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295 records (took 0.049 seconds)

    Double ducted hovering air-vehicle
    273.
    发明授权
    Double ducted hovering air-vehicle 失效
    双管道悬停飞行器

    公开(公告)号：US07658346B2

    公开(公告)日：2010-02-09

    申请号：US11338558

    申请日：2006-01-24

    Applicant: Emray R. Goossen

    Inventor： Emray R. 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。 风扇，定子和控制叶片设计中的每个风道都相同。 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。

    Telescoping wing and airfoil control mechanism
    275.
    发明申请
    Telescoping wing and airfoil control mechanism 失效
    伸缩翼和翼型控制机构

    公开(公告)号：US20090166477A1

    公开(公告)日：2009-07-02

    申请号：US12005600

    申请日：2007-12-28

    Applicant: Samuel Hall Bousfield

    Inventor： Samuel Hall Bousfield

    IPC: B64C3/54 ,  B64C3/52 ,  B64C3/18

    CPC classification number: B64C3/56 ,  B64C3/18 ,  B64C3/52 ,  B64C2201/102

    Abstract: This invention relates generally to a collapsible, nesting wing structure with or without wing warp flight control. The invention also incorporates means to maintain wing extension during flight, methods of wing construction for nesting collapsible wings, and control surfaces for collapsible wings.

    Abstract translation: 本发明一般涉及具有或不具有翼型经线飞行控制的可折叠的嵌套翼结构。 本发明还包括在飞行期间维持机翼延伸的方法，用于嵌套可折叠翼的翼结构的方法以及用于可折叠翼的控制表面。

    Ducted Fan Air Vehicle with Deployable Wings
    276.
    发明申请
    Ducted Fan Air Vehicle with Deployable Wings 失效
    具有可部署翅膀的风扇飞机

    公开(公告)号：US20080272226A1

    公开(公告)日：2008-11-06

    申请号：US11947585

    申请日：2007-11-29

    Applicant: John C. Colclough

    Inventor： John C. Colclough

    IPC: B64C37/00 ,  B64C3/56

    CPC classification number: B64C3/54 ,  B64C27/20 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/102 ,  B64C2201/162 ,  Y02T50/14

    Abstract: A ducted fan air vehicle and method of operation is disclosed for obtaining aerodynamic lift and efficiency in forward flight operation without significantly impacting hover stability. One or more retractable wings are included on the ducted fan air vehicle and are deployed during forward flight to provide aerodynamic lift. The wing or wings are retracted when the vehicle hovers to reduce the impact the wings have on stability in a wind. Each wing may conform to the curvature or profile of the vehicle when retracted, and may be constructed in one or more wing sections. The wing or wings may be deployed and retracted automatically or at the command of an operator. Each wing and related components may be integrated into the vehicle or may be detachable.

    Abstract translation: 公开了一种管道风扇空气动力车辆和操作方法，用于在前进飞行操作中获得空气动力学提升和效率，而不会显着影响悬停稳定性。 一个或多个伸缩翼包括在管道式风扇飞行器上，并且在向前飞行期间部署以提供空气动力学提升。 当车辆悬停时，翼或翼缩回，以减少翼对风中的稳定性的影响。 每个翼可以在缩回时符合车辆的曲率或轮廓，并且可以构造在一个或多个翼部中。 机翼或机翼可以自动部署和撤回，或者在操作员的指令下进行。 每个翼和相关部件可以集成到车辆中或者可以是可拆卸的。

    Lightweight air vehicle and pneumatic launcher
    277.
    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
    278.
    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)
    280.
    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。

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