公开(公告)号：US20170297706A1

公开(公告)日：2017-10-19

申请号：US15338802

申请日：2016-10-31

Applicant: Ewatt Technology Co., Ltd.

Inventor： Guocheng ZHAO ,  Wei LUO

IPC: B64C39/02 ,  B64C25/58 ,  B64C1/06 ,  B64C5/02

CPC classification number: B64C39/024 ,  B64C1/00 ,  B64C1/06 ,  B64C3/00 ,  B64C5/02 ,  B64C25/58 ,  B64C39/028 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/08 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/187

Abstract: The invention discloses a hand-launched unmanned aerial vehicle, and belongs to the technical field of unmanned aerial vehicles. The hand-launched unmanned aerial vehicle comprises a body, a tail, at least one power source and a lens bin, wherein the body comprises a middle section, a first side section and a second side section; two sides of the middle section are respectively detachably connected with the first side section and the second side section correspondingly; the tail is fixed to the middle section; the power source is fixed to the middle section; and the lens bin is fixed to the middle section and provided with a flexible cushion. The invention overcomes the technical defects in the prior art that the body maintenance cost of the hand-launched unmanned aerial vehicle is high and the lens bin is very likely to be damaged due to collision between the lens bin of the hand-launched unmanned aerial vehicle and the ground.

公开(公告)号：US20170240274A1

公开(公告)日：2017-08-24

申请号：US15329848

申请日：2015-07-28

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

Inventor： Eyal REGEV

IPC: B64C29/00 ,  B64C39/02 ,  B64D27/24 ,  B64D35/02 ,  F02B61/04

CPC classification number: B64C29/0033 ,  B64C27/28 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/108 ,  B64D27/24 ,  B64D35/02 ,  B64D35/08 ,  B64D2027/026 ,  F02B61/04 ,  F02B73/00 ,  Y02T50/64

Abstract: A propulsion system is provided, including a first propulsion unit, a second propulsion unit, a rotor, a first coupling and a second coupling. The first propulsion unit is configured for being fixedly mounted to an airframe. The rotor is configured for being pivotably mounted with respect to the first propulsion unit to allow selectively pivoting of the rotor from a horizontal mode to a vertical mode. The first coupling is configured for selectively coupling and decoupling the rotor with respect to the first propulsion unit. The second coupling is configured for selectively coupling and decoupling the rotor with respect to the second propulsion unit, independently of the first coupling.

公开(公告)号：US09731818B2

公开(公告)日：2017-08-15

申请号：US14372060

申请日：2013-01-10

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD.

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

IPC: B64C27/26 ,  B64C29/00 ,  B64C39/02 ,  B64C19/00 ,  G05D1/06 ,  G05D1/08

CPC classification number: B64C27/26 ,  B64C19/00 ,  B64C29/00 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/187 ,  G05D1/0676 ,  G05D1/0858

Abstract: A control system configured to control a deceleration process of an air vehicle which comprises at least one tiltable propulsion unit, each of the at least one tiltable propulsion units 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.

公开(公告)号：US20170197725A1

公开(公告)日：2017-07-13

申请号：US15400796

申请日：2017-01-06

Applicant: Singapore Technologies Aerospace Ltd

Inventor： Chi Hui Frederic FOO ,  Han Lin HSI

IPC: B64D39/02 ,  B64D47/08 ,  B64D43/00 ,  B64D7/00 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C2039/105 ,  B64C2201/063 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/182 ,  B64C2201/185 ,  Y02T50/12

Abstract: An apparatus and method for aerial recovery of an unmanned aerial vehicle (UAV) are provided. The apparatus includes a rigid base having a first section and a second section, wherein the first section is securely mounted to a floor of an aircraft. The apparatus further includes a servicing platform moveably mounted to the base and configured to move along a direction parallel to a longitudinal axis of the aircraft such that in an extended position, the servicing platform at least partially protrudes from a rear cargo door of the aircraft, wherein the servicing platform comprises a capturing mechanism configured to capture the UAV in the extended position.

公开(公告)号：US09672748B2

公开(公告)日：2017-06-06

申请号：US14936632

申请日：2015-11-09

Applicant: AeroVironment Inc.

Inventor： Christopher E. Fisher ,  Thomas Robert Szarek ,  Justin B. McAllister ,  Pavel Belik

IPC: G08G5/02 ,  B64C39/02 ,  G05D1/06 ,  B64D31/00 ,  G05D1/00

CPC classification number: G08G5/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/14 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/18 ,  B64D31/00 ,  G05D1/0011 ,  G05D1/0676

Abstract: An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.

公开(公告)号：US20170146995A1

公开(公告)日：2017-05-25

申请号：US14949541

申请日：2015-11-23

Applicant: EASY AERIAL INC.

Inventor： Ivan STAMATOVSKI ,  Mohammad HEFNY

IPC: G05D1/00 ,  G07C5/00 ,  B64C39/02

CPC classification number: G05D1/0027 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/146 ,  G07C5/008

Abstract: A system and method is provided for the establishment of a fleet of networked unmanned vehicles. The system provides at least one vehicle control device configured to interface with a third party unmanned vehicle and establish communications with other unmanned vehicles and with remote control stations. A plurality of vehicle control devices may be used with a plurality of remote control stations to establish a networked fleet of unmanned vehicles. Communication between the networked vehicles may include control information, sensor information, and mission information.

公开(公告)号：US09650133B2

公开(公告)日：2017-05-16

申请号：US15042090

申请日：2016-02-11

Applicant: AeroVironment, Inc.

Inventor： Christopher Eugene Fisher ,  Jason Sidharthadev Mukherjee ,  William Arden Lott

IPC: B64C27/22 ,  B64C29/02 ,  B64C39/02 ,  B64F1/00

CPC classification number: B64F1/005 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/12 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/18 ,  B64C2201/201 ,  B64F1/12

Abstract: A vertical take-off and landing (VTOL) unmanned aerial vehicle (UAV) system including: a rearward facing tang extending from a rear fuselage portion of a VTOL UAV; one or more metallic contacts disposed on an exterior surface of the tang; a UAV pod including a landing surface; and an opening disposed in the landing surface to receive the tang.

公开(公告)号：US20170057621A1

公开(公告)日：2017-03-02

申请号：US15256178

申请日：2016-09-02

Applicant: Jetoptera, Inc.

Inventor： Andrei Evulet

IPC: B64C21/04 ,  B64C39/02 ,  B64D27/16 ,  B64D27/00

CPC classification number: B64D29/02 ,  B64C9/38 ,  B64C15/00 ,  B64C21/00 ,  B64C21/04 ,  B64C39/024 ,  B64C2201/10 ,  B64C2201/104 ,  B64D27/10 ,  B64D27/18 ,  B64D33/02 ,  B64D33/04 ,  B64D2033/0273 ,  Y02T50/166 ,  Y02T50/32 ,  Y02T50/44

Abstract: A vehicle includes a main body and a gas generator producing a gas stream. At least one fore conduit and tail conduit are fluidly coupled to the generator. First and second fore ejectors are fluidly coupled to the at least one fore conduit. At least one tail ejector is fluidly coupled to the at least one tail conduit. The fore ejectors respectively include an outlet structure out of which gas from the at least one fore conduit flows. The at least one tail ejector includes an outlet structure out of which gas from the at least one tail conduit flows. First and second primary airfoil elements have leading edges respectively located directly downstream of the first and second fore ejectors. At least one secondary airfoil element has a leading edge located directly downstream of the outlet structure of the at least one tail ejector.

Abstract translation: 车辆包括产生气流的主体和气体发生器。 至少一个前导管和尾管与流体耦合到发生器。 第一和第二前喷射器流体地联接到至少一个前导管。 至少一个尾喷射器流体地联接到所述至少一个尾管。 前喷射器分别包括出口结构，来自至少一个前导管的气体流出。 至少一个尾喷射器包括出口结构，来自至少一个尾管的气体从该出口结构流出。 第一和第二主翼元件具有分别位于第一和第二前部喷射器的下游的前缘。 至少一个副翼元件具有位于至少一个尾喷射器的出口结构的下游的前缘。

公开(公告)号：USD776571S1

公开(公告)日：2017-01-17

申请号：US29529811

申请日：2015-06-10

Applicant: University of Kansas

Designer： Ronald M. Barrett ,  Robert B. Honea ,  Richard B. Bramlette

CPC classification number: A63H27/12 ,  A63H27/02 ,  A63H33/003 ,  B64C25/06 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2203/00 ,  B64D27/02

Abstract: An aerial vehicle capable of convertible flight from hover to linear flight includes a body having a longitudinal body axis, a plurality of forward wings, a plurality of aft wings, at least one motor, and at least three aerodynamic propulsors driven by the at least one motor. Each forward wing extends a forward wing plane. Each aft wing extends from an aft wing plane. The aerodynamic propulsors are mounted longitudinally between the plurality of forward wings and plurality of aft wings.

Abstract translation: 能够从悬停到线性飞行的可转换飞行的飞行器包括具有纵向轴线的主体，多个前翼，多个后翼，至少一个马达以及由至少一个驱动的至少三个空气动力推进器 发动机。 每个前翼延伸一个前翼平面。 每个后翼从后翼平面延伸。 空气动力学推进器纵向安装在多个前翼和多个后翼之间。

公开(公告)号：US09511858B2

公开(公告)日：2016-12-06

申请号：US13261813

申请日：2012-08-16

Applicant: Christopher E. Fisher ,  Thomas Robert Szarek ,  Justin B. McAllister ,  Pavel Belik

Inventor： Christopher E. Fisher ,  Thomas Robert Szarek ,  Justin B. McAllister ,  Pavel Belik

IPC: B64C39/02 ,  G05D1/08 ,  G05D1/06

CPC classification number: G01C5/005 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/18 ,  B64D47/08 ,  G05D1/0011 ,  G05D1/0676 ,  G05D1/0808 ,  G05D1/0816

Abstract: An aircraft defining an upright orientation and an inverted orientation, a ground station; and a control system for remotely controlling the flight of the aircraft. The ground station has an auto-land function that causes the aircraft to invert, stall, and controllably land in the inverted orientation to protect a payload and a rudder extending down from the aircraft. In the upright orientation, the ground station depicts the view from a first aircraft camera. When switching to the inverted orientation: (1) the ground station depicts the view from a second aircraft camera, (2) the aircraft switches the colors of red and green wing lights, extends the ailerons to act as inverted flaps, and (3) the control system adapts a ground station controller for the inverted orientation. The aircraft landing gear is an expanded polypropylene pad located above the wing when the aircraft is in the upright orientation.

Abstract translation: 定义直立方向和倒置方向的飞机，地面站; 以及用于远程控制飞机飞行的控制系统。 地面站具有自动地面功能，使飞机以反方向反转，失速和可控地降落，以保护从飞机向下延伸的有效载荷和舵。 在直立方向，地面站描绘从第一架飞机摄像机的视图。 当切换到倒置方向时：（1）地面站描绘从第二架飞机照相机的视图，（2）飞机切换红色和绿色翼灯的颜色，将副翼延伸为反转翼片，（3） 控制系统适应地面站控制器的倒置方向。 飞机起落架是当飞机处于直立方向时位于机翼上方的扩展的聚丙烯垫。