong ,  LEE, Sungki ,  AO, Jiyuan ,  FENG, Zhuang

    IPC: B64C27/08

    CPC classification number: B64C39/024 ,  B64C1/30 ,  B64C27/08 ,  B64C27/12 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/12 ,  B64C2201/201 ,  B64D47/08

    Abstract: Systems and methods are provided for transformation of a UAV from an extended state to a compacted state. The UAV can be transported in the compacted state. The UAV can comprise one or more segmented arms that can be folded to reduce the volume of the UAV. The segmented arms can be sealed to prevent ambient air, dirt, and or water vapor from entering the segmented arm. The UAV can comprise a cooling and air filtering system on-board the UAV.

    Abstract translation: 提供了将UAV从扩展状态转换为压缩状态的系统和方法。 无人机可以在压实状态下运输。 UAV可以包括一个或多个分段的臂，其可被折叠以减小无人机的体积。 分段臂可以被密封以防止环境空气，污垢和/或水蒸气进入分段臂。 无人机可以包括无人机上的冷却和空气过滤系统。

    UNMANNED AERIAL VEHICLE AND METHOD OF CONTROLLING THE SAME
    237.
    发明申请
    UNMANNED AERIAL VEHICLE AND METHOD OF CONTROLLING THE SAME 审中-公开
    无人驾驶的航空器及其控制方法

    公开(公告)号：WO2016148368A1

    公开(公告)日：2016-09-22

    申请号：PCT/KR2015/011438

    申请日：2015-10-28

    Applicant: LG ELECTRONICS INC.

    Inventor： CHO, Taehoon ,  SHIN, Choonghwan

    IPC: B64F1/00 ,  B64C39/02 ,  B64D47/08

    CPC classification number: B64C39/024 ,  B60Q1/52 ,  B60Q7/00 ,  B60Q2400/50 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/201 ,  B64C2201/208 ,  G05D1/0094 ,  G08G1/04 ,  G08G1/0955 ,  G08G1/162 ,  G08G1/205 ,  G08G7/00

    Abstract: An unmanned aerial vehicle according to the present invention includes a housing mounted on a vehicle and having an inner space, the housing provided with a launching unit, an unmanned aerial vehicle accommodated in the housing and configured to be launched from the housing when a driving state of the vehicle meets a preset condition, wing units mounted to the unmanned aerial vehicle and configured to allow the flight of the unmanned aerial vehicle in response to the launch from the housing, an output unit disposed on the unmanned aerial vehicle, and a controller configured to control the wing units to move the unmanned aerial vehicle to a position set based on information related to the driving state when the unmanned aerial vehicle is launched, and control the output unit to output warning information related to the driving state.

    Abstract translation: 根据本发明的无人驾驶飞行器包括安装在车辆上并具有内部空间的壳体，壳体设置有发射单元，容纳在壳体中的被构造成在驾驶状态下从壳体发射的无人驾驶飞行器 所述车辆单元安装到所述无人驾驶飞行器并且被配置为允许所述无人驾驶飞行器响应于从所述壳体的发射而被飞行，设置在所述无人驾驶飞行器上的输出单元以及被配置为 根据与无人驾驶飞行器的驾驶状态相关的信息，控制机翼单元将无人机移动到设定位置，并且控制输出单元输出与驾驶状态有关的警告信息。

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