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：US20100012776A1

公开(公告)日：2010-01-21

申请号：US11752497

申请日：2007-05-23

Applicant: David C. Hursig ,  Steven D. Martinez

Inventor： David C. Hursig ,  Steven D. Martinez

IPC: B64C29/00

CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162 ,  B64D45/04 ,  G05D1/0653 ,  G05D1/0858

Abstract: Takeoff and landing modes are added to a flight control system of a Vertical Take-Off and Landing (VTOL) Unmanned Air Vehicle (UAV). The takeoff and landing modes use data available to the flight control system and the VTOL UAV's existing control surfaces and throttle control. As a result, the VTOL UAV can takeoff from and land on inclined surfaces without the use of landing gear mechanisms designed to level the UAV on the inclined surfaces.

Abstract translation: 起飞和着陆（VTOL）无人机（UAV）的飞行控制系统增加起飞和着陆模式。 起飞和着陆模式使用可用于飞行控制系统和VTOL无人机现有控制面和节气门控制的数据。 因此，VTOL无人机可以在倾斜的表面上起飞和着陆，而不需要使用设计成在倾斜表面上对无人机进行平坦化的起落架机构。

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：US20070228214A1

公开(公告)日：2007-10-04

申请号：US11235057

申请日：2005-09-26

Applicant: Dan Horak

Inventor： Dan Horak

IPC: B64F1/04

CPC classification number: B64C39/028 ,  A63H27/14 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/182 ,  B64F1/04

Abstract: Autonomous micro air vehicles surveillance systems are provided. A MAV system of one embodiment includes an MAV and a launch pad. The MAV has an engine that is adapted to power the MAV. The launch pad has a starter that is adapted to start the engine in the MAV when the MAV is resting on a launching surface of the launch pad. The launch pad further has a battery to power the starter.

Abstract translation: 提供自动微型飞行器车辆监视系统。 一个实施例的MAV系统包括MAV和发射台。 MAV具有适用于为MAV供电的发动机。 发射台具有一个启动器，当MAV在发射台的发射表面上时，该启动器适于在MAV中启动发动机。 发射台还有一个电池为起动器供电。

公开(公告)号：US07261257B2

公开(公告)日：2007-08-28

申请号：US10996799

申请日：2004-11-23

Applicant: Elie Helou, Jr.

Inventor： Elie Helou, Jr.

IPC: B64C1/22

CPC classification number: B64C1/10 ,  B64C1/00 ,  B64C1/061 ,  B64C1/065 ,  B64C39/02 ,  B64C39/024 ,  B64C2001/0072 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/167 ,  B64C2211/00 ,  Y02T50/43

Abstract: An aircraft for carrying at least one rigid cargo container includes a beam structure with a forward fuselage attached to the forward end of the beam structure and an empennage attached to the rearward end of the beam structure. Wings and engines are mounted relative to the beam structure and a fairing creates a cargo bay able to receive standard sized intermodal cargo containers. Intermodal cargo containers of light construction and rigid structure are positioned within the cargo bay and securely mounted therein. The beam structure is designed to support flight, takeoffs and landings when the aircraft is empty but requires the added strength of the containers securely mounted to the beam structure when the aircraft is loaded. The aircraft is contemplated to be a drone.

Abstract translation: 用于承载至少一个刚性货物集装箱的飞机包括具有附接到梁结构的前端的前机身的梁结构和附接到梁结构的后端的后轮。 翼和发动机相对于梁结构安装，整流罩产生能够接收标准尺寸的联运货物集装箱的货舱。 轻型结构和刚性结构的多式联运集装箱定位在货舱内并牢固地安装在货舱内。 梁结构设计用于在飞机空置时支持飞行，起飞和着陆，但是当飞机加载时，需要将集装箱的强度牢固地安装到梁结构上。 飞机被认为是无人机。

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：US20040129833A1

公开(公告)日：2004-07-08

申请号：US10626697

申请日：2003-07-25

Applicant: C.R.F. SOCIETA CONSORTILE PER AZIONI

Inventor： Piero Perlo ,  Denis Bollea ,  Roberto Finizio ,  Cosimo Carvignese ,  Elena Balocco

IPC: B64C039/00

CPC classification number: B64C29/02 ,  B64C27/20 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165

Abstract: VTOL micro-aircraft comprising a first and a second ducted rotor mutually aligned and distanced according to a common axis and whose propellers are driven in rotation in mutually opposite directions. Between the two ducted rotors are positioned a fuselage and a wing system formed by wing profiles forming an X or an H configuration and provided with control flaps.

Abstract translation: VTOL微型飞机包括第一和第二导管转子，该第一和第二导管转子根据公共轴相互对准和间隔，并且其螺旋桨沿彼此相反的方向旋转驱动。 在两个管状转子之间设置有由机翼轮廓形成的机身和机翼系统，所述机翼轮廓形成X或H构造并设置有控制翼片。

公开(公告)号：US06634593B2

公开(公告)日：2003-10-21

申请号：US10218885

申请日：2002-08-14

Applicant: Marc Lepretre ,  Georges Chastang

Inventor： Marc Lepretre ,  Georges Chastang

IPC: B64C2720

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165

Abstract: The invention concerns a remote-controlled flying machine, in particular for surveillance and inspection, capable of hovering and comprising a spherical open-worked resistant shroud integral with a cylindrical fairing wherein rotates a propeller powered by an engine housed in a fuselage secured to the fairing with radial arms and straightening vanes.

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。

公开(公告)号：US06450445B1

公开(公告)日：2002-09-17

申请号：US09868008

申请日：2001-10-12

Applicant: Paul S. Moller

Inventor： Paul S. Moller

IPC: B64C2900

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/162

Abstract: A robotic or remotely controlled flying platform (10) with reduced drag stabilizing control apparatus constructed having an air duct (12) with an air intake (14) on the top and an exhaust (16) at the bottom, containing supported therein a clockwise rotating fan (22) and a counter-clockwise rotating fan (24). Directly below the perimeter of the air duct exhaust are mounted a plurality of trough shaped air deflection assemblies (32) each including a rotatably adjustable half trough (44) for selectively scooping a portion of the drive air, and a stationary adjacent half trough (36) for receiving the scooped drive air and redirecting it outward and upward from the air duct. A centrally positioned plate (112) has a plurality of rods (106), each pivotably connected between the plate (74) and a corresponding lever associated with each of the adjustable half troughs (44) so as to couple the adjustable half trough (44) in or out of the drive air steam according to the position of the plate (74), thereby providing control over the pitch and roll of the flying platform. The plate is driven by first and second motors responding to input control signals. The control signals also direct the yaw of the flying platform by selectively providing independent speed control to each of the clockwise and counter clockwise fan motors resulting in duct rotation in a clockwise or counter clockwise direction accordingly.

Abstract translation: 一种机器人或远程控制的飞行平台（10），其具有减少的阻力稳定控制装置，其构造为具有在顶部具有进气口（14）的空气管道（12）和底部的排气（16），其包含支撑在其中的顺时针旋转 风扇（22）和逆时针旋转的风扇（24）。 安装有多个槽形的空气偏转组件（32），每个包括可旋转的可调节的半槽（44），用于选择性地舀取驱动空气的一部分，以及固定的相邻半槽（36） ），用于接收舀取的驱动空气并将其从空气管道向外和向上引导。 中心定位的板（112）具有多个杆（106），每个杆（106）可枢转地连接在板（74）和与可调节半槽（44）中的每一个相关联的相应杆，以便联接可调节半槽（44） ）根据板（74）的位置进入或离开驱动空气蒸汽，从而提供对飞行平台的俯仰和滚动的控制。 该板由响应于输入控制信号的第一和第二电动机驱动。 控制信号还通过选择性地为每个顺时针和逆时针风扇电动机提供独立的速度控制来引导飞行平台的偏转，从而导致管道沿顺时针或逆时针方向旋转。