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    AUTONOMOUS ENVIRONMENTAL CONTROL SYSTEM AND METHOD FOR POST-CAPTURE AND PRE-LAUNCH MANAGEMENT OF AN UNMANNED AIR VEHICLE
    541.
    发明申请
    AUTONOMOUS ENVIRONMENTAL CONTROL SYSTEM AND METHOD FOR POST-CAPTURE AND PRE-LAUNCH MANAGEMENT OF AN UNMANNED AIR VEHICLE 审中-公开
    自主式环境控制系统及无人驾驶飞机前后发射管理方法

    公开(公告)号：WO2007084172A2

    公开(公告)日：2007-07-26

    申请号：PCT/US2006/016734

    申请日：2006-05-01

    Applicant: LOCKHEED MARTIN CORPORATION (MARYLAND CORPORATION)

    Inventor： STEELE, Daniel, W.

    IPC: B64F1/12

    CPC classification number: B64F1/04 ,  B64C2201/08 ,  B64C2201/182 ,  B64C2201/201 ,  B64F1/02

    Abstract: An embodiment of the invention is directed to a system for controlling and managing a small unmanned air vehicle (UAV) between capture and launch of the UAV. The system includes an enclosure that provides environmental protection and isolation for multiple small UAVs in assembled and/or partially disassembled states. Control and management of the UAVs includes reorientation of a captured UAV from a landing platform and secure hand-off to the enclosure, decontamination, de-fueling, ingress to the enclosure, downloading of mission payload, UAV disassembly, stowage, retrieval and reassembly of the UAV, mission uploading, egress of the UAV from the enclosure, fueling, engine testing and launch readiness. An exemplary system includes two or more robots controlled by a multiple robot controller for autonomously carrying out the functions described above. A modular, compact, portable and autonomous system of UAV control and management is described.

    Abstract translation: 本发明的实施例针对用于在无人飞行器的捕获和发射之间控制和管理小型无人飞行器（UAV）的系统。 该系统包括一个外壳，为组装和/或部分拆卸状态下的多个小型无人机提供环境保护和隔离。 无人机的控制和管理包括从登陆平台重新调整捕获的无人机的方向，确保切换到外壳，净化，去加油，进入外壳，下载任务有效载荷，无人机的拆卸，积载，检索和重新组装 无人机，任务上传，无人机从机箱出口，加油，发动机测试和发射准备。 示例性系统包括由多个机器人控制器控制的用于自主执行上述功能的两个或更多个机器人。 描述了一个模块化，紧凑，便携和自主的无人机控制和管理系统。

    STOWABLE DESIGN FOR UNMANNED AERIAL VEHICLE
    542.
    发明申请
    STOWABLE DESIGN FOR UNMANNED AERIAL VEHICLE 审中-公开
    可持续的空中客车设计

    公开(公告)号：WO2006073750A3

    公开(公告)日：2006-12-28

    申请号：PCT/US2005045715

    申请日：2005-12-16

    Applicant: ALMAN JAMES

    Inventor： ALMAN JAMES

    IPC: B64C3/38

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/105 ,  B64C2201/107 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/201 ,  B64C2201/203

    Abstract: An unmanned aerial vehicle (UAV) having a design for optimum stowability and low cost. The UAV having a collapsible wing section which can be easily removed from the fuselage, allowing for quick assembly and disassembly and ease of portability. The unmanned aerial vehicle includes a primary wing assembly, a fuselage, a means for propelling the unmanned aerial vehicle , and means for remotely controlling the unmanned aerial vehicle. The primary wing assembly includes a wing having a center spar and two outwardly diverging side spars. The wing also has a pliable flexible material supported by the center spar and the at least two outwardly diverging side spars. The pylon is connected to the wing and supports the wing. The fuselage is connected to the pylon such that the pylon extends away from the fuselage and spaces the wing a distance from the fuselage. The fuselage includes a tail having a rudder located along a trailing edge and elevators located along the trailing edge.

    Abstract translation: 无人飞行器（UAV）具有最佳的可收藏性和低成本的设计。 无人机具有可折叠的机翼部分，可以方便地从机身中移除，从而实现快速组装和拆卸，便于携带。 无人飞行器包括主翼组件，机身，用于推动无人驾驶飞行器的装置，以及用于远程控制无人驾驶飞行器的装置。 主翼组件包括具有中心翼梁和两个向外发散的侧翼的翼。 机翼还具有由中心翼梁和至少两个向外发散的侧翼支撑的柔韧的柔性材料。 塔架连接到机翼并支撑机翼。 机身连接到挂架，使得吊架远离机身延伸，并将机翼与机身隔开一段距离。 机身包括尾部，尾部沿着后缘设有方向舵，沿着后缘设有电梯。

    DOUBLE DUCTER HOVERING AIR-VEHICLE
    543.
    发明申请
    DOUBLE DUCTER HOVERING AIR-VEHICLE 审中-公开
    双排气罩空气动力车

    公开(公告)号：WO2006093641A3

    公开(公告)日：2006-11-09

    申请号：PCT/US2006004478

    申请日：2006-02-09

    Applicant: HONEYWELL INT INC ,  GOOSSEN EMRAY R

    Inventor： GOOSSEN EMRAY R

    IPC: B64C39/02

    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: 一种双管道风扇装置，其中管道部件（203），发动机（10）和航空电子设备/有效载荷容器（300,302）能够快速拆卸以适合普通的背包系统。 风扇（201），定子（102）和控制叶片设计中的每个管道相同。 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）到差速器（600）或通过电动机驱动。 通过安装到定子（102）毂的单个齿轮将能量传递到管道风扇。 单个管道风扇的相对速度通过在差速器（600）和管道风扇（203）之间的每个花键轴（601）上的分开的摩擦或发电机负载控制制动机构（603）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（201）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。

    AIR-LAUNCHABLE AIRCRAFT AND METHOD OF USE
    544.
    发明申请
    AIR-LAUNCHABLE AIRCRAFT AND METHOD OF USE 审中-公开
    可升级的飞机及其使用方法

    公开(公告)号：WO2006036183A1

    公开(公告)日：2006-04-06

    申请号：PCT/US2005/004474

    申请日：2005-02-14

    Applicant: RAYTHEON COMPANY ,  CORDER, David, A. ,  KOESSLER, Jeffrey, H. ,  WEBB, George, R.

    Inventor： CORDER, David, A. ,  KOESSLER, Jeffrey, H. ,  WEBB, George, R.

    IPC: B64C39/02

    CPC classification number: B64C3/56 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/123 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/145 ,  B64C2201/165 ,  B64C2201/201

    Abstract: An air-launched aircraft (10) includes deployable wings (16, 18), elevons (20, 22), and vertical fins (26, 28) that deploy from a fuselage (12) during flight. The aircraft may include a control system for operating the elevons, a communication system, and batteries for powering the systems. In addition, the aircraft may include a payload module (14) that mates with an interface in the fuselage. The payload module may include any of a variety of payloads, including cameras, sensors, and/or radar emitters. The aircraft may be powered or unpowered, and may be very small, for example, less than on the order of 10 kg (22 pounds). The deployable surfaces of the aircraft may be configured to deploy in a pre-determined order, allowing the aircraft automatically to enter controlled flight after being launched in a tumbling mode.

    Abstract translation: 空中飞行器（10）包括在飞行期间从机身（12）展开的可展开的机翼（16,18），电梯（20,22）和垂直翼片（26,28）。 飞机可以包括用于操作电梯的控制系统，通信系统和用于为系统供电的电池。 此外，飞行器可以包括与机身中的接口相配合的有效载荷模块（14）。 有效载荷模块可以包括各种有效载荷中的任何一种，包括相机，传感器和/或雷达发射器。 该飞机可能是动力或无动力的，并且可能非常小，例如小于10kg（22磅）的量级。 飞机的可部署表面可以被配置成以预定的顺序部署，允许飞机在以翻滚模式发射之后自动进入受控飞行。

    LIGHTWEIGHT AIR VEHICLE AND PNEUMATIC LAUNCHER
    546.
    发明申请
    LIGHTWEIGHT AIR VEHICLE AND PNEUMATIC LAUNCHER 审中-公开
    轻型空气动力和气动推进器

    公开(公告)号：WO2005023642A2

    公开(公告)日：2005-03-17

    申请号：PCT/US2004/004720

    申请日：2004-02-19

    Applicant: AAI CORPORATION ,  MILLER, Stephen, W. ,  VELAZQUEZ, Matthew, T.

    Inventor： MILLER, Stephen, W. ,  VELAZQUEZ, Matthew, T.

    IPC: B64B

    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。

    MICRO-ROTOCRAFT SURVEILLANCE SYSTEM
    547.
    发明申请
    MICRO-ROTOCRAFT SURVEILLANCE SYSTEM 审中-公开
    MICRO-ROTOCRAFT监控系统

    公开(公告)号：WO03059735A2

    公开(公告)日：2003-07-24

    申请号：PCT/US0241280

    申请日：2002-12-19

    Applicant: ARLTON PAUL E ,  ARLTON DAVID J

    Inventor： ARLTON PAUL E ,  ARLTON DAVID J

    IPC: B64C27/10 ,  B64C39/02 ,  B64C

    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 is provided for remote tactical and operational missions. The unit includes an elongated body having an upper and a lowe end. The body defines a vertical axis. The unit further includes a navigation module including means for determining a global position of the elongated body during flight of the unit. Rotor means of the unit is coupled to the upper end of the elongated body for generating a thrust force that acts in a direction parallel to the verical axis to lift the elongated body into the air. The rotor means is located between the elongated body and the navigation module.

    Abstract translation: 提供了一个飞行的微型旋翼航空器，用于远程战术和作战任务。 该单元包括具有上端和下端的细长体。 身体定义垂直轴。 该单元还包括导航模块，其包括用于在单元飞行期间确定细长主体的全局位置的装置。 该单元的转子装置联接到细长主体的上端，用于产生一个推力，该推力作用在平行于虚拟轴线的方向上，以将细长主体提升到空气中。 转子装置位于细长主体和导航模块之间。

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