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    Aircraft
    91.
    发明授权
    Aircraft 有权
    飞机

    公开(公告)号：US08322650B2

    公开(公告)日：2012-12-04

    申请号：US12847004

    申请日：2010-07-30

    Applicant: Christopher Charles Kelleher

    Inventor： Christopher Charles Kelleher

    IPC: B64C39/12

    CPC classification number: B64C39/024 ,  B64C23/069 ,  B64C23/076 ,  B64C2201/021 ,  B64C2201/126 ,  Y02T50/164

    Abstract: An aircraft, particularly a solar powered, high altitude, long endurance, unmanned aerial vehicle, is equipped with a combination of canted down, raked back wing tips and trailing “tip tails” carried on booms from the tip regions of the mainplane. Each tip tail is positioned to be subject to the upwash field of the respective wing tip vortex, at least in the cruise condition of the aircraft. The wing tip form can achieve a reduction in induced drag and help to relieve wing root bending moment while the tip tails can act through their connections to the mainplane to provide torsional relief to the latter, particularly under lower incidence/higher speed conditions. In the higher incidence/lower speed cruise condition, however, the presence of the tip tails in the upwash fields of the wing tip vortices means that they can generate lift with a component in the forward direction of flight and hence contribute to the thrust requirements of the aircraft.

    Abstract translation: 飞机，特别是太阳能，高空，长寿命，无人驾驶飞行器，配备有从主板的尖端区域承载在悬臂上的倾斜下倾斜后翼翼尖和尾尖尾的组合。 至少在飞行器的巡航条件下，每个末梢尾部定位成受到相应的翼尖涡流的上洗液场的影响。 翼尖形式可以实现诱导阻力的减小，并且有助于减轻翼根弯曲力矩，同时尖端尾部可以通过它们与主平面的连接而起作用，以向后者提供扭转释放，特别是在较低的入射/更高速度条件下。 然而，在较高的发生率/较低速度的巡航条件下，翼尖涡流的上冲流场中尖端尾部的存在意味着它们可以在飞行方向上产生具有部件的升力，因此有助于推力要求 飞机。

    LAYERED ARCHITECTURE FOR CUSTOMER PAYLOAD SYSTEMS
    92.
    发明申请
    LAYERED ARCHITECTURE FOR CUSTOMER PAYLOAD SYSTEMS 有权
    客户付费系统的层次结构

    公开(公告)号：US20120035787A1

    公开(公告)日：2012-02-09

    申请号：US12852159

    申请日：2010-08-06

    Applicant: Troy T. DUNKELBERGER ,  Justin Adkins

    Inventor： Troy T. DUNKELBERGER ,  Justin Adkins

    IPC: B64C39/00 ,  G06F17/00

    CPC classification number: B64C39/024 ,  B64C2201/126

    Abstract: A layered architecture for customer payload systems is disclosed to provide a scalable, reconfigurable integration platform targeted at multiple unmanned aerial vehicles (UAV), and remove both UAV specific and payload equipment specific characteristics that increase complexity during integration. The layered architecture is a modular design architecture that is split by function. Standard interfaces are implemented between functional layers to increase reconfiguration possibilities and to allow reuse of existing components and layers without modification to the payload or UAV. The standard interfaces also promote easy connection and disconnection from other layer components. Additionally, once the layered architecture is implemented, technological or functional requirements changes can be isolated to one specific component layer, not the entire payload stack. As a result, payload designs based on the layered architecture reduces design time and cost, and allows for easier integration, operation, upgrades, maintenance, and repair.

    Abstract translation: 公开了用于客户有效载荷系统的分层架构，以提供针对多个无人机（UAV）的可扩展的可重构集成平台，并且在集成期间移除提高复杂性的UAV特定和有效载荷设备特定特性。 分层架构是一种按功能划分的模块化设计架构。 标准接口在功能层之间实现，以增加重新配置的可能性，并允许现有组件和层的重用，而无需修改有效载荷或UAV。 标准接口还可以方便地连接和断开与其他层组件的连接。 另外，一旦分层架构被实现，技术或功能需求的改变可以被隔离到一个特定的组件层而不是整个有效载荷堆栈。 因此，基于分层架构的有效负载设计减少了设计时间和成本，并且允许更容易的集成，操作，升级，维护和修复。

    SMALL UNMANNED AIR VEHICLE SYSTEM FOR DEPLOYING AND TOWING A SENSOR IN A TOW MEDIUM AND METHODS RELATED THERETO
    93.
    发明申请
    SMALL UNMANNED AIR VEHICLE SYSTEM FOR DEPLOYING AND TOWING A SENSOR IN A TOW MEDIUM AND METHODS RELATED THERETO 失效
    用于分配和传送传感器的小型无人空中车辆系统及其相关方法

    公开(公告)号：US20090224099A1

    公开(公告)日：2009-09-10

    申请号：US11422933

    申请日：2006-06-08

    Applicant: Daniel W. Steele ,  John H. Goodemote ,  David J. Erickson

    Inventor： Daniel W. Steele ,  John H. Goodemote ,  David J. Erickson

    IPC: B64D3/00

    CPC classification number: B64D3/02 ,  B64C39/024 ,  B64C2201/126 ,  F42B12/365 ,  F42B15/08

    Abstract: Embodiments of the invention are directed to an unmanned air vehicle (UAV) system and a small unmanned air vehicle (SUAV) system for deploying and towing a sensor in a tow medium, and to methods related thereto. A UAV-sensor towing package comprises a fixed-wing UAV including a control and signal processing platform, a long range data RF link operably connected to the control and signal processing platform, a UAV wireless data link operably connected to the control and signal processing platform, and a tow body deployment system operably connected to the control and signal processing platform; a tow line attached at an end thereof to the UAV; a tow body attached to another end of the tow line; and a communications link including a transmitter/receiver component coupled to the tow line, and a T/R wireless data transmission link (194) operably connected with the transmitter/receiver component and the UAV wireless data link. A method for towing a tethered tow body through a tow medium along a tow track with a fixed-wing UAV at a tow body velocity that is less than a stall speed of the UAV along a forward UAV tow path comprises providing a UAV, a tow line attached at an end thereof to the UAV, and a tow body attached to another end of the tow line; flying the UAV to locate the tow body in a selected location of a tow medium; maneuvering the UAV along a non-horizontally-oriented, generally circular flight path (altitude tilted orbit) with a forward (surface) velocity along the forward UAV tow path corresponding to the tow track, wherein the tow body velocity in the tow medium is less than a stall speed of the UAV along the forward UAV tow path.

    Abstract translation: 本发明的实施例涉及一种无人机（UAV）系统和用于在牵引介质中部署和拖动传感器的小型无人机（SUAV）系统及其相关方法。 UAV传感器牵引包包括固定翼UAV，其包括控制和信号处理平台，可操作地连接到控制和信号处理平台的远程数据RF链路，可操作地连接到控制和信号处理平台的UAV无线数据链路 以及可操作地连接到控制和信号处理平台的拖车车身部署系统; 在其一端附接到无人机的拖绳; 连接在拖绳的另一端的丝束体; 以及包括耦合到所述拖线的发送器/接收器组件的通信链路以及可操作地与所述发射机/接收机组件和所述无人机无线数据链路连接的T / R无线数据传输链路（194）。 一种通过具有固定翼型UAV的牵引轨道牵引束缚体的拖曳束体的方法，所述固定翼型UAV的牵引体速度小于所述无人机沿着前方UAV牵引路径的失速速度，包括提供无人机， 在其一端附接到无人机的线路，以及附接到牵引线的另一端的丝束体; 飞行无人机以将拖曳物体定位在拖曳介质的选定位置; 沿着非水平取向的大致圆形的飞行路径（高度倾斜轨道）操纵无人机，其前向（表面）速度沿着对应于拖曳轨道的前方UAV拖曳路径，其中，牵引介质中的牵引体速度较小 比无人机前方无人机拖车路径的失速速度快。

    Air vehicle assembly and an associated control system and method
    94.
    发明授权
    Air vehicle assembly and an associated control system and method 有权
    机动车组件及相关控制系统及方法

    公开(公告)号：US07357352B2

    公开(公告)日：2008-04-15

    申请号：US11270342

    申请日：2005-11-09

    Applicant: Thomas E. Speer ,  Richard D. Jones

    Inventor： Thomas E. Speer ,  Richard D. Jones

    IPC: B64C37/02 ,  B64D5/00

    CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  B64C2201/165 ,  B64D5/00

    Abstract: An air vehicle assembly and a corresponding method for launching an air vehicle assembly are provided, along with corresponding control systems and methods. The air vehicle assembly may include a plurality of air vehicles releasably joined to one another during a portion of the flight, such as during take-off and landing. By being releasably joined to one another, such as during take-off and landing, the air vehicles can rely upon and assist one another during the vertical take-off and landing while being designed to have a greater range and higher endurance following the transition to forward flight, either while remaining coupled to or following separation from the other air vehicles. By taking into account the states of the other air vehicles, the control system and method also permit the air vehicles of an air vehicle assembly to collaborate.

    Abstract translation: 提供了一种用于发射空中车辆组件的机动车组件和相应的方法，以及相应的控制系统和方法。 空中车辆组件可以包括在飞行的一部分期间例如在起飞和着陆期间可释放地彼此连接的多个空中飞行器。 通过可释放地彼此接合，例如在起飞和着陆期间，空中车辆可以在垂直起飞和着陆期间依靠和协助彼此，同时被设计成在过渡到 同时保持与其他空中客车分离的距离或距离。 通过考虑其他机动车辆的状态，控制系统和方法还允许机动车组件的空中车辆协作。

    Aerial robot
    95.
    发明申请
    Aerial robot 有权
    空中机器人

    公开(公告)号：US20070200027A1

    公开(公告)日：2007-08-30

    申请号：US11361122

    申请日：2006-02-24

    Applicant: Samuel Johnson

    Inventor： Samuel Johnson

    IPC: F41G7/00

    CPC classification number: B64C39/022 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/148

    Abstract: An aerial robot is disclosed. The aerial robot may include at least one pair of counter-rotating blades or propellers, which may be contained within a circumferential shroud or a duct. In one embodiment, the aerial robot may have the ability to hover and move indefinitely. Electric power to the robot may be provided by a tether or an on-board power supply. In tethered embodiments, a solid-state, electronic voltage transformer may be used to reduce a high voltage, low current source to lower voltage, higher current source. In one embodiment, secure data communication between a ground unit and the aerial robot is facilitated by impressing high bandwidth serial data onto the high voltage tether wires or a thin optical fiber which is co-aligned with the tether wires. In one embodiment, precise navigational and position controls, even under extreme wind loads, are facilitated by an on-board GPS unit and optical digital signal processors. In one embodiment, if the tether detaches, precision free-flight is possible with on-board batteries.

    Abstract translation: 公开了一种空中机器人。 空中机器人可以包括至少一对反向旋转叶片或螺旋桨，其可以包含在周向护罩或管道内。 在一个实施例中，空中机器人可能具有无限期地悬停和移动的能力。 机器人的电力可以由系绳或车载电源提供。 在连接的实施例中，可以使用固态电子电压互感器来将高电压，低电流源降低到更低的电压，更高的电流源。 在一个实施例中，通过将高带宽串行数据压印到高压系绳线上或与系绳相配合的薄光纤来实现地面单元与空中机器人之间的安全数据通信。 在一个实施例中，甚至在极端风力负载下的精确导航和位置控制也由车载GPS单元和光学数字信号处理器促成。 在一个实施例中，如果系绳分离，则使用车载电池可以进行精确的自由飞行。

    Air vehicle assembly and an associated control system and method
    96.
    发明申请
    Air vehicle assembly and an associated control system and method 有权
    机动车组件及相关控制系统及方法

    公开(公告)号：US20070102565A1

    公开(公告)日：2007-05-10

    申请号：US11270342

    申请日：2005-11-09

    Applicant: Thomas Speer ,  Richard Jones

    Inventor： Thomas Speer ,  Richard Jones

    IPC: B64C29/00 ,  B64C37/02

    CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  B64C2201/165 ,  B64D5/00

    Abstract: An air vehicle assembly and a corresponding method for launching an air vehicle assembly are provided, along with corresponding control systems and methods. The air vehicle assembly may include a plurality of air vehicles releasably joined to one another during a portion of the flight, such as during take-off and landing. By being releasably joined to one another, such as during take-off and landing, the air vehicles can rely upon and assist one another during the vertical take-off and landing while being designed to have a greater range and higher endurance following the transition to forward flight, either while remaining coupled to or following separation from the other air vehicles. By taking into account the states of the other air vehicles, the control system and method also permit the air vehicles of an air vehicle assembly to collaborate.

    Abstract translation: 提供了一种用于发射空中车辆组件的机动车组件和相应的方法，以及相应的控制系统和方法。 空中车辆组件可以包括在飞行的一部分期间例如在起飞和着陆期间可释放地彼此连接的多个空中飞行器。 通过可释放地彼此接合，例如在起飞和着陆期间，空中车辆可以在垂直起飞和着陆期间依靠和协助彼此，同时被设计成在过渡到 同时保持与其他空中客车分离的距离或距离。 通过考虑其他机动车辆的状态，控制系统和方法还允许机动车组件的空中车辆协作。

    Aircraft control system
    97.
    发明申请
    Aircraft control system 有权
    飞机控制系统

    公开(公告)号：US20030141409A1

    公开(公告)日：2003-07-31

    申请号：US10310415

    申请日：2002-12-05

    Inventor： Derek L. Lisoski ,  Greg T. Kendall

    IPC: B64C001/00 ,  B64C003/00 ,  B64C005/00

    CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

    Abstract: A solar rechargeable, long-duration, span-loaded flying wing, having no fuselage or rudder. Having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn, pitch and yaw. The wing is configured to deform under flight loads to position the propellers such that the control can be achieved. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface.

    Abstract translation: 太阳能可再充电，长时间，跨度的飞翼，没有机身或方向舵。 拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差速推力来转弯，俯仰和偏航。 机翼构造成在飞行载荷下变形以定位螺旋桨，使得可以实现控制。 翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，以避免加载它们。 五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。

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