公开(公告)号：WO2008010226A1

公开(公告)日：2008-01-24

申请号：PCT/IL2007/000916

申请日：2007-07-19

Applicant: ISRAEL AEROSPACE INDUSTRIES LTD. ,  SHAI, Mordechai

Inventor： SHAI, Mordechai

IPC: F42B10/18 ,  F42B10/20 ,  F42B10/38 ,  F42B10/62 ,  B64C19/02 ,  B64C39/00 ,  B64C39/08

CPC classification number: F42B10/38 ,  B64C3/56 ,  B64C5/12 ,  B64C9/36 ,  B64C39/024 ,  B64C39/068 ,  B64C39/08 ,  B64C2201/102 ,  F42B10/18 ,  F42B10/20 ,  F42B10/62 ,  Y02T50/14

Abstract: A deployable wing arrangement or kit is provided for use with a longitudinally extending fuselage (20) having an upper portion and a lower portion. The kit includes a first pair of wings (100) pivotably mountable with respect to said upper portion and capable of being deployed from a first retracted position to a first deployed position, and a second pair of wings (102) pivotably mountable with respect to said lower portion and capable of being deployed from a second retracted position to a second deployed position. A strut arrangement, having at least one pair of struts (104), interconnect the first pair of wings (100) with the said second pair of wings (102). An air vehicle having such a kit, and a method for increasing the range of an air vehicle are also provided.

Abstract translation: 提供可展开的机翼装置或套件，用于具有上部和下部的纵向延伸的机身（20）。 该套件包括相对于所述上部可枢转地安装并且能够从第一缩回位置展开到第一展开位置的第一对翼（100），以及可相对于所述第一展开位置可枢转地安装的第二对翼 下部并且能够从第二缩回位置展开到第二展开位置。 具有至少一对支柱（104）的支柱装置将第一对翼（100）与所述第二对翼（102）互连。 还提供了一种具有这种套件的空中车辆，以及用于增加空中交通工具的范围的方法。

公开(公告)号：WO2007021361A2

公开(公告)日：2007-02-22

申请号：PCT/US2006/023376

申请日：2006-06-16

Applicant: INFORMATION SYSTEMS LABORATORIES, INC.

Inventor： TIERNEY, Glenn, Martin

IPC: B64C39/00

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，在第一形式之间，其中翼型弦线保持与叶片路径相切的第一模态（压头飞行），以及第二模态，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：WO2007021011A2

公开(公告)日：2007-02-22

申请号：PCT/JP2006/316271

申请日：2006-08-18

Applicant: 株式会社アトリム ,  渡辺隆元

Inventor： 渡辺隆元

CPC classification number: B64C31/032 ,  B64C3/56 ,  B64C39/024 ,  B64C39/04 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2211/00 ,  B64D27/08 ,  B64D47/08 ,  Y02T50/44

Abstract: 【課題】本発明の課題は、小スペースで搬送できるとともに性能の高い航空機を提供することにある。 【課題手段】本発明に係る航空機は、機体本体１００に、カイト翼３００が支柱２１０，２２０を介して取付けられるとともに、プロペラ５００が回転可能に軸支されてなる航空機であって、前記機体本体１００には、該プロペラ５００の外周をガードするためのプロペラガード部１２０が設けられており、該プロペラガード部１２０には、前記支柱２１０，２２０が固定できるように設けられていることを特徴とする。

Abstract translation: [问题]可在小空间内运输，性能高的飞机。 用于解决问题的手段通过支柱（210,220）和螺旋桨（500）将风筝翼（300）附接到飞行器主体（100）的飞行器由轴可旋转地支撑。 用于防护螺旋桨（500）的外周的螺旋桨防护部（120）设置在飞行器主体（100）处。 支柱（210,220）可以固定到螺旋桨保护部分（120）。

公开(公告)号：WO2006093641A2

公开(公告)日：2006-09-08

申请号：PCT/US2006/004478

申请日：2006-02-09

Applicant: HONEYWELL INTERNATIONAL INC. ,  GOOSSEN, Emray, R.

Inventor： GOOSSEN, Emray, R.

IPC: B64C39/02 ,  B64C27/20 ,  B64C29/00

CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C29/0016 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/162 ,  B64C2201/165 ,  B64C2201/201

Abstract: A dual ducted fan arrangement in which the duct components (203), engine (10), and avionics/payload pods (300, 302) are capable of being quickly disassembled to fit within common backpacking systems. Each duct is identical in fan (201 ), stator (102), and control vane design. Assembly connections between ducted fans (203) and electronic modules are also identical. An engine (10) or APU drives the dual ducted fans (203) through a splined shaft (601) to a differential (600) or through electric motors. Energy is transferred to the ducted fans by a single gear mounted to the stator (102) hub. Relative speeds of the individual ducted fans are controlled through separate frictional or generator load control braking mechanisms (603) on each of the splined shafts (601) between the differential (600) and ducted fans (203). In the electric motor case relative speed is through electronic speed control. The fans (201 ) are counter rotating for torque balancing. The electronic module locations are vertically variable for longitudinal center of gravity for variations in payloads.

Abstract translation: 其中管道部件（203），发动机（10）和航空电子设备/有效载荷舱（300,302）能够被快速拆卸以适合于共同的背包装系统的双管道风扇装置。 风扇（201），定子（102）和控制叶片设计中的每个风管都是相同的。 管道风扇（203）和电子模块之间的组装连接也是相同的。 发动机（10）或APU通过花键轴（601）驱动双管道风扇（203）至差速器（600）或通过电动机。 能量通过安装在定子（102）轮毂上的单个齿轮传递到涵道风扇。 通过位于差速器（600）和管道式风扇（203）之间的每个花键轴（601）上的单独的摩擦或发电机负载控制制动机构（603）来控制单个管道式风扇的相对速度。 在电动机的情况下，相对速度是通过电子调速。 风扇（201）反转以实现扭矩平衡。 对于有效载荷的变化，电子模块位置对于纵向重心是垂直可变的。

公开(公告)号：WO2005014390A3

公开(公告)日：2006-03-23

申请号：PCT/US2004001033

申请日：2004-01-17

Applicant: INSITU GROUP ,  DENNIS BRYAN D ,  JACKSON CLIFFORD ,  MCGEER BRIAN T ,  ROESELER CORY ,  VONFLOTOW ANDREAS H

Inventor： DENNIS BRYAN D ,  JACKSON CLIFFORD ,  MCGEER BRIAN T ,  ROESELER CORY ,  VONFLOTOW ANDREAS H

IPC: B64F1/00 ,  B63B27/10 ,  B63B27/16 ,  B63B27/26 ,  B64C25/68 ,  B64C39/02 ,  B64F1/02 ,  B64F1/04 ,  B64F1/06

CPC classification number: B64F1/02 ,  B63B27/26 ,  B64C25/68 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/04 ,  B64F1/06

Abstract: Methods and apparatuses for assembling, launching, recovering, disassembling, capturing, and storing unmanned aircraft (140) and other flight devices or projectiles are described. In one embodiment, the aircraft (140) can be assembled from a container (111) with little or no manual engagement by an operator. The container (111) can include a guide structure to control motion of the aircraft components. The aircraft (140) can be launched from an apparatus that includes an extendable boom (103). The boom (103) can be extended to deploy a recovery line (853) to capture the aircraft (140) in flight. The aircraft (140) can then be returned to its launch platform, disassembled, and stored in the container (111), again with little or no direct manual contact between the operator and the aircraft (140).

Abstract translation: 描述了组装，发射，恢复，拆卸，捕获和存储无人机（140）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（140）可以由操作者很少或没有手动接合的容器（111）组装。 容器（111）可以包括用于控制飞行器部件的运动的引导结构。 飞机（140）可以从包括可伸缩吊杆（103）的装置发射。 悬臂（103）可以延伸以部署回收线（853）以在飞行中捕获飞行器（140）。 然后，飞机（140）可以在操作员和飞行器（140）之间很少或没有直接的手动接触的情况下再次返回到其发射平台，拆卸并存储在容器（111）中。

公开(公告)号：WO01058756A2

公开(公告)日：2001-08-16

申请号：PCT/US2001/004378

申请日：2001-02-07

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

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 (10) 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 (12) top surface (42), the aircraft uses only differential thrust of its propellers (16) to turn. Each segment of the wing has one or more motors (14) and photovoltaic arrays (32), 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（10），其生产便宜，是可操纵的，并且可以几乎无限期地保持机载。 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，并且在大部分机翼（12）顶面（42）上安装有二百英尺翼展，该飞机仅使用其推进器（16）的差动推力来转动。 机翼的每个部分具有一个或多个电动机（14）和光伏阵列（32），并且独立于其它部分产生其自身的电梯，以避免装载它们。 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：US20190248464A1

公开(公告)日：2019-08-15

申请号：US16394966

申请日：2019-04-25

Applicant: SZ DJI TECHNOLOGY CO., LTD.

Inventor： Fangming YE ,  Zhao YANG ,  Di OU ,  Hongshan LI

IPC: B64C1/06 ,  B64C39/02

CPC classification number: B64C1/063 ,  B64C1/061 ,  B64C39/02 ,  B64C39/024 ,  B64C2201/024 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/126

Abstract: An unmanned aerial vehicle includes a fuselage and an arm coupled to the fuselage. The arm includes a first segment, a second segment, and a connecting assembly coupling and locking the first segment and the second segment to each other. The connecting assembly includes a first connecting member and a second connecting member. The first connecting member is rotatably coupled to one of the first segment or the second segment. The second connecting member is coupled to another one of the first segment or the second segment. The first connecting member is rotatable relative to the arm and engages with the second connecting member to lock the first segment and the second segment.

公开(公告)号：US20180320767A1

公开(公告)日：2018-11-08

申请号：US15587945

申请日：2017-05-05

Applicant: Sierra Nevada Corporation

Inventor： Jake Crine ,  Benjamin Paul Cunningham ,  Alec B. Devereaux ,  Sonny J. Lewis ,  Jonathan Peritt

IPC: F16H19/02 ,  F16H57/08

CPC classification number: F16H19/02 ,  B64C3/56 ,  B64C2201/102 ,  F16H25/2252 ,  F16H57/082

Abstract: An expanding pin system is described that can provide automated and/or power controlled locking and unlocking of an expanding pin assembly in a mechanical joint. For example, the expanding pin system can include an actuation assembly that includes a single actuator (e.g., motor) to control an expanding pin assembly for locking and unlocking a mechanical joint.

公开(公告)号：US20180273170A1

公开(公告)日：2018-09-27

申请号：US15927847

申请日：2018-03-21

Applicant: Regents of the University of Minnesota

Inventor： Ruben Raphael D'Sa ,  Nikolaos Papanikolopoulos ,  Devon Jenson ,  Travis Henderson ,  John Kilian

IPC: B64C29/02 ,  B64C39/02 ,  B64C3/56 ,  B64C3/32 ,  B64D27/24 ,  B64C11/30 ,  B64C13/18

CPC classification number: B64C29/02 ,  B64C3/32 ,  B64C3/56 ,  B64C11/30 ,  B64C13/18 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/06 ,  B64C2201/102 ,  B64C2201/162 ,  B64C2201/165 ,  B64D27/24 ,  B64D2211/00

Abstract: An unmanned aerial vehicle (UAV) including wing sections and hinge assemblies. Each wing section includes an airfoil and a propulsion unit. The wing sections are arranged side-by-side, pivotably connected by the hinge assemblies to define an airframe module. The airframe module is transitionable between a fixed-wing state and a rotor state. In the fixed-wing state, the airframe module has an elongated shape extending between opposing, first and second ends. In the rotor state, the first end is immediately proximate the second end. With this construction, the UAV provides two distinct modes of flight (fixed-wing for low power flight, and rotor for high maneuverability flight (including hover)). The wing sections can carry solar cells and a battery. A maximum power point tracker (MPPT) can be provided for optimizing the match between the solar array and the battery. The propulsion unit can include a variable pitch propeller.

公开(公告)号：US20180273166A1

公开(公告)日：2018-09-27

申请号：US15995419

申请日：2018-06-01

Applicant: Paul E. ARLTON ,  David J. ARLTON

Inventor： Paul E. ARLTON ,  David J. ARLTON

IPC: B64C27/605 ,  B64C27/10 ,  B64C27/14 ,  B64C39/02 ,  B64C7/00 ,  B64C27/82

CPC classification number: B64C27/605 ,  B64C7/00 ,  B64C27/10 ,  B64C27/14 ,  B64C39/024 ,  B64C2027/8236 ,  B64C2027/8281 ,  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.