公开(公告)号：US20160244187A1

公开(公告)日：2016-08-25

申请号：US14631137

申请日：2015-02-25

Applicant: Cisco Technology, Inc.

Inventor： Charles Calvin Byers ,  Gonzalo Salgueiro

IPC: B64F5/00 ,  B64F1/12 ,  B64C39/02

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.

Abstract translation: 在一个实施例中，控制器指示停靠在着陆鲈鱼上的无人驾驶飞行器（UAV）执行飞行前测试程序的飞行前测试操作。 响应于执行飞行前测试操作的UAV，控制器从登陆鲈鱼的一个或多个力传感器接收与飞行前测试操作相关联的传感器数据。 控制器确定与飞行前测试操作相关联的传感器数据是否在可接受的范围内。 控制器部分地基于无人机已经通过飞行前测试程序的确定，使无人机从起落架起飞。

公开(公告)号：US20160122015A1

公开(公告)日：2016-05-05

申请号：US14526790

申请日：2014-10-29

Applicant: QUALCOMM Incorporated

Inventor： Donald Bolden Hutson

IPC: B64C39/02 ,  B60F5/02

CPC classification number: B64C39/024 ,  B60F5/02 ,  B64C2201/024 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162 ,  F41H11/12 ,  F41H11/28

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.

Abstract translation: 公开了无人驾驶飞行器及其提供方法。 无人驾驶飞行器可以具有与支撑框架相关的各种构造。 无人驾驶飞行器可以具有各种构造，具有用于地面推进的连续轨道。 无人驾驶飞行器可以具有与有效载荷夹具相关的各种构造。

公开(公告)号：US20160061144A1

公开(公告)日：2016-03-03

申请号：US14468406

申请日：2014-08-26

Applicant: The Boeing Company

Inventor： Evan J. Filter

IPC: F02K1/06 ,  F01D25/00 ,  F01D25/24

CPC classification number: F02K1/06 ,  B64C11/001 ,  B64C2201/162 ,  B64D33/02 ,  B64D2033/0286 ,  F01D25/005 ,  F01D25/24 ,  F02C7/042

Abstract: A variable geometry inlet for a ducted fan is selectively transitionable between a first and second mode. The inlet includes a retractable ring that extends circumferentially about the inlet and is selectively movable between an axially extended position in the first mode and an axially retracted position in the second mode. A tube extends circumferentially proximate the retractable ring, and is pressurizable to a relatively deflated state in the first mode and to a relatively inflated state in the second mode. A stretchable skin extends circumferentially proximate the retractable ring, and is elastically deformable in at least a circumferential direction about a longitudinal axis of the fan. A leading edge of the inlet in the first mode is defined by the stretchable skin disposed against a forward edge of the retractable ring, and in the second mode by the stretchable skin disposed against at least a portion of the tube.

Abstract translation: 用于管道风扇的可变几何入口可在第一和第二模式之间选择性地转换。 所述入口包括可围绕所述入口周向延伸的可伸缩环，并且可选择地在所述第一模式中的轴向延伸位置和所述第二模式中的轴向缩回位置之间移动。 管子周向地延伸靠近可伸缩环延伸，并且在第一模式中可加压到相对放气的状态，并且在第二模式中可以相对膨胀。 可拉伸的皮肤周向地延伸靠近可伸缩环延伸，并且可围绕风扇的纵向轴线在至少周向方向上弹性变形。 第一模式中的入口的前缘由抵靠可伸缩环的前边缘设置的可伸展皮肤限定，并且在第二模式中由靠在管的至少一部分上设置的可伸展皮肤限定。

公开(公告)号：US20160023760A1

公开(公告)日：2016-01-28

申请号：US14801479

申请日：2015-07-16

Applicant: Insitu, Inc.

Inventor： Wayne Goodrich

IPC: B64C39/02 ,  G05D1/12 ,  B64C11/00

CPC classification number: B64C39/024 ,  B64C5/06 ,  B64C11/48 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/162 ,  F41H11/02 ,  F41H13/0006 ,  G05D1/12

Abstract: Systems and methods for countering an unmanned air vehicle are disclosed. Representative methods include directing an interceptor UAV toward a target UAV, and directing the interceptor UAV back to ground along a controlled flight path, for example, in response to an instruction not to engage with the target UAV, and/or in response to an unsuccessful engagement. Another representative method includes disabling the target UAV by deploying a disabling element (e.g., a net) from the interceptor UAV to contact the target UAV. Representative systems include a target acquisition system, a launch control system, and an engagement system carried by the interceptor UAV. In particular embodiments, the interceptor UAV can have a generally cylindrical fuselage, one or more fins carried by the fuselage, counter-rotating propellers carried by the fuselage, and a disabling system that is configured to disable the target UAV.

Abstract translation: 公开了用于对抗无人驾驶飞行器的系统和方法。 代表性的方法包括将拦截器无人机指向目标无人机，并且将拦截器无人机沿着受控飞行路径引导回地面，例如响应于不与目标无人机接合的指令和/或响应于不成功 订婚。 另一个代表性的方法包括通过从拦截器UAV部署禁用元件（例如网）来禁用目标UAV以接触目标UAV。 代表性系统包括目标采集系统，发射控制系统和拦截机无人机所承载的接合系统。 在特定实施例中，拦截器UAV可以具有大致圆柱形的机身，由机身承载的一个或多个翅片，由机身携带的反向旋转螺旋桨，以及被配置为禁用目标UAV的禁用系统。

公开(公告)号：US20150336663A1

公开(公告)日：2015-11-26

申请号：US14507313

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 ,  B64C39/02 ,  B64C29/02

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：US08991751B2

公开(公告)日：2015-03-31

申请号：US13429156

申请日：2012-03-23

Applicant: Mark Allan Page ,  Matthew Robert McCue ,  Robert Anthony Godlasky

Inventor： Mark Allan Page ,  Matthew Robert McCue ,  Robert Anthony Godlasky

IPC: B64C29/02 ,  B64C39/02

CPC classification number: B64C29/02 ,  B64C39/024 ,  B64C2201/088 ,  B64C2201/104 ,  B64C2201/162 ,  B64C2201/165

Abstract: An aircraft for use in fixed wing flight mode and rotor flight mode is provided. The aircraft can include a fuselage, wings, and a plurality of engines. The fuselage can comprise a wing attachment region further comprising a rotating support. A rotating section can comprise a rotating support and the wings, with a plurality of engines attached to the rotating section. In a rotor flight mode, the rotating section can rotate around a longitudinal axis of the fuselage providing lift for the aircraft similar to the rotor of a helicopter. In a fixed wing flight mode, the rotating section does not rotate around a longitudinal axis of the fuselage, providing lift for the aircraft similar to a conventional airplane. The same engines that provide torque to power the rotor in rotor flight mode also power the aircraft in fixed wing flight mode.

Abstract translation: 提供了一种用于固定翼飞行模式和转子飞行模式的飞机。 飞机可以包括机身，机翼和多个发动机。 机身可以包括还包括旋转支撑件的翼连接区域。 旋转部分可以包括旋转支撑件和机翼，其中多个发动机附接到旋转部分。 在转子飞行模式中，旋转部分可以围绕机身的纵向轴线旋转，为类似于直升机的转子的飞机提供升降机。 在固定翼飞行模式中，旋转部分不围绕机身的纵向轴线旋转，为类似于常规飞机的飞机提供升降机。 在转子飞行模式下为转子提供动力的相同发动机也为固定翼飞行模式下的飞机提供动力。

公开(公告)号：US20140339372A1

公开(公告)日：2014-11-20

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 Volvoick

IPC: B64C27/26 ,  B64C19/00 ,  B64C29/00

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.

Abstract translation: 一种被配置为控制包括至少一个可倾斜推进单元的至少一个可倾斜推进单元的空中交通工具的减速过程的控制系统，所述至少一个可倾斜推进单元中的每一个可倾斜以提供其方向至少在一般的垂直推力矢量方向 和相对于空中车辆的总纵向推力向量方向。

公开(公告)号：US08511602B2

公开(公告)日：2013-08-20

申请号：US12695878

申请日：2010-01-28

Applicant: William T. Campbell ,  Armand Losinski ,  Jonathan Fleming

Inventor： William T. Campbell ,  Armand Losinski ,  Jonathan Fleming

IPC: B64C29/00

CPC classification number: B64C27/20 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/162

Abstract: A ducted fan air-vehicle capable of generating control moments. The ducted fan air-vehicle includes an air duct, a fan, a center body, a plurality of control vanes. The vanes are independently controlled and are deflected in the same direction but at different angles, thereby providing an increased control moments to the vehicle compared to the prior art. The increased pitching moment allows for additional control authority. Additional control authority is useful in forward flight and is especially desirable when the ducted fan air-vehicle is maneuvering in unsteady or turbulent winds or with various types of cargo that may effect the vehicle center of gravity location.

Abstract translation: 一种能够产生控制力矩的风扇式风车。 导风扇空气车辆包括风道，风扇，中心体，多个控制叶片。 叶片独立地被控制并且在相同的方向上以不同的角度偏转，从而与现有技术相比提供了对车辆的增加的控制力矩。 增加的俯仰时间允许额外的控制权限。 额外的控制权限在前进飞行中是有用的，并且当管道风扇空气车辆在不稳定或湍流风中操纵时，或者可能影响车辆重心位置的各种类型的货物是特别理想的。

公开(公告)号：US20130206915A1

公开(公告)日：2013-08-15

申请号：US13642521

申请日：2011-04-20

Applicant: Jean-Marc (Joseph) Desaulniers

Inventor： Jean-Marc (Joseph) Desaulniers

IPC: B64C29/00

CPC classification number: B64C29/00 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/162

Abstract: The invention relates to a vertical take-off and landing gyropendular craft or drone device (FIG. 18) able to move around in the following different physical environments: in the air, on land, at sea, underwater or in outer space, comprising upper and lower propulsion units, equipped with an annular fairing accommodating a certain number of electronically slaved wing or gas-powered drive or propulsion units situated in the continuation of the axis of this device, mounted on 3-D ball-joints at the ends of a certain number of telescopic rods, for example set at 120° apart at the periphery of the platform and orientable about the three axis according to the plane of flight of the multimodal multi-environment craft, a vertebral structure by way of a 3-D articulated central body of solid or hollow cylindrical shape for forming a stabilized function of stabilizing, maintaining the position and heading, and of an inertial rotary disc platform equipped underneath with a cabin of hemispherical shape extending from the vertebral structure, accommodating a payload or a useful application, designed for various fields of application i.e. the sector of defence or civil security, so as to perform functions of search and rescue, exploration, navigation, transport, surveillance and telecommunications infrastructure deployment in free space.

Abstract translation: 本发明涉及能够在以下不同物理环境中移动的垂直起飞和降落式陀飞轮或无人机装置（图18）：在空中，陆地，海上，水下或外部空间中，包括上部 和较低的推进单元，其配备有环形整流罩，其容纳一定数量的电子从动翼或气动驱动或推进装置，其位于该装置的轴线的延续中，安装在三维球形接头 一些数量的伸缩杆，例如在平台的周边处设置为120°，并且可根据多模式多环境飞行器的飞行平面绕三轴定向，通过3-D铰接的椎体结构 用于形成稳定，保持位置和行程的稳定功能的固体或中空圆柱形的中心体，以及配备在下面的惯性旋转盘平台与半球形舱室 形状从脊椎结构延伸，容纳有效载荷或有用的应用，设计用于各种应用领域，即防卫部门或民用安全，以执行搜索和救援，勘探，导航，运输，监视和电信基础设施的功能 部署在自由空间。

公开(公告)号：US08387911B2

公开(公告)日：2013-03-05

申请号：US12179690

申请日：2008-07-25

Applicant: Daniel Ross Collette

Inventor： Daniel Ross Collette

IPC: B64C29/00

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/088 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/162

Abstract: A ducted fan core for an unmanned aerial vehicle is provided that accommodates a wide variety of payloads. The ducted fan core comprises a frame, attached to which are an engine, gearbox assembly, fan, and a plurality of control vanes. A first surface on the frame comprises a plurality of connects or electrical traces. The plurality of connects are used to removably attach a variety of pods carrying various payloads. Thus, a wide variety of payloads may be delivered using the same unmanned aerial vehicle, simply by removing and attaching different pods to a fixed vehicle core. These pods may be shaped so as to form part of the vehicle exterior, and when the pods are attached to the frame, they enhance the aerodynamics of the vehicle.

Abstract translation: 提供用于无人驾驶飞行器的管道风扇芯，其容纳各种有效载荷。 风扇风扇芯包括框架，附接到发动机，变速箱组件，风扇和多个控制叶片。 框架上的第一表面包括多个连接或电迹线。 多个连接用于可拆卸地附接携带各种有效载荷的各种吊舱。 因此，可以简单地通过将不同的荚移除并附接到固定的车辆核心，使用相同的无人驾驶飞行器来传送各种有效载荷。 这些荚可以成形为形成车辆外部的一部分，并且当荚附接到框架时，它们增强了车辆的空气动力学。