公开(公告)号：US20170029111A1

公开(公告)日：2017-02-02

申请号：US15264487

申请日：2016-09-13

Applicant: Astigan Limited

Inventor： Andrew Charles ELSON

IPC: B64D5/00 ,  B64C39/02 ,  B64B1/40

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: An embodiment of an unmanned aerial vehicle, which may be connected to a lighter-than-air carrier, may have a ratio of a lifting force of the carrier to a weight of the vehicle from 1.1:1 to 3:1. The vehicle, excluding payload, may have a mass of from 30 kg to 150 kg. The vehicle may have a wingspan of from 20 m to 60 m.

Abstract translation: 可以连接到轻型承载人的无人驾驶飞行器的实施例可以具有从1.1:1到3:1的载体的提升力与车辆重量之比。 车辆（不包括有效载荷）的质量可能为30公斤至150公斤。 车辆可能具有20米至60米的翼展。

公开(公告)号：US20170008625A1

公开(公告)日：2017-01-12

申请号：US15164718

申请日：2016-05-25

Applicant: Orville Olm ,  Zenon Dragan

Inventor： Orville Olm ,  Zenon Dragan

IPC: B64C29/02 ,  B64C3/56 ,  B64C3/32 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C3/56 ,  B64C39/024 ,  B64C39/12 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/20 ,  Y02T50/14

Abstract: A vertical takeoff and landing (VTOL) unmanned aircraft system (UAS) may be uniquely capable of VTOL via a folded wing design while also configured for powered flight as the wings are extended. In a powered flight regime with wings extended, the VTOL UAS may maintain controlled powered flight as a twin pusher canard design. In a zero airspeed (or near zero airspeed) nose up attitude in a VTOL flight regime with the wings folded, the unmanned aircraft system may maintain controlled flight using main engine thrust as well as vectored thrust as a vertical takeoff and landing aircraft. An airborne transition from VTOL flight regime to powered flight and vice versa may allow the VTOL UAS continuous controlled flight in each regime.

Abstract translation: 垂直起飞和着陆（VTOL）无人驾驶飞机系统（UAS）可以通过折翼设计独特地实现垂直起降，同时还可以在机翼延伸时配置为动力飞行。 在具有扩展翼的动力飞行机构中，VTOL UAS可以保持受控的动力飞行作为双推杆的设计。 无人驾驶飞机系统可以以垂直起降飞行系统以零空速（或近零空速）起飞的姿态折叠起来，使用主发动机推力以及作为垂直起降飞机的向心推力来维持受控飞行。 从空中飞行任务飞行状态到动力飞行的空降过渡，反之亦然，可能使VTOL UAS在每个制度中持续控制飞行。

公开(公告)号：US09540121B2

公开(公告)日：2017-01-10

申请号：US14631137

申请日：2015-02-25

Applicant: Cisco Technology, Inc.

Inventor： Charles Calvin Byers ,  Gonzalo Salgueiro

IPC: G06F19/00 ,  B64C27/08 ,  B64F5/00 ,  B64C39/02 ,  B64F1/12

CPC classification number: B64F5/60 ,  A47G29/14 ,  B64C39/024 ,  B64C2201/00 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/08 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/162 ,  B64C2201/18 ,  B64D1/00 ,  B64F1/00 ,  B64F1/04 ,  B64F1/12 ,  G06Q10/0832

Abstract: In one embodiment, a controller instructs an unmanned aerial vehicle (UAV) docked to a landing perch to perform a pre-flight test operation of a pre-flight test routine. The controller receives sensor data associated with the pre-flight test operation from one or more force sensors of the landing perch, in response to the UAV performing the pre-flight test operation. The controller determines whether the sensor data associated with the pre-flight test operation is within an acceptable range. The controller causes the UAV to launch from the landing perch based in part on a determination that UAV has passed the pre-flight test routine.

Abstract translation: 在一个实施例中，控制器指示停靠在着陆鲈鱼上的无人驾驶飞行器（UAV）执行飞行前测试程序的飞行前测试操作。 响应于执行飞行前测试操作的UAV，控制器从登陆鲈鱼的一个或多个力传感器接收与飞行前测试操作相关联的传感器数据。 控制器确定与飞行前测试操作相关联的传感器数据是否在可接受的范围内。 控制器部分地基于无人机已经通过飞行前测试程序的确定，使无人机从起落架起飞。

公开(公告)号：US09527596B1

公开(公告)日：2016-12-27

申请号：US14716785

申请日：2015-05-19

Applicant: Richard D. Adams

Inventor： Richard D. Adams

IPC: B64D17/00 ,  B64C11/00 ,  B64C39/02 ,  B64C3/56

CPC classification number: B64D17/00 ,  B64C3/56 ,  B64C11/001 ,  B64C39/024 ,  B64C2201/107 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/185 ,  B64C2201/203

Abstract: A remotely controlled UAV is disclosed. The UAV includes a parachute, with a cylindrical power and control module suspended vertically below the parachute. In one embodiment, a propulsion source is mounted on top of the power and control module with control lines connected to the module below the propulsion source, and in another embodiment the power and control module is suspended from a point above a propulsion source. The UAV may be flown under a parachute and guided by remote control, or the control module (fuselage) may be released from the parachute and extendable fixed wings deployed to enable the UAV to be flown as a fixed wing vehicle.

Abstract translation: 公开了遥控无人机。 无人机包括一个降落伞，一个圆柱形的电源和控制模块垂直悬挂在降落伞下方。 在一个实施例中，推进源安装在功率和控制模块的顶部，其控制线连接到推进源下方的模块，并且在另一个实施例中，功率和控制模块从推进源上方的点悬挂。 无人机可以在降落伞下飞行并由遥控器引导，或者控制模块（机身）可以从降落伞释放并且可伸展的固定翼部署以使无人机作为固定翼车辆飞行。

公开(公告)号：US20160167780A1

公开(公告)日：2016-06-16

申请号：US14908850

申请日：2014-08-07

Applicant: UNIT 1SRL

Inventor： Pietro GIOVENGA

IPC: B64C29/00 ,  B64C39/02 ,  B64C3/54

CPC classification number: B64C29/0033 ,  B64C3/385 ,  B64C3/54 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/08 ,  Y02T50/14

Abstract: A convertiplane has the ability to take off like a helicopter and then fly horizontally like a conventional aircraft. The aircraft includes a variable incidence front wing of variable span located below the fuselage and mounted on a structure in the form of a venturi tube, a rear wing having two propellers for controlling the stability of the vehicle in pitch and roll installed therein, two counter-rotating, pivotally mounted ducted propellers equipped with four flaps orthogonal to each other provided on the sides of the cockpit, engines placed behind the cockpit close to the center of gravity, a static balancing system for controlling the center of gravity of the aircraft consisting of a weight placed in the lower part of the fuselage, self-propelled on the track rack longitudinally to the fuselage, and a digital flight control system.

Abstract translation: 转换飞机具有像直升机一样起飞的能力，然后像常规飞机一样水平飞行。 飞机包括位于机身下方的可变跨度的可变入射前翼，并安装在文丘里管形式的结构上，后翼具有两个螺旋桨，用于控制安装在其中的俯仰和滚动中的车辆的稳定性，两个计数器 旋转的，枢转安装的管道螺旋桨，其配备有四个彼此正交的翼片，设置在驾驶舱的两侧，放置在靠近重心的驾驶舱后面的发动机，用于控制飞行器重心的静态平衡系统， 放置在机身下部的重量，纵向自动推进到机身，以及数字飞行控制系统。

公开(公告)号：US09365290B1

公开(公告)日：2016-06-14

申请号：US14837866

申请日：2015-08-27

Applicant: MARTIN UAV, LLC

Inventor： Stephen Morris

IPC: B64C29/00 ,  B64C29/02 ,  B64C11/00 ,  G05D1/08 ,  G05D1/10

CPC classification number: B64C29/02 ,  B64C11/001 ,  B64C39/024 ,  B64C2009/005 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/162 ,  G05D1/0858 ,  G05D1/102

Abstract: An aircraft includes a fuselage, a wing, a ducted fan and a controller. The wing and the ducted fan are coupled to the fuselage. The controller is operable to control the aircraft in a vertical flight mode, a horizontal flight more, and transition the aircraft from the vertical flight mode to the horizontal flight mode.

Abstract translation: 飞机包括机身，机翼，风扇和控制器。 机翼和管道风扇耦合到机身。 控制器可操作以以垂直飞行模式，水平飞行更多地控制飞行器，并且将飞行器从垂直飞行模式转换到水平飞行模式。

公开(公告)号：US09297333B2

公开(公告)日：2016-03-29

申请号：US14468406

申请日：2014-08-26

Applicant: The Boeing Company

Inventor： Evan J. Filter

IPC: F02C7/04 ,  B64D33/02 ,  F02K1/06 ,  F01D25/24 ,  F01D25/00 ,  F02C7/042

CPC classification number: F02K1/06 ,  B64C11/001 ,  B64C2201/162 ,  B64D33/02 ,  B64D2033/0286 ,  F01D25/005 ,  F01D25/24 ,  F02C7/042

Abstract: A variable geometry inlet for a ducted fan is selectively transitionable between a first and second mode. The inlet includes a retractable ring that extends circumferentially about the inlet and is selectively movable between an axially extended position in the first mode and an axially retracted position in the second mode. A tube extends circumferentially proximate the retractable ring, and is pressurizable to a relatively deflated state in the first mode and to a relatively inflated state in the second mode. A stretchable skin extends circumferentially proximate the retractable ring, and is elastically deformable in at least a circumferential direction about a longitudinal axis of the fan. A leading edge of the inlet in the first mode is defined by the stretchable skin disposed against a forward edge of the retractable ring, and in the second mode by the stretchable skin disposed against at least a portion of the tube.

Abstract translation: 用于管道风扇的可变几何入口可在第一和第二模式之间选择性地转换。 所述入口包括可围绕所述入口周向延伸的可伸缩环，并且可选择地在所述第一模式中的轴向延伸位置和所述第二模式中的轴向缩回位置之间移动。 管子周向地延伸靠近可伸缩环延伸，并且在第一模式中可加压到相对放气的状态，并且在第二模式中可以相对膨胀。 可拉伸的皮肤周向地延伸靠近可伸缩环延伸，并且可围绕风扇的纵向轴线在至少周向方向上弹性变形。 第一模式中的入口的前缘由抵靠可伸缩环的前边缘设置的可伸展皮肤限定，并且在第二模式中由靠在管的至少一部分上设置的可伸展皮肤限定。

公开(公告)号：US09169014B2

公开(公告)日：2015-10-27

申请号：US13569360

申请日：2012-08-08

Applicant: Andrew Charles Elson ,  Peter Davidson

Inventor： Andrew Charles Elson ,  Peter Davidson

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：US08991740B2

公开(公告)日：2015-03-31

申请号：US13846074

申请日：2013-03-18

Applicant: Draganfly Innovations Inc.

Inventor： Orville Olm ,  Greg Wood ,  Zenon Dragan

IPC: B64C37/00 ,  B60F5/02 ,  B60B1/00

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：US20140312164A1

公开(公告)日：2014-10-23

申请号：US13745322

申请日：2013-01-18

Applicant: JOSHUA M. GIBSON ,  SAGAR JASU PANARA

Inventor： JOSHUA M. GIBSON ,  SAGAR JASU PANARA

IPC: B64C39/02 ,  B64C27/00 ,  B64D47/08

CPC classification number: B64D47/08 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/203

Abstract: A portable unmanned aerial vehicle or aircraft, capable of being easily carried by a single individual by means of a mounting device, which can be fastened on a belt or strap. The aerial vehicle comprises a wing attached at one end to a fan or turbine assembly. The fan or turbine assembly may be electrically driven, with power supplied by one or more batteries. In flight, the fan or turbine assembly causes the aerial vehicle to rotate around its center-of-mass (COM), with lift provided by the wing as it rotates. A camera is located on the aircraft at or near the COM.

Abstract translation: 便携式无人驾驶飞行器或飞机，能够通过安装装置容易地由单个个体携带，该固定装置可紧固在皮带或皮带上。 该飞行器包括在一端附接到风扇或涡轮机组件的翼。 风扇或涡轮组件可以被电驱动，由一个或多个电池供电。 在飞行中，风扇或涡轮机组件使飞行器绕其质心（COM）旋转，随着机翼旋转时提供的升力。 相机位于COM上或附近的飞机上。