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    Unmanned vehicle
    43.
    发明申请
    Unmanned vehicle 有权
    无人车

    公开(公告)号：US20060074557A1

    公开(公告)日：2006-04-06

    申请号：US11011001

    申请日：2004-12-13

    Applicant: Anthony Mulligan ,  Christopher Troudt ,  Jason Michael Douglas

    Inventor： Anthony Mulligan ,  Christopher Troudt ,  Jason Michael Douglas

    IPC: G01C21/26

    CPC classification number: G05D1/0094 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/044 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/205 ,  B64C2201/208

    Abstract: Methods and apparatuses provide surveillance of a convoy. At least one unmanned aerial vehicle (UAV) obtains images around the convoy's position to provide information about potential hostile activity while the UAV follows a generally curvilinear path around the convoy as instructed by one of the convoy vehicles. Path planner algorithm software is executed by the controlling convoy vehicle in which position and velocity information regarding the unmanned aerial vehicle and the convoy are processed to determine values of control variables. The determined values are sent to the unmanned aerial vehicle over a wireless communications channel. The path of the surveillance vehicle may be changed in order to provide evasive measures to avoid an attack on the surveillance vehicle by an adversary.

    Abstract translation: 方法和设备对车队进行监视。 至少一架无人驾驶飞行器（UAV）获取围绕车队位置的图像，以提供关于潜在敌对行为的信息，而无人机按照车队车辆指示的方式沿着车队周围的大致曲线路径。 路径规划器算法软件由控制车队车辆执行，其中处理关于无人机和车队的位置和速度信息以确定控制变量的值。 所确定的值通过无线通信信道发送到无人驾驶飞行器。 监视车辆的路径可能会改变，以便提供回避措施，以避免对手对监控车辆的攻击。

    In-flight loadable and refuelable unmanned aircraft system for continuous flight
    45.
    发明申请
    In-flight loadable and refuelable unmanned aircraft system for continuous flight 失效
    用于连续飞行的飞行中可加载和可加油的无人驾驶飞机系统

    公开(公告)号：US20020074454A1

    公开(公告)日：2002-06-20

    申请号：US09738227

    申请日：2000-12-15

    Inventor： J. Kirston Henderson

    IPC: B64D037/00

    CPC classification number: B64C39/024 ,  B64C2201/082 ,  B64C2201/104 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/146 ,  B64D5/00 ,  B64D39/00

    Abstract: A method for refueling and reloading an unmanned aircraft for continuous flight is disclosed herein wherein the unmanned aircraft is maintained and supported by a support aircraft. Both aircraft maintain cargo bays and in-flight operable doors located on the underside of each aircraft for the purposes of docking and exchanging goods. Preferably the goods comprise loadable cartridges and may contain such items as weapons, cargo, or fuel for example. In one embodiment, when both aircraft are in a docked configuration for exchange of goods during flight, the in-flight operable doors open and the support aircraft is capable of loading such cartridges aboard the unmanned aircraft. When necessary the support aircraft may load gear for the purposes of landing the unmanned aircraft. Alternate methods of reloading an unmanned aircraft for continuous flight is disclosed wherein the unmanned aircraft does not have cargo bay doors and the aircraft is supported by a support aircraft.

    Abstract translation: 本文公开了一种用于加油和重新加载用于连续飞行的无人驾驶飞行器的方法，其中无人飞行器由支撑飞行器维护和支撑。 两架飞机都保持位于每架飞机下侧的货舱和飞行中可操作的门，以便对接和交换货物。 优选地，货物包括可装载的盒，并且可以包含诸如武器，货物或燃料的物品。 在一个实施例中，当两架飞机处于用于在飞行中交换货物的对接配置时，飞行中可操作的门打开，并且支撑飞机能够在无人驾驶飞机上装载这样的卡盘。 必要时，支援飞机可以为无人机着陆而装载装备。 公开了重新装载用于连续飞行的无人飞行器的替代方法，其中无人驾驶飞机没有货舱并且飞机由支撑飞机支撑。

    Transformable gun launched aero vehicle
    46.
    发明授权
    Transformable gun launched aero vehicle 有权
    可变形枪发射航空车

    公开(公告)号：US06260797B1

    公开(公告)日：2001-07-17

    申请号：US09229599

    申请日：1999-01-13

    Applicant: Miles R. Palmer

    Inventor： Miles R. Palmer

    IPC: B64C356

    CPC classification number: F42B15/00 ,  B64C39/024 ,  B64C2201/044 ,  B64C2201/084 ,  B64C2201/088 ,  B64C2201/105 ,  B64C2201/121 ,  B64C2201/126 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/205 ,  B64D1/22 ,  B64D37/04 ,  B64D37/06 ,  B64D37/12 ,  B64D39/00

    Abstract: A transformable gun launched aero vehicle having a ballistic projectile configuration and an aeroplane configuration includes a cylinder forming a shell of the vehicle in the ballistic projectile configuration and wings deployable from the cylinder. The wings are capable of achieving sufficient lift for sustained flight in the aeroplane configuration. The cylinder forms a fuselage of the vehicle in the aeroplane configuration. A wing includes plural rib elements, plural inflatable tubes where each tube is braced by the plural rib elements, and a wind shell disposed around the plural inflatable tubes and the plural rib elements. The vehicle includes an inflatable tail section that is inflated while the vehicle is in the aeroplane configuration. The vehicle includes a parachute that is reversibly deployable from a nose portion of the vehicle. The vehicle includes at least one landing rod. Each landing rod is reversibly extendable from the vehicle. A landing controller controls a first landing rod to extend after the vehicle has begun to vertically descend. The vehicle includes a folding propeller deployable from the fuselage in the aeroplane configuration. The vehicle includes a control system, and the control system includes a module to determine when the vehicle has reached a first predetermined state that defines an initiation of a transition from the ballistic projectile configuration to the aeroplane configuration.

    Abstract translation: 可变形枪发射具有弹道射弹配置的航空车辆，并且飞机配置包括形成弹道射出构造的车辆壳体的气缸和从气缸展开的翼。 机翼能够在飞机配置中实现足够的升力以持续飞行。 汽缸在飞机配置中形成车辆的机身。 翼包括多个肋元件，多个可充气管，其中每个管由多个肋元件支撑，以及设置在多个可充气管和多个肋元件周围的风壳。 车辆包括在车辆处于飞机配置中时充气的可充气尾部。 车辆包括可从车辆的鼻部部分可逆地展开的降落伞。 车辆包括至少一个着陆杆。 每个着陆杆可从车辆可逆地延伸。 着陆控制器控制第一着陆杆在车辆开始垂直下降之后延伸。 该车辆包括在飞机配置中可从机身部署的折叠螺旋桨。 车辆包括控制系统，并且控制系统包括用于确定车辆何时已经达到第一预定状态的模块，该第一预定状态定义了从弹道射弹配置到飞机配置的转变的开始。

    Method of reducing a nose-up pitching moment on a ducted unmanned aerial vehicle
    47.
    发明授权
    Method of reducing a nose-up pitching moment on a ducted unmanned aerial vehicle 失效
    减少管道式无人驾驶飞行器上的起搏俯仰力矩的方法

    公开(公告)号：US06170778B2

    公开(公告)日：2001-01-09

    申请号：US09296716

    申请日：1999-04-22

    Applicant: James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

    Inventor： James P. Cycon ,  Mark Winfield Scott ,  Christopher W. DeWitt

    IPC: B64C2730

    CPC classification number: B64C27/20 ,  B64C27/10 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165

    Abstract: A method for reducing a nose-up pitching moment in an unmanned aerial vehicle during forward flight. The unmanned aerial vehicle includes counter-rotating rotor assemblies that are mounted within a duct. Each rotor assembly includes a plurality of rotor blades. The method involves adjusting the rotor blades to have substantially zero pitch. Then rotating the rotor assemblies to produce a virtual plane across the duct. The virtual plane is operative for substantially deflecting air passing over the fuselage away from the duct. In one embodiment of the invention, the method involves the further step of obstructing at least a portion of the bottom of the duct to inhibit air that is flowing across the bottom of the duct from passing into the duct.

    Abstract translation: 一种用于在远程飞行期间减少无人驾驶飞行器中的起搏俯仰力矩的方法。 无人驾驶飞行器包括安装在管道内的反向旋转转子组件。 每个转子组件包括多个转子叶片。 该方法包括调整转子叶片以使其基本上为零。 然后旋转转子组件以在管道上产生虚拟平面。 虚拟平面可操作用于使穿过机身的空气基本上偏转远离管道。 在本发明的一个实施例中，该方法包括阻碍管道底部的至少一部分的进一步的步骤，以阻止流过管道底部的空气进入管道。

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