公开(公告)号：US20140061362A1

公开(公告)日：2014-03-06

申请号：US13846074

申请日：2013-03-18

Applicant: DRAGANFLY INNOVATIONS INC.

Inventor： Orville OLM ,  Greg WOOD ,  Zenon DRAGAN

IPC: B60F5/00

CPC classification number: B64C37/00 ,  B60B1/00 ,  B60F5/02 ,  B60Y2200/80 ,  B64C39/005 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162

Abstract: A combination rotor and wheel assembly for an unmanned vehicle with ground and aerial mobility has a rotor arm adapted to be attached at an inner end thereof to a vehicle body. A rotor is rotatably connected to an outer end of the rotor arm about a rotor axis, and a rotor drive mounted on the rotor arm rotates the rotor such that the rotor exerts an upward lift force on the rotor arm. An open spoked wheel is rotatably connected about the rotor axis independent of the rotor The diameter of the wheel is greater than that of the rotor, and a bottom edge of the wheel is below the rotor. A wheel drive rotates the wheel. Vehicles can have various numbers and orientations of the rotor and wheel assembly to provide aerial and ground mobility.

Abstract translation: 用于具有地面和空中移动性的无人驾驶车辆的组合转子和车轮组件具有适于在其内端附接到车体的转子臂。 转子围绕转子轴线可旋转地连接到转子臂的外端，并且安装在转子臂上的转子驱动器使转子旋转，使得转子在转子臂上施加向上的升力。 开放式的轮轮围绕转子轴线可旋转地连接，与转子无关。轮的直径大于转子的直径，并且车轮的底部边缘在转子下方。 轮驱动器旋转车轮。 车辆可以具有转子和车轮组件的各种数量和方向，以提供空中和地面的移动性。

公开(公告)号：US20140021288A1

公开(公告)日：2014-01-23

申请号：US13569360

申请日：2012-08-08

Applicant: Andrew Charles ELSON ,  Peter Davison

Inventor： Andrew Charles ELSON ,  Peter Davison

IPC: B64D5/00 ,  B64C39/02

CPC classification number: B64D5/00 ,  B64B1/40 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/123 ,  B64C2201/162 ,  B64C2201/187 ,  B64D2211/00

Abstract: A method of launching a powered unmanned aerial vehicle at an altitude of at least 13,000 m, the method comprising lifting the vehicle by attachment to a lighter-than-air carrier from a substantially ground-level location to an elevated altitude, causing the vehicle to detach from the carrier while the velocity of the vehicle relative to the carrier is substantially zero, the vehicle thereafter decreasing in altitude as it accelerates to a velocity where it is capable of preventing any further descent and can begin independent sustained flight.

Abstract translation: 一种在至少13000米的高度上发射供电的无人驾驶飞行器的方法，该方法包括通过将空载承载装置从基本上地平面的位置附近提升到升高的高度，使得车辆 当车辆相对于承载件的速度基本上为零时，车辆离开载体，然后车辆随着其高度减小到能够防止任何进一步下降并且可以开始独立的持续飞行的速度。

公开(公告)号：US08408489B2

公开(公告)日：2013-04-02

申请号：US13466327

申请日：2012-05-08

Applicant: Harry George Dennis Gosling

Inventor： Harry George Dennis Gosling

IPC: B64C15/00

CPC classification number: B64C39/062 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/162

Abstract: An airborne vehicle having a wing-body which defines a wing-body axis and appears substantially annular when viewed along the wing-body axis, the interior of the annulus defining a duct which is open at both ends. A propulsion system is provided comprising one or more pairs of propulsion devices, each pair comprising a first propulsion device mounted to the wing-body and positioned on a first side of a plane including the wing-body axis, and a second propulsion device mounted to the wing-body and positioned on a second side of the plane including the wing-body axis.

Abstract translation: 一种机载车辆，其具有限定翼体轴线的翼体，并且当沿翼体轴线观察时呈现大致环形，所述环形空间的内部限定在两端敞开的管道。 提供了包括一对或多对推进装置的推进系统，每对推进装置包括安装到翼体上并定位在包括翼体轴线的平面的第一侧上的第一推进装置，以及安装到 翼体并且定位在包括翼体轴线的平面的第二侧上。

公开(公告)号：US08333348B1

公开(公告)日：2012-12-18

申请号：US12705691

申请日：2010-02-15

Applicant: Gerald D. Miller

Inventor： Gerald D. Miller

IPC: B64C23/00

CPC classification number: B64C13/16 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165 ,  Y02T50/44

Abstract: The disclosure provides in one embodiment a wing tip device for a wing of an air vehicle. The device comprises a tip tail element, a boom element attaching the tip tail element to a wing tip, a hinge element connecting the tip tail element to the boom element, and an actuator element connected to the hinge element. One or more wing load sensors sense wing loads, and a flight control system controls the actuator element. A load alleviation method and system for an air vehicle are also provided.

Abstract translation: 本公开在一个实施例中提供了用于机动车辆的机翼的翼尖装置。 该装置包括尖端尾部元件，将尖端尾部元件附接到翼尖的吊杆元件，将末端尾部元件连接到吊杆元件的铰链元件以及连接到铰链元件的致动器元件。 一个或多个机翼负载传感器感测机翼负载，飞行控制系统控制致动器元件。 还提供了一种用于空中交通工具的负载减轻方法和系统。

公开(公告)号：US08310117B2

公开(公告)日：2012-11-13

申请号：US13244583

申请日：2011-09-25

Applicant: Robert S. Violett

Inventor： Robert S. Violett

IPC: H02K9/00 ,  H02K5/18 ,  H02K5/20

CPC classification number: B64D27/24 ,  A63H27/02 ,  A63H29/16 ,  A63H29/22 ,  B64C2201/042 ,  B64C2201/162 ,  B64D33/08 ,  H02K5/18 ,  H02K5/20 ,  H02K7/14 ,  H02K11/33 ,  Y02T50/62

Abstract: A power plant for a jet-type model airplanes and UAVs includes an electric motor and a cover. The cover receives a portion of the electric motor and a sleeve into which the electric motor is inserted. The sleeve has a plurality of fins to dissipate heat and create openings into the cover. Air from the fan rotor passes through the openings to cool an electronic speed control member and exits a rear opening in the cover. The cover may also have additional openings for air to enter into the cover.

Abstract translation: 用于喷气型模型飞机和无人机的发电厂包括电动机和盖子。 盖子容纳电动机的一部分和插入电动马达的套筒。 套筒具有多个散热片以散热并在盖中产生开口。 来自风扇转子的空气通过开口以冷却电子速度控制构件并离开盖中的后开口。 盖子还可以具有用于空气进入盖子的附加开口。

公开(公告)号：US20120234968A1

公开(公告)日：2012-09-20

申请号：US13442544

申请日：2012-04-09

Applicant: FRICK A. SMITH

Inventor： FRICK A. SMITH

IPC: B64C29/00 ,  B64C5/04 ,  B64D35/04

CPC classification number: B64C29/0033 ,  B64C1/1415 ,  B64C1/1476 ,  B64C27/22 ,  B64C27/26 ,  B64C27/28 ,  B64C27/52 ,  B64C27/82 ,  B64C29/00 ,  B64C29/0016 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/088 ,  B64C2201/10 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D17/24 ,  B64D17/34 ,  B64D17/62 ,  B64D17/64 ,  B64D17/80 ,  B64D27/02 ,  B64D31/00 ,  B64D35/04

Abstract: An aircraft may have a fuselage, a left wing extending from the fuselage, a right wing extending from the fuselage, a tail section extending from a rear portion of the fuselage, and a first engine and a second engine operably connected by a common driveshaft, wherein the first and second engines are configured for freewheeling such that if one of the first and second engines loses power the other of the first and second engines continues to power the aircraft.

Abstract translation: 飞机可以具有机身，从机身延伸的左翼，从机身延伸的右翼，从机身的后部延伸的尾部，以及通过共同的驱动轴可操作地连接的第一发动机和第二发动机， 其中所述第一和第二发动机被配置为自由转动，使得如果所述第一和第二发动机中的一个发动机失去动力，则所述第一和第二发动机中的另一个继续为所述飞行器供电。

公开(公告)号：US08225822B2

公开(公告)日：2012-07-24

申请号：US12271527

申请日：2008-11-14

Applicant: Erik M Erben ,  Janet Trujillo ,  Jonathan M Wong

Inventor： Erik M Erben ,  Janet Trujillo ,  Jonathan M Wong

IPC: B65B3/04 ,  B65B31/00 ,  B64D37/00

CPC classification number: B64F1/28 ,  B64C2201/162

Abstract: An electric fueling system for a vehicle that requires a metered amount of fuel comprising: a control box comprising a plurality of switches, a battery, a controller circuit card assembly, and a plurality of light emitting diodes; a flow meter coupled to the control box and to a vehicle; a pump coupled to the flow meter, to the control box, and to a fuel canister; and a housing that contains the control box, flow meter, and pump. The controller circuit card assembly has control logic such that the controller circuit card assembly manages the functions of setting the fuel level, de-fueling the vehicle, fueling the vehicle, and changing the brightness of the light emitting diodes, wherein the control logic receives inputs from the plurality of switches, the flow meter, the battery, and the pump and provides outputs to the plurality of light emitting diodes and the pump.

Abstract translation: 一种用于需要计量燃料的车辆的电动燃料供给系统，包括：包括多个开关的控制箱，电池，控制器电路卡组件和多个发光二极管; 耦合到控制箱和车辆的流量计; 耦合到流量计，控制箱和燃料罐的泵; 以及包含控制箱，流量计和泵的外壳。 控制器电路卡组件具有控制逻辑，使得控制器电路卡组件管理设置燃料水平，减少车辆燃料，燃料车辆和改变发光二极管的亮度的功能，其中控制逻辑接收输入 来自多个开关，流量计，电池和泵，并且向多个发光二极管和泵提供输出。

公开(公告)号：US20120056040A1

公开(公告)日：2012-03-08

申请号：US13257810

申请日：2010-03-22

Applicant: David Brotherton-Ratcliffe ,  Jerzy Lelusz

Inventor： David Brotherton-Ratcliffe ,  Jerzy Lelusz

IPC: B64C29/00 ,  B64C13/00 ,  B64C13/20 ,  B64C27/20 ,  B64D27/24

CPC classification number: B64C29/0016 ,  B64C11/001 ,  B64C27/08 ,  B64C27/20 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/10 ,  B64D27/24 ,  B64D47/08 ,  G05D1/042 ,  Y02T50/64

Abstract: An electric and hybrid Vertical-Take Off and Landing (“VTOL”) aircraft is disclosed comprising a plurality of small Electric Ducted Fans (“EDFs”) of various sizes and orientations. The thrust of each fixed EDF is individually controlled by modulation of motor power by one or more onboard microcomputers connected to a plurality of onboard laser distance measuring sensors, at least three onboard three-axis accelerometers and at least one GPS thereby allowing extremely precise and safe VTOL operation. The aircraft may be employed to allow robotic and passenger vehicles to transition extremely quickly between normal linear flight and VTOL and tb operate in extreme and gusty conditions.

Abstract translation: 公开了一种具有各种尺寸和方向的多个小型电风扇（“EDF”）的电动和混合垂直起飞和着陆（“垂直起落架”）飞机。 每个固定EDF的推力通过一个或多个连接到多个机载激光距离测量传感器，至少三个板载三轴加速度计和至少一个GPS的机载微型计算机调节电机功率来单独控制，从而允许非常精确和安全 VTOL操作。 飞机可能被允许机器人和乘客车辆在正常线性飞行和垂直起落时间之间极快地转变，并且tb在极端和阵风条件下操作。

公开(公告)号：US08104707B1

公开(公告)日：2012-01-31

申请号：US12190516

申请日：2008-08-12

Applicant: Osgar John Ohanian, III

Inventor： Osgar John Ohanian, III

IPC: B64C29/00

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/162

Abstract: Disclosed herein is a propulsion system, which may be implemented in an air-vehicle, such as a ducted-fan organic air-vehicle. The propulsion system comprises (a) a power source, (b) a fan located within a duct and powered by the power source, (c) a plurality of vanes arranged in an x-clocked configuration and configured to produce control moments from the flow generated by the fan. The maximum control moments, which can be created by the vanes in the x-clocked configuration, are substantially oriented along the flight axes of the air-vehicle or the principle axis of the maximum moment of inertia.

Abstract translation: 本文公开了一种推进系统，其可以在诸如管道式风扇有机机动车辆的空中车辆中实现。 推进系统包括（a）电源，（b）位于管道内并由电源供电的风扇，（c）以x时钟配置布置的多个叶片，并配置成从流动产生控制力矩 由风扇产生。 可以由x时钟配置中的叶片产生的最大控制力矩基本上沿着空中车辆的飞行轴线或最大惯性矩的主轴线定向。

公开(公告)号：US07817497B2

公开(公告)日：2010-10-19

申请号：US12372702

申请日：2009-02-17

Applicant: Dan T. Horak ,  Richard A. Burne

Inventor： Dan T. Horak ,  Richard A. Burne

IPC: G01S3/80

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2201/165 ,  F42B12/365 ,  G01S3/8083

Abstract: Embodiments for determining the bearings to targets from a remote location are disclosed. The apparatus consists of an array of acoustic sensors that is capable of autonomous flight. The array may be large in diameter, approximately one meter or greater. The apparatus is capable of navigating its flight to arrive at a predetermined location, measuring acoustic sound waves emitted by targets both during flight and after landing. The apparatus may then calculate the bearings to the targets and transmit this information to a remote location.

Abstract translation: 公开了从远程位置确定到目标​​的轴承的实施例。 该装置由能够自主飞行的声学传感器阵列组成。 该阵列的直径可以大，大约一米或更大。 该装置能够导航其飞行到达预定位置，测量在飞行中和着陆之后目标发出的声音波。 然后，设备可以计算到目标的轴承并将该信息传送到远程位置。