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    Ducted fan air vehicle with deployable wings
    201.
    发明公开
    Ducted fan air vehicle with deployable wings 审中-公开
    Mantelgebläse-Luftfahrzeug mit ausfahrbarenFlügeln

    公开(公告)号：EP1988014A2

    公开(公告)日：2008-11-05

    申请号：EP08155550.0

    申请日：2008-05-01

    Applicant: Honeywell International Inc.

    Inventor： Colclough, John C.

    IPC: B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/02

    CPC classification number: B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/162 ,  Y02T50/14

    Abstract: A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward fliglit operation without significantly impacting hover stability. One or more retractable wings (301) are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be detachable.

    Abstract translation: 公开了一种管道式风扇空气动力车辆和操作方法，用于获得空气动力提升和前进光束操作的效率，而不会显着影响悬停稳定性。 一个或多个伸缩翼（301）被包括在管道式风扇空气车辆上，并且在向前飞行期间展开以提供空气动力提升。 当车辆悬停时，翼或翼缩回，以减少机翼对风中稳定性的影响。 每个翼可以在缩回时符合车辆的曲率或轮廓，并且可以构造在一个或多个翼部中。 机翼或机翼可以自动或根据操作员的指令进行展开和撤回。 每个翼和相关部件可以集成到车辆中或者可以是可拆卸的。

    Autonomous Launch Pad for Micro Air Vehicles
    202.
    发明公开
    Autonomous Launch Pad for Micro Air Vehicles 有权
    Autonome StartrampefürMikroflugzeuge

    公开(公告)号：EP1767453A1

    公开(公告)日：2007-03-28

    申请号：EP06121033.2

    申请日：2006-09-21

    Applicant: Honeywell International Inc.

    Inventor： Horak, Dan T.

    IPC: B64C39/02 ,  B64F1/04 ,  A63H27/14

    CPC classification number: B64C39/028 ,  A63H27/14 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/182 ,  B64F1/04

    Abstract: Autonomous micro air vehicles (102) surveillance systems are provided. A MAV system of one embodiment includes an MAV and a launch pad (120). The MAV has an engine (103) that is adapted to power the MAV. The launch pad has a starter (128) that is adapted to start the engine in the MAV when the MAV is resting on a launching surface (142) of the launch pad. The launch pad further has a battery (126) to power the starter.

    Abstract translation: 提供自动微型飞行器（102）监视系统。 一个实施例的MAV系统包括MAV和发射台（120）。 MAV具有适于为MAV供电的发动机（103）。 所述发射台具有起动器（128），当所述MAV处于所述发射台的发射表面（142）上时，所述起动器适于在所述MAV中启动所述发动机。 发射台还具有用于为起动器供电的电池（126）。

    A snubber assembly for an unmanned aerial vehicle
    208.
    发明公开
    A snubber assembly for an unmanned aerial vehicle 失效
    用于无人驾驶飞行器阻尼器轴承装置

    公开(公告)号：EP0861778A1

    公开(公告)日：1998-09-02

    申请号：EP97118257.1

    申请日：1993-06-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： CYCON, James P. ,  HUNTER, David H., ,  KRAUSS, Albert T.,

    IPC: B64C27/33

    CPC classification number: B64C27/10 ,  B64C27/14 ,  B64C27/20 ,  B64C27/33 ,  B64C27/605 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  F02B2075/025 ,  F16D3/06 ,  F16D3/185

    Abstract: A snubber assembly (230) for an unmanned aerial vehicle (10) including a rotor assembly (100) having ducted counter-rotating rotors (200, 202), the rotor assembly (100) including a rotor shaft (128R or 130R), a torque tube (270) having an inboard end, and a flexbeam (260) having an inboard end (262), comprising:

    a bracket (238) configured to be secured in combination with the inboard end of the torque tube (270);
    a spherical bearing (232) secured in combination with said bracket (238); and
    a rotor hub (204), configured for securement in interlocked, engaged combination with the rotor shaft (128R or 130R), having a plurality of radially extending arms (214), each of said radially extending arms (214) including means for securing the inboard end (262) of the flexbeam (260) in combination with the rotor hub (204) and means for rotatably mounting said spherical bearing (232), bracket (238) combination internally in said rotor hub (204);
    said internally rotatably mounted spherical bearing (232), bracket (238) combination being positioned inboard of said outboard end of said radially extending arm (214) and inboard of the inboard end (262) of the flexbeam (260);
       characterized in that
    said securing means of each said radially extending arm (214) comprises a clevis (220); and
    said rotatably mounting means for each said radially extending arm (214) comprises an inboard internal bulkhead (223), an outboard internal bulkhead (224), said inboard and outboard internal bulkheads (223, 224) in combination defining a bearing cavity (225) and an inboard cavity (226), and a bearing bolt (234);
    said bearing bolt (234) being disposed in combination with said outboard internal bulkhead (224), said spherical bearing (232), and said inboard internal bulkhead (223) for rotatably mounting said spherical bearing (232), bracket (238) combination in said bearing cavity (225).

    AN UNMANNED VTOL GROUND SURVEILLANCE VEHICLE
    209.
    发明授权
    AN UNMANNED VTOL GROUND SURVEILLANCE VEHICLE 失效
    无人垂直起降飞行大队土壤监测

    公开(公告)号：EP0758972B1

    公开(公告)日：1998-03-25

    申请号：EP95919737.7

    申请日：1995-04-27

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： MCGONIGLE, Kevin, P. ,  FERRARO, John ,  CYCON, James, P.

    IPC: B64C39/02 ,  B64C27/20

    CPC classification number: B64D47/08 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162

    Abstract: An unmanned arerial vehicle (UAV) has a toroidal fuselage and a rotor assembly having a pair of counter-rotating rotors secured in fixed coaxial combination with the toroidal fuselage to provide a vertical takeoff and landing (VTOL) capability for the UAV. One embodiment of the VTOL UAV is especially configured for ground surveillance missions by the inclusion of an externally mounted, remotely controllable stowable sensor subsystem (250) that provides an azimuthal scanning capability and a predetermined elevation/depression scanning capability to accomplish the ground surveillance mission and a foldable landing gear subsystem (300) to facilitate landing of the VTOL UAV at unprepared ground surveillance sites. The foldable landing gear subsystem includes a plurality of legs (302), one end of each leg being detachably secured in combination with the toroidal fuselage, a foot that includes a pad member (312) pivotally attached to the other end of each leg, and a non-structural hinge secured to each leg and the toroidal fuselage. The non-structural hinges (306) provide the capability to fold the landing gear subsystem to a stowage configuration wherein each leg, pivoting foot combination is folded within the envelope of the toroidal fuselage.

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