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    Payload quick release for an aerial system
    141.
    发明公开
    Payload quick release for an aerial system 审中-公开
    Nutzlast-Schnellfreigabefürein Luftsystem

    公开(公告)号：EP2236416A2

    公开(公告)日：2010-10-06

    申请号：EP10151254.9

    申请日：2010-01-20

    Applicant: Honeywell International Inc.

    Inventor： Wong, Kimberly ,  Losinski, Armand

    IPC: B64C39/02 ,  B64D1/02 ,  F16B3/00

    CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/127 ,  B64D1/02 ,  F16B21/02

    Abstract: A payload quick release mechanism (100) for an unmanned aerial vehicle is affixed to a structure on the unmanned aerial vehicle, and allows for quick attachment and removal of a payload from the unmanned aerial vehicle. The attachment device comprises a body (110) with a perimeter and a plurality of arms (120) that extend from the body perimeter. Each arm (120) comprises an indented section (124), within which a tab extending from the payload top may be placed. When the payload tab rests within the indented section, the payload is prevented from translation and is attached to the mechanism.

    Abstract translation: 用于无人驾驶飞行器的有效载荷快速释放机构（100）被固定在无人驾驶飞行器上的结构上，并且允许从无人驾驶飞行器快速附接和移除有效载荷。 附接装置包括具有周边的主体（110）和从主体周边延伸的多个臂（120）。 每个臂（120）包括凹入部分（124），其中可以放置从有效载荷顶部延伸的突出部。 当有效载荷标签搁置在缩进部分内时，防止有效载荷平移并附着在机构上。

    AIRSHIP AND METHOD OF OPERATION
    142.
    发明授权
    AIRSHIP AND METHOD OF OPERATION 有权
    飞艇工作程序

    公开(公告)号：EP1519873B1

    公开(公告)日：2007-10-24

    申请号：EP03737791.8

    申请日：2003-06-25

    Applicant: 21st Century Airships Inc.

    Inventor： COLTING, Hokan

    IPC: B64B1/00

    CPC classification number: B64B1/34 ,  B64B1/02 ,  B64B1/32 ,  B64C21/02 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  Y02T50/166

    Abstract: An airship (20) has a generally spherical shape and has an internal envelope (24) for containing a lifting gas such as Helium or Hydrogen. The airship has a propulsion and control system (36, 38) that permits it to be flown to a desired loitering location, and to be maintained in that location for a period of time. In one embodiment the airship may achieve neutral buoyancy when the internal envelope is as little as 7 % full of lifting gas, and may have a service ceiling of about 60,000 ft. The airship has an equipment module (180) that can include either communications equipment, or monitoring equipment, or both. The airship can be remotely controlled from a ground station. The airship has a solar cell array and electric motors (44, 46) of the propulsion and control system are driven by power obtained from the array. The airship also has an auxiliary power unit (52) that can be used to drive the electric motors. The airship can have a pusher propeller that assists in driving the airship and also moves the point of flow separation of the spherical airship further aft. In one embodiment the airship can be refuelled at altitude to permit extended loitering.

    An integrated spline/cone seat subassembly
    147.
    发明公开
    An integrated spline/cone seat subassembly 失效
    集成设置有Zanhwellen /锥形座组件

    公开(公告)号：EP0861777A1

    公开(公告)日：1998-09-02

    申请号：EP97118290.2

    申请日：1993-06-18

    Applicant: UNITED TECHNOLOGIES CORPORATION

    Inventor： MILLEA, Vincent F., ,  HUNTER, David, H., ,  KRAUSS, Albert T.,

    IPC: B64C27/12 ,  B64D35/04

    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: An integrated spline/cone seat subassembly (190) for an unmanned aerial vehicle (10) having a rotor assembly (100) that includes ducted, counter-rotating rotors (200, 202), comprising:

    a rotor shaft (128R or 130R) having an axis, said rotor shaft (128R or 130R) including

    a primary shaft portion (192) having a first diameter (D 1 ),
    an end shaft portion (194) having a second diameter (D 2 ) and having a plurality of shaft splines (198) extending radially outwardly therefrom, and
    a conic transition portion (196) intermediate said primary and end shaft portions (192, 194), said conic transition portion (196) making a predetermined angle (β) with respect to said axis of said rotor shaft (128R or 130R); and

    a rotor hub (204) having a centerline (212), said rotor hub (204) having a shaft aperture (206) having a plurality of hub splines (208) extending radially inwardly therefrom;
    said plurality of hub splines (208) and said plurality of shaft splines (198) being interleaved in combination to provide a rotational interlock between said rotor hub (204) and said rotor shaft (128R or 130R) in the rotor assembly (100);
       characterized in that
    each of said hub splines (208) having an outwardly tapered lower portion (210) that makes a predetermined angle (θ) with respect to said centerline (212); and
    said predetermined angle (θ) of said outwardly tapered lower portions (210) of said hub splines (208) being equal to said predetermined angle (β) of said conic transition portion (196) of said rotor shaft (128R or 130R) wherein said tapered lower portions (210) of said hub splines (208) abuttingly engage and are mechanically supported by said conic transition portion (196) of said rotor shaft (128R or 130R) in the rotor assembly (100).

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