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    Mechanisms for deploying and actuating airfoil-shaped bodies on unmanned aerial vehicles
    71.
    发明授权
    Mechanisms for deploying and actuating airfoil-shaped bodies on unmanned aerial vehicles 有权
    在无人驾驶飞行器上部署并致动翼型的机构

    公开(公告)号：US09533758B2

    公开(公告)日：2017-01-03

    申请号：US14590464

    申请日：2015-01-06

    Applicant: The Boeing Company

    Inventor： Jonathan David Gettinger

    IPC: B64C5/12 ,  B64C39/02 ,  B64C3/56

    CPC classification number: B64C39/024 ,  B64C3/56 ,  B64C5/12 ,  B64C2201/102

    Abstract: Deployment and control actuation mechanisms are incorporated in unmanned aerial vehicles having folding wings and/or folding canards and/or a folding vertical stabilizer. The folding canards and folding vertical stabilizer can be deployed using respective four-bar over-center mechanisms. Elevators pivotably mounted to the folding canards and a rudder pivotably mounted to the folding vertical stabilizer can be controlled by means of respective twist link mechanisms. The folding wings have respective wing roots that are driven by respective gas springs to pivot on bearings about a wing root hub having control servo wire paths.

    Abstract translation: 部署和控制致动机构被并入具有折叠翼和/或折叠的猫和/或折叠的垂直稳定器的无人驾驶飞行器中。 可以使用相应的四杆过中心机构来部署折叠式鸭子和折叠式垂直稳定器。 可枢转地安装到折叠卡瓦的电梯和可枢转地安装到折叠垂直稳定器的舵可以通过相应的扭转连杆机构来控制。 折叠翼具有相应的翼根，其由相应的气弹簧驱动，以围绕具有控制伺服线路径的翼根轮毂的轴承枢转。

    Aerial vehicle with separation of winged surfaces in first and second flexed states
    73.
    发明授权
    Aerial vehicle with separation of winged surfaces in first and second flexed states 有权
    在第一和第二弯曲状态下分离有翼表面的飞行器

    公开(公告)号：US09296468B1

    公开(公告)日：2016-03-29

    申请号：US14032800

    申请日：2013-09-20

    Applicant: Brandebury Tool Company, Inc.

    Inventor： William B. Harvey ,  Matthew G. Amsellem

    IPC: B64C3/40 ,  B64C39/02

    CPC classification number: B64C3/40 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/102

    Abstract: Embodiments include an aerial vehicle. Two winged surfaces are provided in communication with a fuselage. The surfaces are in communication at a front edge via a cuff, at a midsection via a first resilient member, and at a trailing edge via a second resilient member. As the aerial vehicle is in flight, it is subject to loads. The connections of the surfaces provides flexibility and resiliency to maintain the surfaces in communication with the fuselage and to allow regulated separation of the winged surfaces at their rear edges in a first direction in a first flexed state and at their front edges in a second direction, different from the first direction, in a second flexed state.

    Abstract translation: 实施例包括飞行器。 提供与机身连通的两个翼状表面。 这些表面经由袖带在前边缘处经由第一弹性构件在中间连接，并且在后缘处经由第二弹性构件连通。 当飞行器在飞行中时，它将受到负载的影响。 表面的连接提供了灵活性和弹性，以保持与机身连通的表面，并且允许翼形表面在其后边缘处以第一弯曲状态的第一方向和在其第二方向的前边缘处被调节分离， 与第一方向不同，处于第二弯曲状态。

    Long endurance aircraft
    74.
    发明授权
    Long endurance aircraft 有权
    长耐力飞机

    公开(公告)号：US09272783B2

    公开(公告)日：2016-03-01

    申请号：US12058520

    申请日：2008-03-28

    Applicant: Jerome Pearson

    Inventor： Jerome Pearson

    IPC: B64C39/02

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102

    Abstract: A long endurance powered aircraft includes a fuselage, a propeller coupled to the fuselage, a wing coupled to the fuselage, and an energy storage system disposed within the fuselage. The wing includes an adjustable surface area including solar cells configured to collect incident solar energy and convert the collected incident solar energy to electrical energy for powering the aircraft during daylight flight. The energy storage system is configured to convert excess electrical energy converted from collected incident solar energy to chemical energy, store the chemical energy, and convert the stored chemical energy to electrical energy for powering the aircraft during night flight.

    Abstract translation: 长寿命动力飞机包括机身，与机身相连的螺旋桨，与机身相连的机翼，以及设置在机身内的能量存储系统。 机翼包括可调节的表面区域，包括被配置为收集入射的太阳能并且将收集的入射太阳能转换成电能的太阳能电池，以在日间飞行期间为飞机供电。 能量存储系统被配置为将从收集的入射太阳能转换的过量电能转换成化学能，存储化学能，并将存储的化学能转换成电能，以在夜间飞行期间为飞行器供电。

    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE
    75.
    发明申请
    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE 审中-公开
    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：US20160039536A1

    公开(公告)日：2016-02-11

    申请号：US14887675

    申请日：2015-10-20

    Applicant: AEROVIRONMENT, INC.

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

    IPC: B64F1/04 ,  B64C39/02

    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 (100)that comprises at least one inner layer of prepreg substrate (370) disposed about a right parallelepiped aperture (305), at least one outer layer of prepreg substrate (380) disposed about the right parallelepiped aperture, and one or more structural panels (341-344) disposed between the at least one inner layer of prepreg substrate (340) and the at least one outer layer of prepreg substrate (380). An unmanned aerial vehicle (UAV) launch tube (100) that comprises a tethered sabot (700,740) configured to engage a UAV within a launcher volume defined by an inner wall, the tethered sabot(700,740) dimensioned to provide a pressure seal at the inner wall and tethered to the inner wall, and wherein the tethered sabot (700,740) is hollow having an open end oriented toward a high pressure volume and a tether (740) attached within a hollow (910) of the sabot(700) and attached to the inner wall retaining the high pressure volume or attach to the inner base wall (1013). A system comprising a communication node (1500-1505) and a launcher (1520) comprising an unmanned aerial vehicle (UAV) in a pre-launch state configured to receive and respond to command inputs from the communication node (1500-1505).

    Abstract translation: 一种无人驾驶飞行器（UAV）发射管（100），其包括设置在右平行六面体孔（305）周围的至少一个预浸料衬底内层（370），至少一个预浸料衬底外周层 平行六面体的孔和设置在至少一层预浸料衬底（340）的内层与至少一层预浸料衬底（380）之间的一个或多个结构面板（341-344）。 一种无人驾驶飞行器（UAV）发射管（100），其包括被构造成接合由内壁限定的发射器体积内的UAV的拴系的膛体（700,740），所述拴系的炮（700,740）的尺寸被设计成在内部提供压力密封 并且其中所述系留式破坏物（700,740）是中空的，具有朝向高压容积定向的开口端和连接在所述破坏物（700）的中空（910）内的系绳（740），并且附接到 所述内壁保持高压容积或附接到所述内底壁（1013）。 包括通信节点（1500-1505）和发射器（1520）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通信节点（1500-1505）的命令输入。

    COMBINED SUBMERSIBLE VESSEL AND UNMANNED AERIAL VEHICLE
    76.
    发明申请
    COMBINED SUBMERSIBLE VESSEL AND UNMANNED AERIAL VEHICLE 有权
    组合的不合格船只和无人驾驶的航空器

    公开(公告)号：US20150375586A1

    公开(公告)日：2015-12-31

    申请号：US14851453

    申请日：2015-09-11

    Applicant: Aurora Flight Sciences Corporation

    Inventor： ROBERT PARKS ,  ADAM WOODWORTH ,  TOM VANECK ,  JUSTIN MCCLELLAN

    IPC: B60F5/02 ,  B64C39/02 ,  B63G8/08

    CPC classification number: B64C37/00 ,  B60F5/02 ,  B63G8/001 ,  B63G8/08 ,  B63G2008/005 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/08 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/165 ,  B64C2201/167 ,  F42B15/20

    Abstract: A combined submersible vessel and unmanned aerial vehicle preferably includes a body structure, at least one wing structure, at least one vertical stabilizer structure, and at least one horizontal stabilizer structure. A propulsion system is coupled to the body structure and is configured to propel the flying submarine in both airborne flight and underwater operation. Preferably, the propulsion system includes a motor, a gearbox coupled to the motor and configured to receive power generated by the motor and provide variable output power, a drive shaft coupled to the gearbox and configured to transfer the variable output power provided by the gearbox, and a propeller coupled to the drive shaft and configured to accept power transferred to it from the drive shaft. The propeller is further configured to rotate and propel the flying submarine in both an airborne environment and in an underwater environment.

    Abstract translation: 组合潜艇和无人驾驶飞行器优选地包括主体结构，至少一个翼结构，至少一个垂直稳定器结构和至少一个水平稳定器结构。 推进系统联接到车身结构并且被构造成在空中飞行和水下操作中推进飞行潜艇。 优选地，推进系统包括电动机，耦合到电动机并被配置为接收由电动机产生的电力并提供可变输出功率的变速箱;耦合到齿轮箱并被配置为传递由变速箱提供的可变输出功率的驱动轴， 以及联接到所述驱动轴并被配置为接受从所述驱动轴传递到其的动力的螺旋桨。 螺旋桨进一步构造成在空中环境和水下环境中旋转和推进飞行潜艇。

    AIR-LAUNCHABLE CONTAINER FOR DEPLOYING AIR VEHICLE
    78.
    发明申请
    AIR-LAUNCHABLE CONTAINER FOR DEPLOYING AIR VEHICLE 有权
    用于空运车辆的空运集装箱

    公开(公告)号：US20150266578A1

    公开(公告)日：2015-09-24

    申请号：US14018493

    申请日：2013-09-05

    Applicant: Raytheon Company

    Inventor： Erick W. Elkins ,  Matthew Glenn Murphy ,  Scott D. Thomas

    IPC: B64D1/12 ,  B64C39/02

    CPC classification number: B64D1/12 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/201 ,  B64C2201/206

    Abstract: A container is used to launch a small aircraft, such as an unmanned aerial vehicle (UAV), from a host aircraft. The container protects the UAV from stresses during the initial ejection from a launcher that is part of the host aircraft. The initial stresses may be due to turbulence in the vicinity of the host aircraft, high airspeed, and/or tumbling that may result from the ejection from the host aircraft moving at a high airspeed. The container may deploy a drag device, such as a drogue chute, to slow the container down and reorient the container, prior to deployment of the UAV from the container. During the time between ejection from the host aircraft and deployment from the container, the UAV may be powered up and acquire data, such as global positioning system (GPS) data, to allow the UAV a “hot start” enabling immediate mission commencement.

    Abstract translation: 一个集装箱用于从一架主机上发射一架小型飞机，如无人飞行器（UAV）。 该容器保护无人机在最初从作为主机的一部分的发射器弹出之前受到压力。 初始应力可能是由于主机飞机附近的湍流，高空速和/或可能由主飞机从高空速下移动而导致的翻滚造成的。 在从容器部署UAV之前，容器可以部署拖动装置，例如锥形滑槽，以使容器向下减速并重新定向容器。 在从主机飞行器和从集装箱部署之间的时间内，UAV可以被加电并且获取诸如全球定位系统（GPS）数据的数据，以允许UAV“启动”，从而能够立即启动任务。

    HOVERING UNMANNED AERIAL VEHICLE
    79.
    发明申请
    HOVERING UNMANNED AERIAL VEHICLE 有权
    不顾一切的空中客车

    公开(公告)号：US20150259066A1

    公开(公告)日：2015-09-17

    申请号：US14436310

    申请日：2013-10-17

    Applicant: AERYON LABS INC.

    Inventor： Glen Johannesson ,  David Kroetsch ,  Michael Peasgood ,  Stephen Marchetti

    IPC: B64C39/02

    CPC classification number: B64C39/024 ,  B64C1/30 ,  B64C27/08 ,  B64C2201/024 ,  B64C2201/027 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/165 ,  B64C2201/20

    Abstract: In an aspect, an apparatus includes a hovering unmanned aerial vehicle (HUAV). The HUAV includes an arm assembly configured to support a propeller in such a way that propeller drag of the propeller is decoupled from yaw torque requirements associated with the hovering unmanned aerial vehicle. In another aspect, an apparatus includes an HUAV that has an arm assembly that is field-foldable relative to the HUAV between a flight-ready state and a folded state. In another aspect, an apparatus includes an HUAV having an arm assembly that is keyed in such a way as to facilitate field-assembly relative to the HUAV.

    Abstract translation: 一方面，一种装置包括悬停无人机（HUAV）。 HUAV包括臂组件，其构造成支撑螺旋桨，使螺旋桨的螺旋桨阻力与悬停的无人驾驶飞行器相关的偏航扭矩要求分离。 在另一方面，一种装置包括具有臂组件的HUAV，所述臂组件相对于在待飞状态和折叠状态之间的HUAV是可折叠的。 在另一方面，一种装置包括具有臂组件的HUAV，该臂组件以便于相对于HUAV的现场组装的方式键入。

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