公开(公告)号：US07114680B2

公开(公告)日：2006-10-03

申请号：US10759742

申请日：2004-01-16

Applicant: Brian D. Dennis

Inventor： Brian D. Dennis

IPC: B64F1/04

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/04

Abstract: Methods and apparatuses for launching and capturing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to retrieve the aircraft in flight. The aircraft can then be retrieved from the recovery line. The boom can be retracted when not in use to reduce the volume it occupies.

Abstract translation: 描述了用于发射和捕获无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以从包括可扩展起重臂的装置发射。 可以扩展繁荣部署恢复线以在飞行中检索飞机。 然后可以从回收线检索飞机。 当不使用吊杆时，可以收起吊杆，以减少其占用的体积。

公开(公告)号：US07104495B2

公开(公告)日：2006-09-12

申请号：US11269395

申请日：2005-11-08

Applicant: Brian T. McGeer

Inventor： Brian T. McGeer

IPC: B64F5/00

CPC classification number: B64F1/04 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64F1/02 ,  B64F1/06

Abstract: Methods and apparatuses for launching, capturing, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can be assembled from a container with little or no manual engagement by an operator. The container can include a guide structure to control motion of the aircraft components. The aircraft can be launched from an apparatus that includes an extendable boom. The boom can be extended to deploy a recovery line to capture the aircraft in flight. The aircraft can then be returned to its launch platform, disassembled, and stored in the container, again with little or no direct manual contact between the operator and the aircraft.

Abstract translation: 描述了用于发射，捕获和存储无人机和其他飞行装置或射弹的方法和装置。 在一个实施例中，飞行器可以由操作者很少或没有手动接合的容器组装。 容器可以包括用于控制飞机部件的运动的引导结构。 飞机可以从包括可伸缩吊杆的装置发射。 可以扩展繁荣部署一个恢复线，以便在飞行中捕获飞机。 飞机然后可以返回到其发射平台，拆卸并存储在容器中，再次与操作员和飞机之间的很少或没有直接的手动接触。

公开(公告)号：US07066430B2

公开(公告)日：2006-06-27

申请号：US10758956

申请日：2004-01-16

Applicant: Brian D. Dennis ,  Clifford Jackson ,  Brian T. McGeer ,  Andreas H. von Flotow

Inventor： Brian D. Dennis ,  Clifford Jackson ,  Brian T. McGeer ,  Andreas H. 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机和回收管线的冲击相关联的力。

公开(公告)号：US06576880B2

公开(公告)日：2003-06-10

申请号：US10150726

申请日：2002-05-17

Applicant: Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland, Jr.

Inventor： Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland, Jr.

IPC: B64C351

CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load and high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.

公开(公告)号：US6142421A

公开(公告)日：2000-11-07

申请号：US231368

申请日：1999-01-13

Applicant: Miles R. Palmer

Inventor： Miles R. Palmer

IPC: B64C39/02 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D37/12 ,  B64D39/00 ,  F42B15/00 ,  B64C39/00 ,  B64D37/02

CPC classification number: B64D37/12 ,  B64C39/024 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D39/00 ,  F42B15/00 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/105 ,  B64C2201/121 ,  B64C2201/126 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/205

Abstract: A vehicle refueling system includes an aero vehicle and a fuel bladder system. The fuel bladder system includes a fuel bladder, a pickup loop of a predetermined loop size, a reel mechanism to retract at least one side of the pickup loop to reduce the loop size, a snag sensor to sense when the pickup loop has been hooked by the retractable hook, the snag sensor initiating the reel mechanism, a compass to sense the random orientation of the loop, a radio navigation receiver to sense a location of the loop, and a transmitter to transmit the random orientation and the location. The vehicle includes a fuselage, a retractable hook with a hook sensor to detect when a fuel bladder is hooked and the loop size has been reduced by the reel mechanism, a fuel bladder stowage chamber within the fuselage, a fuel intake tube capable of drawing fuel from the fuel bladder stowed in the stowage chamber, a retraction mechanism to retract the retractable hook, a fuel transfer mechanism to transfer fuel from the fuel bladder into an internal fuel tank, and a fuel bladder discard mechanism to discard the fuel bladder after the fuel has been drawn from the fuel bladder.

Abstract translation: 车辆加油系统包括航空车辆和燃料囊系统。 燃料囊系统包括燃料囊，预定环尺寸的拾取环，卷绕机构，用于缩回拾取环的至少一侧以减小环的尺寸;阻挡传感器，用于感测拾取环何时已被钩住 可伸缩钩，启动卷轴机构的阻塞传感器，用于感测环路的随机取向的罗盘，用于感测回路位置的无线电导航接收器，以及发送器，以发送随机取向和位置。 车辆包括机身，具有钩传感器的可伸缩钩，用于检测燃料囊何时被钩住，并且通过卷轴机构减小了环路尺寸，机身内部的燃料囊存放室，能够吸引燃料的燃料进入管 从装载在储存室中的燃料气囊，收回缩回钩的缩回机构，用于将燃料从燃料气囊输送到内部燃料箱中的燃料转移机构，以及在燃料之后废弃燃料气囊的燃料气体排出机构 已从燃油囊中抽出。

公开(公告)号：US6119976A

公开(公告)日：2000-09-19

申请号：US13551

申请日：1998-01-27

Applicant: Michael E. Rogers

Inventor： Michael E. Rogers

IPC: B64C39/02 ,  B64C3/56

CPC classification number: B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/203

Abstract: A shoulder launched unmanned reconnaissance system for providing overhead visual surveillance of remote targets is disclosed. The present system includes a reconnaissance air vehicle which may be fired from a portable launcher, accelerated to flight speed, and remotely controlled using a ground control system. The vehicle is flown to the target area to enable an onboard wide angle video system to transmit video images of the target by radio or fiber optics link to the ground control system for processing and display. The ground control system enables the reconnaissance vehicle to be flown to a recovery area and to descend in a stall mode after the flight is completed for maintenance prior to reuse. The air vehicle includes collapsible wings which are deployable after launch by a spring actuated mechanism. The fuselage of the air vehicle carries an onboard video camera, an electric motor, a battery, a global positioning system receiver, flight controls, and a data link system.In an alternative embodiment, the fuselage of the air vehicle includes a storage bay with a rotary mechanism capable of deploying sensors for chemical and biological warfare agents or other dropable payloads such as dye markers for marking fleeing motor vehicles. The present system is capable of conducting overhead surveillance up to a range of approximately 10 kilometers.

Abstract translation: 披露了发射无人侦察系统，用于提供远程目标的架空视觉监控。 本系统包括可从便携式发射器发射的加速飞行速度的遥感飞行器，并使用地面控制系统进行远程控制。 车辆飞行到目标区域，使得车载广角视频系统能够通过无线电或光纤链路将目标的视频图像传送到地面控制系统进行处理和显示。 地面控制系统使得侦察车辆能够在飞行完成之后飞行到恢复区域并以失速模式下降，以便在重新使用之前进行维护。 机动车辆包括可弹起的机翼，它们在由弹簧致动机构发射之后可部署。 机载机身载有车载摄像机，电动马达，电池，全球定位系统接收器，飞行控制和数据链接系统。 在替代实施例中，机动车辆的机身包括具有旋转机构的存储舱，该旋转机构能够部署用于化学和生物战剂或其它可下载的有效载荷的传感器，例如用于标记逃离机动车辆的染色标记。 目前的系统能够进行大约10公里范围的架空监视。

公开(公告)号：US4530476A

公开(公告)日：1985-07-23

申请号：US292260

申请日：1981-08-12

Applicant: Charles H. Thurber, Jr. ,  Frederick A. Behrens ,  John H. Hunton

Inventor： Charles H. Thurber, Jr. ,  Frederick A. Behrens ,  John H. Hunton

IPC: B64C39/02 ,  B64F1/10 ,  F41G7/00 ,  F41G7/22 ,  F41F3/00 ,  F42B15/16

CPC classification number: F41G7/22 ,  B64C39/024 ,  B64F1/06 ,  F41G7/007 ,  B64C2201/021 ,  B64C2201/046 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/208

Abstract: A method and system for delivering ordnance to a target via a remotely piloted or programmable aircraft including a yaw-to-turn guidance system, a deployment and launching system and packaging for the aircraft are disclosed.

Abstract translation: 公开了一种用于通过远程驾驶或可编程飞行器向目标提供弹药的方法和系统，包括偏航转弯引导系统，用于飞行器的展开和发射系统和包装。

公开(公告)号：US20180134412A1

公开(公告)日：2018-05-17

申请号：US15566603

申请日：2016-04-29

Applicant: Chung Kiak POH ,  Chung How POH

Inventor： Chung Kiak POH ,  Chung How POH

IPC: B64F1/12 ,  B64C39/02 ,  H02S20/30

CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/02 ,  B64F1/222 ,  H02S20/30

Abstract: The present invention generally relates to a system and method of a docking system (1) for fixed wing unmanned aerial vehicle, or non-fixed wing unmanned aerial vehicle (2) such as rotorcraft, or combination thereof, comprising at least a docking and/or launching pad capable of being arranged in an array or staggered manner; said pad has a surface (6) for said vehicle docking and launching, said docking and launching surface (6) comprising moveable pads (31) which include electromagnets that can be energized to capture a docking vehicle (2); and another energy harvesting surface (4) has photovoltaic panel to harness solar energy to generate electricity or hydrogen fuel for a variety of on-board applications such as to charge said vehicle (2) and to power the docking system and providing a safe stowage and protected storage for the said vehicle (2).

公开(公告)号：US09957064B2

公开(公告)日：2018-05-01

申请号：US14707424

申请日：2015-05-08

Applicant: AAI Corporation

Inventor： Stephen W. Miller ,  Zachary J. Smith ,  Peter J. Helman

IPC: B64F1/06 ,  B64F1/02 ,  B64C39/02

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/084 ,  B64C2201/182 ,  B64F1/02 ,  B64F1/025

Abstract: An unmanned aerial vehicle (UAV) platform includes a stationary base constructed and arranged to reside over a fixed location on a surface (e.g., a ground location, a ship's deck, a trailer or other vehicle, etc.). The UAV platform further includes a set of UAV interfaces constructed and arranged to interface directly with a UAV (e.g., a launcher, a net apparatus, etc.). The UAV platform further includes a turntable assembly which couples to the stationary base. The turntable assembly is constructed and arranged to couple to each UAV interface and control angular direction of that UAV interface over the fixed location. A method of operating a UAV platform includes deploying the UAV platform over a fixed location, preparing a UAV interface on a turntable assembly of the UAV platform, and rotating the turntable to control angular direction of the UAV interface over the fixed location.

公开(公告)号：US20170313442A1

公开(公告)日：2017-11-02

申请号：US15583226

申请日：2017-05-01

Applicant: CIRCOR AEROSPACE, INC.

Inventor： Russell S. SIRVIS ,  Christopher R. LOVASCO ,  Juan VASQUEZ ,  David W. GASS ,  Corey C. JORDAN ,  Liron DROR ,  John NELLIKUNNEL ,  Jeffrey HORNING ,  Christopher OLSEN

IPC: B64F1/06 ,  B64C39/02

CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/084

Abstract: An aerial vehicle launcher including a rail having a first end and a longitudinal axis and a piston movable in a passageway formed in the rail, the piston connected to a carriage by at least two elongate flexible members. The carriage having a support device for releasably engaging the aerial vehicle. Upon the carriage and the aerial vehicle approaching one end of the rail, the support device controllably disengaging the aerial vehicle, permitting the aerial vehicle to be launched. A device is connected to a pressurized gas source, the device controllably providing pressurized gas from the pressurized gas source to the passageway for drivingly moving the piston, the carriage, and aerial vehicle along the rail for launching the aerial vehicle. The device includes a reservoir for holding pressurized gas, the reservoir being a conduit, the pressurized gas in the reservoir providing the driving force for launching the aerial vehicle.