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    LIGHTWEIGHT AIR VEHICLE AND PNEUMATIC LAUNCHER
    11.
    发明申请
    LIGHTWEIGHT AIR VEHICLE AND PNEUMATIC LAUNCHER 审中-公开
    轻型气动车和气动式发射器

    公开(公告)号：WO2005023642A3

    公开(公告)日：2005-11-10

    申请号：PCT/US2004004720

    申请日：2004-02-19

    Applicant: AAI CORP ,  MILLER STEPHEN W ,  VELAZQUEZ MATTHEW T

    Inventor： MILLER STEPHEN W ,  VELAZQUEZ MATTHEW T

    IPC: B64B20060101 ,  B64B1/00 ,  B64C3/56 ,  B64C39/02 ,  B64F1/04 ,  B64F1/06

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06

    Abstract: A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

    Abstract translation: 提供了一种便携式无人飞行器和发射器系统，其包括具有压力管的可折叠无人驾驶飞行器; 用于容纳发射气体的发射气体储存器; 发射管，可操作地连接到发射气体储存器并且具有定位在飞行器的压力管中的自由端; 位于发射管内的自由活塞; 和一个自由活塞止动件，以防止自由活塞离开发射管。 发射气体储存器中的发射气体的第一部分被释放到发射管中并且迫使自由活塞从初始位置移动到自由活塞通过自由活塞止挡而停止的终点位置。

    OBSTACLE AVOIDANCE SYSTEM FOR STABILIZED AERIAL VEHICLE AND METHOD OF CONTROLLING SAME
    12.
    发明公开
    OBSTACLE AVOIDANCE SYSTEM FOR STABILIZED AERIAL VEHICLE AND METHOD OF CONTROLLING SAME 审中-公开
    维多利亚州立大学维吾尔自治区维吾尔自治区

    公开(公告)号：EP3170056A1

    公开(公告)日：2017-05-24

    申请号：EP14897852.1

    申请日：2014-07-16

    Applicant: Her Majesty The Queen in Right of Canada as represented by The Minister of National Defence

    Inventor： WONG, Franklin ,  BILODEAU, Pierre Richard

    IPC: G05D1/10 ,  B64C19/00 ,  B64C39/02

    CPC classification number: B64C39/024 ,  B64C19/00 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/203 ,  G05B6/02 ,  G05D1/0088 ,  G05D1/042 ,  G05D1/0816 ,  G05D1/101 ,  G05D1/102 ,  G08G5/0073 ,  G08G5/045

    Abstract: An obstacle avoidance system for a stabilized aerial vehicle and a method of controlling same are provided. Using low angular resolution obstacle proximity data, such as from low angular resolution obstacle detection sensors, when a determination is made that an operator command to a vehicle propulsion system will result in a collision, the system overrides the operator command and substitutes an avoidance speed command and avoidance heading, while maintaining operator situational awareness, in a manner that is transparent to the operator. In an implementation, examination of objects requires the obstacle avoidance system to allow the vehicle to get close to obstacles. A human-portable aerial vehicle according to an implementation can be used for building surveillance, route inspection, surveillance of windows/hallways/rooftops, power distribution towers, pipelines, bridges, buildings or close examination of suspect objects.

    Abstract translation: 提供了一种用于稳定的飞行器的避障系统及其控制方法。 使用低角度分辨率障碍物近距离数据，例如来自低角度分辨率障碍物检测传感器，当确定对车辆推进系统的操作者命令将导致碰撞时，系统将覆盖操作员命令并代替避免速度命令 并以对运营商透明的方式维护运营商的态势感知，避免航向。 在实施中，物体的检查需要避障系统，使车辆靠近障碍物。 根据实施的人造便携式飞行器可用于建筑物的监视，路线检查，窗户/走廊/屋顶，配电塔，管道，桥梁，建筑物的监视或可疑物体的仔细检查。

    UAV KIT
    14.
    发明公开
    UAV KIT 有权
    KIT无人机（UAV）

    公开(公告)号：EP2691300A2

    公开(公告)日：2014-02-05

    申请号：EP12717216.1

    申请日：2012-03-26

    Applicant: Prox Dynamics AS

    Inventor： MUREN, Petter

    IPC: B64C39/02

    CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C39/028 ,  B64C2201/024 ,  B64C2201/127 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2203/00 ,  B64D47/08

    Abstract: The embodiments herein disclose a personal UAV kit for storing, preparing and remote control of micro UAVs. The UAV kit includes a base unit, a control unit and at least one UAV. The UAVs can typically be a winged aircraft with foldable wings or a helicopter with a two-bladed or foldable rotor. The base unit comprises UAV compartments for housing at least one UAV, a bay for storing the control unit, batteries and electronic components for charging, communication, control and processing and storing of data. In addition, the system includes an eye near display device for viewing system information and sensor data, typically live video, transmitted from the UAV.

    MORPHING AIRCRAFT
    18.
    发明申请
    MORPHING AIRCRAFT 审中-公开
    MORPHING飞机

    公开(公告)号：WO2010027801A3

    公开(公告)日：2010-05-27

    申请号：PCT/US2009054917

    申请日：2009-08-25

    Applicant: UNIV FLORIDA ,  LIND CHARLES RICHARD JR ,  GRANT DANIEL THURMOND ,  EATON DAVID

    Inventor： LIND CHARLES RICHARD JR ,  GRANT DANIEL THURMOND ,  EATON DAVID

    IPC: B64C39/02 ,  B25J5/00 ,  B64C3/56 ,  B64C13/20 ,  B64C27/22

    CPC classification number: B64C39/024 ,  B60F3/00 ,  B64C37/00 ,  B64C2001/0045 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/203

    Abstract: A morphing aircraft that is achieves multi- modality location and camouflage for payload emplacement The morphing aircraft includes a substantially cylindrical fuselage including a shape configured as a packaging container with a first end and a second end A set of wings is coupled to the fuselage The set of wings includes a first position where the set of wings is extended outwards from the fuselage and a second position where the set of wings is retracted inwards towards the fuselage A tail is coupled to the second end of the cylindrical fuselage The tail includes a first position where the tail is extended outward from the fuselage and a second position where the tail is retracted inward towards the fuselage A propeller is mounted to the first end of the fuselage An engine is mechanically coupled to the propeller The engine is enclosed within the fuselage and powers the propeller.

    Abstract translation: 实现多模式位置和伪装用于有效载荷的变形飞机变形飞机包括基本上圆柱形的机身，其包括被配置为具有第一端和第二端的包装容器的形状。一组翼结合到机身。该组 的翼部包括第一位置，其中所述一组翼从机身向外延伸，并且第二位置，其中该组翼向内朝向机身A缩回。尾部联接到圆柱形机身的第二端。尾部包括第一位置 其中尾部从机身向外延伸，而第二位置则尾部朝向机身向内缩进。螺旋桨安装在机身的第一端。发动机机械地联接到螺旋桨发动机被封闭在机身内并且动力 螺旋桨

    MORPHING AIRCRAFT
    19.
    发明申请
    MORPHING AIRCRAFT 审中-公开
    变形飞机

    公开(公告)号：WO2010027801A2

    公开(公告)日：2010-03-11

    申请号：PCT/US2009/054917

    申请日：2009-08-25

    Applicant: UNIVERSITY OF FLORIDA RESEARCH FOUNDATION, INC. ,  LIND, Charles, Richard, Jr. ,  GRANT, Daniel, Thurmond ,  EATON, David

    Inventor： LIND, Charles, Richard, Jr. ,  GRANT, Daniel, Thurmond ,  EATON, David

    IPC: B64C39/02 ,  B64C13/20 ,  B64C27/22 ,  B64C3/56 ,  B25J5/00

    CPC classification number: B64C39/024 ,  B60F3/00 ,  B64C37/00 ,  B64C2001/0045 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/203

    Abstract: A morphing aircraft that is achieves multi- modality location and camouflage for payload emplacement The morphing aircraft includes a substantially cylindrical fuselage including a shape configured as a packaging container with a first end and a second end A set of wings is coupled to the fuselage The set of wings includes a first position where the set of wings is extended outwards from the fuselage and a second position where the set of wings is retracted inwards towards the fuselage A tail is coupled to the second end of the cylindrical fuselage The tail includes a first position where the tail is extended outward from the fuselage and a second position where the tail is retracted inward towards the fuselage A propeller is mounted to the first end of the fuselage An engine is mechanically coupled to the propeller The engine is enclosed within the fuselage and powers the propeller.

    Abstract translation: 实现用于有效载荷安置的多模式位置和伪装的变形飞行器变体飞机包括基本上圆柱形的机身，该机身包括被配置为包装容器的形状，该包装容器具有第一端和第二端， 机翼被耦合到机身。该组机翼包括第一位置和第二位置，其中该组机翼从机身向外延伸，在第二位置该组机翼朝向机身A向内缩回。尾部耦合到机身的第二端 圆柱形机身尾部包括尾部从机身向外延伸的第一位置和尾部朝着机身向内缩回的第二位置。螺旋桨安装到机身的第一端。发动机机械地耦合到螺旋桨上。 发动机封闭在机身内并为螺旋桨提供动力。

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