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    Aerial vehicle with variable aspect ratio deployable wings
    214.
    发明授权
    Aerial vehicle with variable aspect ratio deployable wings 有权

    公开(公告)号：US07841559B1

    公开(公告)日：2010-11-30

    申请号：US11707088

    申请日：2007-02-16

    Applicant: Hank O'Shea

    Inventor： Hank O'Shea

    IPC: B64C3/40

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/102

    Abstract: Embodiments of the present invention relate a wing arrangement for an aerial vehicle configured to adjust the vehicles aspect ratio in response to flight mission parameters. The wing arrangement may include a pair of wing assemblies capable of deploying to a first winged position defining a first aspect ratio. Each wing assembly may have a forward inboard wing pivotally connected to the fuselage and an aft inboard wing pivotally connected to the carriage. The forward inboard wing and aft inboard wing of each assembly may be connected, forming a bi-plane configuration. Additionally, the each assembly may include a set of outboard wings configured to telescope from the inboard wings to an extended winged position defining a second aspect ratio greater than the first aspect ratio.

    COLLAPSIBLE WING BEAMS AND METHOD
    216.
    发明申请
    COLLAPSIBLE WING BEAMS AND METHOD 有权
    不可思议的翅膀和方法

    公开(公告)号：US20100116937A1

    公开(公告)日：2010-05-13

    申请号：US12616812

    申请日：2009-11-12

    Applicant: Terry M. Sanderson ,  David R. Sar

    Inventor： Terry M. Sanderson ,  David R. Sar

    IPC: B64C3/00 ,  B64C3/18 ,  E04H12/18

    CPC classification number: B64C3/185 ,  B64C3/48 ,  B64C3/56 ,  B64C2201/102

    Abstract: A wing, such as a wing for an unmanned aerial vehicle (UAV), includes a beam or box that can be selectively expanded from a collapsed condition, to increase the thickness of the wing. The beam may include a pair of plates that are close together when the beam is in a collapsed condition, and separate from one another to put the beam in an expanded condition. The plates may be substantially parallel to each other, and may have shape memory foam and/or resilient devices, such as coil springs, between them, in order to provide a force to separate the plates before, during, and/or after deployment of the wing. The expandable/collapsible beam may have a lock mechanism to lock it into place when the beam is in an expanded condition.

    Abstract translation: 诸如用于无人驾驶飞行器（UAV）的机翼的机翼包括可以从折叠状态选择性地扩展的梁或箱，以增加机翼的厚度。 梁可以包括一对板，当梁处于折叠状态时，彼此分离并将梁放置在膨胀状态下，它们靠近在一起。 板可以基本上彼此平行，并且在它们之间可以具有形状记忆泡沫和/或弹性装置，例如螺旋弹簧，以便在部署之前，期间和/或之后提供力分离板 机翼。 可膨胀/可折叠的梁可以具有锁定机构，以在梁处于膨胀状态时将其锁定到位。

    Ducted fan air vehicle with deployable wings
    217.
    发明授权
    Ducted fan air vehicle with deployable wings 失效
    带有可展翅膀的风扇飞机

    公开(公告)号：US07681832B2

    公开(公告)日：2010-03-23

    申请号：US11947585

    申请日：2007-11-29

    Applicant: John C. Colclough

    Inventor： John C. Colclough

    IPC: B64C15/00

    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 flight operation without significantly impacting hover stability. One or more retractable wings 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: 公开了一种管道风扇空气动力车辆和操作方法，用于在前进飞行操作中获得空气动力学提升和效率，而不会显着影响悬停稳定性。 一个或多个伸缩翼包括在管道式风扇飞行器上，并且在向前飞行期间部署以提供空气动力学提升。 当车辆悬停时，翼或翼缩回，以减少翼对风中的稳定性的影响。 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部署和撤回，或者在操作员的指令下进行。 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。

    Ballistically deployed telescoping aircraft wing
    219.
    发明申请
    Ballistically deployed telescoping aircraft wing 审中-公开
    弹道部署伸缩飞机机翼

    公开(公告)号：US20090206193A1

    公开(公告)日：2009-08-20

    申请号：US11450720

    申请日：2006-06-09

    Applicant: David J. File

    Inventor： David J. File

    IPC: B64C3/54 ,  B64C1/00

    CPC classification number: B64C3/54 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127 ,  Y02T50/14

    Abstract: An apparatus for increasing an aerodynamic surface area of an aircraft, e.g., a wing thereof, includes coaxially disposed first and second elongated airfoils and an inflatable device arranged to move the first airfoil coaxially relative to the second airfoil. The second airfoil has a root end fixed to the vehicle and an opposite outboard end, and the first airfoil is arranged to move axially between a retracted position generally inboard of the outboard end of the second airfoil and a deployed position generally outboard thereof. When the movable airfoil is deployed, a latching mechanism locks it in position. The inflatable device can include a collapsible duct that is sealed at one end and coupled at a second end to an inflating source, such as a reservoir of a compressed gas or a pyrotechnic gas generator.

    Abstract translation: 用于增加飞行器（例如其翼）的空气动力学表面积的装置包括同轴布置的第一和第二细长翼型件以及布置成使第一翼型件相对于第二翼型件同轴地移动的可充气装置。 第二翼型件具有固定到车辆的根部端部和相对的外侧端部，并且第一翼型件布置成在第二翼型件的外侧端部的大致内侧的缩回位置和大致在其外侧的展开位置之间轴向移动。 当可移动翼片展开时，闩锁机构将其锁定就位。 可膨胀装置可以包括可折叠的管道，其在一端被密封并且在第二端处连接到充气源，例如压缩气体或烟火气体发生器的储存器。

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