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    Multi-layer metal/shape memory polymer roll-up wing structures for fitment-constrained air vehicles
    433.
    发明授权
    Multi-layer metal/shape memory polymer roll-up wing structures for fitment-constrained air vehicles 有权
    多层金属/形状记忆聚合物卷起翼结构用于装备受限的空中飞行器

    公开(公告)号：US08528863B2

    公开(公告)日：2013-09-10

    申请号：US12463400

    申请日：2009-05-10

    Applicant: Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

    Inventor： Terry M. Sanderson ,  Brian J. Gowler ,  David R. Sar ,  Thomas P. McCreery

    IPC: B64C3/20 ,  B64C3/56

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  F42B10/14 ,  F42B10/146 ,  F42B10/16 ,  F42B10/20

    Abstract: A laminated wing structure includes at least one layer of metal material and at least one layer of a shape memory polymer (SMP) material. The SMP is heated to a temperature in its glass transition band Tg to roll the wing around the air vehicle into a stored position. The metal layer(s) must be thin enough to remain below its yield point when rolled up. In preparation for launch, the SMP material is thermally activated allowing the strain energy stored in the layer of metal material to return the wing to its deployed position at launch. Once deployed, the SMP cools to its glassy state. The SMP material may be reinforced with fiber to form a polymer matrix composite (PMC). SMP may be used to provide shear strain relief for multiple metal layers. By offloading the motive force required to return the wing to its original deployed position from the SMP to the metal, the polymer does not acquire a permanent set and the wing may be deployed accurately.

    Abstract translation: 层压翼结构包括至少一层金属材料和至少一层形状记忆聚合物（SMP）材料。 将SMP加热到其玻璃化转变带Tg的温度，以将机身周围的机翼卷绕成储存位置。 金属层必须足够薄以便在卷起时保持低于其屈服点。 在准备发射时，SMP材料被热激活，允许存储在金属材料层中的应变能在发射时将机翼返回到其展开位置。 一旦部署，SMP冷却到玻璃状态。 SMP材料可以用纤维增强以形成聚合物基质复合材料（PMC）。 SMP可用于为多个金属层提供剪切应变消除。 通过卸载将机翼从SMP返回到金属的原始展开位置所需的动力，聚合物不会获得永久变形，并且可以准确地展开机翼。

    Unmanned aerial vehicle base station
    434.
    发明授权
    Unmanned aerial vehicle base station 有权
    无人机基地台

    公开(公告)号：US08511606B1

    公开(公告)日：2013-08-20

    申请号：US12634146

    申请日：2009-12-09

    Applicant: Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

    Inventor： Kevin Reed Lutke ,  Aaron Jonathan Kutzmann

    IPC: B64D41/00

    CPC classification number: B64C39/024 ,  B64C39/028 ,  B64C2201/042 ,  B64C2201/066 ,  B64C2201/201

    Abstract: A method and apparatus comprising a platform, a battery system, a power generation system, a number of charging stations, and a controller. The platform is configured to house a number of unmanned aerial vehicles. The power generation system is connected to the battery system. The power generation system is configured to generate electrical energy from an environment in which the platform is located, and store the electrical energy in the battery system. The number of charging stations is connected to the battery system. The controller is connected to the battery system and is configured to receive sensor data from the number of unmanned aerial vehicles, generate information from the sensor data, and send the information to a remote location.

    Abstract translation: 一种包括平台，电池系统，发电系统，多个充电站以及控制器的方法和装置。 该平台被配置为容纳许多无人机。 发电系统连接到电池系统。 发电系统被配置为从平台所在的环境产生电能，并且将电能存储在电池系统中。 充电站的数量连接到电池系统。 控制器连接到电池系统，并被配置为从无人驾驶飞行器的数量接收传感器数据，从传感器数据生成信息，并将信息发送到远程位置。

    LOAD-CARRYING SYSTEM FOR TRANSPORT AEROPLANE
    436.
    发明申请
    LOAD-CARRYING SYSTEM FOR TRANSPORT AEROPLANE 有权
    运输机场装载系统

    公开(公告)号：US20120292444A1

    公开(公告)日：2012-11-22

    申请号：US13574457

    申请日：2011-01-19

    Applicant: Benoit Jaurand

    Inventor： Benoit Jaurand

    IPC: B64D1/10 ,  B64C1/22

    CPC classification number: B64D1/02 ,  B64C39/024 ,  B64C2201/082 ,  B64C2201/201 ,  B64C2201/206

    Abstract: The system comprises an outer container which is fixed, directly and fully, in the hold of the transport aeroplane (AC), and in which there is an inner container that can be moved longitudinally and brought from a first carrying position (AC) in which it is situated fully inside said outer container into a second off-loading position (P2), position (P2) in which it is longitudinally offset towards the rear of the aircraft (AC) so that a part of said inner container is then situated outside the transport aeroplane (AC).

    Abstract translation: 该系统包括直接和完全固定在运输飞机（AC）的保持件中的外部容器，并且其中存在能够纵向移动并从第一运送位置（AC）带动的内部容器 它完全位于所述外部容器内部进入第二卸载位置（P2），位置（P2）中，其朝向飞行器（AC）的后部纵向偏移，使得所述内部容器的一部分然后位于外部 运输飞机（AC）。

    UNMANNED AERIAL VEHICLE LAUNCH SYSTEM
    437.
    发明申请
    UNMANNED AERIAL VEHICLE LAUNCH SYSTEM 有权
    无人机驾驶系统

    公开(公告)号：US20120205488A1

    公开(公告)日：2012-08-16

    申请号：US13367494

    申请日：2012-02-07

    Applicant: David Powell ,  Earl Mark ,  John T. Houck ,  Keith Huber

    Inventor： David Powell ,  Earl Mark ,  John T. Houck ,  Keith Huber

    IPC: B64F1/04

    CPC classification number: B64C39/024 ,  B63G8/30 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/205

    Abstract: A system for launching an unmanned aerial vehicle (UAV) payload includes a launch tube, liquid rocket, and launch control assembly. The rocket is positioned in the launch tube and contains the UAV payload. A booster assembly may include a canister partially filled with liquid. A gas cylinder is filled with compressed gas. The liquid is pre-pressurized by the gas or mixed with the gas right before launch such that, upon launch, liquid and gaseous thrust stages launch the rocket to a threshold altitude. The UAV payload deploys after reaching the threshold altitude. Optional stability tubes may be connected to the launch tube, which may be buoyant for water-based operations. An optional tether may be connected to the liquid rocket for arresting its flight prior to reaching apogee. The UAV payload is not launched directly by the gas/liquid mix. A method of launching the UAV payload is also disclosed.

    Abstract translation: 用于发射无人机（UAV）有效载荷的系统包括发射管，液体火箭和发射控制组件。 火箭定位在发射管中，并包含无人机的有效载荷。 增压组件可以包括部分地填充有液体的罐。 气瓶内充满压缩气体。 液体被气体预加压或在发射前与气体混合，使得在发射时，液体和气体推进阶段将火箭发射到阈值高度。 无人机有效载荷在达到阈值高度后部署。 可选的稳定管可以连接到发射管，其可以浮动用于水基操作。 可选的系绳可以连接到液体火箭，以在达到远地点之前停止其飞行。 无人机有效载荷不直接由气/液混合发射。 还公开了一种启动无人机有效载荷的方法。

    SYSTEM FOR PROVIDING A RAPIDLY ELEVATED AEROSTAT PLATFORM
    438.
    发明申请
    SYSTEM FOR PROVIDING A RAPIDLY ELEVATED AEROSTAT PLATFORM 审中-公开
    提供快速高空作战平台的系统

    公开(公告)号：US20120181380A1

    公开(公告)日：2012-07-19

    申请号：US13009207

    申请日：2011-01-19

    Applicant: Peter K. Van Staagen ,  William Douglas McDaniel ,  James H. Boschma, JR.

    Inventor： Peter K. Van Staagen ,  William Douglas McDaniel ,  James H. Boschma, JR.

    IPC: B64B1/50 ,  B64B1/40

    CPC classification number: B64B1/50 ,  B64B1/58 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/123 ,  B64C2201/201 ,  B64C2201/208 ,  B64F1/14

    Abstract: A system and method for deploying a payload with an aerostat uses a mobile transporter for moving the system to a deployment site. Structurally, the system includes a base unit with a rotation head mounted thereon. An envelope container for holding a deflated aerostat is mounted on the rotation head and a rotation of the container on the rotation head positions the aerostat for optimal compliance with the existing wind condition. Also included in the system is an inflator that is mounted on the base unit to inflate the aerostat with a Helium gas. And, the system includes a tether control unit for maintaining a connection with the aerostat during its deployment, in-flight use, and recovery. Preferably, a deployment computer is used for a coordinated control of the rotation head, inflator and tether.

    Abstract translation: 用空气净化器部署有效载荷的系统和方法使用移动运输装置将系统移动到部署现场。 在结构上，该系统包括其上安装有旋转头的基座单元。 用于保持放气式放气器的信封容器安装在旋转头上，并且旋转头上的容器的旋转定位了空气调节器，以最佳地符合现有的风况。 还包括在系统中的是充气机，其安装在基座单元上以用氦气对空气净化器进行充气。 而且，该系统包括一个系绳控制单元，用于在其部署，飞行中使用和恢复期间维持与浮空器的连接。 优选地，部署计算机用于旋转头，充气机和系绳的协调控制。

    Launch and capture systems for vertical take-off and landing (VTOL) vehicles
    439.
    发明授权
    Launch and capture systems for vertical take-off and landing (VTOL) vehicles 有权
    用于垂直起飞和着陆（VTOL）车辆的启动和捕获系统

    公开(公告)号：US08162256B2

    公开(公告)日：2012-04-24

    申请号：US12051552

    申请日：2008-03-19

    Applicant: Emray R. Goossen ,  Yogendra Y. Sheoran

    Inventor： Emray R. Goossen ,  Yogendra Y. Sheoran

    IPC: B64F1/00

    CPC classification number: B64C39/024 ,  B64C2201/027 ,  B64C2201/088 ,  B64C2201/182 ,  B64C2201/201 ,  B64C2201/205 ,  B64C2201/208 ,  B64F1/04

    Abstract: A launch and capture system for capturing a vertical take-off and landing (VTOL) vehicle having a thruster and a duct configured to direct airflow generated by the thruster includes a capture plate and an extension. The capture plate is configured to alter the airflow and generate a force attracting the duct to the capture plate. The extension is coupled to the capture plate, and is configured to at least facilitate holding the VTOL vehicle against the capture plate.

    Abstract translation: 用于捕获具有推进器和构造成引导由推进器产生的气流的管道的垂直起飞和着陆（VTOL）车辆的发射和捕获系统包括捕获板和延伸部。 捕获板被配置为改变气流并产生吸引到捕获板的管道的力。 延伸部联接到捕获板，并且被构造成至少有利于将VTOL车辆保持抵靠捕获板。

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