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    Air Vehicle Flight Mechanism and Control Method for Non-Sinusoidal Wing Flapping
    32.
    发明申请
    Air Vehicle Flight Mechanism and Control Method for Non-Sinusoidal Wing Flapping 审中-公开

    公开(公告)号：US20190055014A1

    公开(公告)日：2019-02-21

    申请号：US16047395

    申请日：2018-07-27

    Applicant: AeroVironment, Inc.

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

    IPC: B64C39/00 ,  B64C33/02 ,  B64C39/02

    Abstract: 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.

    Air vehicle flight mechanism and control method for non-sinusoidal wing flapping
    33.
    发明授权
    Air vehicle flight mechanism and control method for non-sinusoidal wing flapping 有权

    公开(公告)号：US10065737B2

    公开(公告)日：2018-09-04

    申请号：US15581976

    申请日：2017-04-28

    Applicant: AeroVironment, Inc.

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

    IPC: B64C33/02 ,  B64C39/00

    Abstract: 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.

    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE
    35.
    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。

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