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    FLYER ASSEMBLY
    221.
    发明申请
    FLYER ASSEMBLY 有权
    飞机装配

    公开(公告)号：US20030089820A1

    公开(公告)日：2003-05-15

    申请号：US10150726

    申请日：2002-05-17

    Inventor： Richard T. Martorana ,  Jamie Anderson ,  Simon Mark Spearing ,  Seth Kessler ,  Brent Appleby ,  Edward Bergmann ,  Sean George ,  Steven Jacobson ,  Donald Fyler ,  Mark Drela ,  Gregory Kirkos ,  William McFarland JR.

    IPC: F42B015/01 ,  F42B015/10 ,  F42B015/20 ,  F42B015/22

    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 and 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。 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片段组成。 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负载和高温环境，并且可以容忍约16,000g的安装载荷。

    RAMP OF CATAPULT
    226.
    发明申请
    RAMP OF CATAPULT 审中-公开

    公开(公告)号：US20170297740A1

    公开(公告)日：2017-10-19

    申请号：US15426273

    申请日：2017-02-07

    Applicant: Robonic Ltd Oy

    Inventor： Pentti Lipponen

    IPC: B64F1/06 ,  B64C39/02 ,  F41F3/04

    CPC classification number: B64F1/06 ,  B64C39/024 ,  B64C2201/084 ,  F41F3/0406

    Abstract: The invention relates to a ramp of a catapult and to a catapult. The catapult comprises a carriage (4) for fastening an aircraft (5). The carriage (4) is supported on a ramp (1). The ramp is formed of one or more ramp elements (1a-1m). The ramp element comprises four frame plates, namely two parallel side plates (20a, 20b), a top plate (21) and a bottom plate (22). The frame plates are separate pieces which are connected at fastening points (25) to each other by means of mechanical fastening elements (26).

    Launch Tube Restraint System For Unmanned Aerial Vehicle (UAV)
    229.
    发明申请
    Launch Tube Restraint System For Unmanned Aerial Vehicle (UAV) 有权
    无人机（UAV）发射管约束系统

    公开(公告)号：US20170029135A1

    公开(公告)日：2017-02-02

    申请号：US15292908

    申请日：2016-10-13

    Applicant: AeroVironment, Inc.

    Inventor： Guan H. Su ,  Marcos Henry Rodriguez

    IPC: B64F1/04 ,  B64C39/02 ,  F41B11/80

    CPC classification number: B64F1/04 ,  B64C39/024 ,  B64C2201/08 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/201 ,  B64F1/06 ,  F41B11/80 ,  F41F3/00 ,  F41F3/042 ,  F41F3/052 ,  F41F3/073

    Abstract: An unmanned aerial launch vehicle (UAV) launch apparatus is disclosed that includes a UAV (400) having an exterior surface, an aerial vehicle (AV) tab (510) extending from the exterior surface, a tube (440) containing the UAV (400), the tube (440) including a tab stop (515) configured to controllably hinder travel of the AV tab (510) past the tab stop (515), and a pair of opposing tab guides (700, 705) configured to position the AV tab (510) for travel over the tab stop (515).

    Abstract translation: 公开了一种无人驾驶飞行器（UAV）发射装置，其包括具有外表面的UAV（400），从外表面延伸的飞行器（AV）突片（510），包含无人机（400）的管（440） ），所述管（440）包括构造成可控制地阻碍所述AV突片（510）经过所述突片止动件（515）的移动的突片止动件（515），以及一对相对的突片引导件（700,705），其被配置为 AV选项卡（510），用于在制表位（515）上移动。

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