公开(公告)号：US20150274289A1

公开(公告)日：2015-10-01

申请号：US14231610

申请日：2014-03-31

Applicant: The Boeing Corporation

Inventor： Daniel Ira Newman ,  Roger W. Lacy ,  Robin M. Preator ,  Elia N. Gianopulos ,  Perry Ziegenbein

IPC: B64C27/26 ,  B64C29/00 ,  B64C27/28

CPC classification number: B64C27/26 ,  B64C27/28 ,  B64C29/0008 ,  B64C29/0025 ,  B64C29/0033 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

Abstract: An aircraft takes off, lands, or hovers with at least one wing-mounted thrust-producing device attached to at least one wing of the aircraft and at least two fuselage-mounted thrust-producing devices attached to a fuselage of the aircraft both providing vertical thrust. The aircraft is flown while the at least one wing-mounted thrust-producing device provides horizontal thrust and with the at least two fuselage-mounted thrust-producing devices not providing any thrust.

Abstract translation: 飞机起飞，着陆或悬停，至少有一个安装在飞行器的至少一个机翼上的机翼安装推力产生装置，以及至少两个安装在飞机机体上的机身安装的推力产生装置， 推力。 飞机飞行，同时至少一个机翼安装的推力产生装置提供水平推力，并且至少两个安装有机身的推力产生装置不提供任何推力。

公开(公告)号：US08960592B1

公开(公告)日：2015-02-24

申请号：US13553080

申请日：2012-07-19

Applicant: D. Anthony Windisch

Inventor： D. Anthony Windisch

IPC: B64C29/00 ,  B64D35/00 ,  B64D33/02

CPC classification number: A63H27/06 ,  A63H30/04 ,  B64C29/0025 ,  B64C2201/162 ,  B64C2203/00 ,  B64D35/00

Abstract: An aircraft, such as a radio controlled aircraft, capable of vertical take-off and landing. The aircraft has a compressor in a fuselage that contains an interconnected first and second fans driven by a motor. An intake provides air to the first fan, while a bypass duct directs airflow to the second fan. Air flow from the first fan to the second fan is controlled by a valve, which is operated in tandem with doors in the bypass duct. Nozzles direct air flow out of the compressor in a selected one of a vertical or non-vertical direction for conventional flight or for hover. Hover tubes are provided to adjust the aircraft in pitch, yaw and roll. The hover tubes operate simultaneously with conventional flight controls.

Abstract translation: 飞机，如无线电控制的飞机，能够垂直起飞和着陆。 飞机在机身中具有压缩机，其包含由电动机驱动的互连的第一和第二风扇。 进气口向第一风扇提供空气，而旁路管道将气流引导到第二风扇。 从第一风扇到第二风扇的气流由与旁通管道中的门串并联操作的阀来控制。 喷嘴直接以常规飞行或悬停的垂直或非垂直方向中的一个方式从压缩机流出。 提供悬停管，以调整俯仰，偏航和滚动的飞机。 悬停管与常规飞行控制同时操作。

公开(公告)号：US20150021430A1

公开(公告)日：2015-01-22

申请号：US14507228

申请日：2014-10-06

Applicant: Aurora Flight Sciences Corporation

Inventor： JAMES DONALD PADUANO ,  PAUL NILS DAHLSTRAND ,  JOHN BROOKE WISSLER ,  ADAM WOODWORTH

IPC: B64C3/42 ,  B64C25/10 ,  B64C9/00 ,  B64D27/02 ,  B64C5/02 ,  B64C29/00 ,  B64D43/00

CPC classification number: B64C27/52 ,  B64C3/42 ,  B64C5/02 ,  B64C9/00 ,  B64C13/16 ,  B64C25/10 ,  B64C29/00 ,  B64C29/0033 ,  B64C29/0091 ,  B64C29/02 ,  B64C29/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/187 ,  B64D27/02 ,  B64D43/00

Abstract: A vertical take-off and landing (VTOL) aircraft according to an aspect of the present invention comprises a fuselage, an empennage having an all-moving horizontal stabilizer located at a tail end of the fuselage, a wing having the fuselage positioned approximately halfway between the distal ends of the wing, wherein the wing is configured to transform between a substantially straight wing configuration and a canted wing configuration using a canted hinge located on each side of the fuselage. The VTOL aircraft may further includes one or more retractable pogo supports, wherein a retractable pogo support is configured to deploy from each of the wing's distal ends.

公开(公告)号：US20140367509A1

公开(公告)日：2014-12-18

申请号：US14251850

申请日：2014-04-14

Applicant: Frick A. Smith

Inventor： Frick A. Smith

IPC: B64C27/22 ,  B64C29/00 ,  B64C27/52 ,  B64C39/02 ,  B64D17/34 ,  B64C1/14 ,  B64D17/80 ,  B64D17/62 ,  B64D17/24 ,  B64D27/02 ,  B64D31/00

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：US08820672B2

公开(公告)日：2014-09-02

申请号：US13465948

申请日：2012-05-07

Applicant: Erik Erben ,  Robert Habing ,  Nader Tubbeh

Inventor： Erik Erben ,  Robert Habing ,  Nader Tubbeh

IPC: B64C29/00

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162 ,  G01N1/2273 ,  G01N2001/2279 ,  G01N2001/2285 ,  G01N2001/245

Abstract: Environmental samples are collected and analyzed using an unmanned aerial vehicle (UAV). In some examples, the sample is drawn into engagement with a sensor onboard a UAV by the existing fluid flow generated by a rotor fan through a duct of a ducted fan of the UAV. The quality characteristics of the fluid sample may be physically or wirelessly delivered to a remote location. In some examples, samples are drawn into engagement with the sensor by a flexible tube that is attached to an outer surface of the UAV. The flexible tube may allow the UAV to precisely target and collect samples of dust and moisture and other materials from the ground over which the UAV operates.

Abstract translation: 使用无人机（UAV）收集和分析环境样本。 在一些示例中，样品通过由转子风扇通过无人机的风扇的管道产生的现有流体流被吸引到UAV上的传感器。 流体样品的质量特性可以物理地或无线地传送到远程位置。 在一些示例中，通过附接到无人机的外表面的柔性管，将样品牵引成与传感器接合。 柔性管可以允许无人机从无人机运行的地面精确地瞄准和收集灰尘和水分以及其他材料的样品。

公开(公告)号：US08720814B2

公开(公告)日：2014-05-13

申请号：US13442544

申请日：2012-04-09

Applicant: Frick A. Smith

Inventor： Frick A. Smith

IPC: B64C37/00 ,  B64C27/26 ,  B64C27/28

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：US08602348B2

公开(公告)日：2013-12-10

申请号：US12865429

申请日：2009-02-02

Applicant: Ashley Christopher Bryant

Inventor： Ashley Christopher Bryant

IPC: B64C15/12 ,  B64C29/00 ,  B64C39/10

CPC classification number: B64C29/0033 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/162 ,  B64C2201/165

Abstract: A vertical take-off and landing flying-wing aircraft has a pair of thrust-vectoring propulsion units mounted fore and aft of the aircraft pitch axis on strakes at opposite extremities of the wing-structure, with the fore unit below, and the aft unit above, the wing-structure. The propulsion units are pivoted to the strakes, either directly or via arms, for individual angular displacement for thrust-vectored maneuvering of the aircraft in yaw, pitch and roll and for hover and forward and backward flight. When arms are employed, the arms of fore and aft propulsion units are intercoupled via chain drives or linkages. The wing-structure may have fins, slats and flaps and other aerodynamic control-surfaces, and enlarged strakes may incorporate rudder surfaces. Only one propulsion unit may be mounted at each extremity and additional fan units may be used.

Abstract translation: 垂直起飞和着陆的飞翼飞机具有一对推力矢量推进装置，其在机翼结构的相对两端的前翼和后部单元的前后悬架的飞机俯仰轴上前后安装 以上，翼结构。 推进单元直接或经由臂枢转到斜面，用于单独的角位移，用于以偏航，俯仰和滚动以及用于悬停和向前和向后飞行的推力向导操纵飞行器。 当使用武器时，前后推进单元的臂通过链条驱动器或连杆相互联接。 机翼结构可以具有翅片，板条和翼片以及其它空气动力学控制表面，并且扩大的履带可以包括舵面。 每个末端只能安装一个推进装置，也可以使用额外的风扇装置。

公开(公告)号：US20130134254A1

公开(公告)日：2013-05-30

申请号：US13306419

申请日：2011-11-29

Applicant: Jason Moore

Inventor： Jason Moore

IPC: B64C27/00 ,  A62C99/00 ,  B64C39/02

CPC classification number: B64C39/022 ,  A62C29/00 ,  A62C99/00 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/148 ,  B64C2201/162 ,  B64D1/16

Abstract: An unmanned aerial vehicle (UAV) designed to extinguish fires from the air while remaining tethered to the ground via a tether system fashioned to provide the UAV with power and extinguishant. The UAV is preferably electrically powered and is stabilized in the air via a system of gyroscopes fashioned to work in concert with a series of electric motors capable of moving to counteract the opposing recoil force exhibited as water escapes the nozzle of the tether. A command and control unit on the ground supplies the UAV with electricity and water via the tether. The UAV is preferably stored within and launched from the command and control unit. Controls and sensor readings are communicated to a controller—be it autonomous or human—on the ground, preferably within or proximal to the command and control unit.

Abstract translation: 一种无人驾驶飞行器（UAV），旨在扑灭空气中的火焰，同时通过系绳系统将其连接到地面，以提供无人机的动力和灭火。 UAV优选地是电动的，并且通过陀螺仪系统被稳定在空气中，陀螺仪的系统与一系列电动机协同工作，该电动机能够移动以抵消随着水逸出系绳的喷嘴而呈现的相反反冲力。 地面上的指挥和控制单元通过系绳向无人机供电和供水。 UAV优选地存储在命令和控制单元中并从命令和控制单元发射。 控制器和传感器读数传达给控制器（无论是自主的还是人的），优选在指令和控制单元内或近端。

公开(公告)号：US20120305714A1

公开(公告)日：2012-12-06

申请号：US13466327

申请日：2012-05-08

Applicant: Harry George Dennis Gosling

Inventor： Harry George Dennis Gosling

IPC: B64C39/06

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.

公开(公告)号：US08220737B2

公开(公告)日：2012-07-17

申请号：US12480312

申请日：2009-06-08

Applicant: Ryan S. Wood ,  Darold B. Cummings ,  David W. Hall

Inventor： Ryan S. Wood ,  Darold B. Cummings ,  David W. Hall

IPC: B64C29/00 ,  B64C15/02 ,  B64C15/14 ,  B64C23/06 ,  B64C3/58 ,  B64C39/06

CPC classification number: B64C29/0025 ,  B64C39/024 ,  B64C39/068 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/162

Abstract: An aircraft capable of vertical take-off and landing is provided. The aircraft includes a fuselage having a forward portion and an aft portion. A lift fan extends though a duct, which extends through the fuselage. The aircraft further includes a pair of wing sets where each set of wings include first and second wings. Each set of wings has a first wing with a first wing root interconnected to the fuselage forward of a central axis of the lift fan and a second wing having a second wing root interconnected to the fuselage aft of the central axis of the lift fan. The tips of each set of wings are connected. The aircraft further includes a pusher fan.

Abstract translation: 提供能够垂直起飞和着陆的飞机。 飞机包括具有前部和后部的机身。 升降风扇延伸穿过机身延伸的导管。 飞机还包括一对翼组，其中每组翼包括第一和第二翼。 每组翼具有第一翼，其具有与提升风扇的中心轴线前方的机身相互连接的第一翼根，第二翼具有与提升风扇的中心轴线的机身后部相互连接的第二翼根。 每组翅膀的尖端连接。 飞机还包括推动风扇。