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    MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL
    31.
    发明申请
    MODULAR MINIATURE UNMANNED AIRCRAFT WITH VECTORED-THRUST CONTROL 有权
    具有矢量控制的模块化MINIATURE UNIMANNED飞机

    公开(公告)号：US20140061390A1

    公开(公告)日：2014-03-06

    申请号：US13954362

    申请日：2013-07-30

    Applicant: Aurora Flight Sciences Corporation

    Inventor： Adam John Woodworth ,  James Peverill ,  Greg Vulikh ,  Jeremy Scott Hollman

    IPC: B64C15/00

    CPC classification number: B64C1/30 ,  A63H27/001 ,  A63H27/02 ,  B64C15/00 ,  B64C19/00 ,  B64C39/028 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/104 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/18 ,  B64C2201/187 ,  B64C2201/201 ,  B64D1/14 ,  B64D9/00 ,  B64D27/26

    Abstract: An aircraft for unmanned aviation is described. The aircraft includes an airframe, a pair of fins attached to a rear portion of the airframe, a pair of dihedral braces attached to a bottom portion of the airframe, a first thrust-vectoring (“T/V”) module and a second T/V module, and an electronics module. The electronics module provides commands to the two T/V modules. The two T/V modules are configured to provide lateral and longitudinal control to the aircraft by directly controlling a thrust vector for each of the pitch, the roll, and the yaw of the aircraft. The use of directly articulated electrical motors as T/V modules enables the aircraft to execute tight-radius turns over a wide range of airspeeds.

    Abstract translation: 描述了一种无人驾驶飞机。 飞行器包括机身，连接到机身的后部的一对翼片，连接到机身的底部的一对二面支架，第一推力矢量（“T / V”）模块和第二T / V模块，以及电子模块。 电子模块向两个T / V模块提供命令。 两个T / V模块被配置为通过直接控制飞行器的俯仰，滚动和偏航中的每一个的推力矢量来向飞行器提供侧向和纵向控制。 使用直接连接的电动机作为T / V模块，使飞机能够在大范围的空速下执行紧半径的转弯。

    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE
    36.
    发明申请
    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE 有权
    用于远程操作的无人驾驶航空器报警系统和设备 - 带便携式射频透明发射管的超级发射器

    公开(公告)号：US20110315817A1

    公开(公告)日：2011-12-29

    申请号：US13229377

    申请日：2011-09-09

    Applicant: Carlos Thomas Miralles ,  Guan H. Su ,  Oleksandr Andryukov ,  John McNeil

    Inventor： Carlos Thomas Miralles ,  Guan H. Su ,  Oleksandr Andryukov ,  John McNeil

    IPC: B64F1/04

    CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/146 ,  B64C2201/201 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F41F3/042 ,  F42B39/14

    Abstract: An unmanned aerial vehicle (UAV) launch tube that comprises a tethered sabot configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot is hollow having an open end oriented toward a high pressure volume and a tether attached within a hollow of the sabot and attached to the inner wall retaining the high pressure volume or attach to the inner base wall. A system comprising a communication node and a launcher comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node.

    Abstract translation: 一种无人驾驶飞行器（UAV）发射管，其包括被配置为将UAV接合在由内壁限定的发射器体积内的拴系的艉板，所述拴系的突出部的尺寸被设计成在内壁处提供压力密封并且系在内壁上，以及 其中所述系留式破碎器是中空的，其具有朝向高压容积的开口端，并且连接在所述破坏物的中空部内并且附接到保持高压容积的内壁或附接到内底壁的内壁的系绳。 一种包括通信节点和发射器的系统，其包括处于预发射状态的无人驾驶飞行器（UAV），其被配置为接收并响应来自所述通信节点的命令输入。

    METHODS AND APPARATUS FOR MARINE DEPLOYMENT
    39.
    发明申请
    METHODS AND APPARATUS FOR MARINE DEPLOYMENT 有权
    海上部署的方法和装置

    公开(公告)号：US20110073707A1

    公开(公告)日：2011-03-31

    申请号：US12233254

    申请日：2008-09-18

    Applicant: DAVID E. BOSSERT ,  Jeffrey N. Zerbe ,  Ray Sampson

    Inventor： DAVID E. BOSSERT ,  Jeffrey N. Zerbe ,  Ray Sampson

    IPC: B64F1/04 ,  B63G8/00 ,  H04Q5/22 ,  H01Q1/34

    CPC classification number: F41F3/07 ,  B64C2201/201 ,  B64C2201/205 ,  F42B15/20

    Abstract: Methods and apparatus for marine deployment according to various aspects of the present invention may operate in conjunction with a floatable housing adapted to be deployed by a marine vehicle. The floatable housing may be adapted to be launched from a marine vehicle and rise to the surface. Assets, such as an unmanned aerial vehicle, may be deployed from the surfaced floatable housing.

    Abstract translation: 根据本发明的各个方面的用于船舶部署的方法和装置可以与适于由船用车辆展开的可浮动壳体结合操作。 可浮动壳体可以适于从船用车辆发射并升起到地面。 诸如无人驾驶飞行器的资产可以从表面浮动的壳体部署。

    MULTI-LAYER METAL/SHAPE MEMORY POLYMER ROLL-UP WING STRUCTURES FOR FITMENT-CONSTRAINED AIR VEHICLES
    40.
    发明申请
    MULTI-LAYER METAL/SHAPE MEMORY POLYMER ROLL-UP WING STRUCTURES FOR FITMENT-CONSTRAINED AIR VEHICLES 有权
    多层金属/形状记忆聚合物旋转翼型结构

    公开(公告)号：US20100282906A1

    公开(公告)日：2010-11-11

    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: B64C3/00 ,  B64C1/00

    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。

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