公开(公告)号：US20170190423A1

公开(公告)日：2017-07-06

申请号：US15467463

申请日：2017-03-23

Applicant: Cisco Technology, Inc.

Inventor： Gonzalo Salgueiro ,  Charles Calvin Byers

IPC: B64D1/00 ,  G06Q10/08 ,  B64C39/02 ,  B64F1/04 ,  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.

公开(公告)号：US09688397B2

公开(公告)日：2017-06-27

申请号：US15204547

申请日：2016-07-07

Applicant: Frick A. Smith

Inventor： Frick A. Smith

IPC: B64D35/04 ,  B64D27/02 ,  B64C27/22 ,  B64C29/00 ,  B64C1/14 ,  B64C27/52 ,  B64C39/02 ,  B64D17/24 ,  B64D17/34 ,  B64D17/62 ,  B64D17/80 ,  B64D31/00 ,  B64C27/26 ,  B64C27/28 ,  B64C27/82 ,  B64D17/64

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.

公开(公告)号：US20170057633A1

公开(公告)日：2017-03-02

申请号：US15152416

申请日：2016-05-11

Applicant: MARTIN UAV, LLC

Inventor： Stephen Morris

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

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.

公开(公告)号：US20170057632A1

公开(公告)日：2017-03-02

申请号：US15152413

申请日：2016-05-11

Applicant: MARTIN UAV, LLC

Inventor： Stephen Morris

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

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：US09567075B2

公开(公告)日：2017-02-14

申请号：US14176960

申请日：2014-02-10

Applicant: Northrop Grumman Systems Corporation

Inventor： Thomas S. Tighe

IPC: B64C29/02 ,  B64C39/02

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 sensor 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：US20170029131A1

公开(公告)日：2017-02-02

申请号：US15220624

申请日：2016-07-27

Applicant: Airbus Defence and Space GmbH

Inventor： Jürgen Steinwandel ,  Ning Wang ,  Michael Judas ,  Jan Van Toor

IPC: B64D35/08 ,  B64C39/02 ,  B64C29/00 ,  B64D27/24

CPC classification number: B64D35/08 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/24 ,  B64D2027/026

Abstract: A vertical take-off aircraft with a propulsion drive for generating a driving force being effective in a horizontal direction and with a lift drive for generating a lifting force being effective in a vertical direction includes a motor for providing mechanical energy for the propulsion drive and a first generator for providing electrical energy for the lift drive. Moreover, the aircraft includes an exhaust gas turbocharger for the motor with a first turbine being driven by an exhaust gas flow of the motor, wherein the first turbine is configured to provide mechanical energy for the propulsion drive.

Abstract translation: 具有用于产生在水平方向上有效的驱动力的推进驱动器的垂直起飞飞机和用于产生在垂直方向上有效的提升力的提升驱动装置包括用于为推进驱动提供机械能的马达和 第一发电机，用于为升降机驱动提供电能。 此外，飞行器包括用于电动机的排气涡轮增压器，其中第一涡轮机由电动机的废气流驱动，其中第一涡轮机构造成为推进驱动提供机械能。

公开(公告)号：US09540100B2

公开(公告)日：2017-01-10

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: G05D1/00 ,  B64C27/52 ,  B64C29/00 ,  B64C39/02 ,  G05D1/10 ,  G05D1/04 ,  G05D1/08

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。

公开(公告)号：US20160257400A1

公开(公告)日：2016-09-08

申请号：US14641468

申请日：2015-03-09

Applicant: Draganfly Innovations Inc.

Inventor： Orville OLM ,  Greg WOOD ,  Zenon DRAGAN

IPC: B64C37/00 ,  B64C39/00 ,  B60F5/02 ,  B64C39/02

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：US20160221671A1

公开(公告)日：2016-08-04

申请号：US14990057

申请日：2016-01-07

Applicant: Vantage Robotics, LLC

Inventor： Tobin Fisher ,  Johannes Becker Van Niekerk

IPC: B64C27/08 ,  B64C27/32 ,  B64D47/08 ,  B64C39/02

CPC classification number: B64C27/08 ,  B64C27/20 ,  B64C27/32 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162 ,  B64D47/08

Abstract: An unmanned aerial vehicle (UAV) includes a body that supports breakaway components. One component is a battery pack which powers the vehicle. Two other components are pod assemblies, which each include at least one motor and one propeller. Each motor is supported within a support ring using spokes or filament. The spokes keep the motor firmly stable during operation and also effectively encage the otherwise dangerous spinning propeller. This allows the vehicle to operate with a higher level of safety than conventional UAVs. The breakaway feature can be established using magnets.

Abstract translation: 无人飞行器（UAV）包括一个支撑分离部件的机身。 一个组件是为车辆供电的电池组。 另外两个组件是荚组件，每个组件包括至少一个电动机和一个螺旋桨。 每个电机都使用辐条或灯丝支撑在支撑环内。 轮辐在运行过程中保持电机的稳定，并有效地包裹其他危险的旋转螺旋桨。 这允许车辆以比常规UAV更高的安全性运行。 可以使用磁铁建立分离特征。

公开(公告)号：US20160009388A1

公开(公告)日：2016-01-14

申请号：US14796267

申请日：2015-07-10

Applicant: Geola Technologies, Ltd.

Inventor： David Brotherton-Ratcliffe ,  Jerzy Lelusz

IPC: B64C29/00 ,  B64C27/20 ,  B64C11/00 ,  B64D27/24 ,  B64D27/10 ,  B64C27/08 ,  G05D1/04 ,  B64D47/08

CPC classification number: B64C29/0016 ,  B64C11/001 ,  B64C27/08 ,  B64C27/20 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/10 ,  B64D27/24 ,  B64D47/08 ,  G05D1/042 ,  Y02T50/64

Abstract: An electric and hybrid Vertical-Take Off and Landing (“VTOL”) aircraft is disclosed comprising a plurality of small Electric Ducted Fans (“EDFs”) of various sizes and orientations. The thrust of each fixed EDF is individually controlled by modulation of motor power by one or more onboard microcomputers connected to a plurality of onboard laser distance measuring sensors, at least three onboard three-axis accelerometers and at least one GPS thereby allowing extremely precise and safe VTOL operation. The aircraft may be employed to allow robotic and passenger vehicles to transition extremely quickly between normal linear flight and VTOL and tb operate in extreme and gusty conditions.

Abstract translation: 公开了一种具有各种尺寸和方向的多个小型电风扇（“EDF”）的电动和混合垂直起飞和着陆（“垂直起落架”）飞机。 每个固定EDF的推力通过一个或多个连接到多个机载激光距离测量传感器，至少三个板载三轴加速度计和至少一个GPS的机载微型计算机调节电机功率来单独控制，从而允许非常精确和安全 VTOL操作。 飞机可能被允许机器人和乘客车辆在正常线性飞行和垂直起落时间之间极快地转变，并且tb在极端和阵风条件下操作。