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    METHODS, APPARATUS AND SYSTEMS FOR AERIAL ASSESSMENT OF GROUND SURFACES
    81.
    发明申请
    METHODS, APPARATUS AND SYSTEMS FOR AERIAL ASSESSMENT OF GROUND SURFACES 审中-公开
    方法，用于对地面进行空气评估的装置和系统

    公开(公告)号：US20140312165A1

    公开(公告)日：2014-10-23

    申请号：US14217387

    申请日：2014-03-17

    Applicant: Armen Mkrtchyan

    Inventor： Armen Mkrtchyan

    IPC: B64D47/08 ,  B64C39/02

    CPC classification number: B64D47/08 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/165 ,  G06K9/00657 ,  G06K9/2018

    Abstract: A hand-launched unmanned aerial vehicle (UAV) to determine various characteristics of ground surfaces. The UAV includes a lightweight and robust body/wing assembly, and is equipped with multiple consumer-grade digital cameras that are synchronized to acquire high-resolution images in different spectra. In one example, one camera acquires a visible spectrum image of the ground over which the UAV is flown, and another camera is modified to include one or more filters to acquire a similar near-infrared image. A camera mount/holder system facilitates acquisition of high-quality images without impacting the UAV's flight characteristics, as well as easy coupling and decoupling of the cameras to the UAV and safeguarding of the cameras upon landing. An intuitive user interface allows modestly trained individuals to operate the UAV and understand and use collected data, and image processing algorithms derive useful information regarding crop health and/or soil characteristics from the acquired images.

    Abstract translation: 一种手动无人机（UAV）来确定地面各种特性。 无人机包括一个轻量级和坚固的身体/翼组件，并配备了多个消费级数码相机，同步以获取不同光谱的高分辨率图像。 在一个示例中，一个摄像机获取飞行无人机的地面的可见光谱图像，并且修改另一摄像机以包括一个或多个滤波器以获取类似的近红外图像。 相机安装/支架系统便于获取高质量的图像，而不会影响UAV的飞行特性，以及轻松耦合和解耦相机到UAV，并在着陆时保护相机。 直观的用户界面允许受过训练的人员操作无人机，了解和使用收集的数据，图像处理算法从所获取的图像中得到有关作物健康和/或土壤特性的有用信息。

    INFLATABLE AIRFOIL SYSTEM HAVING REDUCED RADAR AND INFRARED OBSERVABILITY
    83.
    发明申请
    INFLATABLE AIRFOIL SYSTEM HAVING REDUCED RADAR AND INFRARED OBSERVABILITY 审中-公开
    具有减少雷达和红外可观察性的可充气飞行器系统

    公开(公告)号：US20140255189A1

    公开(公告)日：2014-09-11

    申请号：US14250385

    申请日：2014-04-11

    Applicant: The Boeing Company

    Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

    IPC: B64C3/30

    CPC classification number: B64C3/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/105

    Abstract: A method and apparatus for operating an airfoil system. A gas may be generated. The gas may be sent into an inflatable airfoil system comprising an inflatable air foil and a section. The inflatable airfoil may have an inner end and an outer end in which the inflatable airfoil may be comprised of a number of materials that substantially pass electromagnetic waves through the inflatable airfoil. The section may have a number of openings in which the inner end of the inflatable airfoil may be associated with the section. The section may be configured to be associated with a fuselage. The number of openings may be configured to provide communications with an interior of the inflatable airfoil. The section with the number of openings may be configured to reduce reflection of the electromagnetic waves encountering the section.

    Abstract translation: 一种用于操作翼型系统的方法和装置。 可能产生气体。 气体可以被送入包括可膨胀的气翼和截面的充气翼型系统中。 可膨胀翼型件可以具有内端和外端，其中可膨胀翼型可以由许多基本上通过电磁波通过可充气翼型的材料构成。 该部分可以具有多个开口，其中可充气翼片的内端可以与该部分相关联。 该部分可以被配置为与机身相关联。 开口的数量可以被配置为提供与可膨胀翼型件的内部的通信。 具有开口数量的部分可以被配置为减少遇到该部分的电磁波的反射。

    Method and apparatus for retrieving a hovering aircraft
    84.
    发明授权
    Method and apparatus for retrieving a hovering aircraft 有权

    公开(公告)号：US08708278B2

    公开(公告)日：2014-04-29

    申请号：US13900191

    申请日：2013-05-22

    Applicant: Aerovel Corporation

    Inventor： Brian T. McGeer ,  Andreas H. von Flotow ,  Corydon C. Roeseler

    IPC: B64F1/02 ,  B64F1/04

    CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/182 ,  B64F1/04 ,  B64F5/00

    Abstract: For retrieval of a hovering aircraft, a cable, bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separated supports. The aircraft slowly flies into this fixture, which then slides along the aircraft in a direction approximately parallel with the aircraft's thrust line. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer, which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light and unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy.

    UAV launch attachment assembly and launch system
    85.
    发明授权
    UAV launch attachment assembly and launch system 失效
    无人机发射附件组装和发射系统

    公开(公告)号：US08511607B2

    公开(公告)日：2013-08-20

    申请号：US12836496

    申请日：2010-07-14

    Applicant: Andrew B. Robinson

    Inventor： Andrew B. Robinson

    IPC: B64F1/04

    CPC classification number: B64F1/04 ,  B64C2201/021 ,  B64C2201/084 ,  B64F1/06

    Abstract: A UAV attachment assembly, used with a UAV launch assembly comprising a frame and a launch driver, comprises a base, a UAV support, a biasing element, a coupler, and a retainer. The base is operably coupled to the launch driver. The UAV support is mounted to the base and is placeable in vertically collapsed and vertically extended orientations. The biasing element biases the UAV support towards the collapsed orientation. The coupler releasably couples the UAV support to a UAV when the UAV support is in the extended orientation, the UAV support being free of the UAV when in the collapsed orientation. The retainer maintains the UAV support in the vertically extended orientation prior to launch and releases the UAV support at launch so that the biasing element can cause the UAV support to move towards the collapsed orientation and to disengage from the UAV.

    Abstract translation: 与包括框架和发射驱动器的UAV发射组件一起使用的UAV附件组件包括基座，UAV支撑件，偏置元件，联接器和保持器。 基座可操作地联接到发射驱动器。 无人机支撑安装在基座上，可放置在垂直折叠和垂直延伸的方向上。 偏置元件使无人机支撑朝向折叠方向偏移。 当UAV支撑处于延伸方向时，联接器将UAV支撑件可释放地耦合到UAV，UAV支撑在处于折叠方向时无UAV。 保持架在启动之前将UAV支撑件保持在垂直延伸的方向，并在发射时释放UAV支撑，使得偏置元件可以使UAV支撑件朝向折叠方向移动并与UAV脱离接合。

    Unmanned aerial vehicle based sonar buoy
    87.
    发明授权
    Unmanned aerial vehicle based sonar buoy 有权
    无人机基于声纳浮标

    公开(公告)号：US08492692B2

    公开(公告)日：2013-07-23

    申请号：US13097394

    申请日：2011-04-29

    Applicant: Jeremy F. Fisher

    Inventor： Jeremy F. Fisher

    IPC: F42B12/56 ,  F42B15/01 ,  F42B15/08 ,  H04B1/59 ,  F42B15/00 ,  H04B1/00

    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。

    FOLDING WING FOR AIRCRAFT
    89.
    发明申请
    FOLDING WING FOR AIRCRAFT 有权
    飞机折页

    公开(公告)号：US20120280080A1

    公开(公告)日：2012-11-08

    申请号：US13462422

    申请日：2012-05-02

    Applicant: Jacob G. LUBENOW ,  Andrew S. McComas ,  Jeremy A. Zanzig ,  Jeffrey A. Gerhart ,  Alan R. Klug ,  Jonathan P. Clark

    Inventor： Jacob G. LUBENOW ,  Andrew S. McComas ,  Jeremy A. Zanzig ,  Jeffrey A. Gerhart ,  Alan R. Klug ,  Jonathan P. Clark

    IPC: B64C3/56

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/102

    Abstract: A folding wing for an aircraft comprises first and second inboard wing sections, and first and second outboard wing sections. The first and second inboard wing sections rotate about a centerline hinge, and a centerline spring applies force to the first and second inboard wing sections to rotate the first and second inboard wing sections from a stowed position to a deployed position. At least one of the first and second inboard wing sections translates along the axis of rotation of the first and second inboard wing sections as they move from the stowed to the deployed positions. The first and second outboard wing sections rotate between the stowed and the deployed positions about first and second outboard hinges.

    Abstract translation: 用于飞机的折翼包括第一和第二内侧翼部，以及第一和第二外侧翼部。 第一和第二内侧翼部围绕中心线铰链旋转，并且中心线弹簧对第一和第二内侧翼部施加力，以将第一和第二内侧翼部从收起位置旋转到展开位置。 第一和第二内侧翼部分中的至少一个在它们从收起的位置移动到展开位置时沿着第一和第二内侧翼部的旋转轴线平移。 第一和第二外侧翼部分围绕第一和第二外侧铰链在收起和展开位置之间旋转。

    METHOD AND APPARATUS FOR RETRIEVING A HOVERING AIRCRAFT
    90.
    发明申请
    METHOD AND APPARATUS FOR RETRIEVING A HOVERING AIRCRAFT 有权
    检测飞机的方法和装置

    公开(公告)号：US20120273612A1

    公开(公告)日：2012-11-01

    申请号：US13540032

    申请日：2012-07-02

    Applicant: Brian T. McGeer ,  Andreas H. von Flotow ,  Corydon C. Roeseler

    Inventor： Brian T. McGeer ,  Andreas H. von Flotow ,  Corydon C. Roeseler

    IPC: B64F1/22 ,  B64F1/04

    CPC classification number: B64F1/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/182 ,  B64F1/04 ,  B64F5/00

    Abstract: For retrieval of a hovering aircraft, a cable, bar, or similar fixture is suspended in an approximately horizontal orientation across the retrieval area between two well-separated supports. The aircraft slowly flies into this fixture, which then slides along the aircraft in a direction approximately parallel with the aircraft's thrust line. This leads to the aircraft becoming fastened to the fixture by an interceptor or aircraft capturer, which in alternative embodiments are respectively on the aircraft or the fixture or both. Thrust is then reduced, and the aircraft comes to rest hanging from the fixture for subsequent removal. Retrieval is thus accomplished with simple and economical apparatus, light and unobtrusive elements on the aircraft, low risk of damage, and only moderate piloting accuracy.

    Abstract translation: 为了检索悬停的飞行器，电缆，杆或类似的固定装置悬挂在两个分离好的支撑件之间的取回区域的大致水平的方向上。 飞机慢慢地飞入这个固定装置，然后沿着与飞机的推力线大致平行的方向沿飞机滑动。 这导致飞行器通过拦截器或飞行器捕获器被固定到固定装置上，在替代实施例中飞行器或飞机捕获器分别在飞行器或固定装置上或两者上。 然后减小推力，飞机从固定装置上休息，以便随后拆卸。 因此，在飞机上使用简单经济的装置，轻便和不引人注意的元件来实现检索，损坏风险低，而且只有适度的驾驶准确性。

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