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    Aerodynamically stable, VTOL aircraft
    2.
    发明授权
    Aerodynamically stable, VTOL aircraft 失效
    空中动力学稳定，垂直起降飞机

    公开(公告)号：US07249732B2

    公开(公告)日：2007-07-31

    申请号：US11379963

    申请日：2006-04-24

    申请人： John K. Sanders, Jr. ,  J. Kenneth Sanders ,  Arturo Aviles, Jr.

    发明人： John K. Sanders, Jr. ,  J. Kenneth Sanders ,  Arturo Aviles, Jr.

    IPC分类号： B64C15/00

    CPC分类号： B64C39/024 ,  B64C27/12 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/127

    摘要： A hover aircraft employs an air impeller engine having an air channel duct and a rotor with outer ends of its blades fixed to an annular impeller disk that is driven by magnetic induction elements arrayed in the air channel duct. The air-impeller engine is arranged vertically in the aircraft frame to provide vertical thrust for vertical takeoff and landing. Preferably, the air-impeller engine employs dual, coaxial, contra-rotating rotors for increased thrust and gyroscopic stability. An air vane assembly directs a portion of the air thrust output at a desired angle to provide a horizontal thrust component for flight maneuvering or translation movement. The aircraft can employ a single engine in an annular fuselage, two engines on a longitudinal fuselage chassis, three engines in a triangular arrangement for forward flight stability, or other multiple engine arrangements in a symmetric, balanced configuration. Other flight control mechanisms may be employed, including side winglets, an overhead wing, and/or air rudders or flaps. An integrated flight control system can be used to operate the various flight control mechanisms. Electric power is supplied to the magnetic induction drives by high-capacity lightweight batteries or fuel cells. The hover aircraft is especially well suited for applications requiring VTOL deployment, hover operation for quiet surveillance, maneuvering in close air spaces, and long duration flights for continuous surveillance of ground targets and important facilities requiring constant monitoring.

    摘要翻译： 悬停飞行器采用具有空气通道管道的空气叶轮发动机和其叶片的外端固定到环形叶轮盘的转子，其由排列在空气通道管道中的磁感应元件驱动。 空气叶轮发动机垂直布置在飞机框架中，以提供用于垂直起飞和着陆的垂直推力。 优选地，空气叶轮发动机采用双重同轴的反转转子，以提高推力和陀螺稳定性。 空气叶片组件将一部分空气推力输出引导到期望的角度，以提供用于飞行机动或平移运动的水平推力分量。 飞机可以在环形机身中使用单个发动机，在纵向机身底盘上使用两个发动机，三个发动机以三角形布置用于向前飞行稳定性，或以对称平衡配置的其它多个发动机装置。 可以采用其他飞行控制机构，包括侧翼，顶部翼和/或空气方向舵或翼。 集成的飞行控制系统可用于操作各种飞行控制机构。 电力通过大容量轻型电池或燃料电池供应给磁感应驱动器。 悬停式飞机特别适用于需要垂直起落架的部署，悬停操作，可进行安静的监视，在空中空间中进行机动操作，以及长时间飞行，以持续监视地面目标和需要持续监控的重要设施。

    Quiet vertical takeoff and landing aircraft using ducted, magnetic induction air-impeller rotors
    3.
    发明授权
    Quiet vertical takeoff and landing aircraft using ducted, magnetic induction air-impeller rotors 失效
    安静的垂直起飞和着陆飞机使用导管的磁感应空气叶轮转子

    公开(公告)号：US07032861B2

    公开(公告)日：2006-04-25

    申请号：US10763973

    申请日：2004-01-22

    申请人： John K. Sanders, Jr. ,  J. Kenneth Sanders ,  Arturo Aviles, Jr. ,  Arturo F. Aviles

    发明人： John K. Sanders, Jr. ,  J. Kenneth Sanders ,  Arturo Aviles, Jr. ,  Arturo F. Aviles

    IPC分类号： B64C15/00

    CPC分类号： B64C39/024 ,  B64C27/12 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/127

    摘要： A hover aircraft employs an air impeller engine having an air channel duct and a rotor with outer ends of its blades fixed to an annular impeller disk that is driven by magnetic induction elements arrayed in the air channel duct. The air-impeller engine is arranged vertically in the aircraft frame to provide vertical thrust for vertical takeoff and landing. Preferably, the air-impeller engine employs dual, coaxial, contra-rotating rotors for increased thrust and gyroscopic stability. An air vane assembly directs a portion of the air thrust output at a desired angle to provide a horizontal thrust component for flight maneuvering or translation movement. The aircraft can employ a single engine in an annular fuselage, two engines on a longitudinal fuselage chassis, three engines in a triangular arrangement for forward flight stability, or other multiple engine arrangements in a symmetric, balanced configuration. Other flight control mechanisms may be employed, including side winglets, an overhead wing, and/or air rudders or flaps. An integrated flight control system can be used to operate the various flight control mechanisms. Electric power is supplied to the magnetic induction drives by high-capacity lightweight batteries or fuel cells. The hover aircraft is especially well suited for applications requiring VTOL deployment, hover operation for quiet surveillance, maneuvering in close air spaces, and long duration flights for continuous surveillance of ground targets and important facilities requiring constant monitoring.

    摘要翻译： 悬停飞行器采用具有空气通道管道的空气叶轮发动机和其叶片的外端固定到环形叶轮盘的转子，其由排列在空气通道管道中的磁感应元件驱动。 空气叶轮发动机垂直布置在飞机框架中，以提供用于垂直起飞和着陆的垂直推力。 优选地，空气叶轮发动机采用双重同轴的反转转子，以提高推力和陀螺稳定性。 空气叶片组件将一部分空气推力输出引导到期望的角度，以提供用于飞行机动或平移运动的水平推力分量。 飞机可以在环形机身中使用单个发动机，在纵向机身底盘上使用两个发动机，三个发动机以三角形布置用于向前飞行稳定性，或以对称平衡配置的其它多个发动机装置。 可以采用其他飞行控制机构，包括侧翼，顶部翼和/或空气方向舵或翼。 集成的飞行控制系统可用于操作各种飞行控制机构。 电力通过大容量轻型电池或燃料电池供应给磁感应驱动器。 悬停式飞机特别适用于需要垂直起落架的部署，悬停操作，可进行安静的监视，在空中空间中进行机动操作，以及长时间飞行，以持续监视地面目标和需要持续监控的重要设施。

    Personal renewable-energy fueling and storage station for electric-powered vehicles
    4.
    发明授权
    Personal renewable-energy fueling and storage station for electric-powered vehicles 失效
    用于电动车辆的个人可再生能源加油和储存站

    公开(公告)号：US07248018B2

    公开(公告)日：2007-07-24

    申请号：US11110094

    申请日：2005-04-19

    申请人： John K. Sanders, Jr. ,  J. Kenneth Sanders ,  Jeffrey Sanders

    发明人： John K. Sanders, Jr. ,  J. Kenneth Sanders ,  Jeffrey Sanders

    IPC分类号： H02J7/00

    CPC分类号： B60L11/1824 ,  B60L8/00 ,  B60L8/003 ,  B60L11/1816 ,  B60L11/1842 ,  B60L2200/26 ,  B60L2230/22 ,  B60S5/02 ,  B62D31/003 ,  E04H5/02 ,  H01M2250/20 ,  H02J7/355 ,  H02S30/20 ,  H02S40/38 ,  Y02E60/721 ,  Y02T10/7083 ,  Y02T10/7094 ,  Y02T90/121 ,  Y02T90/128 ,  Y02T90/14 ,  Y02T90/163 ,  Y02T90/32 ,  Y04S10/126

    摘要： A personal refueling station for a personal-sized electric vehicle has a polygonal base structure housing a refueling system and a plurality of flat panels hinged thereto which open to form a flat surface and close up to an upright pyramid for storage. The flat panels have solar PV arrays mounted on their inside surfaces which generate electricity from sunlight in the open position. The electricity is used to generate hydrogen for hydrogen-fuel-cell vehicles, or is stored for recharging non-hydrogen electric vehicles. Alternatively, hydrogen or electricity may be provided from an external renewable power source. The station can also have utility hookups to provide excess hydrogen or electricity to an external energy usage, such as a home, business, or other station. The personal refueling station has a compact design that can be installed at home or business locations. It is designed to accommodate a personal-use electric vehicle such as an electric car or cart or a personal VTOL hovercraft. It can be used in a stationary location or transported for remote use, as well as operated by remote control.

    摘要翻译： 用于个人电动车辆的个人加油站具有容纳加油系统的多边形基座结构和与其铰接的多个平板，其打开以形成平坦表面并且靠近直立金字塔以用于存储。 平板有安装在其内表面的太阳能光伏阵列，其中阳光从打开位置产生电力。 电用于生成用于氢燃料电池车辆的氢气，或者用于对非氢电动车辆进行再充电。 或者，可以从外部可再生电源提供氢或电。 该站还可以具有公用事业连接，以向外部能源使用提供过量的氢气或电力，例如家庭，商业或其他车站。 个人加油站具有紧凑的设计，可以安装在家庭或商业场所。 它设计用于容纳个人使用的电动车辆，例如电动汽车或推车或个人VTOL气垫船。 它可以在一个固定的位置使用或运输远程使用，也可以通过遥控器操作。