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    Autonomous flying wing
    61.
    发明授权
    Autonomous flying wing 失效
    自主飞翼

    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。

    Unmanned airborne reconnaissance system
    62.
    发明申请
    Unmanned airborne reconnaissance system 有权
    无人机载侦察系统

    公开(公告)号：US20030155463A1

    公开(公告)日：2003-08-21

    申请号：US10194814

    申请日：2002-07-12

    Applicant: MISSION TECHNOLOGIES, INC.

    Inventor： Beverly Cox ,  Hampton Dews ,  Nicholas Nyroth

    IPC: F41G007/00

    CPC classification number: F41G3/02 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06 ,  Y02T50/82

    Abstract: An unmanned airborne reconnaissance system, the unmanned airborne reconnaissance system including a lightweight, portable, powered aircraft and a foldable launch rail, the aircraft, in a broken down condition and the launch rail in a broken down condition fitable inside a box, the box capable of being carried by one man. The launch system includes an elongated launch rail with the carriage assembly, and a propulsion means for accelerating the carriage assembly from one end of the launch rail to the other. The carriage assembly releasably engages the aircraft so as to propel the aircraft from one end of the launch rail to the other. The propulsion may be by a cartridge that explodes and releases a gas through a cylinder, or by elastic cords. The aircraft is guided through the air either by a programmed onboard computer which controls the control surfaces of the aircraft and/or by remote control. The aircraft typically contains a camera for recording and transmitting images received from the ground below.

    Abstract translation: 一种无人机载侦察系统，无人机载侦察系统，包括轻型便携式动力飞机和折叠式发射轨道，该飞机处于分解状态，发射导轨处于可折叠状态的箱体内，该箱体能够 由一个男人携带。 发射系统包括具有滑架组件的细长的发射轨道和用于将滑架组件从发射轨道的一端加速到另一端的推进装置。 滑架组件可释放地接合飞行器，以便将飞机从发射轨的一端推动到另一端。 推进可以是通过气缸爆炸和释放气体的弹药筒或弹性帘线。 飞机通过编程的机载计算机被引导通过空中，控制飞机的控制面和/或通过遥控。 飞机通常包含用于记录和发射从下面接地的图像的照相机。

    Moving apparatus
    64.
    发明申请
    Moving apparatus 有权
    移动装置

    公开(公告)号：US20020117583A1

    公开(公告)日：2002-08-29

    申请号：US10085181

    申请日：2002-02-27

    Inventor： Masaki Hamamoto ,  Yoshiji Ohta ,  Keita Hara

    IPC: B64C033/02

    CPC classification number: B64C33/02 ,  B64C39/028 ,  B64C2201/025 ,  B64C2201/044 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146

    Abstract: On a main body portion of a fluttering apparatus, a wing (left wing) is formed which has a front wing shaft, a rear wing shaft and a wing film provided spreading over the front and rear wing shafts. Further, on the main body portion, a rotary actuator for driving the front wing shaft and a rotary actuator for driving the rear wing shaft are mounted. The front (rear) wing shafts reciprocate in a plane orthogonally crossing an axis of rotation with the actuator serving as the fulcrum. Thus, a moving apparatus is obtained which has superior maneuverability and can move not hindered by any obstacle or geometry both indoors and outdoors.

    Abstract translation: 在飘动装置的主体部分上，形成有一个翼翼（左翼），其具有前翼轴，后翼轴和设置在前翼和后翼轴上的翼片。 此外，在主体部上安装有用于驱动前翼轴的旋转致动器和用于驱动后翼轴的旋转致动器。 前（后）翼轴在与作为支点的致动器正交的旋转轴线的平面中往复运动。 因此，获得具有优异的机动性并且可以在室内和室外不受任何障碍物或几何形状阻碍的移动装置。

    Passively stable hovering system
    67.
    发明授权
    Passively stable hovering system 失效
    被动稳定的悬停系统

    公开(公告)号：US5070955A

    公开(公告)日：1991-12-10

    申请号：US583477

    申请日：1990-09-17

    Applicant: Peter B. S. Lissaman ,  Herman M. Drees ,  Charles J. Sink ,  William D. Watson

    Inventor： Peter B. S. Lissaman ,  Herman M. Drees ,  Charles J. Sink ,  William D. Watson

    IPC: B64C27/20 ,  B64C39/02

    CPC classification number: B64C27/20 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/108 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/162

    Abstract: A flight system capable of passively stable hover and horizontal translatory flight, comprises an apparatus defining a vertical axis, and including multiple ducts with substantially vertical axes in hover mode, spaced the axis; fluid momentum generators in the ducts to effect flow of fluid downwardly in the ducts in hover; and fluid flow deflector structure in the path of the flowing duct fluid, and angled to deflect the fluid flow away from the axis, in such manner as to provide stability in hover of the apparatus, as well as stability when the entire device is tilted through approximately 90.degree. to execute horizontal translatory flight.

    Abstract translation: 能够被动地稳定悬停和水平平移的飞行系统包括限定垂直轴的装置，并且包括多个具有悬挂模式的基本垂直轴线的管道，该轴线间隔开; 管道中的流体动量发生器以在悬浮的管道中使流体向下流动; 以及在流动管道流体的路径中的流体流动偏转器结构，并且成角度以使流体流离开轴线，以便提供装置悬停的稳定性，以及当整个装置倾斜通过时的稳定性 大约90°执行水平平移飞行。

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