公开(公告)号：US20060151667A1

公开(公告)日：2006-07-13

申请号：US10758948

申请日：2004-01-16

Applicant: Brian Dennis ,  Andreas von Flotow

Inventor： Brian Dennis ,  Andreas von Flotow

IPC: B64F1/04

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

Abstract: Methods and apparatuses for launching 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. A launch carriage is positioned on a launch guide structure of the boom and carries the aircraft during takeoff. An energy reservoir is configured to provide energy to the launch carriage during takeoff of the aircraft, and can absorb energy from the launch carriage to decelerate the launch carriage after takeoff. The apparatus can further include a transmission that smoothly and rapidly accelerates and/or decelerates the launch carriage.

Abstract translation: 描述了发射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。 发射架位于起重臂的发射导向结构上，并在起飞时承载飞机。 能量储存器构造成在飞行器起飞期间向发射台提供能量，并且可以从起飞台吸收能量，以在起飞后减速发射台。 该装置还可以包括使发射台平滑且快速地加速和/或减速的变速器。

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：US20060011777A1

公开(公告)日：2006-01-19

申请号：US11105746

申请日：2005-04-14

Applicant: Paul Arlton ,  David Arlton

Inventor： Paul Arlton ,  David Arlton

IPC: B64C27/22

CPC classification number: B64C27/10 ,  B64C27/22 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/205

Abstract: A rotary wing vehicle includes a body structure having an elongated tubular backbone or core, and a counter-rotating coaxial rotor system having rotors with each rotor having a separate motor to drive the rotors about a common rotor axis of rotation. The rotor system is used to move the rotary wing vehicle in directional flight.

公开(公告)号：US06932296B2

公开(公告)日：2005-08-23

申请号：US10690284

申请日：2003-10-21

Applicant: Glenn Martin Tierney

Inventor： Glenn Martin Tierney

IPC: B64B1/30 ,  B64C39/00 ,  B64C39/02 ,  B64C27/22

CPC classification number: B64C39/005 ,  B64B1/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/104 ,  B64C2201/165

Abstract: A system and method for moving an aerial vehicle along a flight path includes rotatable hubs mounted on opposite sides of the vehicle. Elongated airfoils are mounted on the hubs parallel to a common hub axis for rotation about the hub axis on a blade path. Each airfoil defines a chord line and the system includes a gear assembly changeable, during hub rotation, between a first modality wherein airfoil chord lines remain tangential to the blade path (curtate flight), and a second modality wherein airfoil chord lines remain parallel to the flight path of the vehicle (prolate flight). Also, rotation of the hub can be stopped and the airfoils used for fixed wing flight.

Abstract translation: 沿着飞行路径移动飞行器的系统和方法包括安装在车辆的相对侧上的可旋转轮毂。 细长的翼型件平行于公共轮毂轴线安装在轮毂上，以便在叶片路径上围绕轮毂轴线旋转。 每个翼型件限定弦线，并且该系统包括齿轮组件，在轮毂旋转期间，其中翼型弦线保持与叶片路径相切的第一模态（curtate飞行）和第二模态，其中翼型弦线保持平行于 车辆的飞行路线（长跑）。 此外，轮毂的旋转可以停止，翼型件用于固定翼飞行。

公开(公告)号：US06931247B2

公开(公告)日：2005-08-16

申请号：US09789450

申请日：2001-02-20

Applicant: Earl C. Cox ,  Kyle D. Swanson

Inventor： Earl C. Cox ,  Kyle D. Swanson

IPC: B64C39/00 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/02 ,  B64C39/10 ,  B64D27/24 ,  B64D31/06 ,  G05D1/00 ,  H04B7/185 ,  H04Q7/20

CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

Abstract: This disclosure provides a solar rechargeable aircraft that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Traveling at relatively slow speeds, and having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's top surface, the aircraft uses only differential thrust of its eight propellers to turn. Each of five segments of the wing has one or more motors and photovoltaic arrays, and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface. The aircraft includes hinges and actuators capable of providing an adjustable dihedral for the wing. The actuators can be motors or control surfaces. Alternately, the actuators can be movable masses within the wing, which may be capable of deforming the wing to alter the aerodynamics of the wing, and thereby actuate the hinges. Because of wing dihedral, the aircraft includes motors both above and below the center of drag, and the aircraft uses differential thrust to control aircraft pitch. The aircraft has a wide variety of applications, which include serving as a long term high altitude platform that serves to link a ground station using radio wave signals and a satellite using optical signals.

Abstract translation: 本公开提供了一种太阳能可再充电飞机，其生产便宜，是可操纵的，并且几乎可以无限期地保持空中飞行。 首选飞机是一个装有跨距的飞翼，没有机身或方向舵。 以相对较慢的速度行驶，并且拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差动推力来转动。 翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，以避免加载它们。 五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。 飞机包括铰链和致动器，能够为机翼提供可调节的二面体。 执行器可以是电机或控制面。 或者，致动器可以是机翼内的可移动质量块，其可以使机翼变形以改变机翼的空气动力学，从而致动铰链。 由于机翼二面体，飞机包括在阻力中心上方和下方的电机，飞机使用差速推力来控制飞机俯仰。 该飞机具有广泛的应用，其中包括作为长期高空平台，用于使用无线电波信号连接地面站和使用光信号的卫星。

公开(公告)号：US20050093507A1

公开(公告)日：2005-05-05

申请号：US10976566

申请日：2004-10-29

Applicant: Steven Sliwa ,  Andreas von Flotow ,  Brian Dennis

Inventor： Steven Sliwa ,  Andreas von Flotow ,  Brian Dennis

IPC: B63H20060101 ,  B64C11/00 ,  B64C11/04 ,  B64C11/14 ,  B64C11/28 ,  B64C39/02 ,  B64D41/00 ,  F02K5/02 ,  H02J7/00

CPC classification number: B64C11/003 ,  A63H27/02 ,  B64C11/04 ,  B64C11/14 ,  B64C11/28 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/206 ,  B64D41/007 ,  F02K5/023 ,  F05D2260/85 ,  Y02T50/44 ,  Y02T50/672

Abstract: Methods and systems for starting propeller driven aircraft and other devices are disclosed. A system in accordance with one embodiment of the invention includes a removable fixture that is coupled to the propeller and has at least one portion exposed to a flowstream to rotate the propeller during engine start-up. The fixture is configured to separate from the propeller after the engine begins to turn over (e.g., after the engine starts and/or rotates above a threshold rate). Accordingly, the system can include a releasable link between the fixture and the propeller.

Abstract translation: 公开了用于启动螺旋桨驱动的飞机和其他装置的方法和系统。 根据本发明的一个实施例的系统包括可拆卸的固定装置，其连接到螺旋桨并且具有暴露于流动流中的至少一个部分以在发动机起动期间旋转螺旋桨。 发动机开始翻转（例如在发动机起动和/或旋转高于阈值速率之后），该固定装置构造成与螺旋桨分离。 因此，系统可以包括夹具和螺旋桨之间的可释放的连接。

公开(公告)号：US06742741B1

公开(公告)日：2004-06-01

申请号：US10373211

申请日：2003-02-24

Applicant: Louis D. Rivoli

Inventor： Louis D. Rivoli

IPC: B64C1500

CPC classification number: B64C39/024 ,  B64C3/40 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/165 ,  B64D27/06 ,  Y02T50/14

Abstract: An unmanned air vehicle includes a singular rear landing gear wheel on the aft end of the fuselage. Port and starboard wings with rear facing propellers are retractable to the aft of the fuselage. Upon retraction, the propellers may freewheel and a reversible motor-generator is provided to convert the freewheeling propeller energy into electric power. Photovoltaic cells also provide electric power to the unmanned air vehicle. Port and starboard nose fairings are control surfaces for the vehicle. The port and starboard nose fairings also include landing gear wheels. A method of flying an unmanned air vehicle includes retracting port and starboard wings to achieve a ballistic dive.

Abstract translation: 无人驾驶飞行器在机身后端包括一个单独的后起落架。 具有后面螺旋桨的端口和右舷翼可以伸缩到机身后部。 在收回时，推进器可以飞行，并且提供可逆的电动发电机以将续流螺旋桨能量转换成电力。 光伏电池还向无人驾驶飞行器提供电力。 港口和右舷整流罩是车辆的控制面。 港口和右舷整流罩也包括起落架轮。 飞行无人驾驶飞行器的方法包括缩回端口和右舷翼以实现弹道潜水。

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：US20020066825A1

公开(公告)日：2002-06-06

申请号：US09884852

申请日：2001-06-18

Inventor： Carlos T. Miralles ,  Bart D. Hibbs

IPC: B64C003/56

CPC classification number: B64G1/222 ,  B64C1/30 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/185 ,  B64C2201/203 ,  B64G1/105 ,  B64G1/62

Abstract: Disclosed is a spacecraft carrying a number of pods, each containing an aircraft that has been folded to fit in the pod. Each aircraft has a vertical stabilizer and outboard wing-portions that fold around fore-and-aft axes. Each aircraft also has a fuselage that folds around a lateral axis. The spacecraft releases one or more of the pods into an atmosphere. Each of the pods is configured with an ablative heat shield and parachutes to protect its aircraft when the pod descends through the atmosphere. The pod releases its aircraft at a desired altitude or location, and the aircraft unfolds while free-falling. The aircraft then acquires and follows a flight path, and activates scientific experiments and instruments that it carries. The aircraft relays results and readings from the experiments and instruments to the spacecraft, which in turn relays the results and readings to a mission command center.

Abstract translation: 公开了一种携带多个荚的飞船，每个荚都包含已折叠以适应荚的飞机。 每架飞机都有一个垂直的稳定器和外侧翼部分，它们围绕前后轴线折叠。 每架飞机还具有折叠横轴的机身。 航天器将一个或多个荚释放到气氛中。 每个荚配置有烧蚀式防护罩和降落伞，以在荚果通过大气层时保护其飞机。 吊舱将其飞机放置在所需的高度或位置，飞机在自由落体时展开。 飞机然后获得并遵循飞行路线，并激活它所携带的科学实验和仪器。 飞机将实验和仪器的结果和读数中继到航天器，然后将结果和读数中继到任务指挥中心。

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。