公开(公告)号：US20060284005A1

公开(公告)日：2006-12-21

申请号：US11510013

申请日：2006-08-25

Applicant: Peter Ifju ,  Kyu-Ho Lee ,  Roberto Albertani ,  Shawn Mitryk ,  Frank Boria ,  Mujahid Abdulrahim

Inventor： Peter Ifju ,  Kyu-Ho Lee ,  Roberto Albertani ,  Shawn Mitryk ,  Frank Boria ,  Mujahid Abdulrahim

IPC: B64C3/56 ,  B64C3/00

CPC classification number: B64C39/028 ,  A63H27/007 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201

Abstract: A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Abstract translation: 具有能够使微型飞行器飞行的可弯曲翼的微型飞行器。 可弯曲翼可以向下弯曲，使得翼展可以减小以存储微型飞行器。 可弯曲翼可以由一层或多层材料形成，并且翼可以具有弯曲，使得翼的凹面朝向下方。 机翼可以基本上抵抗向上弯曲并且可以将提升力传递到微型飞行器的中心体。 此外，机翼可能通过对机翼的尖端施加力而严重地向下弯曲。 微型飞行器能够存储在小圆柱形管中，并且可以通过从管中简单地释放微型飞行器而从管展开。

公开(公告)号：US07140575B2

公开(公告)日：2006-11-28

申请号：US10758955

申请日：2004-01-16

Applicant: Brian T. McGeer ,  Cory Roeseler ,  Andreas H. von Flotow

Inventor： Brian T. McGeer ,  Cory Roeseler ,  Andreas H. von Flotow

IPC: B64F1/04

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

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can belaunched from an apparatus that includes a launch carriage that moves along a launch axis. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the fuselage of the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff.

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，飞行器可以从包括沿着发射轴移动的发射台的装置掀起。 由发射托架携带的夹具可以具有至少一个与飞行器接触的抓握部分，同时发射托架沿着发射轴加速。 随着发射台减速，至少一个把手部分可以与飞机的机身脱离接触，释放飞机起飞。

公开(公告)号：US07121507B2

公开(公告)日：2006-10-17

申请号：US10758943

申请日：2004-01-16

Applicant: Brian D. Dennis ,  Clifford Jackson ,  Brian T. McGeer

Inventor： Brian D. Dennis ,  Clifford Jackson ,  Brian T. McGeer

IPC: B64F1/00

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

Abstract: Methods and apparatuses for capturing, recovering, disassembling, and storing unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the boom can be extended to deploy a recovery line to capture the aircraft in flight, a process that can be aided by a line capture device having retainers in accordance with further aspects of the invention. The aircraft can then be returned to its launch platform, disassembled, and stored, again with little or no direct manual contact between the operator and the aircraft, for example, by capturing a first wing of the aircraft and securing a second wing before releasing the first.

Abstract translation: 描述了用于捕获，恢复，拆卸和存储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，吊杆可以被延伸以部署回收线以在飞行中捕获飞行器，这是根据本发明的其它方面能够由具有保持器的线捕获装置辅助的过程。 然后，飞机然后可以返回到其发射平台，拆卸和存储，再次与操作者和飞机之间的很少或没有直接的手动接触，例如通过捕获飞行器的第一翼并且在释放之前固定第二翼 第一。

公开(公告)号：US20060192047A1

公开(公告)日：2006-08-31

申请号：US11338558

申请日：2006-01-24

Applicant: Emray Goossen

Inventor： Emray Goossen

IPC: B64C27/08

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

Abstract translation: 双管风扇装置，其中管道部件，发动机和航空电子设备/有效载荷容器能够快速拆卸以适合普通的背包系统。每个管道在风扇，定子和控制叶片设计中是相同的。 管道风扇和电子模块之间的组装连接也相同。 发动机或APU通过花键轴驱动双管道风扇到差速器或通过电动机驱动。 能量通过安装在定子毂上的单个齿轮传递到管道风扇。 单个管道风扇的相对速度通过在差速风扇和管道风扇之间的每个花键轴上的单独的摩擦或发电机负载控制制动机构来控制。 在电动机壳体中，相对速度是通过电子速度控制。 风扇反向旋转以进行扭矩平衡。 电子模块位置对于纵向重心是垂直可变的，用于有效载荷的变化。

公开(公告)号：US07097133B2

公开(公告)日：2006-08-29

申请号：US10922047

申请日：2004-08-19

Applicant: Daryl B. Elam

Inventor： Daryl B. Elam

IPC: F42B15/01

CPC classification number: F42B10/146 ,  B64C39/024 ,  B64C2201/102

Abstract: An articulated wing (20) is readily deployable from a stowed configuration that occupies minimal volume to an extended configuration for flight. The wing (20) includes a frame (24) having a pair of beams (30) spaced by one or more ribs (36), and a flexible covering material (26) over the frame (24) that defines the surface of the wing (20). Each beam (30) typically has multiple segments (40), and each segment (40) is pivotally connected to an adjacent segment (40) at a joint (42). A flexible actuation line (52) extends past each joint (42) and is attached to a portion of the beam beyond the joint. The beam (30) also includes portions that act as stops (46). The stops (46) limit the range of angular motion through which the respective segments (40) can rotate relative to one another. Consequently, when tension is applied to the line (52), the segments (40) rotate until respective stops (46) prevent further rotation. Tension in each line (52) keeps the wing (20) in its extended configuration.

Abstract translation: 铰接翼（20）可以从占有最小体积的收起构型展开到用于飞行的延伸构型。 机翼（20）包括具有由一个或多个肋（36）间隔开的一对梁（30）的框架（24）以及限定翼的表面的框架（24）上方的柔性覆盖材料（26） （20）。 每个梁（30）通常具有多个段（40），并且每个段（40）在接头（42）处枢转地连接到相邻段（40）。 柔性致动线（52）延伸穿过每个接头（42）并且被附接到梁的超过接头的一部分。 梁（30）还包括用作挡块（46）的部分。 止动件（46）限制角运动的范围，相应的段（40）可以相对于彼此旋转。 因此，当向线（52）施加张力时，片段（40）旋转直到相应的挡块（46）阻止进一步旋转。 每条线（52）中的张力保持机翼（20）处于其延伸构型。

公开(公告)号：US20060175463A1

公开(公告)日：2006-08-10

申请号：US11269395

申请日：2005-11-08

Applicant: Brian McGeer

Inventor： Brian 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：US20050178894A1

公开(公告)日：2005-08-18

申请号：US10758955

申请日：2004-01-16

Applicant: Brian McGeer ,  Cory Roeseler ,  Andreas von Flotow

Inventor： Brian McGeer ,  Cory Roeseler ,  Andreas von Flotow

IPC: B64C39/02 ,  B64F1/04 ,  B64F1/06

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

Abstract: Methods and apparatuses for launching unmanned aircraft and other flight devices or projectiles are described. In one embodiment, the aircraft can belaunched from an apparatus that includes a launch carriage that moves along a launch axis. A gripper carried by the launch carriage can have at least one grip portion in contact with the aircraft while the launch carriage accelerates along the launch axis. The at least one grip portion can move out of contact with the fuselage of the aircraft as the launch carriage decelerates, releasing the aircraft for takeoff.

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，飞行器可以从包括沿着发射轴移动的发射台的装置掀起。 由发射托架携带的夹具可以具有至少一个与飞行器接触的抓握部分，同时发射托架沿着发射轴加速。 随着发射台减速，至少一个把手部分可以与飞机的机身脱离接触，释放飞机起飞。

公开(公告)号：US20050118952A1

公开(公告)日：2005-06-02

申请号：US09789450

申请日：2001-02-20

Applicant: Earl Cox ,  Kyle Swanson

Inventor： Earl Cox ,  Kyle 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：US20040245393A1

公开(公告)日：2004-12-09

申请号：US10731777

申请日：2003-12-09

Applicant: University of Florida

Inventor： Peter Ifju ,  Kyu-Ho Lee ,  Roberto Albertani ,  Shawn J. Mitryk ,  Frank J. Boria ,  Mujahid Abdulrahim

IPC: B64C001/00

CPC classification number: B64C39/028 ,  A63H27/007 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/201

Abstract: A micro air vehicle having a bendable wing enabling the micro air vehicle to fly. The bendable wing may be bent downwards so that the wingspan may be reduced for storing the micro air vehicle. The bendable wing may be formed from one or more layers of material, and the wing may have a camber such that a concave surface of the wing faces downward. The wing may substantially resist flexing upwards and may transfer uplift forces to a central body of the micro air vehicle. In addition, the wing may be bent severely downwards by applying a force to tips of the wing. The micro air vehicle is capable of being stored in a small cylindrical tube and may be deployed from the tube by simply releasing the micro air vehicle from the tube.

Abstract translation: 具有能够使微型飞行器飞行的可弯曲翼的微型飞行器。 可弯曲翼可以向下弯曲，使得翼展可以减小以存储微型飞行器。 可弯曲翼可以由一层或多层材料形成，并且翼可以具有弯曲，使得翼的凹面朝向下方。 机翼可以基本上抵抗向上弯曲并且可以将提升力传递到微型飞行器的中心体。 此外，机翼可能通过对机翼的尖端施加力而严重地向下弯曲。 微型飞行器能够存储在小圆柱形管中，并且可以通过从管中简单地释放微型飞行器而从管展开。

公开(公告)号：US06626397B2

公开(公告)日：2003-09-30

申请号：US09895332

申请日：2001-07-02

Applicant: Aharon Yifrach

Inventor： Aharon Yifrach

IPC: B65C300

CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/167 ,  B64C2201/201 ,  B64D5/00 ,  Y10S244/90 ,  Y10S244/901

Abstract: An unmanned flying vehicle comprises an autonomous flying wing having at least two wing portions arranged substantially symmetrically about a center portion. Each wing portion is pivotally attached to each adjoining portion such that the wing portions are foldable for storage and openable for deployment. A preferred form is the so-called seagull wing having four wing portions. The vehicles may be programmable from a mother aircraft whilst being borne to a deployment zone using a data link which may be wireless.

Abstract translation: 无人驾驶飞行器包括具有至少两个围绕中心部分大致对称​​布置的翼部的自主飞行翼。 每个翼部可枢转地附接到每个相邻部分，使得翼部可折叠以用于存储并且可展开。 优选的形式是所谓的具有四个翼部的海鸥翼。 车辆可以从母机飞行器编程，同时使用可能是无线的数据链路承载到部署区域。