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    RETENTION SYSTEM AND METHOD FOR A WING
    321.
    发明申请
    RETENTION SYSTEM AND METHOD FOR A WING 有权
    保持系统和方法

    公开(公告)号：US20150053842A1

    公开(公告)日：2015-02-26

    申请号：US13974388

    申请日：2013-08-23

    Applicant: Becklin Holdings, Inc.

    Inventor： Matthew P. Phelan ,  Adrian P. Tayne

    IPC: F16M9/00 ,  F16B2/10 ,  B64C39/02

    CPC classification number: F16B2/10 ,  B64C39/024 ,  B64C2201/201 ,  B65D85/68 ,  B65D2585/687 ,  F16B43/003 ,  F16M9/00

    Abstract: A retention system includes a base supporting a wing spar and a post extending through the base from a first side of the base to a second side of the base. The post inserts through an aperture in the spar. A stop is selectively securable to the post over the second side of the base. A locking member engages the post on the first side of the base. The locking member is configured to selectively move the post from an unlocked position to a locked position in which the post is withdrawn toward the first side relative to the unlocked position. A biasing member encircles the post and is positioned between the stop and the second side. When the locking member is in a closed position the biasing member expands to engage the aperture and resist movement of the wing spar. A plurality of cradles may support the wing.

    Abstract translation: 保持系统包括支撑翼梁的基座和从基座的第一侧到基座的第二侧延伸穿过基座的柱。 柱穿过翼梁中的孔。 在基座的第二侧上，可以选择性地固定在支柱上。 锁定构件在基座的第一侧上接合柱。 锁定构件被构造成选择性地将柱从解锁位置移动到锁定位置，在锁定位置中柱相对于解锁位置朝向第一侧撤回。 偏置构件环绕柱，并且位于止挡件和第二侧之间。 当锁定构件处于关闭位置时，偏压构件膨胀以接合孔并阻止翼梁的运动。 多个托架可以支撑机翼。

    FUSELAGE INDEXING SYSTEM AND METHOD
    322.
    发明申请
    FUSELAGE INDEXING SYSTEM AND METHOD 有权
    融合指标体系及方法

    公开(公告)号：US20150053819A1

    公开(公告)日：2015-02-26

    申请号：US13974350

    申请日：2013-08-23

    Applicant: Becklin Holdings, Inc.

    Inventor： Dennis S. Becklin ,  Dean A. Weathers ,  Adrian P. Tayne

    IPC: B64C1/26

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/201 ,  Y10T29/49815

    Abstract: A system is disclosed including at least one indexing stub secured to a fuselage in the place of one or more wing stubs and including indexing members protruding from opposite sides of the fuselage. A pair of receivers are mounted to a container and define channels to receive the indexing members. The channels may include an upper flared portion and a lower straight portion. The indexing members are lowered into the channels and the flared portions guide the indexing members into the straight portions. In some embodiments, a pair of clamping members are configured to selectively lock the indexing members within the channels. The indexing members may have a cylindrical shape and may be rotatably mounted to the at least one indexing stub.

    Abstract translation: 公开了一种系统，其包括至少一个固定到机身的索引短截线代替一个或多个翼桩，并且包括从机身的相对侧突出的分度构件。 一对接收器被安装到容器并且定义用于接收索引构件的通道。 通道可以包括上部扩口部分和下部直线部分。 分度构件下降到通道中，并且扩口部分引导分度构件进入直线部分。 在一些实施例中，一对夹紧构件被配置成选择性地将索引构件锁定在通道内。 分度构件可以具有圆柱形形状并且可以可旋转地安装到至少一个分度桩。

    Unmanned aerial vehicle launch system
    324.
    发明授权
    Unmanned aerial vehicle launch system 有权
    无人机发射系统

    公开(公告)号：US08662441B2

    公开(公告)日：2014-03-04

    申请号：US13367494

    申请日：2012-02-07

    Applicant: David Powell ,  Earl Mark ,  John T. Houck ,  Keith Huber

    Inventor： David Powell ,  Earl Mark ,  John T. Houck ,  Keith Huber

    IPC: B64F1/10

    CPC classification number: B64C39/024 ,  B63G8/30 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/205

    Abstract: A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed.

    Abstract translation: 用于发射无人机（UAV）有效载荷的系统包括发射管，液体火箭和发射控制组件。 火箭定位在发射管中，并包含无人机的有效载荷。 增压组件可以包括部分地填充有液体的罐。 气瓶内充满压缩气体。 液体被气体预加压或在发射前与气体混合，使得在发射时，液体和气体推进阶段将火箭发射到阈值高度。 无人机有效载荷在达到阈值高度后部署。 可选的稳定管可以连接到发射管，其可以浮动用于水基操作。 可选的系绳可以连接到液体火箭，以在达到远地点之前停止其飞行。 无人机有效载荷不直接由气/液混合发射。 还公开了一种启动无人机有效载荷的方法。

    Unmanned Aerial Vehicle Based Sonar Buoy
    327.
    发明申请
    Unmanned Aerial Vehicle Based Sonar Buoy 有权
    无人机基于声纳浮标

    公开(公告)号：US20120138727A1

    公开(公告)日：2012-06-07

    申请号：US13097394

    申请日：2011-04-29

    Applicant: Jeremy F. Fisher

    Inventor： Jeremy F. Fisher

    IPC: F42B15/01 ,  B64D1/02 ,  B64C3/56 ,  F42B10/14

    CPC classification number: F42B15/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205 ,  F41F1/08 ,  F41F3/042

    Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.

    Abstract translation: 声纳浮标包括具有管状形状的机身，耦合到机身的一个或多个翼，耦合到机身的发动机，并且可操作以通过飞行推进声纳浮标;以及引导计算机，其可操作以将声纳浮标引导到 预定位置。 声纳浮标还包括可拆卸地联接到机身并形成机身的至少一部分的声纳和可拆卸地联接到机身的火箭发动机。 一个或多个翼可操作以折叠到允许声纳浮标布置在联接到车辆的发射管内并且在从发射管发射声纳浮标之后自动部署到适当位置用于飞行的位置。 火箭发动机从发射管推进声纳浮标，并在发射后从机身分离。

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