公开(公告)号：US20170158327A1

公开(公告)日：2017-06-08

申请号：US15370592

申请日：2016-12-06

Applicant: AAI Corporation

Inventor： Neal H. Willford

IPC: B64C39/02 ,  B64C29/02 ,  B64C25/34 ,  B64D17/80 ,  G05D1/08 ,  G05D1/00

CPC classification number: B64C39/024 ,  B64C25/34 ,  B64C27/50 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64C2201/165 ,  B64D17/80 ,  G05D1/0055 ,  G05D1/0816 ,  G05D1/0858

Abstract: A technique is directed to operating an unmanned aerial vehicle (UAV) having a fuselage defining a flight direction of the UAV and wing-plate assemblies that propel the UAV in the flight direction defined by the fuselage. The technique involves providing, while the flight direction defined by fuselage of the UAV points vertically from a takeoff location on the ground, thrust from propulsion units of the wing-plate assemblies to fly the UAV along a vertical takeoff path. The technique further involves maneuvering, after the UAV flies along the vertical takeoff path, the UAV to align the flight direction along a horizontal flight path that is perpendicular to the vertical takeoff path. The technique further involves providing, after the UAV flies along the horizontal flight path, thrust from the propulsion units of the wing-plate assemblies to land the UAV along a vertical landing path that is perpendicular to the horizontal flight path.

公开(公告)号：US09550567B1

公开(公告)日：2017-01-24

申请号：US14524956

申请日：2014-10-27

Applicant: Amazon Technologies, Inc.

Inventor： Jack Erdozain, Jr. ,  Berk Ozturk ,  Nicholas Hampel Roberts ,  Brian C. Beckman

IPC: B64C27/22 ,  B64C29/02 ,  B64C3/54 ,  B64C39/02 ,  B64D27/24 ,  B64D47/08

CPC classification number: B64C29/02 ,  B64C1/30 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/18 ,  Y02T50/14

Abstract: This disclosure is directed to an unmanned aerial vehicle (“UAV”) that transitions in-flight between vertical flight configuration and horizontal flight configuration by changing an orientation of the UAV by approximately ninety degrees. The UAV may include propulsion units that are coupled to a wing. The wing may include wing segments rotatably coupled together by pivots that rotate to position the propulsion units around a center of mass of the UAV when the fuselage is oriented perpendicular with the horizon. In this vertical flight configuration, the UAV may perform vertical flight or hover. During the vertical flight, the UAV may cause the wing to extend outward via the pivots such that the wing segments become positioned substantially parallel to one another and the wing resembles a conventional fixed wing. With the wing extended, the UAV assumes a horizontal flight configuration that provides upward lift generated from the wing.

Abstract translation: 本公开涉及通过将UAV的方向改变大约九十度而在垂直飞行构型和水平飞行构型之间转换的无人驾驶飞行器（“UAV”）。 无人机可以包括联接到机翼的推进单元。 机翼可以包括通过枢转可旋转地联接在一起的翼段，当机身垂直于水平线时，枢轴旋转以将推进单元围绕UAV的质心定位。 在这种垂直飞行配置中，无人机可以执行垂直飞行或悬停。 在垂直飞行期间，UAV可以使机翼经由枢轴向外延伸，使得机翼段基本上彼此平行地定位，并且翼类似于常规的固定翼。 在机翼延伸的情况下，UAV采取水平飞行配置，提供从机翼产生的向上升力。

公开(公告)号：US09540101B2

公开(公告)日：2017-01-10

申请号：US14507198

申请日：2014-10-06

Applicant: Aurora Flight Sciences Corporation

Inventor： James Donald Paduano ,  Paul Nils Dahlstrand ,  John Brooke Wissler ,  Adam Woodworth

IPC: B64C27/52 ,  B64C29/04 ,  B64C29/02 ,  B64C39/02 ,  B64C29/00 ,  B64C3/42 ,  B64C5/02 ,  B64C9/00 ,  B64C25/10 ,  B64D27/02 ,  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.

Abstract translation: 根据本发明的一个方面的垂直起飞（VTOL）飞机包括机身，具有位于机身尾端的全移动水平稳定器的尾翼，机身具有位于机身的大致中间位置 翼的远端​​，其中翼被配置成使用位于机身的每一侧上的倾斜铰链在基本上直的机翼构型和倾斜翼结构之间转换。 垂直起落飞行器还可以包括一个或多个可伸缩的弹簧支撑件，其中可伸缩的弹簧支撑构造成从翼的远端中的每一个展开。

公开(公告)号：US09493235B2

公开(公告)日：2016-11-15

申请号：US14940379

申请日：2015-11-13

Applicant: Dylan T X Zhou ,  Andrew H B Zhou ,  Tiger T G Zhou

Inventor： Dylan T X Zhou ,  Andrew H B Zhou ,  Tiger T G Zhou

IPC: B64C35/00 ,  B60F5/02 ,  B64C29/00 ,  B64C39/02 ,  G05D1/04 ,  B60F3/00 ,  G05D1/00 ,  B63G8/00 ,  G01S19/39 ,  G08G3/02 ,  G08G5/04 ,  H04N7/18 ,  H04N5/232 ,  H04N5/265 ,  B63G8/16 ,  G06Q20/32 ,  G06Q20/36

CPC classification number: B64C35/008 ,  B60F5/02 ,  B63G8/001 ,  B63G8/16 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/145 ,  B64C2201/162 ,  B64C2201/165 ,  G05D1/102 ,  H04N5/2252 ,  H04N5/23206 ,  H04N5/2328 ,  H04N5/23296

Abstract: An amphibious vertical takeoff and landing (VTOL) unmanned device includes a modular and expandable waterproof body. An outer body shell, at least one wing, and a door are connected to the modular and expandable waterproof body. A propulsion system of the amphibious VTOL unmanned device includes a plurality of motors and propellers and a propeller protection system. The amphibious VTOL unmanned device further includes a battery, a charging station for batteries, an onboard electricity generator a power distribution board, an electrical power storage device, and an electrical machine electrically connected to the electrical power storage device. The amphibious VTOL unmanned device is further equipped with a landing system, an onboard air compressor, an onboard electrolysis system, a cooling device, vision aiding and orientative lights, an apparatus for internally housing a cargo, and a manually or automatically deployable parachute.

Abstract translation: 水陆两用垂直起降（VTOL）无人机包括一个模块化和可扩展的防水体。 外壳体，至少一个翼和门连接到模块化和可扩展的防水体。 水陆两用VTOL无人驾驶装置的推进系统包括多个电动机和推进器以及螺旋桨保护系统。 水陆两用VTOL无人装置还包括电池，电池充电站，车载发电机，配电板，电力存储装置以及与蓄电装置电连接的电机。 水陆两用VTOL无人装置还配有着陆系统，车载空气压缩机，车载电解系统，冷却装置，视觉辅助和定向灯，用于内部容纳货物的装置以及手动或可自动展开的降落伞。

公开(公告)号：US20160311530A1

公开(公告)日：2016-10-27

申请号：US15204547

申请日：2016-07-07

Applicant: Frick A. Smith

Inventor： Frick A. Smith

IPC: B64C29/00 ,  B64C27/28 ,  B64D31/00 ,  B64C39/02 ,  B64C27/82 ,  B64D17/64 ,  B64D17/80 ,  B64D27/02 ,  B64C1/14 ,  B64C27/52 ,  B64C27/26 ,  B64D17/24

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：US20160229534A1

公开(公告)日：2016-08-11

申请号：US14527674

申请日：2014-10-29

Applicant: QUALCOMM Incorporated

Inventor： Donald Bolden Hutson

IPC: B64D1/22 ,  B64C37/00 ,  B64C39/02 ,  B64C27/08

CPC classification number: B64C37/00 ,  B60F5/02 ,  B64C25/38 ,  B64C27/08 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/128 ,  B64C2201/162 ,  B64D1/22

Abstract: Unmanned aerial vehicles and methods for providing the same are disclosed. The unmanned aerial vehicles may have various configurations related to a support frame. The unmanned aerial vehicles may have various configurations with a continuous track for ground propulsion. The unmanned aerial vehicles may have various configurations related to payload clamps.

公开(公告)号：US20160009387A1

公开(公告)日：2016-01-14

申请号：US14689443

申请日：2015-04-17

Applicant: Propulsive Wing, LLC

Inventor： Joseph Kummer ,  Jimmie B. Allred, III

IPC: B64C27/20 ,  B64C11/00 ,  B64C11/46 ,  B64C27/26

CPC classification number: B64C29/0025 ,  B64C29/0066 ,  B64C29/0083 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  Y02T50/12

Abstract: A hybrid axial/cross-flow fan aerial vehicle includes both axial and cross-flow fan propulsion for efficient hover and forward flight performance. The axial fans provide primarily vertical thrust, while the cross-flow fan provides horizontal, as well as vertical, thrust. The vehicle takes off vertically, is capable of hover, and can fly forward by vectoring the thrust of the cross-flow fan system. This approach provides large internal cargo capacity and high forward flight speeds.

Abstract translation: 混合轴向/横流风扇航空器包括轴向和横流风扇推进，用于高效悬停和前进飞行性能。 轴流风扇主要提供垂直推力，而横流风扇提供水平和垂直推力。 车辆垂直起飞，可以悬停，并且可以通过向量来推动横流风扇系统的推力飞行。 这种方法提供了大的内部货物能力和高的前进飞行速度。

公开(公告)号：US20150336666A1

公开(公告)日：2015-11-26

申请号：US14507198

申请日：2014-10-06

Applicant: Aurora Flight Sciences Corporation

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

IPC: B64C29/04

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：US20150225071A1

公开(公告)日：2015-08-13

申请号：US14176960

申请日：2014-02-10

Applicant: Northrop Grumman Systems Corporation

Inventor： Thomas S. Tighe

IPC: B64C3/32 ,  B64C3/38 ,  B64C29/00

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162

Abstract: A multi-engine aircraft is disclosed which is convertible from horizontal flight mode to a vertical flight mode. The aircraft comprises an aircraft fuselage defining a fuselage longitudinal axis, and the first and second wing attached to the fuselage. Each wing defines first and second wing segments. The first segments are translatable about the fuselage longitudinal axis, from a horizontal mode position adjacent the second wing segments to vertical fight mode wherein the first wing segment are substantially offset from the second wing segments. An aircraft propulsion unit is attached to each of the first and second wing segments. The propulsion units attached to a common wing being disposed in substantial axial alignment when the aircraft operates in a horizontal flight mode, and being substantially offset when the aircraft operates in a vertical flight mode. A senor unit is connected to a forward portion of the fuselage.

Abstract translation: 公开了一种可从水平飞行模式转换为垂直飞行模式的多引擎飞机。 该飞机包括一个定义机身纵向轴线的飞机机身，以及连接到机身的第一和第二翼。 每个翼限定第一和第二翼段。 第一段可绕机身纵向轴线平移，从邻近第二翼段的水平模式位置到垂直起搏模式，其中第一翼段基本上偏离第二翼段。 飞机推进单元附接到第一和第二翼段中的每一个。 当飞机以水平飞行模式操作时，连接到共同翼的推进单元被布置成基本上轴向对准，并且当飞机以垂直飞行模式操作时基本上偏移。 传感器单元连接到机身的前部。

公开(公告)号：US20150197335A1

公开(公告)日：2015-07-16

申请号：US14415433

申请日：2013-09-12

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： Guy Dekel ,  Lior Zivan ,  Yoav Efraty ,  Amit Wolff ,  Avner Volovick

IPC: B64C27/52 ,  G05D1/08 ,  G05D1/04

CPC classification number: B64C27/52 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/187 ,  G05D1/042 ,  G05D1/0808 ,  G05D1/0858 ,  G05D1/102

Abstract: A control system configured to control an acceleration of an air vehicle which comprises a tiltable propulsion unit that is tiltable to provide a thrust whose direction is variable at least between a general vertical thrust vector direction and a general longitudinal thrust vector direction with respect to the air vehicle, the control system comprising: (a) an input interface for receiving information indicative of a monitored airspeed of the air vehicle; and (b) a control unit, configured to issue controlling commands to a controller of the tiltable propulsion unit for controlling the acceleration of the air vehicle.

Abstract translation: 一种被配置为控制空中交通工具的加速度的控制系统，该控制系统包括可倾斜的推进单元，该倾斜推进单元可倾斜以提供方向至少相对于空气在一般的垂直推力矢量方向和一般纵向推力向量方向之间变化的推力 车辆，所述控制系统包括：（a）输入接口，用于接收指示所述空中交通工具的监控空速的信息; 以及（b）控制单元，被配置为向所述可倾斜推进单元的控制器发出控制命令，以控制所述空中交通工具的加速度。