公开(公告)号：US20110193959A1

公开(公告)日：2011-08-11

申请号：US12658543

申请日：2010-02-11

Applicant: Steven Roger Brandon

Inventor： Steven Roger Brandon

IPC: H04N7/18 ,  B64C27/82 ,  B64D7/00

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C2201/024 ,  B64C2201/044 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2211/00

Abstract: This device, a modular minihelicopter, is a radio-controlled, gas-powered aircraft designed to perform varying missions based upon the functions of interchangeable modular-systems mounted on the minihelicopter's chassis.

Abstract translation: 该装置是一种模块化小型飞行器，是一种无线电控制的气动飞机，旨在根据安装在小型飞机底盘上的可互换模块化系统的功能执行不同的任务。

公开(公告)号：US20100308161A1

公开(公告)日：2010-12-09

申请号：US12804988

申请日：2010-08-02

Applicant: Greg T. Kendall ,  Derek L. Lisoski ,  Walter R. Morgan ,  John A. Griecci

Inventor： Greg T. Kendall ,  Derek L. Lisoski ,  Walter R. Morgan ,  John A. Griecci

IPC: B64C3/38

CPC classification number: B64C3/38 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C17/00 ,  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 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55

Abstract: A span-loaded, highly flexible flying wing, having horizontal control surfaces mounted aft of the wing on extended beams to form local pitch-control devices. Each of five spanwise wing segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other wing segments, to minimize inter-segment loads. Wing dihedral is controlled by separately controlling the local pitch-control devices consisting of a control surface on a boom, such that inboard and outboard wing segment pitch changes relative to each other, and thus relative inboard and outboard lift is varied.

公开(公告)号：US07673831B2

公开(公告)日：2010-03-09

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: B64C39/02

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.

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）。

公开(公告)号：US20100019098A1

公开(公告)日：2010-01-28

申请号：US12179690

申请日：2008-07-25

Applicant: Daniel Ross Collette

Inventor： Daniel Ross Collette

IPC: B64C29/00

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162

Abstract: A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame, attached to which are an engine, gearbox assembly, fan, and a plurality of control vanes. A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle.

Abstract translation: 提供用于无人驾驶飞行器的管道风扇芯，其容纳各种有效载荷。 风扇风扇芯包括框架，附接到发动机，变速箱组件，风扇和多个控制叶片。 框架上的第一表面包括多个连接或电迹线。 多个连接用于可拆卸地附接携带各种有效载荷的各种吊舱。 因此，可以简单地通过将不同的荚移除并附接到固定的车辆核心，使用相同的无人驾驶飞行器来传送各种有效载荷。 这些荚可以成形为形成车辆外部的一部分，并且当荚附接到框架时，它们增强了车辆的空气动力学。

公开(公告)号：US20090050750A1

公开(公告)日：2009-02-26

申请号：US12104432

申请日：2008-04-16

Applicant: Emray R. Goossen

Inventor： Emray R. Goossen

IPC: B64C13/00 ,  B25J9/02

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/126 ,  B64C2201/128 ,  B64C2201/162 ,  B64D1/22

Abstract: A manipulator arm system on a ducted air-fan UAV is disclosed herein. The target site may be accurately located by the UAV, and the manipulator system may accurately locate the payload at the target site. The manipulator arm may select tools from a toolbox located on-board the UAV to assist in payload placement or the execution of remote operations. The system may handle the delivery of mission payloads, environmental sampling, and sensor placement and repair.

Abstract translation: 本文公开了一种管道式空气风扇UAV上的操纵臂系统。 目标站点可以由UAV精确定位，并且机械手系统可以准确地定位目标位置的有效载荷。 操纵臂可以从位于无人机上的工具箱中选择工具，以帮助有效载荷放置或执行远程操作。 该系统可以处理任务有效载荷的交付，环境取样以及传感器的放置和修理。

公开(公告)号：US07299130B2

公开(公告)日：2007-11-20

申请号：US11011001

申请日：2004-12-13

Applicant: Anthony C. Mulligan ,  Christopher D. Troudt ,  Jason Michael K. Douglas

Inventor： Anthony C. Mulligan ,  Christopher D. Troudt ,  Jason Michael K. Douglas

IPC: G01C21/26

CPC classification number: G05D1/0094 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/205 ,  B64C2201/208

Abstract: Methods and apparatuses provide surveillance of a convoy. At least one unmanned aerial vehicle (UAV) obtains images around the convoy's position to provide information about potential hostile activity while the UAV follows a generally curvilinear path around the convoy as instructed by one of the convoy vehicles. Path planner algorithm software is executed by the controlling convoy vehicle in which position and velocity information regarding the unmanned aerial vehicle and the convoy are processed to determine values of control variables. The determined values are sent to the unmanned aerial vehicle over a wireless communications channel. The path of the surveillance vehicle may be changed in order to provide evasive measures to avoid an attack on the surveillance vehicle by an adversary.

Abstract translation: 方法和设备对车队进行监视。 至少一架无人驾驶飞行器（UAV）获取围绕车队位置的图像，以提供关于潜在敌对行为的信息，而无人机按照车队车辆指示的方式沿着车队周围的大致曲线路径。 路径规划器算法软件由控制车队车辆执行，其中处理关于无人机和车队的位置和速度信息以确定控制变量的值。 所确定的值通过无线通信信道发送到无人驾驶飞行器。 监视车辆的路径可能会改变，以便提供回避措施，以避免对手对监控车辆的攻击。

公开(公告)号：US06931247B2

公开(公告)日：2005-08-16

申请号：US09789450

申请日：2001-02-20

Applicant: Earl C. Cox ,  Kyle D. Swanson

Inventor： Earl C. Cox ,  Kyle D. Swanson

IPC: B64C39/00 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/02 ,  B64C39/10 ,  B64D27/24 ,  B64D31/06 ,  G05D1/00 ,  H04B7/185 ,  H04Q7/20

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: This disclosure provides a solar rechargeable aircraft that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Traveling at relatively slow speeds, and 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. 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. The aircraft includes hinges and actuators capable of providing an adjustable dihedral for the wing. The actuators can be motors or control surfaces. Alternately, the actuators can be movable masses within the wing, which may be capable of deforming the wing to alter the aerodynamics of the wing, and thereby actuate the hinges. Because of wing dihedral, the aircraft includes motors both above and below the center of drag, and the aircraft uses differential thrust to control aircraft pitch. The aircraft has a wide variety of applications, which include serving as a long term high altitude platform that serves to link a ground station using radio wave signals and a satellite using optical signals.

Abstract translation: 本公开提供了一种太阳能可再充电飞机，其生产便宜，是可操纵的，并且几乎可以无限期地保持空中飞行。 首选飞机是一个装有跨距的飞翼，没有机身或方向舵。 以相对较慢的速度行驶，并且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动推力来转动。 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。 飞机包括铰链和致动器，能够为机翼提供可调节的二面体。 执行器可以是电机或控制面。 或者，致动器可以是机翼内的可移动质量块，其可以使机翼变形以改变机翼的空气动力学，从而致动铰链。 由于机翼二面体，飞机包括在阻力中心上方和下方的电机，飞机使用差速推力来控制飞机俯仰。 该飞机具有广泛的应用，其中包括作为长期高空平台，用于使用无线电波信号连接地面站和使用光信号的卫星。

公开(公告)号：US06883750B2

公开(公告)日：2005-04-26

申请号：US10620793

申请日：2003-07-16

Applicant: Yuriy Gmirya

Inventor： Yuriy Gmirya

IPC: B64C29/00 ,  B64C39/02 ,  B64D35/04 ,  B64D27/00

CPC classification number: F16H1/22 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165 ,  B64D35/04

Abstract: A powerplant system for a vehicle such as a hybrid UAV includes a miniature gas turbine engine and a gearbox assembly. The engine is mounted to the gearbox assembly through a support structure which provides for pivotal movement of the engine relative thereto. The input gear is engaged with two gears such that the pivoted engine arrangement permits the input gear to float until gear loads between the input gear and the first and second gear are balanced. Regardless of the gear teeth errors or gearbox shaft misalignments the input gear will float and split the torque between the two gears.

Abstract translation: 用于诸如混合UAV的车辆的动力装置系统包括微型燃气涡轮发动机和齿轮箱组件。 发动机通过支撑结构安装到齿轮箱组件，该支撑结构提供发动机相对于其的枢转运动。 输入齿轮与两个齿轮接合，使得枢转的发动机装置允许输入齿轮浮动，直到输入齿轮与第一和第二齿轮之间的齿轮负载平衡。 齿轮齿轮误差或齿轮箱轴不对准，输入齿轮将浮动并分离两个齿轮之间的转矩。

公开(公告)号：US20040211862A1

公开(公告)日：2004-10-28

申请号：US10423187

申请日：2003-04-25

Inventor： Daryl B. Elam

IPC: B64D041/00

CPC classification number: A63H27/02 ,  B64C39/024 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/167 ,  B64D27/24 ,  Y02T50/44 ,  Y02T50/62

Abstract: An unmanned aerial vehicle, such as a remotely-piloted airplane, includes lift-producing wings that have batteries embedded or otherwise located within them. Locating the batteries within the wings allows more efficient use of the interior space of the unmanned vehicle. Space within a fuselage of the vehicle, which would otherwise be used for batteries, may be used for other components. Alternatively, fuselage, weight and/or size of the unmanned aerial vehicle may be reduced. In addition, locating the batteries within the wings may provide better structural performance of the wings, and/or may allow characteristics of the wings, such as inertia and moments, to be optimized.

Abstract translation: 诸如遥控飞机的无人驾驶飞行器包括具有嵌入或以其他方式位于其中的电池的升降机翼。 将电池放置在机翼内可以更有效地利用无人驾驶车辆的内部空间。 车辆的机身中的空间，否则将用于电池，可用于其他部件。 或者，可以减少无人驾驶飞行器的机身，重量和/或尺寸。 此外，将电池定位在机翼内可以提供更好的机翼的结构性能，和/或可以允许优化机翼的特性，例如惯性和力矩。

公开(公告)号：US06575402B1

公开(公告)日：2003-06-10

申请号：US10124572

申请日：2002-04-17

Applicant: Mark Winfield Scott

Inventor： Mark Winfield Scott

IPC: B64C1500

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C29/0025 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165 ,  B64D33/08 ,  F01P5/02 ,  F01P2050/20

Abstract: A cooling system for a hybrid aircraft includes an inlet which extends through the body to communicate airflow to a powerplant subsystem and out through an exhaust within a rotor duct. In a hover mode, there is a significant low-pressure area created inside the rotor duct by the rotor system. The low-pressure area within the rotor duct assists in drawing air through the inlet and over the engine via the exhaust. A cooling fan is located adjacent the inlet to augment cooling-air flow. The cooling fan is smaller than conventional practice because it does not have to provide the entire pressure difference to force air-cooling flow over the engine. In a transition mode, the low-pressure area created inside the rotor duct decreases but ram air pressure through the inlet increases. In a forward flight mode, the pressure inside the rotor duct is approximately atmospheric but significant ram air is provided from the inlet due to forward flight speed.

Abstract translation: 用于混合动力飞行器的冷却系统包括延伸穿过主体以将气流传送到动力装置子系统并通过转子管道内的排气流出的入口。 在悬停模式中，通过转子系统在转子管道内产生显着的低压区域。 转子管道内的低压区域有助于通过进气口抽吸空气，并通过排气口将引擎通过发动机。 冷却风扇位于入口附近以增加冷却空气流量。 冷却风扇比传统惯例要小，因为它不必提供整个压力差来强制空气冷却流过发动机。 在过渡模式中，转子管道内产生的低压区域减小，但通过入口的冲压空气压力增加。 在向前飞行模式中，转子管道内的压力大致为大气压，但是由于向前的飞行速度，从入口提供显着的冲压空气。