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    APPARATUS FOR USE ON UNMANNED VEHICLES
    35.
    发明申请
    APPARATUS FOR USE ON UNMANNED VEHICLES 有权
    用于无人驾驶车辆的装置

    公开(公告)号：US20140222249A1

    公开(公告)日：2014-08-07

    申请号：US14129195

    申请日：2012-06-20

    Applicant: BAE SYSTEMS PLC

    Inventor： Isobel Louise Freeman ,  Keith Antony Rigby

    IPC: B64C39/02

    CPC classification number: B64C39/024 ,  B64C2201/00 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/127 ,  F41H7/005 ,  F41H13/00 ,  F42B12/365

    Abstract: An apparatus, and a method performed by the apparatus, are disclosed wherein the apparatus can be mounted on an unmanned vehicle and arranged to act upon a payload. The payload can be mounted on the unmanned vehicle and, under an action of the apparatus, is able to be activated. The method can include receiving an activation instruction from an entity remote from the unmanned vehicle; determining whether or not the received activation instruction is valid by performing a validation process; and in response to determining that the received activation instruction is valid, activating the payload. In response to determining that the received activation instruction is not valid, activation of the payload may be prevented or opposed.

    Abstract translation: 公开了一种装置和由该装置执行的方法，其中该装置可以安装在无人驾驶车辆上并被布置成作用在有效载荷上。 有效载荷可以安装在无人驾驶车辆上，并且在装置的作用下能够被激活。 该方法可以包括从远程无人驾驶车辆的实体接收激活指令; 通过执行验证过程来确定所接收到的激活指令是否有效; 并且响应于确定所接收到的激活指令是有效的，激活有效载荷。 响应于确定接收到的激活指令无效，可以防止或反对有效载荷的激活。

    UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION
    36.
    发明申请
    UNMANNED AERIAL VEHICLE ANGULAR REORIENTATION 有权
    不定期的空中客车航向转向

    公开(公告)号：US20140172200A1

    公开(公告)日：2014-06-19

    申请号：US14016602

    申请日：2013-09-03

    Applicant: AEROVIRONMENT, INC.

    Inventor： Carlos Miralles

    IPC: B64C13/16

    CPC classification number: B64C13/16 ,  B64B2201/00 ,  B64C39/024 ,  B64C2201/04 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/165 ,  F41G7/2253 ,  F41G7/2286 ,  F41G7/2293 ,  G05D1/12

    Abstract: A system comprising an unmanned aerial vehicle (UAV) having wing elements and tail elements configured to roll to angularly orient the UAV by rolling so as to align a longitudinal plane of the UAV, in its late terminal phase, with a target. A method of UAV body re-orientation comprising: (a) determining by a processor a boresight angle error correction value bases on distance between a target point and a boresight point of a body-fixed frame; and (b) effecting a UAV maneuver comprising an angular role rate component translating the target point to a re-oriented target point in the body-fixed frame, to maintain the offset angle via the offset angle correction value.

    Abstract translation: 一种包括具有翼元件和尾部元件的无人飞行器（UAV）的系统，其被配置成滚动以通过滚动来成角度地定向UAV，以便在其后期终点阶段将UAV的纵向平面与目标对准。 一种UAV身体重定向的方法，包括：（a）由处理器确定基于身体固定框架的目标点和视轴之间的距离的视轴角度误差校正值; 和（b）实现UAV机动，其包括将目标点平移到身体固定框架中的重定向目标点的角度角色率分量，以经由偏移角度校正值来保持偏移角度。

    Micro-unmanned aerial vehicle deployment system
    37.
    发明授权
    Micro-unmanned aerial vehicle deployment system 失效
    微型无人机部署系统

    公开(公告)号：US08708285B1

    公开(公告)日：2014-04-29

    申请号：US13004152

    申请日：2011-01-11

    Applicant: Paul J. Carreiro

    Inventor： Paul J. Carreiro

    IPC: B64C13/20

    CPC classification number: B64C39/028 ,  B64C2201/082 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/206 ,  F42B12/60 ,  F42B15/10

    Abstract: A micro-unmanned aerial vehicle deployment system is provided for a cruise missile having submunition compartments. The system includes a vehicle launch module releasable from the cruise missile submunition compartment. The vehicle launch system has a control circuit and at least one micro-unmanned aerial vehicle contained therein. Structure is provided in the launch module for deploying the micro-unmanned aerial vehicle. A separable tether can be joined between the cruise missile and the vehicle launch module that separates when subjected to tension after deployment of the vehicle launch module.

    Abstract translation: 为具有子弹药舱的巡航导弹提供了一种微型无人驾驶飞行器部署系统。 该系统包括可从巡航导弹子弹药室释放的车辆发射模块。 车辆发射系统具有控制电路和其中容纳的至少一个微型无人驾驶飞行器。 在发射模块中提供了用于部署微型无人驾驶飞行器的结构。 可以在巡航导弹和在车辆发射模块部署之后经受张力时分离的车辆发射模块之间连接可分离系绳。

    APPARATUS FOR UNMANNED VEHICLE
    39.
    发明申请
    APPARATUS FOR UNMANNED VEHICLE 审中-公开
    未经规定的车辆的装置

    公开(公告)号：US20130304282A1

    公开(公告)日：2013-11-14

    申请号：US13996812

    申请日：2011-12-14

    Applicant: Kevin William Beggs ,  Richard Descond Joseph Axford

    Inventor： Kevin William Beggs ,  Richard Descond Joseph Axford

    IPC: B64D45/00

    CPC classification number: B64D45/00 ,  B64C2201/121 ,  F42C15/00

    Abstract: An apparatus and a method are disclosed, such as an apparatus wholly or partially mounted on an unmanned vehicle and arranged to act upon a payload, the payload being mounted on the unmanned vehicle and, under an action of the apparatus, being changeable from being in a first state to being in a second state. The method can include: receiving an instruction that the unmanned vehicle, with the payload mounted thereon, is to travel to a location; determining that the payload is in the first state; and responsive to determining that the payload is in the first state: opposing the payload being changed to being in the second state; and providing, for an entity remote from the unmanned vehicle, an indication that the payload is in the first state.

    Abstract translation: 公开了一种装置和方法，例如完全或部分地安装在无人驾驶车辆上并且被布置成作用在有效载荷上的装置，有效负载被安装在无人驾驶车辆上，并且在装置的作用下可以改变为 处于第二状态的第一状态。 该方法可以包括：接收指示，其上安装有有效载荷的无人驾驶车辆将行进到一个位置; 确定有效载荷处于第一状态; 并且响应于确定所述有效载荷处于所述第一状态：将所述有效载荷改变为处于所述第二状态; 以及为远离所述无人驾驶车辆的实体提供所述有效载荷处于所述第一状态的指示。

    Telescoping and sweeping wing that is reconfigurable during flight
    40.
    发明申请
    Telescoping and sweeping wing that is reconfigurable during flight 审中-公开
    在飞行中可重构的伸缩和扫掠翼

    公开(公告)号：US20110001016A1

    公开(公告)日：2011-01-06

    申请号：US12314534

    申请日：2008-12-12

    Applicant: Robert Stewart Skillen ,  Raymond Charles Jones ,  Ross Michael Jones

    Inventor： Robert Stewart Skillen ,  Raymond Charles Jones ,  Ross Michael Jones

    IPC: B64C3/54 ,  B64D37/04

    CPC classification number: B64D37/14 ,  B64C3/40 ,  B64C3/54 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/102 ,  B64C2201/121 ,  B64C2201/127

    Abstract: An aircraft wing includes a stationary root section and a telescoping end section slideable in the span wise direction, where the loads for the root and extendable end sections are carried predominately by the airfoil composite skins, rather than a framework of spars and ribs as in conventional aircraft wings. In a single-telescoping configuration the telescoping end section slides within the root section as it extends and retracts during flight, and in another, the telescoping end section slides over the root section as it extends and retracts during flight. The aircraft wing can also include a second telescoping distal end section, and can sweep back during flight, while the end sections or distal end sections are extended or retracted.

    Abstract translation: 飞行器机翼包括固定的根部段和可在跨度方向上滑动的伸缩端部，其中根部和可延伸的端部的负载主要由翼型复合材料外壳承载，而不是如常规的翼梁和肋骨框架 飞机机翼。 在单伸缩构型中，伸缩端部在飞行过程中延伸和缩回时在根部段内滑动，并且在另一方面，伸缩端部在飞行期间延伸和缩回时滑过根部。 飞行器机翼还可以包括第二伸缩远端部分，并且在飞行期间可以向后扫掠，同时端部部分或远端部分延伸或缩回。

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