公开(公告)号：US08536501B2

公开(公告)日：2013-09-17

申请号：US10692039

申请日：2003-10-22

Applicant: Minas Tanielian

Inventor： Minas Tanielian

IPC: F41G7/24 ,  F42B15/01 ,  F41G7/00 ,  F42B15/00

CPC classification number: B64C39/024 ,  B64C2201/022 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/101 ,  B64C2201/108 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64C2201/162 ,  B64C2201/208 ,  B64D2211/00 ,  G05D1/0022 ,  H02J7/025 ,  H02J17/00 ,  H02J50/30 ,  H02J50/50 ,  H02J50/90 ,  Y02T50/55

Abstract: The present invention provides a position control system for a remote-controlled vehicle, a vehicle operated by the control system, and a method for operating a remote-controlled vehicle. An electromagnetic energy receiver is configured to receive an electromagnetic beam. The electromagnetic energy receiver is further configured to determine a position of the remote-controlled vehicle relative to a position of the electromagnetic beam. The vehicle is directed to maneuver to track the position of the electromagnetic beam.

Abstract translation: 本发明提供了一种用于遥控车辆的位置控制系统，由控制系统操作的车辆以及用于操作遥控车辆的方法。 电磁能量接收器被配置为接收电磁波束。 电磁能量接收器还被配置为确定遥控车辆相对于电磁波束的位置的位置。 车辆被引导以操纵以跟踪电磁波束的位置。

公开(公告)号：US08511607B2

公开(公告)日：2013-08-20

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：US08492692B2

公开(公告)日：2013-07-23

申请号：US13097394

申请日：2011-04-29

Applicant: Jeremy F. Fisher

Inventor： Jeremy F. Fisher

IPC: F42B12/56 ,  F42B15/01 ,  F42B15/08 ,  H04B1/59 ,  F42B15/00 ,  H04B1/00

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，耦合到机身的发动机，并且可操作以通过飞行推进声纳浮标;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用于飞行的位置。 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：US20130020428A1

公开(公告)日：2013-01-24

申请号：US13623551

申请日：2012-09-20

Applicant: Gerald Miller ,  James Stewart

Inventor： Gerald Miller ,  James Stewart

IPC: F41G7/22 ,  B64F1/04

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：US08276844B2

公开(公告)日：2012-10-02

申请号：US12364206

申请日：2009-02-02

Applicant: Amnon Kariv

Inventor： Amnon Kariv

IPC: B64F1/02

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

Abstract: The invention relates to a system for landing UAV's. The system comprises a slingshot structure that includes arm based structure and an axis installed along the arm of the structure and enabling the arm to move around it. The system comprises a base connecting the axis to a platform at which the system is installable. The system also includes a controlled pulling and braking means that connects the arm of the structure and the platform upon which the system is installable and stretchable elastic 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 of the system essentially breaks the motion of the arm based structure that is propelled to revolve around the system's axis, and propels the structure to move around the axis.

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并且使得臂能够在其周围移动。 该系统包括将轴连接到可安装系统的平台的基座。 该系统还包括控制的拉动和制动装置，其连接结构的臂和系统可安装的平台和可拉伸的弹性的平台，其以形成在两个臂之间的间隙的方式安装并设置成与着陆UAV连接。 在着陆阶段，系统的受控牵引和制动基本上打破了基于臂的结构的运动，该结构被推进围绕系统的轴线旋转，并且推动结构围绕轴移动。

公开(公告)号：US08191831B2

公开(公告)日：2012-06-05

申请号：US11992188

申请日：2005-11-30

Applicant: Ronen Nadir

Inventor： Ronen Nadir

IPC: B64D17/00 ,  B64D17/54

CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/104 ,  B64C2201/146 ,  B64C2201/185 ,  B64D17/80

Abstract: The disclosure provides a parachute release device which may include a connecting element capable of connecting to an aircraft and to a parachute and a locking mechanism capable of releasing the connecting element from the aircraft upon being actuated by an actuator, wherein the parachute may be connected to the connecting element by a multiplicity of points, wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator and wherein the device may be suitable for use in small weights aircrafts due to its small size and weight. The disclosure further provides a method for releasing a parachute from an aircraft, the method may include activating an actuator capable of releasing a locking mechanism, wherein the locking mechanism is adapted to release a connecting element from an aircraft upon being actuated, wherein the connecting element is adapted to connect a parachute and wherein the locking mechanism is adapted to inhibit a force from being applied to the actuator.

Abstract translation: 本公开提供了一种降落伞释放装置，其可以包括能够连接到飞机和降落伞的连接元件，以及能够由致动器致动时能够从飞行器释放连接元件的锁定机构，其中降落伞可以连接到 所述连接元件由多个点组成，其中所述锁定机构适于阻止施加到所述致动器的力，并且其中所述装置由于其小的尺寸和重量而适合用于小型重量飞机。 本发明还提供了一种用于从飞行器释放降落伞的方法，所述方法可包括激活能够释放锁定机构的致动器，其中所述锁定机构适于在致动时从飞行器释放连接元件，其中所述连接元件 适于连接降落伞，并且其中所述锁定机构适于阻止施加在所述致动器上的力。

公开(公告)号：US08157203B2

公开(公告)日：2012-04-17

申请号：US12262747

申请日：2008-10-31

Applicant: Lloyd E. Kinsey ,  Patrick Kranking

Inventor： Lloyd E. Kinsey ,  Patrick Kranking

IPC: B64C27/22

CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/028 ,  B64C2201/084 ,  B64C2201/088

Abstract: Methods and apparatus for a transforming aerial vehicle according to various aspects of the present invention may operate in conjunction with a launch system configured to rotate the aerial vehicle about its longitudinal axis. A lifting surface pivotally connected to the aerial vehicle may be positioned such that the rotation of the aerial vehicle causes the lifting surface to generate a lifting force on the aerial vehicle. This lift causes the aerial vehicle to rise gyroscopically before the lifting surface is rotated to a second position such that the aerial vehicle transforms from a gyroscopic mode to a fixed-wing aerial vehicle. The lifting surface may then be rotated again to allow the aerial vehicle to land as an auto gyro.

Abstract translation: 根据本发明的各个方面的用于变换航空器的方法和装置可以与被配置为围绕其纵向轴线旋转飞行器的发射系统一起操作。 枢转地连接到飞行器的提升表面可以被定位成使得飞行器的旋转导致提升表面在飞行器上产生提升力。 该升降机使得飞行器在提升表面旋转到第二位置之前陀螺地升高，使得飞行器从陀螺仪模式转换为固定翼型飞行器。 然后可以再次旋转提升表面，以允许飞行器作为自动陀螺仪着陆。

公开(公告)号：US20120080556A1

公开(公告)日：2012-04-05

申请号：US12897926

申请日：2010-10-05

Applicant: George Raymond Root, JR.

Inventor： George Raymond Root, JR.

IPC: B64F1/04 ,  B65D88/00 ,  G01W1/00 ,  B64F1/02

CPC classification number: B64F1/02 ,  B64C2201/084 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/06 ,  G01W1/08

Abstract: Systems and methods are disclosed for autonomous or remote-controlled operation of unmanned aerial vehicles (“UAVs”). An integrated mechanical and electrical system is capable of launching, controlling, snagging, recovering, securing, parking, and servicing UAVs without human intervention at the site of the system. The illustrative embodiment comprises a boom and a container that houses the boom and UAV(s). The boom rotates about its longitudinal axis to operationally orient a plurality of faces thereof. Each face is associated with certain system operations, including but not limited to: launching a UAV, snagging a UAV from the air, and securing a UAV to the boom.

Abstract translation: 公开了用于无人驾驶飞行器（“UAV”）的自主或遥控操作的系统和方法。 集成的机电系统能够在系统现场无需人为干预即可启动，控制，拦截，恢复，固定，停车和维修无人机。 说明性实施例包括悬臂和容纳悬臂和无人机的容器。 吊臂围绕其纵向轴线旋转以可操作地定向其多个面。 每个人的脸都与某些系统操作相关联，包括但不限于：发射无人机，从无人机上吸住无人机，并将无人机固定在繁荣时期。

公开(公告)号：US20110101155A1

公开(公告)日：2011-05-05

申请号：US12612227

申请日：2009-11-04

Applicant: Timothy D. Smith

Inventor： Timothy D. Smith

IPC: B64C29/04

CPC classification number: B64C39/064 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/084 ,  B64C2201/205

Abstract: A torque production vehicle includes a plenum body having a wall with a central port and a radial port formed within the wall, an impeller disposed within the plenum body to move air through the central port, an engine coupled to the impeller to rotate the impeller about an axis, at least one arm coupled to the plenum body, and a plurality of foils disposed in the radial port to direct air about the plenum body to provide a torque force about the plenum body.

Abstract translation: 扭矩生产车辆包括具有中心端口和形成在壁内的径向端口的壁的增压室，设置在增压室内的叶轮以将空气移动通过中心端口，发动机联接到叶轮以使叶轮围绕 一个轴线，至少一个连接到集气室主体的臂，以及设置在该径向端口中的多个箔，以引导围绕该增压室的空气以提供围绕该增压室的转矩力。

公开(公告)号：US07739938B2

公开(公告)日：2010-06-22

申请号：US11856037

申请日：2007-09-15

Applicant: Michael L. Nair ,  John A. Condon

Inventor： Michael L. Nair ,  John A. Condon

IPC: F41A1/04

CPC classification number: B64F1/04 ,  B64C2201/084 ,  F41A21/18 ,  F41B11/62 ,  F41F1/00

Abstract: The launching of an unmanned projectile includes pre-packaging a barrel with a projectile, a pusher cup, and a gas generator. The gas generator generates gas to propel the projectile out of the barrel. A pressure chamber increases a pressure of the gas in the barrel. The pressure chamber comprises a front body portion connected to the gas generator; an aft body portion connected to the front body portion and the gas generator; and a vent sleeve positioned around the front body portion and adapted to provide an aperture through which the gas exits the barrel in order to control a level of gas pressure in the barrel. A triggering of the gas generator causes the pusher cup to push the projectile out of the barrel at a predetermined launch velocity in order to attain a predetermined self-propelled flight trajectory, wherein the triggering causes the pusher cup to exit the barrel.

Abstract translation: 发射无人射弹包括用弹丸预先包装桶，推杯和气体发生器。 气体发生器产生气体以将射弹推出枪​​管。 压力室增加了桶中气体的压力。 压力室包括连接到气体发生器的前主体部分; 连接到前主体部分和气体发生器的后体部分; 以及排气套，其定位在前主体部分周围并且适于提供孔，气体通过该孔离开筒体，以便控制桶中的气体压力水平。 气体发生器的触发导致推动器杯以预定的发射速度将射弹推出筒体，以便获得预定的自推进飞行轨迹，其中触发使推动杯离开枪管。