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    FLYER ASSEMBLY
    112.
    发明申请
    FLYER ASSEMBLY 审中-公开
    飞机装配

    公开(公告)号：WO02032762A2

    公开(公告)日：2002-04-25

    申请号：PCT/US2001/031631

    申请日：2001-10-11

    IPC: B64C39/02 ,  F42B15/10 ,  B64C

    CPC classification number: F42B15/105 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/185 ,  B64C2201/201

    Abstract: A flyer assembly is adapted for launching with, transit in, and deployment from an artillery shell having a central void region extending along a ballistic shell axis. The flyer assembly includes a jettisonable shroud and a flyer. The shroud extends along a shroud axis, and is positionable within the central void region with the shroud axis substantially parallel to the shell axis. The flyer is adapted to withstand a launch acceleration force along a flyer axis when in a first state, and to effect aerodynamic flight when in a second state. When in the first state, the flyer is positionable within the shroud with the flyer axis parallel to the shroud axis and the shell axis. The flyer includes a body member disposed about the flyer axis, and a foldable wing assembly mounted to the body member. The wing assembly is configurable in a folded state characterized by a plurality of nested wing segments when the flyer is in the first state. The wing assembly is configurable in an unfolded state characterized by a substantially uninterrupted aerodynamic surface when the flyer is in the second state. The flyer assembly is adapted to be launched from a ballistic delivery system such as an artillery cannon, and can thus reach a target quickly, without expending system energy stored within the flyer. During launch, the flyer is coupled to the shroud so as to maintain a portion of the flyer in tension during an acceleration of the flyer along the flyer axis resulting from the launch. The flyer assembly is adapted to withstand the high g-load an high temperature environments of a cannon launch, and can tolerate a set-back g load of about 16,000 g.

    Abstract translation: 飞行器组件适用于从具有沿弹道壳轴线延伸的中心空隙区域的炮弹发射，转移和展开。 传单组件包括可喷射的护罩和传单​​。 护罩沿护罩轴线延伸，并且可定位在中心空隙区域内，护罩轴线基本上平行于外壳轴线。 飞行器适于在处于第一状态时承受沿飞行器轴的发射加速力，并且在处于第二状态时实现空气动力学飞行。 当处于第一状态时，传单可定位在护罩内，飞翼轴线平行于护罩轴线和外壳轴线。 传单包括围绕飞翼轴设置的主体部件和安装到主体部件的可折叠翼组件。 机翼组件可配置成折叠状态，其特征在于当传单处于第一状态时由多个嵌套翼段组成。 机翼组件可配置为展开状态，其特征在于当传单处于第二状态时基本上不间断的空气动力学表面。 飞行器组件适于从诸如炮兵炮的弹道传送系统发射，并且因此可以快速到达目标，而不会消耗存储在飞行物内的系统能量。 在发射期间，传单联接到护罩上，以便在飞行物沿着由发射引起的飞翼轴的加速期间，使传单的一部分保持张紧。 飞行器组件适于承受大炮发射的高温环境的高负载，并且可以承受大约16,000g的安装载荷。

    NOISE SUPPRESSION DEVICE FOR A DRONE LAUNCH TUBE
    113.
    发明授权
    NOISE SUPPRESSION DEVICE FOR A DRONE LAUNCH TUBE 有权

    公开(公告)号：EP3133019B1

    公开(公告)日：2018-12-05

    申请号：EP16179915.0

    申请日：2010-09-09

    Applicant: AeroVironment, Inc.

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

    IPC: B64F1/04 ,  F41F3/04 ,  F41F1/06

    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).

    AN UNMANNED AERIAL VEHICLE
    117.
    发明授权
    AN UNMANNED AERIAL VEHICLE 有权
    无人机空中车辆

    公开(公告)号：EP3130535B1

    公开(公告)日：2018-04-18

    申请号：EP16157916.4

    申请日：2016-02-29

    Applicant: Wirth Research Limited

    Inventor： WIRTH, Nicholas

    IPC: B64C3/56 ,  B64C39/02

    CPC classification number: B64C3/56 ,  B64C3/16 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/201

    Abstract: An unmanned aerial vehicle 2 comprising: a fuselage 4; and a wing 6 comprising a central wing section 12 pivotably mounted to the fuselage 4 and a pair of outer wing sections 14a, 14b pivotably mounted to the central wing section 12; wherein the wing 6 has a folded configuration in which the central wing section 12 and the outer wing sections 14a, 14b are stacked on top of one another and are aligned with a longitudinal axis of the fuselage 4; and a deployed configuration in which the central wing section 12 is substantially perpendicular to the fuselage 4 and the outer wing sections 14a, 14b extend from the central wing section 12 away from the fuselage 4.

    FOLDABLE WING WITH AN ACTUATOR ARRANGEMENT
    119.
    发明公开
    FOLDABLE WING WITH AN ACTUATOR ARRANGEMENT 审中-公开
    可折叠翼带执行器安排

    公开(公告)号：EP3254956A1

    公开(公告)日：2017-12-13

    申请号：EP16173835.6

    申请日：2016-06-09

    Applicant: Airbus Operations GmbH

    Inventor： Winkelmann, Christoph ,  Rupp, Johannes

    IPC: B64C3/56 ,  F15B9/10

    CPC classification number: B64C3/56 ,  B64C2201/102 ,  F15B9/10 ,  Y02T50/14

    Abstract: The present invention relates to a wing arrangement for an aircraft (1), comprising a wing (9) having a base section (11) and a tip section (13) pivotably connected to the base section (11) such that the tip section (13) is pivotable between a deployed position and a stowed position in which the spanwise length of the wing (9) is smaller than in the deployed position. The wing arrangement also has an actuating arrangement (19) including a linear hydraulic actuator (21) coupled between the base section (11) and the tip section (13) such that it is operable to selectively move the tip section (13) between the deployed position and the stowed position, a first and a second hydraulic connection portion (79a, 79b) connected to the linear hydraulic actuator (21) such that they are in fluid communication with different chamber sections (27a, 27b) of a cylinder (25) of the linear hydraulic actuator (21), and a first hydraulic subsystem (81a) and a second hydraulic subsystem (81b), each connected to and branching off the first and second hydraulic connection portions (79a, 79b), and each operable to supply pressurized hydraulic fluid to the first and second hydraulic connection portions (79a, 79b). A first shut-off valve (87a) is located between the first hydraulic subsystem (81a) and the first and second hydraulic connection portions (79a, 79b). The first hydraulic subsystem (81a) comprises a first hydraulic supply (89a) including a first connector assembly (91a) adapted to be connected to a first hydraulic system of an aircraft (1), and the second hydraulic subsystem (81b) comprises a motor (107, 137) and a pump (109, 141), wherein the motor (107, 137) is operable to drive the pump (109, 141) to pump hydraulic fluid contained in the second hydraulic subsystem (81b) to the first and second hydraulic connection portions (79a, 79b).

    Abstract translation: 本发明涉及一种用于飞机（1）的机翼装置，包括具有基部（11）和可枢转地连接到基部（11）的末端部分（13）的机翼（9），使得末端部分 13）能够在展开位置和收起位置之间枢转，在收起位置中，机翼（9）的翼展方向长度小于展开位置。 机翼装置还具有致动装置（19），该致动装置包括联接在底座部分（11）和尖端部分（13）之间的线性液压致动器（21），使得其可操作以选择性地将尖端部分（13） 第一和第二液压连接部分（79a，79b），连接到线性液压致动器（21），使得它们与气缸（25）的不同腔室部分（27a，27b）流体连通， ）和第一液压子系统（81a）和第二液压子系统（81b），所述第一液压子系统（81a）和第二液压子系统（81b）分别与所述第一液压连接部分和所述第二液压连接部分（79a，79b）连接并分支， 将加压的液压流体供应到第一和第二液压连接部分（79a，79b）。 第一截止阀（87a）位于第一液压子系统（81a）与第一和第二液压连接部分（79a，79b）之间。 第一液压子系统（81a）包括第一液压源（89a），该第一液压源包括适于连接到飞机（1）的第一液压系统的第一连接器组件（91a），并且第二液压子系统（81b）包括马达 （107,137）和泵（109,141），其中所述马达（107,137）可操作以驱动所述泵（109,141）以将包含在所述第二液压子系统（81b）中的液压流体泵送到所述第一和第二液压子系统 第二液压连接部分（79a，79b）。

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