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    UNMANNED FLYING DEVICE
    171.
    发明公开
    UNMANNED FLYING DEVICE 审中-公开
    无人飞行装置

    公开(公告)号：EP3218263A1

    公开(公告)日：2017-09-20

    申请号：EP15859431.7

    申请日：2015-11-10

    Applicant: Ascent Aerosystems Inc.

    Inventor： MERINGER, Jonathan, R. ,  MERINGER, Nathaniel, R.

    IPC: B64C27/10 ,  B64C27/32 ,  B64C27/50

    CPC classification number: B64C39/024 ,  B64C27/10 ,  B64C27/50 ,  B64C2201/102 ,  B64C2201/108 ,  B64C2201/18

    Abstract: An unmanned flying device including a body; a first blade and at least a second blade; a coupling assembly for coupling the first blade and the at least second blade to the body, wherein the coupling assembly urges the collapsing of the first blade and the at least second blade towards the body; and wherein both the first blade and the at least second blade are rotatable about the body, and wherein the first blade and the at least second blade are deployable away from the body via rotation of the first and the at least second blades about the body.

    Abstract translation: 一种无人飞行装置，包括一个身体; 第一刀片和至少一个第二刀片; 联接组件，其用于将所述第一叶片和所述至少第二叶片联接到所述主体，其中所述联接组件推动所述第一叶片和所述至少第二叶片朝向所述主体的塌缩; 并且其中所述第一刀片和所述至少第二刀片都可围绕所述主体旋转，并且其中所述第一刀片和所述至少第二刀片可通过所述第一刀片和所述至少第二刀片围绕所述主体的旋转而远离所述主体展开。

    VERTICAL TAKE-OFF AND LANDING AIRCRAFT
    172.
    发明公开
    VERTICAL TAKE-OFF AND LANDING AIRCRAFT 有权
    VERTIKAL STARTENDES UND LANDENDES FLUGZEUG

    公开(公告)号：EP3057867A4

    公开(公告)日：2017-07-26

    申请号：EP14878419

    申请日：2014-10-10

    Applicant: SWIFT ENG INC

    Inventor： GODLASKY ROBERT ,  OGAWA NATE ,  STREETT ANDREW

    IPC: B64C29/00 ,  B64C3/56 ,  B64C5/02 ,  B64C29/02 ,  B64D27/02

    CPC classification number: B64D27/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102

    Abstract: A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.

    Abstract translation: VTOL飞机包括至少一个牵引转子和至少一个推动器转子。 例如，VTOL飞机可能包括三个牵引转子和一个推动转子。 静态牵引器和推进器转子的组合允许转子相对于VTOL飞机的机翼和机身保持固定的定向（即，不需要移动的机械轴），同时能够将飞行器从大致垂直的飞行 到基本水平的飞行路径的路径。

    AIR VEHICLE AND METHOD AND APPARATUS FOR CONTROL THEREOF
    174.
    发明公开
    AIR VEHICLE AND METHOD AND APPARATUS FOR CONTROL THEREOF 审中-公开
    LUFTFAHRZEUG UND VERFAHREN UND VORRICHTUNG ZU DESSEN STEUERUNG

    公开(公告)号：EP3162701A1

    公开(公告)日：2017-05-03

    申请号：EP15275223

    申请日：2015-10-30

    Applicant: BAE SYSTEMS PLC

    IPC: B64C3/46 ,  B64C3/44 ,  B64C3/48 ,  B64C29/02

    CPC classification number: B64C3/48 ,  B64C3/44 ,  B64C3/46 ,  B64C29/02 ,  B64C2003/142 ,  B64C2201/088 ,  B64C2201/102 ,  Y02T50/12 ,  Y02T50/145

    Abstract: A wing member (14b) for an air vehicle (10), said wing member comprising a core section (20) defining its longitudinal axis and having upper and lower surfaces, at least one of said surfaces comprising apparatus (22) selectively configurable between at least two positions, wherein in a fully extended position, at least portions of said apparatus extend outwardly from said respective surface so as to increase the effective cross-sectional area of said wing member and define an effective aerofoil in respect thereof.

    Abstract translation: 一种用于飞行器（10）的机翼构件（14b），所述机翼构件包括限定其纵向轴线并具有上表面和下表面的核心部分（20），所述表面中的至少一个包括设备（22），所述设备（22） 至少两个位置，其中在完全伸展的位置中，所述设备的至少部分从所述相应的表面向外延伸，以便增加所述翼部件的有效横截面积并限定相对于其的有效翼面。

    VERTICAL TAKEOFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV)
    175.
    发明公开
    VERTICAL TAKEOFF AND LANDING (VTOL) UNMANNED AERIAL VEHICLE (UAV) 审中-公开
    无人机（无人机）麻省理工学院VERTIKALEM TAKEOFF UND LANDUNG（VTOL）

    公开(公告)号：EP3140188A2

    公开(公告)日：2017-03-15

    申请号：EP15784502.5

    申请日：2015-04-24

    Applicant: Northrop Grumman Systems Corporation

    Inventor： CREASMAN, Son F.

    IPC: B64C3/56 ,  B64C25/04 ,  B64C29/02 ,  B64C3/54 ,  B64C29/00

    CPC classification number: G05D1/102 ,  B64C3/546 ,  B64C3/56 ,  B64C9/00 ,  B64C11/48 ,  B64C25/04 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/102 ,  B64C2201/108 ,  B64F1/007 ,  G05D1/0011

    Abstract: One example embodiment includes a vertical takeoff and landing (VTOL) unmanned aerial vehicle (UAV). The VTOL UAV includes a flight control system configured to provide avionic control of the VTOL UAV in a hover mode and in a level-flight mode. The VTOL UAV also includes a body encapsulating an engine and the flight control system. The VTOL UAV further includes a propeller disk coupled to the engine and configured to provide vertical thrust in the hover mode and to provide horizontal thrust for flight during the level-flight mode.

    Abstract translation: 一个示例性实施例包括垂直起飞和着陆（VTOL）无人机（UAV）。 VTOL无人机包括飞行控制系统，配置为以悬停模式和水平飞行模式提供垂直起降无人机的航空电子控制。 VTOL无人机还包括一个封装发动机和飞行控制系统的机身。 垂直起落架无人机还包括联接到发动机并被构造成在悬停模式下提供垂直推力并在水平飞行模式期间提供水平推力以用于飞行的螺旋桨盘。

    VERTICAL TAKE-OFF AND LANDING AIRCRAFT
    176.
    发明公开
    VERTICAL TAKE-OFF AND LANDING AIRCRAFT 有权
    VERTIKAL STARTENDES UND LANDENDES FLUGZEUG

    公开(公告)号：EP3057867A2

    公开(公告)日：2016-08-24

    申请号：EP14878419.2

    申请日：2014-10-10

    Applicant: Swift Engineering, Inc.

    Inventor： GODLASKY, Robert ,  OGAWA, Nate ,  STREETT, Andrew

    IPC: B64C29/00 ,  B64C3/56 ,  B64D27/02 ,  B64C29/02 ,  B64C5/02

    CPC classification number: B64D27/02 ,  B64C29/02 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/088 ,  B64C2201/102

    Abstract: A VTOL aircraft includes at least one puller rotor and at least one pusher rotor. The VTOL aircraft, for example, may include three puller rotors and one pusher rotor. The combination of static puller and pusher rotors allows the rotors to remain in a fixed orientation (i.e., no moving mechanical axes are required) relative to the wings and fuselage of the VTOL aircraft, while being able to transition the aircraft from a substantially vertical flight path to a substantially horizontal flight path.

    Abstract translation: 垂直起降飞机包括至少一个牵引转子和至少一个推动器转子。 例如，VTOL飞机可以包括三个牵引转子和一个推动器转子。 静态牵引器和推动器转子的组合允许转子相对于垂直起降飞机的机翼和机身保持在固定的方向（即，不需要移动的机械轴），同时能够使飞机从基本垂直的飞行 到大致水平的飞行路径的路径。

    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE
    180.
    发明公开
    SYSTEMS AND DEVICES FOR REMOTELY OPERATED UNMANNED AERIAL VEHICLE REPORT-SUPPRESSING LAUNCHER WITH PORTABLE RF TRANSPARENT LAUNCH TUBE 有权
    VerstärktesRohr zum katapultieren von Drohnen

    公开(公告)号：EP2475578A2

    公开(公告)日：2012-07-18

    申请号：EP10833731.2

    申请日：2010-09-09

    Applicant: AeroVironment, Inc.

    Inventor： MIRALLES, Carlos Thomas ,  SU, Guan H. ,  ANDRYUKOV, Oleksandr ,  MCNEIL, John

    IPC: B64F1/04 ,  F41F3/04 ,  B64C13/20

    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 (305), 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），其包括围绕右平行六面体孔（305）设置的至少一个预浸料衬底内层（370），至少一个围绕右侧设置的预浸料衬底（380）外层 平行六面体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），其包括被构造成与在内壁限定的发射器体内接合无人机的拴系的膛体（700,740），所述拴系的炮（700,740）的尺寸设置成在内部提供压力密封 并且其中所述系绳式突破（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）的中空部（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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