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    SPLIT CHORD DEPLOYABLE WING
    123.
    发明申请
    SPLIT CHORD DEPLOYABLE WING 审中-公开

    公开(公告)号：US20170336184A1

    公开(公告)日：2017-11-23

    申请号：US15161261

    申请日：2016-05-22

    Applicant: Raytheon Company

    Inventor： Paul A. Merems

    IPC: F42B10/14 ,  F42B15/01 ,  B64C3/56 ,  B64C39/02

    CPC classification number: F42B10/14 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/102 ,  F42B15/01

    Abstract: A split-chord deployable wing for aerial vehicles such as missiles, UAVs, MALDs and SDBs that require both longer wing span and increased chord length. Such split-chord deployable wings must address unique problems such as synchronized deployment and integrity of the deployed wing to both vertical and sheer loads. Each wing comprises a pair of wing sections stowed fore and aft along the fuselage. Complementary gear teeth synchronize deployment of the wing sections. A deployment mechanism synchronizes deployment of the wings. Complementary tongue and groove surface portions of the wing sections progressive engage as the wing sections pivot away from the fuselage. The surface portions are segmented so that tongue segments are nested within complementary groove segments to provide both vertical and sheer stability.

    Aircraft With Polygonal Wings
    128.
    发明申请
    Aircraft With Polygonal Wings 审中-公开

    公开(公告)号：US20170106977A1

    公开(公告)日：2017-04-20

    申请号：US15317005

    申请日：2015-06-10

    Applicant: DANIELSON AIRCRAFT SYSTEMS

    Inventor： Frédéric Hubschwerlen

    IPC: B64C39/06 ,  B64C1/30 ,  B64C9/14 ,  B64C3/56 ,  B64C39/02 ,  B64C3/16

    CPC classification number: B64C39/068 ,  B64C1/30 ,  B64C3/16 ,  B64C3/56 ,  B64C9/14 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/127

    Abstract: An aerial vehicle including at least two side fuselages interconnected via a wing, at least one propulsion mechanism, and two side wings extending from respective ones of the side fuselages. Each side wing has a section as seen from the front that is in the shape of a polygon having at least four sides. The ratio between the height of the side wings and the wingspan of the aerial vehicle is between 0.15 to 0.25. Each side wing has a first wing portion extending in the same plane as the wing, a second wing portion extending vertically above the first wing portion and inclined rearwards and upwards, a third wing portion extending parallel to the first wing portion and extending rearwards while forming an angle with the front plane of the aerial vehicle, and a fourth wing portion extending vertically down to the rear end of the side fuselage.

    Stowable and deployable unmanned aerial vehicle
    130.
    发明授权
    Stowable and deployable unmanned aerial vehicle 有权
    可存放和可部署的无人机

    公开(公告)号：US09522725B2

    公开(公告)日：2016-12-20

    申请号：US14179697

    申请日：2014-02-13

    Applicant: Northrop Grumman Systems Corporation

    Inventor： Christopher N. Torre

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

    CPC classification number: B64C3/56 ,  B64C1/30 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/102 ,  B64C2201/201

    Abstract: An unmanned aerial vehicle (UAV) can be deployed from a small stowed package for flight and stowed back into the package after the flight is complete is disclosed. The UAV is retracted to a volume that is less than half of it's fully deployed volume. This allows the UAV to be transported to any desired field position on a truck or other convenient transportation. The UAV may also be launched from a ship deck. In a further aspect, the flexible deployment of the UAV will allow a single UAV to be used in place of multiple types of UAVs.

    Abstract translation: 飞行完成后，可以从一个小型收起的包装中部署无人驾驶飞行器（UAV）并将其收回包装。 UAV被缩回到小于其完全部署卷的一半的卷。 这样可以将无人机运送到卡车上的任何所需的现场位置或其他方便的交通工具。 无人机也可以从船甲板上发射。 在另一方面，UAV的灵活部署将允许使用单个UAV来代替多种类型的UAV。

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