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    AN UNMANNED AERIAL VEHICLE LAUNCHING AND LANDING SYSTEM
    81.
    发明公开
    AN UNMANNED AERIAL VEHICLE LAUNCHING AND LANDING SYSTEM 有权
    START和着陆系统的无人机

    公开(公告)号：EP2046644A1

    公开(公告)日：2009-04-15

    申请号：EP07736228.3

    申请日：2007-04-18

    Applicant: ELBIT SYSTEMS LTD.

    Inventor： KARIV, Amnon

    IPC: B64F1/02 ,  B64F1/04 ,  B64F1/08

    CPC classification number: B64F1/06 ,  B64C2201/084 ,  B64C2201/182 ,  B64F1/02

    Abstract: A system for landing UAV's comprising a slingshot structure (25) that includes a central arm (26) and an axis means (45) installed along the central arm of the structure and wherein it enables the central arm to move around it in addition, the system comprises base means (50) connecting the axis means to a platform (20) at which the system is installable. The system also include a controlled pulling and braking means (55) that connects between lower end of the central arm of the structure and the platform upon which the system is installable and an assembly (35), essentially formed as a substantially 'Y' shape part that is installable unto the top end of the central arm of the structure and a stretchable elastic means (30) installed in a stretched manner at a gap formed between the two arms of the assembly and set to connect with a landing UAV(15). At the landing phase, the controlled pulling and braking means of the system, essentially brakes the motion of the central arm of the structure that is propelled to revolve around the system's axis means, from a time that the UAV forms contact with the elastic means and with it propels the structure to move around the axis means.

    THRUST VECTORING FREE WING AIRCRAFT
    83.
    发明授权
    THRUST VECTORING FREE WING AIRCRAFT 失效
    带飞翼和推力反向PLANE

    公开(公告)号：EP0629164B1

    公开(公告)日：1999-05-26

    申请号：EP93907455.5

    申请日：1993-03-12

    Applicant: SCHMITTLE, Hugh J.

    Inventor： SCHMITTLE, Hugh J.

    IPC: B64C3/38

    CPC classification number: B64C39/024 ,  B64C3/385 ,  B64C29/0033 ,  B64C29/02 ,  B64C39/04 ,  B64C2201/044 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64D2201/00

    Abstract: The VTOL aircraft (10) includes a free wing (16) having wings on opposite sides of the fuselage (12) connected to one another for joint free rotation and for differential pitch settings under pilot, computer or remote control. On vertical launch, pitch, yaw and roll control is effected by the elevators (26), rudder (24) and the differential pitch settings of the wings, respectively. At launch, the elevator (26) pitches the fuselage (12) nose downwardly to alter the thrust vector and provide horizontal speed to the aircraft whereby the free wing (16) rotates relative to the fuselage (12) into a generally horizontal orientation to provide lift during horizontal flight. Transition from horizontal to vertical flight is achieved by the reverse process and the aircraft may be gently recovered in or on a resilient surface such as a net (66).

    TECHNIQUES FOR EMPLACING AN UNMANNED AERIAL VEHICLE LAUNCHER PRIOR TO LAUNCHING AN UNMANNED AERIAL VEHICLE
    85.
    发明申请
    TECHNIQUES FOR EMPLACING AN UNMANNED AERIAL VEHICLE LAUNCHER PRIOR TO LAUNCHING AN UNMANNED AERIAL VEHICLE 有权
    在开通无人驾驶的车辆之前采用无人驾驶的机动车前进的技术

    公开(公告)号：US20160137313A1

    公开(公告)日：2016-05-19

    申请号：US14225751

    申请日：2014-03-26

    Applicant: AAI CORPORATION

    Inventor： Jason J. Wallace ,  Paul Nesline ,  Richard C. Uskert ,  Samuel Padilla

    IPC: B64F1/06 ,  B64C39/02

    CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/084

    Abstract: A technique is directed to launching an unmanned aerial vehicle (UAV). The technique involves positioning a UAV launcher over a ground location. The technique further involves installing, after the UAV launcher is positioned over the ground location and prior to launching the UAV, an anchor into the ground location to anchor the UAV launcher to the ground location. The technique further involves operating, after the UAV launcher is anchored to the ground location, the UAV launcher to impart launching force onto the UAV to launch the UAV, the anchor holding the UAV launcher substantially in place at the ground location to minimize energy loss as the UAV launcher imparts launching force onto the UAV. In some arrangements, the UAV launcher is capable of pivoting while remaining anchored between launches to accommodate changes in wind direction while maintaining substantial connection to the ground location for enhanced consistency and performance.

    Abstract translation: 一种技术旨在发射无人机（UAV）。 该技术涉及将UAV发射器定位在地面位置。 该技术还涉及在UAV发射器定位在地面位置之后并且在发射无人机之前安装一个锚点到地面位置以将UAV发射器锚定到地面位置。 该技术进一步涉及在UAV发射器固定在地面之后，UAV发射器向无人机发射发射力以发射无人机，该主机将无人机发射器固定在地面位置，以将能量损失最小化 无人机发射机向无人机发射启动力。 在某些安排中，无人机的发射器能够枢转，同时保持锚固在发射之间，以适应风向的变化，同时保持与地面位置的实质连接，以提高一致性和性能。

    Delta Wing Unmanned Aerial Vehicle (UAV) and Method of Manufacture of the Same
    88.
    发明申请
    Delta Wing Unmanned Aerial Vehicle (UAV) and Method of Manufacture of the Same 审中-公开
    三角翼无人机（UAV）及其制造方法

    公开(公告)号：US20140197280A1

    公开(公告)日：2014-07-17

    申请号：US13572877

    申请日：2012-08-13

    Applicant: Donald Earl Smith ,  Mark D. Herres

    Inventor： Donald Earl Smith ,  Mark D. Herres

    IPC: B64C3/10 ,  B64D47/08 ,  B64C39/02

    CPC classification number: B64C3/10 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/084 ,  B64C2201/182 ,  B64D47/08 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06 ,  G06K7/10366

    Abstract: This disclosure pertains to the field of small-unmanned aerial vehicles (UAVs). The delta wing vehicle consists of an isosceles triangular shaped lifting body milled from Styrofoam. The longitudinal axis is approximately 65% of the lateral axis. The horizontal wing projections, or tiplets, are attached to the main lifting body at an approximately 10 degree upward angle from horizontal, have a 30 degree sweep back leading edge, and each one comprises 5% of the total wing area. The airfoil is a rhomboid or diamond shape. The chord is swept back at a 45-degree angle from the longitudinal centerline. The airfoil is symmetrical about the longitudinal center. The aircraft is controlled by a set of combined elevator/aileron surfaces (elevons) at the rear as well as a vertical stabilizer/rudder combination. This resulting lightweight UAV can make flat (unbanked) unbanked turns, fly in high winds, and has superior flexibility in payload capability.

    Abstract translation: 本公开涉及小型无人机（UAV）领域。 三角翼车由聚苯乙烯泡沫塑料研磨的等腰三角形提升体组成。 纵向轴线约为横轴的65％。 水平机翼突出物或者台阶以与水平方向大约10度的角度附接到主提升体，具有30度的倒退前缘，并且每个包括总机翼面积的5％。 翼型是菱形或菱形。 弦从纵向中心线以45度角扫掠。 翼型件关于纵向中心对称。 飞机由后面的一组组合式电梯/副翼表面（电梯）以及垂直稳定器/方向舵组合控制。 这种轻型无人机可以使平坦（无库存）的无库存转弯，高风飞行，并且在有效载荷能力方面具有卓越的灵活性。

    SELF-SUSTAINING DRONE AIRCRAFT FREIGHT AND OBSERVATION SYSTEM
    89.
    发明申请
    SELF-SUSTAINING DRONE AIRCRAFT FREIGHT AND OBSERVATION SYSTEM 审中-公开
    自主持续飞机飞行和观察系统

    公开(公告)号：US20140110527A1

    公开(公告)日：2014-04-24

    申请号：US14126846

    申请日：2011-06-17

    Applicant: Robert L. Sing

    Inventor： Robert L. Sing

    IPC: B64D9/00

    CPC classification number: B64D9/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/145 ,  B64C2201/187

    Abstract: The self-sustaining drone aircraft freight and observation system (5) comprises a fleet of jet-powered drone aircraft (10) designed to carry freight (12) only. The drones (10) operate from a separate airfield in outlying areas to decrease land costs and to avoid disturbing residential and business areas. Navigation is automated using guidance from GPS satellites (16), and the aircraft (10) can be assisted by a hydraulic catapult (13) during takeoff to reduce the fuel payload. The observation component (18) includes sensors that can observe weather conditions and emergency signals from boats, ships and other sources. The system (5) may include a large-scale energy production center and multi-acre vegetable, herb and flower production center (26). The energy production center includes solar panels (30), fuel cells (38), and batteries (44). Thus, the system (5) does not need to be connected to the public utility electrical grid.

    Abstract translation: 自维持无人机飞机货运观察系统（5）包括一个仅用于运输（12）的喷气式无人机（10架）舰队。 无人机（10）从外围地区的独立机场运营，以降低土地成本，避免住宅和商业区域的不安。 导航使用GPS卫星（16）的指导进行自动化，飞机（10）可在起飞期间由液压弹射器（13）辅助以减少燃料有效载荷。 观察部件（18）包括能够观察船舶，船舶和其他来源的天气状况和紧急信号的传感器。 系统（5）可以包括一个大型能源生产中心和多英亩蔬菜，草药花卉生产中心（26）。 能源生产中心包括太阳能电池板（30），燃料电池（38）和电池（44）。 因此，系统（5）不需要连接到公共事业电网。

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