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    MODULAR ARTICULATED-WING AIRCRAFT
    263.
    发明申请
    MODULAR ARTICULATED-WING AIRCRAFT 有权
    MODULAR ARTICULATED-WING飞机

    公开(公告)号：US20100193625A1

    公开(公告)日：2010-08-05

    申请号：US11475085

    申请日：2006-06-27

    Applicant: Geoffrey S. Sommer

    Inventor： Geoffrey S. Sommer

    IPC: B64C37/02 ,  B64D27/02 ,  G05D1/00

    CPC classification number: B64C39/024 ,  B64C37/02 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/143 ,  B64C2201/165 ,  B64C2201/206

    Abstract: Systems and/or methods for forming a multiple-articulated flying system (skybase) having a high aspect ratio wing platform, operable to loiter over an area of interest at a high altitude are provided. In certain exemplary embodiments, autonomous modular flyers join together in a wingtip-to-wingtip manner. Such modular flyers may derive their power from insolation. The autonomous flyers may include sensors which operate individually, or collectively after a skybase is formed. The skybase preferably may be aggregated, disaggregated, and/or re-aggregated as called for by the prevailing conditions. Thus, it may be possible to provide a “forever-on-station” aircraft.

    Abstract translation: 提供了用于形成具有高纵横比翼平台的多关节飞行系统（天基）的系统和/或方法，其可操作以在高海拔地区的感兴趣区域上游荡。 在某些示例性实施例中，自主模块化飞行器以翼尖到翼尖的方式连接在一起。 这样的模块化飞行器可以从日晒中获得其功率。 自主传单可以包括单独操作的传感器，或者在形成天空基础之后集体运行。 天空基优选地可以按照主要条件的要求进行聚合，分解和/或再聚集。 因此，可能提供“永远在车”的飞机。

    Double ducted hovering air-vehicle
    264.
    发明授权
    Double ducted hovering air-vehicle 失效
    双管道悬停飞行器

    公开(公告)号：US07658346B2

    公开(公告)日：2010-02-09

    申请号：US11338558

    申请日：2006-01-24

    Applicant: Emray R. Goossen

    Inventor： Emray R. Goossen

    IPC: B64C27/08

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C29/0016 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/201

    Abstract: A dual ducted fan arrangement in which the duct components, engine, and avionics/payload pods are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan, stator, and control vane design. Assembly connections between ducted fans and electronic modules are also identical. An engine or APU drives the dual ducted fans through a splined shaft to a differential or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms on each of the splined shafts between the differential and ducted fans. In the electric motor case relative speed is through electronic speed control. The fans are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

    Abstract translation: 双管风扇装置，其中管道部件，发动机和航空电子设备/有效载荷容器能够快速拆卸以适合普通的背包系统。 风扇，定子和控制叶片设计中的每个风道都相同。 管道风扇和电子模块之间的组装连接也相同。 发动机或APU通过花键轴驱动双管道风扇到差速器或通过电动机驱动。 能量通过安装在定子毂上的单个齿轮传递到管道风扇。 单个管道风扇的相对速度通过在差速风扇和管道风扇之间的每个花键轴上的单独的摩擦或发电机负载控制制动机构来控制。 在电动机壳体中，相对速度是通过电子速度控制。 风扇反向旋转以进行扭矩平衡。 电子模块位置对于纵向重心是垂直可变的，用于有效载荷的变化。

    SYSTEMS AND METHODS FOR CAPTURING AND CONTROLLING POST-RECOVERY MOTION OF UNMANNED AIRCRAFT
    265.
    发明申请
    SYSTEMS AND METHODS FOR CAPTURING AND CONTROLLING POST-RECOVERY MOTION OF UNMANNED AIRCRAFT 有权
    用于捕获和控制未经规定的飞机的恢复后运动的系统和方法

    公开(公告)号：US20100025528A1

    公开(公告)日：2010-02-04

    申请号：US11775600

    申请日：2007-07-10

    Applicant: Clifford Jackson

    Inventor： Clifford Jackson

    IPC: B64F1/02

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/086 ,  B64C2201/165 ,  B64C2201/182

    Abstract: Systems and methods for capturing and controlling post-recovery motion of an unmanned aircraft are disclosed herein. An aircraft system in accordance with one embodiment of the invention, for example, can include a line capture assembly carried by an unmanned aircraft having a fuselage and a lifting surface. The line capture assembly can include a flexible support line having a first portion attached to an attachment point on the fuselage and a second portion extending from the attachment point spanwise along the lifting surface of the aircraft. The line capture assembly can also include an engagement device coupled to the second portion of the support line. The engagement device is releasably secured to the lifting surface.

    Abstract translation: 本文公开了用于捕获和控制无人飞行器的恢复后运动的系统和方法。 例如，根据本发明的一个实施例的飞行器系统可以包括由具有机身和提升表面的无人飞行器承载的线捕获组件。 线捕获组件可以包括柔性支撑线，其具有附接到机身上的附接点的第一部分和从飞行器的提升表面沿着方向从附接点延伸的第二部分。 线捕获组件还可以包括联接到支撑线的第二部分的接合装置。 接合装置可释放地固定到提升表面。

    Unmanned aerial vehicle and launch assembly
    268.
    发明授权
    Unmanned aerial vehicle and launch assembly 有权
    无人机和发射组件

    公开(公告)号：US07556219B2

    公开(公告)日：2009-07-07

    申请号：US11064287

    申请日：2005-02-22

    Applicant: Mark A. Page ,  Doug McLarty ,  Adrian Fazio ,  Christian Durand ,  Bob Emerick

    Inventor： Mark A. Page ,  Doug McLarty ,  Adrian Fazio ,  Christian Durand ,  Bob Emerick

    IPC: B64F1/04

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/165 ,  B64C2201/201

    Abstract: An unmanned aerial vehicle (UAV) is provided, that is cost effective to use and manufacture and that includes a low count of component parts, allowing mission planners to use the UAVs in a disposable manner. The UAV includes an airframe having a central body and wings extending from the central body, defining an interior cavity. The airframe includes an upper and a lower shell, each configured of a unitary piece of plastic. The upper and lower shells have walls among them that define a fuel tank and a payload bay in a stacked configuration. The airframe can further include a payload cover configured to enclose the payload bay and to contribute to the central body of the airframe. A launch assembly is also provided. In a first configuration, a launch assembly is provided, that includes a container for housing multiple UAVs and a deployment mechanism that initiates rapid ejection of the UAVs from the container. In a second configuration, a launch assembly is provided, that includes an elastic tether connecting a UAV to an accelerated mass for gentle acceleration to flight speed under a stable tow.

    Abstract translation: 提供无人驾驶飞行器（UAV），使用和制造具有成本效益，并且包括低数量的部件，允许任务规划人员以一次性方式使用无人机。 无人机包括具有中心体的机身和从中心体延伸的翼，限定内腔。 机身包括一个上部和下部壳体，每个都由整体塑料构成。 上壳体和下壳体之间具有限定了堆叠构造的燃料箱和有效载荷的壁。 机身还可以包括配置成包围有效载荷舱并有助于机身的中心主体的有效载荷盖。 还提供发射组件。 在第一配置中，提供了一种发射组件，其包括用于容纳多个UAV的容器和启动无人机从容器的快速喷射的展开机构。 在第二构造中，提供了一种发射组件，其包括将UAV连接到加速质量块的弹性系绳，以在稳定的丝束下平缓加速到飞行速度。

    Corded Orientation System For Lighter-Than-Air Aircraft
    269.
    发明申请
    Corded Orientation System For Lighter-Than-Air Aircraft 审中-公开
    轻型飞机有线方向系统

    公开(公告)号：US20090045284A1

    公开(公告)日：2009-02-19

    申请号：US11840607

    申请日：2007-08-17

    Applicant: Adam N. Chu

    Inventor： Adam N. Chu

    IPC: B64B1/00

    CPC classification number: B64C39/024 ,  B64B1/02 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/165

    Abstract: An orientation system is disclosed for a lighter-than-air aircraft having a lower stage suspended from an envelope. The orientation system includes cords interconnecting the envelope and the lower stage and means for adjusting the length of at least one of the cords between the lower stage and the envelope. Adjusting the length produces a shift in the angle of attack of the envelope with respect to the lower stage.

    Abstract translation: 公开了一种具有从信封悬挂的较低级的轻型飞机的定向系统。 定向系统包括将信封和下层相互连接的绳索和用于调节下层和包封之间的至少一根帘线长度的装置。 调整长度会导致信封相对于下层的迎角发生偏移。

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