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32 条记录 (耗时 0.016 秒)

    Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube
    3.
    发明授权
    Systems and devices for remotely operated unmanned aerial vehicle report-suppressing launcher with portable RF transparent launch tube 有权

    公开(公告)号：US10450089B2

    公开(公告)日：2019-10-22

    申请号：US16137196

    申请日：2018-09-20

    申请人： AEROVIRONMENT, INC.

    发明人： Carlos Thomas Miralles ,  Guan H Su ,  Alexander Andryukov ,  John McNeil

    IPC分类号： B64F1/04 ,  B64C39/02 ,  B64F1/06 ,  F41A21/02 ,  F41F3/042 ,  F42B39/14 ,  F41F1/00

    摘要： An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. 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.

    System for detachably coupling an unmanned aerial vehicle within a launch tube
    4.
    发明授权
    System for detachably coupling an unmanned aerial vehicle within a launch tube 有权

    公开(公告)号：US10442554B2

    公开(公告)日：2019-10-15

    申请号：US14561894

    申请日：2014-12-05

    申请人： AEROVIRONMENT, INC.

    发明人： Alexander Andryukov

    IPC分类号： B64F1/04 ,  B64C39/02

    摘要： A system comprising an unmanned aerial vehicle launch tube comprising a sabot disposed in an interior of the launch tube, the sabot having a first clasp tab and an expandable skirt. The sabot is hollow, and the expandable skirt has a circumferential skirt protrusion and is configured to provide a pressure seal with the inner circumferential wall of the launch tube. The system further comprises a clasp detachably coupled to the first clasp tab and contacting the inner circumferential wall of the launch tube.

    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE
    7.
    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

    公开(公告)号：US20200140120A1

    公开(公告)日：2020-05-07

    申请号：US16574344

    申请日：2019-09-18

    申请人： AEROVIRONMENT, INC.

    发明人： Carlos Thomas Miralles ,  Guan H Su ,  Alexander Andryukov ,  John McNeil

    IPC分类号： B64F1/04 ,  B64C39/02 ,  B64F1/06 ,  F41A21/02 ,  F41F1/00 ,  F42B39/14 ,  F41F3/042

    摘要： An unmanned aerial vehicle (UAV) launch tube that comprises at least one inner layer of prepreg substrate disposed about a right parallelepiped aperture, at least one outer layer of prepreg substrate disposed about the right parallelepiped aperture, and one or more structural panels disposed between the at least one inner layer of prepreg substrate and the at least one outer layer of prepreg substrate. 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.

    Air Vehicle Flight Mechanism and Control Method for Non-Sinusoidal Wing Flapping
    10.
    发明申请
    Air Vehicle Flight Mechanism and Control Method for Non-Sinusoidal Wing Flapping 有权
    非正弦翼飞行器的飞行器飞行机构与控制方法

    公开(公告)号：US20140158821A1

    公开(公告)日：2014-06-12

    申请号：US13969258

    申请日：2013-08-16

    申请人： AeroVironment, Inc.

    发明人： Matthew Todd Keennon ,  Alexander Andryukov ,  Karl Robert Klingebiel ,  Henry Thome Won

    IPC分类号： B64C39/00

    CPC分类号： B64C39/003 ,  B64C33/02 ,  B64C39/028 ,  B64C2201/025 ,  B64C2201/042

    摘要： A flapping wing driving apparatus includes at least one crank gear capstan rotatably coupled to a crank gear, the at least one crank gear capstan disposed radially offset from a center of rotation of the crank gear; a first wing capstan coupled to a first wing, the first wing capstan having a first variable-radius drive pulley portion; and a first drive linking member configured to drive the first wing capstan, the first drive linking member windably coupled between the first variable-radius drive pulley portion and one of the at least one crank gear capstan; wherein the first wing capstan is configured to non-constantly, angularly rotate responsive to a constant angular rotation of the crank gear.

    摘要翻译： 拍动翼驱动装置包括可旋转地联接到曲柄齿轮的至少一个曲柄齿轮主动轮，所述至少一个曲柄齿轮主动轮设置在径向偏离曲柄齿轮的旋转中心; 第一翼形绞盘，其联接到第一翼，所述第一翼形绞盘具有第一可变半径的驱动皮带轮部分; 以及第一驱动连接构件，其构造成驱动所述第一翼形主导轮，所述第一驱动连接构件可变地联接在所述第一可变半径驱动滑轮部分和所述至少一个曲柄齿轮绞盘之一之间; 其中所述第一翼形绞盘被配置成响应于所述曲柄齿轮的恒定角度旋转而不间断地，有角度地旋转。