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    Lightweight air vehicle and pneumatic launcher
    65.
    发明授权
    Lightweight air vehicle and pneumatic launcher 有权
    轻型机动车和气动发射器

    公开(公告)号：US07410124B2

    公开(公告)日：2008-08-12

    申请号：US10509659

    申请日：2004-02-19

    Applicant: Stephen W. Miller ,  Matthew T. Velazquez

    Inventor： Stephen W. Miller ,  Matthew T. Velazquez

    IPC: F41B11/00

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06

    Abstract: A portable unmanned air vehicle and launcher system including a foldable unmanned air vehicle with a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

    Abstract translation: 一种便携式无人驾驶飞行器和发射系统，包括带压力管的可折叠无人驾驶飞行器; 用于发射气体的发射气藏; 操作地连接到发射气体储存器并具有位于空中载体的压力管中的自由端的发射管; 位于发射管内的自由活塞; 和自由活塞止挡件，以防止自由活塞离开发射管。 发射气体储存器中的发射气体的第一部分被释放到发射管中，并且将自由活塞从初始位置推动到自由活塞由自由活塞停止的终止位置。

    LIGHTWEIGHT AIR VEHICLE AND PNEUMATIC LAUNCHER
    66.
    发明申请
    LIGHTWEIGHT AIR VEHICLE AND PNEUMATIC LAUNCHER 有权
    轻型空气动力和气动推进器

    公开(公告)号：US20080093501A1

    公开(公告)日：2008-04-24

    申请号：US11877201

    申请日：2007-10-23

    Applicant: Stephen Miller ,  Matthew Velazquez

    Inventor： Stephen Miller ,  Matthew Velazquez

    IPC: B64C3/56 ,  B64F1/04

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203 ,  B64F1/06

    Abstract: A portable unmanned air vehicle and launcher system is provided that includes a foldable unmanned air vehicle having a pressure tube; a launch gas reservoir for holding launch gas; a launch tube operatively connected to the launch gas reservoir and having a free end that is positioned in the pressure tube of the air vehicle; a free piston positioned within the launch tube; and a free piston stop to prevent the free piston from leaving the launch tube. A first portion of the launch gas in the launch gas reservoir is released into the launch tube and forces the free piston from an initial position to an end position at which the free piston is stopped by the free piston stop.

    Abstract translation: 提供了一种便携式无人驾驶飞行器和发射系统，其包括具有压力管的可折叠无人驾驶飞行器; 用于发射气体的发射气藏; 操作地连接到发射气体储存器并具有位于空中载体的压力管中的自由端的发射管; 位于发射管内的自由活塞; 和自由活塞止挡件，以防止自由活塞离开发射管。 发射气体储存器中的发射气体的第一部分被释放到发射管中，并且将自由活塞从初始位置推动到自由活塞由自由活塞停止的终止位置。

    Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV)
    67.
    发明授权
    Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV) 失效
    自主的，可回填计算机控制的无人机（UAV）

    公开(公告)号：US07237750B2

    公开(公告)日：2007-07-03

    申请号：US10976153

    申请日：2004-10-29

    Applicant: Tien Seng Chiu ,  Jay Willmott

    Inventor： Tien Seng Chiu ,  Jay Willmott

    IPC: B64C1/00

    CPC classification number: B64C1/00 ,  A45C5/00 ,  A45C13/02 ,  B64C1/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/201 ,  B64C2201/203

    Abstract: A modular unmanned aerial vehicle (UAV) having a fuselage, a nose cone, a left wing piece, a right wing piece, and a tail section. The tail section and nose cone each join to the fuselage through mating bulkhead structures that provide quick connection capability while being readily separated so as to enable the UAV to break apart at these connection points and thereby absorb or dissipate impact upon landing. The UAV is capable of rapid assembly in the field for two-man launch and data retrieval, as well as quick disassembly into these five component parts for transport and storage in a highly compact transport case that can be carried as a backpack.

    Abstract translation: 具有机身，鼻锥，左翼片，右翼片和尾部的模块化无人驾驶飞行器（UAV）。 尾部和鼻锥每个通过配合的隔板结构连接到机身，提供快速的连接能力，同时易于分离，以便使UAV在这些连接点处分裂，从而吸收或消散着陆时的冲击。 无人机能够在现场快速组装两人发射和数据检索，以及快速拆卸到这五个部件中，用于运输和存储，可以作为背包携带的高度紧凑的运输箱。

    Micro-rotorcraft surveillance system
    68.
    发明申请
    Micro-rotorcraft surveillance system 审中-公开
    微旋翼航空器监控系统

    公开(公告)号：US20050051667A1

    公开(公告)日：2005-03-10

    申请号：US10499530

    申请日：2002-12-19

    Applicant: Paul Arlton ,  David Arlton

    Inventor： Paul Arlton ,  David Arlton

    IPC: B64C27/10 ,  B64C39/02 ,  B64C27/00

    CPC classification number: G08B13/19621 ,  B64C27/10 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/208 ,  G08B13/19619 ,  G08B13/1963

    Abstract: A flying micro-rotorcraft unit (18, 24, 310, 330, 370) is provided for remote tactical and operational missions. The unit (18, 24, 310, 330, 370) includes an elongated body (52) having an upper and a lower end. The body (52) defines a vertical axis (60). The unit (18, 24, 310, 330, 370) further includes a navigation module (54) including means for determining a global position of the elongated body (52) during flight of the unit (18, 24, 310, 330, 370). Rotor means of the unit (18, 24, 310, 330, 370) is coupled to the upper end of the elongated body (52) for generating a thrust force that acts in a direction parallel to the vertical axis (60) to lift the elongated body (52) into the air. The rotor means is located between the elongated body (52) and the navigation module (54).

    Abstract translation: 飞行的微型旋翼航空器（18,24,310,330,370）用于远程战术和作战任务。 单元（18,24,310,330,370）包括具有上端和下端的细长主体（52）。 主体（52）限定垂直轴线（60）。 该单元（18,24,310,330,370）还包括导航模块（54），该导航模块（54）包括用于在单元（18,24,310,330,370）的飞行期间确定细长主体（52）的全局位置的装置 ）。 单元（18,24,310,330,370）的转子装置联接到细长主体（52）的上端，用于产生沿平行于垂直轴线（60）的方向作用的推力，以提升 细长的主体（52）进入空气。 转子装置位于细长主体（52）和导航模块（54）之间。

    Unmanned airborne reconnaissance system
    69.
    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。

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