公开(公告)号：US09586683B1

公开(公告)日：2017-03-07

申请号：US14580066

申请日：2014-12-22

Applicant: Amazon Technologies, Inc.

Inventor： Daniel Buchmueller ,  Gur Kimchi ,  Louis LeRoi LeGrand, III ,  Samuel Park ,  Christopher Hammond Sczudlo ,  Ricky Dean Welsh ,  Neil Whitney Woodward, III

IPC: G05D1/10 ,  B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  G05D1/0005 ,  G05D1/0858 ,  G05D1/101

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (UAV) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a thrusting motor and propeller assembly that is oriented at approximately ninety degrees to one or more of the lifting motors. When the UAV is moving horizontally, it may be determined if the horizontal airspeed of the UAV exceeds an airspeed threshold. If the horizontal airspeed exceeds the airspeed threshold, the thrusting motor may be engaged and the thrusting propeller will aid in the horizontal propulsion of the UAV.

Abstract translation: 本公开描述了将有助于延长飞行持续时间的无人驾驶飞行器（UAV）的配置。 无人机可能有任何数量的起重马达。 例如，无人机可以包括四台提升马达（也称为四通机），八台起升马达（八重直升机）等。同样地，为了提高水平飞行的效率，无人机还包括推进马达和推进器 组件，其定向在一个或多个起重马达上大约九十度。 当UAV水平移动时，可以确定UAV的水平空速是否超过空速阈值。 如果水平空速超过空速阈值，则推力马达可以接合，并且推进螺旋桨将有助于UAV的水平推进。

公开(公告)号：US09586673B2

公开(公告)日：2017-03-07

申请号：US14184560

申请日：2014-02-19

Applicant: AeroVironment, Inc.

Inventor： Jason Allen Firanski ,  Justin Bates McAllister ,  Ronald Howard Olch ,  Lane Dennis Dalan ,  Emil Ghapgharan

IPC: H02K29/08 ,  B64C11/00 ,  B64C11/02 ,  B64C39/02 ,  B64D27/24 ,  B64D31/06 ,  B64C1/00 ,  B64C3/00 ,  H02P6/16 ,  H02K29/12 ,  H02P6/14

CPC classification number: B64D31/06 ,  B64C1/00 ,  B64C3/00 ,  B64C11/002 ,  B64C11/02 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/165 ,  B64D27/24 ,  H02K29/08 ,  H02K29/10 ,  H02K29/12 ,  H02P3/025 ,  H02P6/14 ,  H02P6/16 ,  Y02T50/44 ,  Y02T50/62

Abstract: A motor assembly that includes a motor (102) having a rotatable shaft, a hub coupled to the rotatable shaft, the hub having a propeller indexer to receive a propeller (104), when the propeller is present, a sensor trigger rotatable with the shaft (100) and positioned at a propeller offset angle θPROP from the propeller indexer, and a sensor coupled to the motor and positioned to detect the sensor trigger so that the propeller indexer may be positioned at the propeller offset angle θPROP from the sensor through rotation of the shaft so that said sensor is proximate to the sensor trigger.

Abstract translation: 一种电动机组件，其包括具有可旋转轴的电动机（102），联接到所述可旋转轴的轮毂，所述轮毂具有螺旋桨分度器，以在所述螺旋桨存在时接收螺旋桨（104），所述螺旋桨分度器可与所述轴 （100）并且位于螺旋桨偏移角度θPROP与螺旋桨分度器之间，以及耦合到电动机并被定位成检测传感器触发器的传感器，使得螺旋桨分度器可以通过旋转传感器从传感器定位在螺旋桨偏移角度θPROP 所述轴使得所述传感器接近传感器触发器。

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。

公开(公告)号：US20160272315A1

公开(公告)日：2016-09-22

申请号：US14625806

申请日：2015-02-19

Applicant: U.S.A. as represented by the Administrator of the National Aeronautics and Space Administration

Inventor： Michael J. Logan ,  Mark A. Motter ,  Richard Deloach ,  Thomas L. Vranas ,  Joseph M. Prendergast ,  Brittney N. Lipp

IPC: B64C39/00 ,  B64C29/00 ,  B64C39/02 ,  B64C39/08 ,  B64C27/82 ,  B64C5/06

CPC classification number: B64C39/005 ,  B64C15/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/165

Abstract: Systems, methods, and devices are provided that enable robust operations of a small unmanned aircraft system (sUAS) using a compound wing. The various embodiments may provide a sUAS with vertical takeoff and landing capability, long endurance, and the capability to operate in adverse environmental conditions. In the various embodiments a sUAS may include a fuselage and a compound wing comprising a fixed portion coupled to the fuselage, a wing lifting portion outboard of the fixed portion comprising a rigid cross member and a controllable articulating portion configured to rotate controllable through a range of motion from a horizontal position to a vertical position, and a freely rotating wing portion outboard of the wing lifting portion and configured to rotate freely based on wind forces incident on the freely rotating wing portion.

Abstract translation: 提供了系统，方法和设备，其使得能够使用复合翼的小型无人飞行器系统（sUAS）的鲁棒操作。 各种实施例可以提供具有垂直起飞和着陆能力，长期耐久性和在不利环境条件下操作的能力的sUAS。 在各种实施例中，一个sUAS可以包括一个机身和一个复合机翼，它包括一个与机身相连的固定部分，固定部分外侧的机翼提升部分包括一个刚性横梁和一个可控制的铰接部分， 从水平位置到垂直位置的运动，以及在所述机翼提升部分的外侧自由旋转的翼部，并且被构造成基于入射到所述自由旋转的翼部上的风力而自由旋转。

公开(公告)号：US20160244157A1

公开(公告)日：2016-08-25

申请号：US14626357

申请日：2015-02-19

Applicant: Amazon Technologies, Inc.

Inventor： Ricky Dean Welsh

IPC: B64C27/52 ,  B64C11/46 ,  B64C39/02 ,  B64C27/28

CPC classification number: B64C27/52 ,  B62D63/04 ,  B63B1/32 ,  B63B2035/006 ,  B63H25/00 ,  B64C11/46 ,  B64C27/28 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165 ,  B64G1/10 ,  B64G1/22

Abstract: This disclosure describes a configuration of an unmanned aerial vehicle (“UAV”) that will facilitate extended flight duration. The UAV may have any number of lifting motors. For example, the UAV may include four lifting motors (also known as a quad-copter), eight lifting motors (also known as an octo-copter), etc. Likewise, to improve the efficiency of horizontal flight, the UAV also includes a pivot assembly that may rotate about an axis from a lifting position to a thrusting position. The pivot assembly may include two or more offset motors that generate a differential force that will cause the pivot assembly to rotate between the lifting position and the thrusting position without the need for any additional motors or gears.

Abstract translation: 本公开描述了将有助于延长飞行持续时间的无人驾驶飞行器（“UAV”）的配置。 无人机可能有任何数量的起重马达。 例如，无人机可以包括四个提升马达（也称为四通机），八个提升马达（也称为八重直升机）等。同样，为了提高水平飞行的效率，UAV还包括一个 枢轴组件可以围绕轴线从提升位置旋转到推动位置。 枢转组件可以包括两个或更多个偏移电动机，其产生将使枢转组件在提升位置和推动位置之间旋转的差动力，而不需要任何附加的电动机或齿轮。

公开(公告)号：US20160236789A1

公开(公告)日：2016-08-18

申请号：US15041424

申请日：2016-02-11

Applicant: AIRBUS DEFENCE AND SPACE GMBH

Inventor： Simon BURNS

IPC: B64D27/02 ,  B64C39/02 ,  B64C31/00

CPC classification number: B64D27/02 ,  B64C31/00 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/00 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/165

Abstract: An aircraft which has a supporting structure which has at least one fuselage, a wing structure and at least one drive apparatus. The drive apparatus has at least one propeller and a drive motor. The aircraft has at least one energy store for providing energy for operation of the drive apparatus. The at least one drive apparatus and the at least one energy store are mechanically connected to the supporting structure and/or the wing structure of the aircraft by a securing device.

Abstract translation: 具有至少一个机身，机翼结构和至少一个驱动装置的支撑结构的飞机。 驱动装置具有至少一个螺旋桨和驱动马达。 飞机具有至少一个能量存储器，用于为驱动装置的操作提供能量。 所述至少一个驱动装置和所述至少一个能量存储器通过固定装置机械连接到所述飞行器的支撑结构和/或机翼结构。

公开(公告)号：US20160236774A1

公开(公告)日：2016-08-18

申请号：US15019717

申请日：2016-02-09

Applicant: Airbus Defence and Space GmbH

Inventor： Hans Niedzballa

IPC: B64C29/00 ,  B64D27/02 ,  B64D27/24

CPC classification number: B64C29/0025 ,  B64C27/30 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/02 ,  B64D27/24 ,  B64D2027/026

Abstract: An aircraft has a bearing structure, the bearing structure having at least one central fuselage and two pylons each situated at a distance laterally from the fuselage. In addition, the aircraft has a wing structure, at least four hub rotors, and at least one thrust drive. Each hub rotor is fastened to the bearing structure, has a propeller having two propeller blades, and produces, through rotation of the propeller, an upward drive force acting in the vertical direction on the aircraft. The thrust drive is produces a thrust force acting in the horizontal direction on the bearing structure. The pylons each have two hub rotors, the hub rotors being configured to arrest respective propeller blades of a hub rotor in a position relative to the pylons. In the arrested position, the propeller blades of a hub rotor do not extend beyond the outer dimensions of the pylons.

Abstract translation: 飞机具有轴承结构，轴承结构具有至少一个中心机身和两个塔架，每个塔架与机身横向距离设置。 此外，飞机具有翼结构，至少四个轮毂转子和至少一个推力驱动。 每个轮毂转子固定在轴承结构上，具有一个具有两个螺旋桨叶片的螺旋桨，通过螺旋桨的旋转产生一个在垂直方向上作用在飞机上的向上驱动力。 推力驱动器在轴承结构上产生沿水平方向作用的推力。 塔架每个都具有两个轮毂转子，轮毂转子构造成在相对于塔架的位置中阻止轮毂转子的相应螺旋桨叶片。 在停止的位置，轮毂转子的螺旋桨叶片不延伸超过塔架的外部尺寸。

公开(公告)号：US20160214712A1

公开(公告)日：2016-07-28

申请号：US14706905

申请日：2015-05-07

Applicant: AEROVIRONMENT, INC.

Inventor： CHRISTOPHER EUGENE FISHER ,  JASON SIDHARTHADEV MUKHERJEE ,  WILLIAM ARDEN LOTT ,  PAVEL BELIK ,  BART DEAN HIBBS

IPC: B64C29/00 ,  B64C27/54 ,  B64C27/26 ,  B64D27/24 ,  B64C11/32 ,  B64C27/605

CPC classification number: B64C29/0025 ,  B64C11/32 ,  B64C27/26 ,  B64C27/54 ,  B64C27/605 ,  B64C29/00 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/24 ,  G05D1/0858

Abstract: A flight control apparatus for fixed-wing aircraft includes a first port wing and first starboard wing, a first port swash plate coupled between a first port rotor and first port electric motor, the first port electric motor coupled to the first port wing, and a first starboard swash plate coupled between a first starboard rotor and first starboard electric motor, the first starboard electric motor coupled to the first starboard wing.

公开(公告)号：US20160207625A1

公开(公告)日：2016-07-21

申请号：US14915101

申请日：2014-08-29

Applicant: Airbus Defence and Space GmbH ,  STEUBBEUS FLUGZEUG- UND LEICHTBAU GMBH

Inventor： Michael JUDAS ,  Friederike STRATENBERG ,  Jan VAN TOOR ,  Werner SCHOLZ ,  Berthold KARRAIS ,  Wolfgang STANGL

IPC: B64C29/00 ,  B64C27/08 ,  B64C27/473 ,  B64C3/38 ,  B64C5/08 ,  B64D27/02 ,  B64D27/24 ,  B64C39/02 ,  B64C39/08

CPC classification number: B64C29/0025 ,  B64C3/38 ,  B64C5/08 ,  B64C27/08 ,  B64C27/473 ,  B64C39/024 ,  B64C39/08 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/165 ,  B64D27/02 ,  B64D27/24 ,  B64D2027/026

Abstract: The invention relates to an aircraft which can both take off and land vertically and can hover and also fly horizontally at a high cruising speed. The aircraft has a support structure, a wing structure, at least three and preferably at least four lifting rotors and at least one thrust drive. The wing structure is designed to generate a lifting force for the aircraft during horizontal motion. To achieve this the wing structure has at least one mainplane provided with a profile that generates dynamic lift. The wing structure is preferably designed as a tandem wing structure. Each of the lifting rotors is fixed to the support structure, has a propeller and is designed to generate a lifting force for the aircraft by means of a rotation of the propeller, said force acting in a vertical direction. The thrust drive is designed to generate a thrust force on the support structure, said force acting in a horizontal direction. The lifting rotors can have a simple construction, i.e. they can have a simple rigid propeller for example, and a vertical take-off or hovering of the aircraft can be controlled, in a similar manner to quadcopters, by a simple control of the speeds of the lifting rotors. High cruising speeds can be achieved as a result of the additional horizontally acting thrust drive.

Abstract translation: 本发明涉及一种能够垂直起飞和着陆的飞机，其可以悬停并且以高巡航速度水平飞行。 飞行器具有支撑结构，翼结构，至少三个，优选至少四个提升转子和至少一个推力驱动。 机翼结构被设计成在水平运动期间为飞机产生提升力。 为了实现这一点，翼结构具有至少一个主平面，其具有产生动态升力的轮廓。 机翼结构优选地被设计为串联翼结构。 每个提升转子固定在支撑结构上，具有螺旋桨，并被设计成通过螺旋桨的旋转而产生用于飞行器的提升力，所述力作用在垂直方向上。 推力驱动器被设计成在支撑结构上产生推力，所述力在水平方向上作用。 提升转子可以具有简单的结构，例如它们可以具有简单的刚性推进器，并且可以通过简单地控制速度来简单地控制飞机的垂直起飞或悬停 提升转子。 由于额外的水平作用推力驱动，可以实现高巡航速度。

公开(公告)号：US20160152316A1

公开(公告)日：2016-06-02

申请号：US15012068

申请日：2016-02-01

Applicant: SZ DJI TECHNOLOGY Co., LTD

Inventor： Tao Wang ,  Tao Zhao ,  Hao Du ,  Mingxi Wang

IPC: B64C1/06 ,  B64C27/08 ,  B64D47/08 ,  B64C39/02

CPC classification number: B64C1/063 ,  A63H27/12 ,  B64C1/00 ,  B64C1/061 ,  B64C25/32 ,  B64C27/08 ,  B64C39/024 ,  B64C39/028 ,  B64C2025/325 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/14 ,  B64C2201/146 ,  B64C2201/165 ,  B64D47/00 ,  B64D47/08 ,  G05D1/042

Abstract: Systems, devices, and methods for a transformable aerial vehicle are provided. In one aspect, a transformable aerial vehicle includes: a central body and at least two transformable frames assemblies respectively disposed on the central body, each of the at least two transformable frame assemblies having a proximal portion pivotally coupled to the central body and a distal portion; an actuation assembly mounted on the central body and configured to pivot the at least two frame assemblies to a plurality of different vertical angles relative to the central body; and a plurality of propulsion units mounted on the at least two transformable frame assemblies and operable to move the transformable aerial vehicle.

Abstract translation: 提供了可变形飞行器的系统，装置和方法。 一方面，可变形飞行器包括：中心体和分别设置在中心体上的至少两个可变形框架组件，所述至少两个可变形框架组件中的每一个具有枢转地联接到中心体的近侧部分和远端部分 ; 驱动组件，其安装在所述中心主体上并且构造成将所述至少两个框架组件相对于所述中心体枢转到多个不同的垂直角度; 以及安装在所述至少两个可变形框架组件上并可操作以移动所述可变形飞行器的多个推进单元。