公开(公告)号：WO2015195175A2

公开(公告)日：2015-12-23

申请号：PCT/US2015/022001

申请日：2015-03-23

Applicant: BORKO, Brandon

Inventor： BORKO, Brandon

IPC: B64F1/04 ,  E04H6/44

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/08 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/12

Abstract: A system for facilitating automated landing and takeoff of an autonomous or pilot controlled hovering air vehicle with a cooperative underbody at a stationary or mobile landing place and an automated storage system used in conjunction with the landing and takeoff mechanism that stores and services a plurality of UAVs is described. The system is primarily characterized in that the landing mechanism is settable with 6 axes in roll, pitch, yaw, and x, y and z and becomes aligned with and intercepts the air vehicle in flight and decelerates the vehicle with respect to vehicle's inertial limits. The air vehicle and capture mechanism are provided with a transmitter and receiver to coordinate vehicle priority and distance and angles between landing mechanism and air vehicle. The landing and takeoff system has means of tracking the position and orientation of the UAV in real time. The landing mechanism will be substantially aligned to the base of the air vehicle. With small UAVs, their lifting capacity is limited. Reducing sensing and computation requirements by having the landing plate perform the precision adjustments for the landing operation allows for increased flight time and/or payload capacity.

Abstract translation: 一种用于促进自主着陆和起飞的自动着陆和起飞的系统，其具有在固定或移动着陆地点的协作车身，以及与着陆和起飞机构结合使用的自动存储系统，其存储和服务多个UAV 被描述。 该系统的主要特征在于，着陆机构可设置为具有卷轴，俯仰，偏航以及x，y和z的6个轴线，并且与飞行中的空中车辆对准并截取，并相对于车辆的惯性极限使车辆减速。 飞行器和捕获机构设置有发射器和接收器，以协调车辆优先级，着陆机构和机动车辆之间的距离和角度。 着陆和起飞系统具有实时跟踪无人机的位置和方向的方法。 着陆机构将基本上与机动车辆的底座对准。 对于小型无人机，起重能力有限。 通过使着陆板执行着陆操作的精确调整来减少感测和计算要求，可以增加飞行时间和/或有效负载能力。

公开(公告)号：WO2014158914A1

公开(公告)日：2014-10-02

申请号：PCT/US2014/020853

申请日：2014-03-05

Applicant: LIQUID ROBOTICS, INC.

Inventor： HINE, Roger G. ,  HINE, Derek L.

IPC: B63H19/02

CPC classification number: B63B35/50 ,  B63B35/00 ,  B63H19/02 ,  B64C19/00 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/141 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/04 ,  B64F1/221 ,  Y02T70/59

Abstract: Equipment and methods that combine the use of wave powered vehicles and unmanned aerial vehicles (UAVs or drones). A UAV can be launched from a wave-powered vehicle, observe another vessel, and report the results of its observation to the wave-powered vehicle, and the wave-powered vehicle can report the results of the observation to a remote location. The UAV can land on water and can then be recovered by the wave-powered vehicle.

Abstract translation: 结合使用波动车辆和无人机（无人机或无人机）的设备和方法。 无人机可以从波浪式车辆发射，观察另一艘船，并将其观测结果报告给波动车辆，波浪式车辆可以将观测结果报告给偏远地区。 无人机可以登陆水面，然后可以由波浪式车辆回收。

公开(公告)号：WO2014035518A2

公开(公告)日：2014-03-06

申请号：PCT/US2013044697

申请日：2013-06-07

Applicant: AEROVIRONMENT INC

Inventor： ANDRYUKOVQ OLEKSANDR

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201

Abstract: An unmanned aerial vehicle (UAV) launch tube (100) that has at least one layer of prepeg substrate disposed about an aperture (106) to form a tube, a sabot (110) disposed in an interior of said tube (100), said sabot (110) having a first clasp tab (126), and a clasp (124) detachably coupled to said first clasp tab and contacting an inner circumferential wall (102) of said tube (100) so that said clasp (124) is rotationally constrained by the inner circumferential wall (102) and said first clasp tab (126).

Abstract translation: 1。一种无人飞行器（UAV）发射管（100），其具有至少一层围绕孔（106）设置以形成管的预剥离基板，设置在所述管（100）内部的弹壳（110），所述 具有第一扣紧片（126）的弹壳（110）和可拆卸地连接到所述第一扣紧片并与所述管（100）的内圆周壁（102）接触的扣环（124），使得所述扣环（124）旋转地 由内圆周壁（102）和所述第一扣钩（126）约束。

公开(公告)号：WO2013126111A3

公开(公告)日：2013-10-17

申请号：PCT/US2012067086

申请日：2012-11-29

Applicant: AEROVIRONMENT INC ,  SU GUAN ,  RODRIGUEZ MARCOS

Inventor： SU GUAN ,  RODRIGUEZ MARCOS

IPC: F41F3/04 ,  B64C1/00 ,  B64F1/04 ,  F41A15/00

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/201 ,  B64F1/06 ,  F41B11/80 ,  F41F3/00 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).

Abstract translation: 公开了一种无人驾驶飞行器（UAV）发射装置，其包括具有外表面的UAV（400），从外表面延伸的飞行器（AV）突片（510），包含无人机（400）的管（440） ），所述管（440）包括构造成可控制地阻碍所述AV突片（510）经过所述突片止动件（515）的移动的突片止动件（515），以及一对相对的突片引导件（700,705），其被配置为 AV选项卡（510），用于在制表位（515）上移动。

公开(公告)号：WO2012130790A2

公开(公告)日：2012-10-04

申请号：PCT/EP2012/055298

申请日：2012-03-26

Applicant: PROX DYNAMICS AS ,  MUREN, Petter

Inventor： MUREN, Petter

IPC: B64C39/02

CPC classification number: B64C39/024 ,  A63H27/12 ,  B64C39/028 ,  B64C2201/024 ,  B64C2201/127 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2203/00 ,  B64D47/08

Abstract: The embodiments herein disclose a personal UAV kit for storing, preparing and remote control of micro UAVs. The UAV kit includes a base unit, a control unit and at least one UAV. The UAVs can typically be a winged aircraft with foldable wings or a helicopter with a two-bladed or foldable rotor. The base unit comprises UAV compartments for housing at least one UAV, a bay for storing the control unit, batteries and electronic components for charging, communication, control and processing and storing of data. In addition, the system includes an eye near display device for viewing system information and sensor data, typically live video, transmitted from the UAV.

Abstract translation: 本文的实施例公开了用于存储，准备和远程控制微型无人机的个人UAV套件。 UAV套件包括基本单元，控制单元和至少一个UAV。 无人机通常可以是具有可折叠翼的有翼飞机或具有双叶片或可折叠转子的直升机。 基座单元包括用于容纳至少一个UAV的UAV隔间，用于存储控制单元的舱，用于对数据进行充电，通信，控制和处理和存储的电池和电子组件。 此外，该系统包括用于观看系统信息的眼睛附近，以及从UAV发送的通常是实时视频的传感器数据。

公开(公告)号：WO2012099699A1

公开(公告)日：2012-07-26

申请号：PCT/US2011/068207

申请日：2011-12-30

Applicant: INFORMATION SYSTEMS LABORATORIES, INC.

Inventor： VAN STAAGEN, Peter, K. ,  MCDANIEL, William, Douglas ,  BOSCHMA, James, H., Jr.

IPC: B64F3/00

CPC classification number: B64B1/50 ,  B64B1/58 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/123 ,  B64C2201/201 ,  B64C2201/208 ,  B64F1/14

Abstract: A system and method for deploying a payload with an aerostat uses a mobile transporter for moving the system to a deployment site. Structurally, the system includes a base unit with a rotation head mounted thereon. An envelope container for holding a deflated aerostat is mounted on the rotation head and a rotation of the container on the rotation head positions the aerostat for optimal compliance with the existing wind condition. Also included in the system is an inflator that is mounted on the base unit to inflate the aerostat with a Helium gas. And, the system includes a tether control unit for maintaining a connection with the aerostat during its deployment, in-flight use, and recovery. Preferably, a deployment computer is used for a coordinated control of the rotation head, inflator and tether.

Abstract translation: 用空气净化器部署有效载荷的系统和方法使用移动运输装置将系统移动到部署现场。 在结构上，该系统包括其上安装有旋转头的基座单元。 用于保持放气空气净化器的信封容器安装在旋转头上，并且旋转头上的容器的旋转定位了空气调节器，以最佳地符合现有的风况。 还包括在系统中的是充气机，其安装在基座单元上，以用氦气对空气净化器进行充气。 而且，该系统包括一个系绳控制单元，用于在其部署，飞行中使用和恢复期间维持与浮空器的连接。 优选地，部署计算机用于旋转头，充气机和系绳的协调控制。

公开(公告)号：WO2011137335A1

公开(公告)日：2011-11-03

申请号：PCT/US2011/034543

申请日：2011-04-29

Applicant: ELBIT SYSTEMS OF AMERICA, LLC ,  FISHER, Jeremy, F.

Inventor： FISHER, Jeremy, F.

IPC: B64C3/56 ,  B64D1/02 ,  F42B15/10

CPC classification number: F42B15/10 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/165 ,  B64C2201/167 ,  B64C2201/201 ,  B64C2201/205 ,  F41F1/08 ,  F41F3/042

Abstract: A sonar buoy includes a fuselage having a tube-like shape, one or more wings coupled to the fuselage, an engine coupled to the fuselage and operable to propel the sonar buoy through flight, and a guidance computer operable to direct the sonar buoy to a predetermined location. The sonar buoy further includes a sonar detachably coupled to the fuselage and forming at least a part of the fuselage, and a rocket motor detachably coupled to the fuselage. The one or more wings are operable to be folded into a position to allow the sonar buoy to be disposed within a launch tube coupled to a vehicle and to automatically deploy to an appropriate position for flight after the sonar buoy is launched from the launch tube. The rocket motor propels the sonar buoy from the launch tube and detaches from the fuselage after launch.

Abstract translation: 声纳浮标包括具有管状形状的机身，耦合到机身的一个或多个翼，耦合到机身并可操作以通过飞行推进声纳浮标的发动机，以及引导计算机，其可操作以将声纳浮标引导到 预定位置。 声纳浮标还包括可拆卸地联接到机身并形成机身的至少一部分的声纳和可拆卸地联接到机身的火箭发动机。 一个或多个翼可操作以折叠到允许声纳浮标布置在联接到车辆的发射管内并且在从发射管发射声纳浮标之后自动部署到适当位置进行飞行的位置。 火箭发动机从发射管推进声纳浮标，并在发射后从机身分离。

公开(公告)号：WO2011066030A2

公开(公告)日：2011-06-03

申请号：PCT/US2010048313

申请日：2010-09-09

Applicant: AEROVIRONMENT INC ,  MIRALLES CARLOS THOMAS ,  SU GUAN H ,  ANDRYUKOV OLEKSANDR ,  MCNEIL JOHN

Inventor： MIRALLES CARLOS THOMAS ,  SU GUAN H ,  ANDRYUKOV OLEKSANDR ,  MCNEIL JOHN

IPC: B64F1/04 ,  B64C13/20 ,  F41F3/04

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/201 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F41F3/042 ,  F42B39/14

Abstract: An unmanned aerial vehicle (UAV) launch tube (100) that comprises at least one inner layer of prepreg substrate (370) disposed about a right parallelepiped aperture (305), at least one outer layer of prepreg substrate (380) disposed about the right parallelepiped aperture (305), and one or more structural panels (341-344) disposed between the at least one inner layer of prepreg substrate (340) and the at least one outer layer of prepreg substrate (380). An unmanned aerial vehicle (UAV) launch tube (100) that comprises a tethered sabot (700,740) configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot (700,740) dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot (700,740) is hollow having an open end oriented toward a high pressure volume and a tether (740) attached within a hollow (910) of the sabot (700) and attached to the inner wall retaining the high pressure volume or attach to the inner base wall (1013). A system comprising a communication node (1500-1505) and a launcher (1520) comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node (1500-1505).

Abstract translation: 一种无人驾驶飞行器（UAV）发射管（100），其包括设置在右平行六面体孔（305）周围的至少一个预浸料衬底内层（370），至少一个预浸料衬底外周层 平行六面体孔（305）和设置在至少一层预浸料衬底（340）的内层与至少一层预浸料衬底（380）之间的一个或多个结构板（341-344）。 一种无人驾驶飞行器（UAV）发射管（100），其包括被配置成将内部空间限定的发射器体内的无人机接合的拴系膛（700,740），所述拴系膛（700,740）的尺寸被设计成在内部提供压力密封 并且其中所述系留式破坏物（700,740）是中空的，具有朝向高压容积定向的开口端和连接在所述破坏物（700）的中空（910）内的系绳（740），并且附接到 所述内壁保持高压容积或附接到所述内底壁（1013）。 包括通信节点（1500-1505）和发射器（1520）的系统，其包括处于预发射状态的无人驾驶飞行器（UAV），其被配置为接收并响应来自通信节点（1500-1505）的命令输入。

公开(公告)号：WO2007084172A3

公开(公告)日：2008-08-21

申请号：PCT/US2006016734

申请日：2006-05-01

Applicant: LOCKHEED MARTIN CORP MARYLAND

Inventor： STEELE DANIEL W

IPC: B64F1/22

CPC classification number: B64F1/04 ,  B64C2201/08 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/02

Abstract: An embodiment of the invention is directed to a system for controlling and managing a small unmanned air vehicle (UAV) between capture and launch of the UAV. The system includes an enclosure that provides environmental protection and isolation for multiple small UAVs in assembled and/or partially disassembled states. Control and management of the UAVs includes reorientation of a captured UAV from a landing platform and secure hand-off to the enclosure, decontamination, de-fueling, ingress to the enclosure, downloading of mission payload, UAV disassembly, stowage, retrieval and reassembly of the UAV, mission uploading, egress of the UAV from the enclosure, fueling, engine testing and launch readiness. An exemplary system includes two or more robots controlled by a multiple robot controller for autonomously carrying out the functions described above. A modular, compact, portable and autonomous system of UAV control and management is described.

Abstract translation: 本发明的实施例涉及一种用于在捕获和发射UAV之间控制和管理小型无人驾驶飞行器（UAV）的系统。 该系统包括为组装和/或部分拆卸状态下的多台小型无人机提供环境保护和隔离的外壳。 无人机的控制和管理包括从着陆平台重新定位捕获的无人机，并确保切换到机柜，去污，去加油，进入机柜，下载任务有效载荷，无人机拆卸，装载，检索和重新组装 无人机，任务上载，无人机从外壳出来，加油，发动机测试和发射准备。 示例性系统包括由多机器人控制器控制的两个或更多个机器人，用于自主执行上述功能。 描述了UAV控制和管理的模块化，紧凑型，便携式和自主的系统。

公开(公告)号：WO2007084186A3

公开(公告)日：2007-10-11

申请号：PCT/US2006032105

申请日：2006-08-17

Applicant: CHANG INDUSTRY INC ,  DE LA TORRE SAMUEL

Inventor： DE LA TORRE SAMUEL

IPC: B64C39/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/201 ,  B64C2201/203

Abstract: An aerial surveillance device (100) is provided, comprising an image capturing device (150.) capable of being supported by an airframe structure (200) above the ground. The airframe structure includes a body portion (300) defining a longitudinal axis and configured to support the image - capturing device. A tail portion (400) having control surfaces (425,450) is operably engaged with the body portion along the axis. Transversely- extending wing portions (800, 850) are directly engaged with the body portion. Each wing portion is defined by longitudinally-opposed spars (800A, 800B, 850A, 850B) extending from a spaced-apart disposition at the body portion to a common connection (800C, 850C) distally from the body portion. The spars have a fabric extending therebetween to provide a wing surface. A support member (900, 950) extends along an aerodynamic center, transversely to the body portion, of each wing portion, to tension and rigidify the wing portions so as to provide a positive camber for the wing portions and to form an airfoil.

Abstract translation: 提供了一种空中监视装置（100），包括能够由地面上方的机身结构（200）支撑的图像捕获装置（150）。 机身结构包括限定纵向轴线并构造成支撑图像捕获装置的主体部分（300）。 具有控制表面（425,450）的尾部（400）与主体部分沿轴线可操作地接合。 横向延伸的翼部（800,850）直接与主体部分接合。 每个翼部分由纵向相对的翼梁（800A，800B，850A，850B）限定，该翼梁从主体部分处的间隔布置延伸到远离主体部分的公共连接（800C，850C）。 翼梁具有在其间延伸的织物以提供机翼表面。 支撑构件（900,950）沿着每个翼部的横向于主体部分的空气动力学中心延伸，以张紧和刚化翼部，以便为翼部提供正弧形并形成翼型。