公开(公告)号：US20120097801A1

公开(公告)日：2012-04-26

申请号：US13279827

申请日：2011-10-24

Applicant: Ronald M. Barrett

Inventor： Ronald M. Barrett

IPC: B64C27/24 ,  B64C29/00 ,  B64C27/00 ,  B64C30/00

CPC classification number: B64C29/02 ,  B64C27/24 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/084 ,  B64C2201/102

Abstract: Embodiments of the present invention include an aircraft capable of sustained out-of-ground-effect hover flight and sustained supersonic flight. At least some embodiments includes two wings powered by an engine to counterrotate while hovering, and to not rotate and sweep while flying at transonic and supersonic speeds. Other embodiments include two rotating wings that generate a force per unit area of under 100 lb/ft2 within the rotating wing disk during hover. Still other embodiment include a vehicle with rotating wings that can increase pitch to accelerate the aircraft, align the chord line of the wings with the airstream, and sweep the wings. Still further embodiments include a power plant that powers unducted rotating wings during hover and disengages from the wings to propel the aircraft at supersonic speeds.

Abstract translation: 本发明的实施例包括能够持续地面效应悬停飞行和持续的超音速飞行的飞机。 至少一些实施例包括由发动机驱动的两个翼，以在盘旋时反向旋转，并且在以跨音速和超音速飞行的同时不旋转和扫掠。 其它实施例包括两个旋转翼，其在悬停期间在旋转翼盘内产生每100英寸/ ft 2以下的每单位面积的力。 另外的实施例包括具有旋转翼的车辆，其可以增加俯仰以加速飞行器，将翼的弦线与气流对准，并且扫掠翼。 另外的实施例包括在悬停期间为未被引导的旋转翼提供动力的动力装置，并且与翼分离，以超音速推进飞行器。

公开(公告)号：US20120012695A1

公开(公告)日：2012-01-19

申请号：US12836496

申请日：2010-07-14

Applicant: Andrew B. Robinson

Inventor： Andrew B. Robinson

IPC: B64F1/04

CPC classification number: B64F1/04 ,  B64C2201/021 ,  B64C2201/084 ,  B64F1/06

Abstract: A UAV attachment assembly, used with a UAV launch assembly comprising a frame and a launch driver, comprises a base, a UAV support, a biasing element, a coupler, and a retainer. The base is operably coupled to the launch driver. The UAV support is mounted to the base and is placeable in vertically collapsed and vertically extended orientations. The biasing element biases the UAV support towards the collapsed orientation. The coupler releasably couples the UAV support to a UAV when the UAV support is in the extended orientation, the UAV support being free of the UAV when in the collapsed orientation. The retainer maintains the UAV support in the vertically extended orientation prior to launch and releases the UAV support at launch so that the biasing element can cause the UAV support to move towards the collapsed orientation and to disengage from the UAV.

Abstract translation: 与包括框架和发射驱动器的UAV发射组件一起使用的UAV附件组件包括基座，UAV支撑件，偏置元件，联接器和保持器。 基座可操作地联接到发射驱动器。 无人机支撑安装在基座上，可放置在垂直折叠和垂直延伸的方向上。 偏置元件使无人机支撑朝向折叠方向偏移。 当UAV支撑处于延伸方向时，联接器将UAV支撑件可释放地耦合到UAV，UAV支撑在处于折叠方向时无UAV。 保持架在启动之前将UAV支撑件保持在垂直延伸的方向，并在发射时释放UAV支撑，使得偏置元件可以使UAV支撑件朝向折叠方向移动并与UAV脱离接合。

公开(公告)号：US20110147515A1

公开(公告)日：2011-06-23

申请号：US12640585

申请日：2009-12-17

Applicant: Gerald Miller ,  James Stewart

Inventor： Gerald Miller ,  James Stewart

IPC: G05D1/12 ,  B64F1/04 ,  F23Q7/00 ,  G05D1/00 ,  G01C21/00 ,  G01C21/16 ,  F42C13/00

CPC classification number: B64C19/00 ,  B64C39/028 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/201 ,  B64C2201/203 ,  F41F3/042 ,  F41G7/008 ,  F41G7/2206 ,  F41G7/2253 ,  F41G7/2293 ,  F42B12/20 ,  F42B12/365 ,  F42B15/01 ,  F42B15/10 ,  G05D1/12

Abstract: An unmanned aerial vehicle including a controller operating in a search mode of operation where a receiver of an acquisition sensor searches for a target and causes flight control surfaces to guide the vehicle in a downward spiral path, a terminal mode of operation where the acquisition sensor detects a target and causes flight control surfaces to direct the vehicle toward the target, and an activation mode of operation where a trigger sensor detects a target within a predetermined distance to the vehicle and the controller activates a responder.

Abstract translation: 一种无人驾驶飞行器，其包括在搜索操作模式下操作的控制器，其中采集传感器的接收器搜索目标并使飞行控制表面以向下的螺旋路径引导车辆，其中采集传感器检测到的操作的终端操作 目标并使飞行控制表面引导车辆朝向目标;以及激活操作模式，其中触发传感器检测到与车辆预定距离内的目标，并且控制器激活响应者。

公开(公告)号：US20110024559A1

公开(公告)日：2011-02-03

申请号：US12702935

申请日：2010-02-09

Applicant: Brian T. McGeer ,  Andreas H. Von Flotow

Inventor： Brian T. McGeer ,  Andreas H. Von Flotow

IPC: B64C25/68

CPC classification number: B64F1/12 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/084 ,  B64C2201/182 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06 ,  B64F1/125 ,  B64F1/28 ,  B64F5/00

Abstract: An aircraft capable of thrust-borne flight can be automatically retrieved, serviced, and launched using equipment suitable for use on a small vessel, or a base with similarly limited space or irregular motion. For retrieval, the aircraft drops a weighted cable, and pulls it at low relative speed into a broad aperture of a base apparatus. Continued translation of the aircraft may pull the cable clear of the apparatus, in which case it can continue in free flight and return for another retrieval attempt. Alternatively, the cable will be dragged along guiding surfaces of the apparatus into and through a slot or similar channel, until its free end is captured. The aircraft, having thus become anchored to the base station, is then pulled down by the cable into a receptacle. Guiding surfaces of the receptacle adjust the position and orientation of a probe on the aircraft, while directing the probe to mate with a docking fixture. Once mated to the fixture, the cable can be released and stored aboard the aircraft; the aircraft can be automatically shut down; and fueling or other servicing can be completed through appropriate connectors in the docking fixture. The aircraft can remain docked as needed, and when desired, be automatically started and tested in preparation for launch. It can then be released into free flight. A full ground-handling cycle can thus accomplished with simple and economical apparatus. It can be used with low risk of damage, and only moderate piloting accuracy.

Abstract translation: 可以使用适合在小型船舶上使用的设备或具有相似空间或不规则运动的基座来自动检索，维修和启动能够推力飞行的飞机。 为了进行检索，飞机将一个加权电缆丢弃，并以相对较低的速度将其拉到一个基本设备的宽孔中。 飞机的连续翻译可将电缆从设备中拉出，在这种情况下，它可以继续自由飞行并返回以进行另外的检测尝试。 或者，电缆将沿着设备的引导表面拖入并穿过槽或相似的通道，直到其自由端被捕获。 因此，已经锚定到基站的飞机然后被电缆拉到插座中。 插座的导向面调整飞机上探头的位置和方向，同时引导探头与对接固定装置配合。 一旦配合到固定装置上，电缆可以被释放并存放在飞机上; 飞机可以自动关机; 并且可以通过对接固定装置中的适当连接器来完成加油或其它维修。 飞机可以根据需要保持对接，并且在需要时，可以自动启动和测试以准备发射。 然后可以将其释放到免费飞行中。 因此，可以用简单而经济的装置实现完整的地面处理循环。 它可以使用低损害风险，只有适度的驾驶准确性。

公开(公告)号：US20090224097A1

公开(公告)日：2009-09-10

申请号：US12364206

申请日：2009-02-02

Applicant: Amnon Kariv

Inventor： Amnon Kariv

IPC: B64F1/02 ,  B64F1/04

CPC classification number: B64F1/06 ,  B64C2201/084 ,  B64C2201/182 ,  B64F1/02

Abstract: The present invention relates to a system for landing UAV's. The system comprises a slingshot structure that includes arm based structure and an axis means installed along the arm of the structure and wherein it enables the arm to move around it in addition, the system comprises base means connecting the axis means to a platform at which the system is installable. The system also include a controlled pulling and braking means that connects between the arm of the structure and the platform upon which the system is installable and a stretchable elastic means installed in a stretched manner at a gap formed between two arms and set to connect with a landing UAV. At the landing phase, the controlled pulling and braking means of the system, essentially breaks the motion of the arm based structure that is propelled to revolve around the system's axis means, from a time that the UAV forms contact with the elastic means and with it propels the structure to move around the axis means.

Abstract translation: 本发明涉及无人机的着陆系统。 该系统包括弹弓结构，其包括基于臂的结构和沿着结构的臂安装的轴线装置，并且其中使得臂能够围绕它移动，该系统包括将轴装置连接到平台的基部装置， 系统可以安装。 该系统还包括连接在结构的臂和系统可安装的平台之间的受控的拉动和制动装置，以及以可伸缩的方式安装在两个臂之间的间隙处的可拉伸的弹性装置，并设置成与一个 登陆无人机。 在着陆阶段，系统的受控牵引和制动装置基本上打破了从无人机与弹性装置接触的时间开始推进而围绕系统的轴线装置旋转的基于臂的结构的运动 推动结构围绕轴移动。

公开(公告)号：US07335067B2

公开(公告)日：2008-02-26

申请号：US11191094

申请日：2005-07-27

Applicant: Kang Lee ,  Thomas Forrester ,  Tomasz Jannson ,  Andrew Kostrzewski ,  Gajendra Savant

Inventor： Kang Lee ,  Thomas Forrester ,  Tomasz Jannson ,  Andrew Kostrzewski ,  Gajendra Savant

IPC: H01R13/24

CPC classification number: B64F1/06 ,  B64C2201/084 ,  B64C2201/182 ,  H01R13/005 ,  H01R13/2421 ,  H01R35/04 ,  H01R39/64 ,  Y10T403/32606

Abstract: Two embodiments of a connector that can be mated without regard for its orientation are disclosed. One embodiment is mated and demated autonomously as part of a system for recovering, docking with, recharging and re-launching unmanned aerial vehicles. Another embodiment is employed on the decks of vessels to facilitate mating and demating of various equipment providing different functions to reconfigure the vessel. Because both embodiments are configured for connection irrespective of angular orientation over 360°, they are especially suited for harsh environments including autonomous operation, rough seas, darkness and the like.

Abstract translation: 公开了可以不考虑其取向而配合的连接器的两个实施例。 作为用于恢复，对接，再充电和重新发射无人驾驶飞行器的系统的一部分，一个实施例被自动地配合和排列。 在容器的甲板上采用另一个实施例，以便于提供不同功能的各种设备的配合和排气以重新配置容器。 由于两个实施例都被配置为连接，而不管角度取向超过360°，它们特别适用于恶劣的环境，包括自主操作，粗糙的海洋，黑暗等。

公开(公告)号：US07318565B2

公开(公告)日：2008-01-15

申请号：US11304535

申请日：2005-12-16

Applicant: Gregory S. Page

Inventor： Gregory S. Page

IPC: B64F1/10

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/165 ,  F42B15/36

Abstract: A takeoff assist device for an air vehicle, such as an unmanned air vehicle is provided. The device features an electric motor and is much less complex and lighter than takeoff assist devices heretofore known. A body member is shaped to fit to a portion of the air vehicle. The body member defines a housing in which the majority of the components are housed, including the electric motor, a motor controller, an electrical power source and a main controller. A propeller is attached to a shaft of the electric motor outside of the housing and rotates with a shaft of the electric motor. In addition, there is a latch mechanism that removeably attaches the body member to the host air vehicle for takeoff, and then is controlled to release from the air vehicle after it is airborne at a desired airspeed and altitude. The electric motor-driven takeoff assist device can launch an air vehicle with minimal auxiliary equipment and can be remotely controlled to launch from a site at which a takeoff ready vehicle can be left for extended periods of time.

Abstract translation: 提供了一种用于空中客车的起飞辅助装置，例如无人机。 该装置具有电动机，并且比迄今为止已知的起飞辅助装置复杂和轻巧。 身体构件被成形为适合于空中车辆的一部分。 主体构件限定了容纳大部分部件的壳体，包括电动马达，马达控制器，电源和主控制器。 螺旋桨安装在外壳外的电动机的轴上，并与电动机的轴一起旋转。 此外，还有一个可将主体部件可移除地连接到主机空中的起飞位置的闩锁机构，然后在空气车辆以期望的空速和高度空降后被控制以释放。 电动马达起飞辅助装置可以发射具有最小辅助设备的空中飞行器，并且可以远程控制以从起飞准备好的车辆可以长时间留下的地点发射。

公开(公告)号：US07210654B1

公开(公告)日：2007-05-01

申请号：US10625399

申请日：2003-07-23

Applicant: Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

Inventor： Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

IPC: B64F1/06

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64F1/06 ,  F42B12/365 ,  Y02T50/82

Abstract: An unmanned airborne reconnaissance system, the unmanned airborne reconnaissance system including a lightweight, portable, powered aircraft and a foldable launch rail, the aircraft, in a broken down condition and the launch rail in a broken down condition fitable inside a box, the box capable of being carried by one man. The launch system includes an elongated launch rail with the carriage assembly, and a propulsion means for accelerating the carriage assembly from one end of the launch rail to the other. The carriage assembly releasably engages the aircraft so as to propel the aircraft from one end of the launch rail to the other. The propulsion may be by a cartridge that explodes and releases a gas through a cylinder, or by elastic cords. The aircraft is guided through the air either by a programmed onboard computer which controls the control surfaces of the aircraft and/or by remote control. The aircraft typically contains a camera for recording and transmitting images received from the ground below.

Abstract translation: 一种无人机载侦察系统，无人机载侦察系统，包括轻型便携式动力飞机和折叠式发射轨道，该飞机处于分解状态，发射导轨处于可折叠状态的箱体内，该箱体能够 由一个男人携带。 发射系统包括具有滑架组件的细长的发射轨道和用于将滑架组件从发射轨道的一端加速到另一端的推进装置。 滑架组件可释放地接合飞行器，以便将飞机从发射轨的一端推动到另一端。 推进可以是通过气缸爆炸和释放气体的弹药筒或弹性帘线。 飞机通过编程的机载计算机被引导通过空中，控制飞机的控制面和/或通过遥控。 飞机通常包含用于记录和发射从下面接地的图像的照相机。

公开(公告)号：US07175135B2

公开(公告)日：2007-02-13

申请号：US10759545

申请日：2004-01-16

Applicant: Brian D. Dennis ,  Brian T. McGeer ,  Cory Roeseler

Inventor： Brian D. Dennis ,  Brian T. McGeer ,  Cory Roeseler

IPC: B64F1/02

CPC classification number: B64C39/024 ,  B64C25/68 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06

Abstract: Methods and apparatuses for capturing and constraining motion of unmanned aircraft and other flight devices or projectiles. In one embodiment, the aircraft can be captured at an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. A trigger mechanism coupled to the recovery line can actuate a hoist device to reduce slack in the recovery line. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft on the recovery line.

Abstract translation: 用于捕获和限制无人驾驶飞机和其他飞行装置或射弹的运动的方法和装置。 在一个实施例中，飞机可以在可延伸的吊杆上被捕获。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 联接到回收管线的触发机构可以启动提升装置以减少回收管线中的松弛。 耦合到回收管线的张紧装置可以吸收与飞机在回收管线上的冲击相关联的力。

公开(公告)号：US20060102783A1

公开(公告)日：2006-05-18

申请号：US10758956

申请日：2004-01-16

Applicant: Brian Dennis ,  Clifford Jackson ,  Brian McGeer ,  Andreas von Flotow

Inventor： Brian Dennis ,  Clifford Jackson ,  Brian McGeer ,  Andreas von Flotow

IPC: B64F1/02

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/06 ,  B64F1/222

Abstract: Methods and apparatuses for capturing and recovering unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be captured at an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. The boom can be retracted when not in use to reduce the volume it occupies. A tension device coupled to the recovery line can absorb forces associated with the impact of the aircraft and the recovery line.

Abstract translation: 描述了用于捕获和恢复无人驾驶飞机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞机可以在可延伸的吊杆上被捕获。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 当不使用吊杆时，可以收起吊杆，以减少其占用的体积。 耦合到回收管线的张紧装置可以吸收与飞行器和回收管线的冲击相关联的力。