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    HYDROGEN POWERED AIRCRAFT
    1.
    发明申请
    HYDROGEN POWERED AIRCRAFT 审中-公开
    氢动力飞机

    公开(公告)号：WO2005084156A3

    公开(公告)日：2006-02-16

    申请号：PCT/US2004019746

    申请日：2004-06-21

    Applicant: AEROVIRONMENT INC

    Inventor： MACCREADY PAUL B ,  HIBBS BART D ,  SWANSON KYLE D ,  CURTIN ROBERT F

    IPC: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/02 ,  B64C39/10 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  B64D27/00

    CPC classification number: B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  B64D27/24 ,  B64D37/30 ,  B64D2041/005 ,  Y02T50/12 ,  Y02T50/32 ,  Y02T50/44 ,  Y02T50/64 ,  Y02T90/36

    Abstract: Disclosed is an aircraft, configured to have a wide range of flight speeds, consuming low levels of power for an extended period of time, while supporting a communications platform with an unobstructed downward-looking view. The aircraft includes an extendable slat at the leading edge of the wing, and a reflexed trailing edge. The aircraft comprises a flying wing extending laterally between two ends and a center point. The wing is swept and has a relatively constant chord. The aircraft also includes a power module configured to provide power via a fuel cell. The fuel cell stores liquid hydrogen as fuel, but uses gaseous hydrogen in the fuel cell. A fuel tank heater is used to control the boil-rate of the fuel in the fuel tank. The fuel cell compresses ambient air for an oxidizer, and operates with the fuel and oxidizer at pressures below one atmosphere. The aircraft of the invention includes a support structure including a plurality of supports, where the supports form a tetrahedron that affixes to the wing.

    Abstract translation: 公开了一种被配置为具有宽范围的飞行速度的飞机，在延长的时间段内消耗低水平的电力，同时以无阻碍的向下观看的方式支持通信平台。 飞机在机翼的前缘包括一个可延伸的板条，以及一个反光后缘。 飞机包括在两端之间横向延伸的飞翼和中心点。 机翼被扫掠并具有相对恒定的和弦。 飞机还包括被配置为经由燃料电池提供动力的功率模块。 燃料电池将液态氢作为燃料储存，而在燃料电池中使用气态氢。 燃料箱加热器用于控制燃料箱中燃料的沸腾率。 燃料电池压缩氧化剂的环境空气，并在低于一个大气压的燃料和氧化剂下操作。 本发明的飞行器包括支撑结构，该支撑结构包括多个支撑件，其中支撑件形成固定在机翼上的四面体。

    CLOSED LOOP ENERGY STORAGE SYSTEM
    2.
    发明申请
    CLOSED LOOP ENERGY STORAGE SYSTEM 审中-公开
    闭环能源储存系统

    公开(公告)号：WO2004015796A3

    公开(公告)日：2004-11-11

    申请号：PCT/US0312147

    申请日：2003-04-17

    Applicant: AEROVIRONMENT INC

    Inventor： HIBBS BART D ,  PARKS WILLIAM H ,  VELEV OMOURTAG A

    IPC: B64C3/14 ,  B64D27/02 ,  C25B1/00 ,  C25B1/04 ,  H01M8/00 ,  H01M8/02 ,  H01M8/04 ,  H01M8/06 ,  H01M8/18

    CPC classification number: B64D27/24 ,  B64C2201/042 ,  B64D2041/005 ,  B64D2211/00 ,  H01M8/04097 ,  H01M8/04164 ,  H01M8/04373 ,  H01M8/04768 ,  H01M8/0656 ,  H01M8/186 ,  Y02E60/368 ,  Y02E60/528 ,  Y02P20/134 ,  Y02T50/44 ,  Y02T50/62 ,  Y02T50/69 ,  Y02T90/36

    Abstract: A closed loop energy storage system configured with a hydrogen tank, an oxygen tank, a fuel cell stack and an electrolyzer. A heat exchanger freeze-dries the hydrogen and oxygen prior to their storage in their respective tanks. The heat exchanger also uses excess fuel cell heat to preheat streams of hydrogen and oxygen coming from the tanks. Phase separators serve both to separate water from hydrogen and oxygen, and to store the water. A thermal management system encloses all the system components except the tanks. An airfoil-shaped shell covers the system, and the larger of the two tanks extends substantially across the shell at its point of greatest camber thickness. The tanks are composed of polymer liners integral with composite shells.

    Abstract translation: 一种闭环储能系统，其配置有氢罐，氧气罐，燃料电池堆和电解槽。 热交换器在将氢气和氧气储存在各自的储罐中之前将其冷冻干燥。 热交换器还使用过量的燃料电池热来预热来自罐的氢气和氧气流。 相分离器用于将水与氢气和氧气分开，并储存水分。 一个热管理系统包含除油箱外的所有系统部件。 翼型壳体覆盖系统，并且两个坦克中的较大的壳体在其最大外倾厚度的点处基本上延伸穿过壳体。 这些罐由聚合物衬垫组成，与复合壳一体。

    AIRCRAFT
    3.
    发明申请
    AIRCRAFT 审中-公开
    飞机

    公开(公告)号：WO0158756A9

    公开(公告)日：2002-10-31

    申请号：PCT/US0104378

    申请日：2001-02-07

    Applicant: AEROVIRONMENT INC

    Inventor： MACCREADY PAUL ,  HIBBS BART D ,  COX EARL C ,  LISOSKI DEREK L ,  KENDALL GREG T

    IPC: B64C39/00 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/02 ,  B64C39/10 ,  B64D27/24 ,  B64D31/06 ,  G05D1/00 ,  H04B7/185

    CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/145 ,  Y02T50/44 ,  Y02T50/62 ,  Y02T50/69

    Abstract: This disclosure provides a solar rechargeable aircraft (10) that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Traveling at relatively slow speeds, and having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's (12) top surface (42), the aircraft uses only differential thrust of its propellers (16) to turn. Each segment of the wing has one or more motors (14) and photovoltaic arrays (32), and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface. The aircraft includes hinges and actuators capable of providing an adjustable dihedral for the wing. The actuators can be motors or control surfaces. Alternately, the actuators can be movable masses within the wing, which may be capable of deforming the wing to alter the aerodynamics of the wing, and thereby actuate the hinges. Because of wing dihedral, the aircraft includes motors both above and below the center of drag, and the aircraft uses differential thrust to control aircraft pitch. The aircraft has a wide variety of applications, which include serving as a long term high altitude platform that serves to link a ground station using radio wave signals and a satellite using optical signals.

    Abstract translation: 本公开提供了一种太阳能可再充电飞机（10），其生产便宜，是可操纵的，并且可以几乎无限期地保持机载。 首选飞机是一个装有跨距的飞翼，没有机身或方向舵。 以相对较慢的速度行驶，并且在大部分机翼（12）顶面（42）上安装有二百英尺翼展，该飞机仅使用其推进器（16）的差动推力来转动。 机翼的每个部分具有一个或多个电动机（14）和光伏阵列（32），并且独立于其它部分产生其自身的电梯，以避免装载它们。 五个双面光伏阵列总体上安装在机翼上，并且接收能量入射到机翼的顶部并且从下方入射的光能通过底部的透明表面。 飞机包括铰链和致动器，能够为机翼提供可调节的二面体。 执行器可以是电机或控制面。 或者，致动器可以是机翼内的可移动质量块，其可以使机翼变形以改变机翼的空气动力学，从而致动铰链。 由于机翼二面体，飞机包括在阻力中心上方和下方的电机，飞机使用差速推力来控制飞机俯仰。 该飞机具有广泛的应用，其中包括作为长期高空平台，用于使用无线电波信号连接地面站和使用光信号的卫星。

    HIGH ALTITUDE PLATFORM DEPLOYMENT SYSTEM
    6.
    发明申请
    HIGH ALTITUDE PLATFORM DEPLOYMENT SYSTEM 审中-公开
    高海拔平台部署系统

    公开(公告)号：WO2004004157A3

    公开(公告)日：2004-03-25

    申请号：PCT/US0312138

    申请日：2003-04-17

    Applicant: AEROVIRONMENT INC

    Inventor： HIBBS BART D ,  COX EARL C

    IPC: H04B7/185

    CPC classification number: H04B7/18504

    Abstract: A communication system for supporting communications with a target market area. The system includes one or more solar-powered aircraft maintained in, or successively passing through, flight stations or flight patterns around the market area. Each of the aircraft targets limited beamwidth communication antennas on a substantial portion of the target market area. The control system is configured to fly selective flight patterns depending on the aircraft characteristics and the flight conditions. The flight patterns may emphasize high-power-generation patterns such as flying away from the sun for aircraft with wing-mounted solar cells.

    Abstract translation: 支持与目标市场区域通信的通信系统。 该系统包括一个或多个太阳能飞机，该飞机维持在市场区域周围的飞行站或飞行模式中，或依次通过该飞行器。 每个飞机在目标市场区域的大部分目标上都有限的波束宽度通信天线。 控制系统配置为根据飞机特性和飞行条件飞行选择性飞行模式。 飞行模式可能会强调高功率发电模式，例如带有翼型太阳能电池的飞机从太阳飞出。

    AIRCRAFT
    7.
    发明申请
    AIRCRAFT 审中-公开
    飞机

    公开(公告)号：WO0158756A3

    公开(公告)日：2002-01-03

    申请号：PCT/US0104378

    申请日：2001-02-07

    Applicant: AEROVIRONMENT INC

    Inventor： MACCREADY PAUL ,  HIBBS BART D ,  COX EARL C ,  LISOSKI DEREK L ,  KENDALL GREG T

    IPC: B64C39/00 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/02 ,  B64C39/10 ,  B64D27/24 ,  B64D31/06 ,  G05D1/00 ,  H04B7/185

    CPC classification number: B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/102 ,  B64C2201/122 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/165 ,  B64D27/24 ,  B64D31/06 ,  B64D2211/00 ,  G05D1/0022 ,  G05D1/0077 ,  H04B7/18504 ,  Y02T50/12 ,  Y02T50/145 ,  Y02T50/44 ,  Y02T50/62 ,  Y02T50/69

    Abstract: This disclosure provides a solar rechargeable aircraft (10) that is inexpensive to produce, is steerable, and can remain airborne almost indefinitely. The preferred aircraft is a span-loaded flying wing, having no fuselage or rudder. Traveling at relatively slow speeds, and having a two-hundred foot wingspan that mounts photovoltaic cells on most all of the wing's (12) top surface (42), the aircraft uses only differential thrust of its propellers (16) to turn. Each segment of the wing has one or more motors (14) and photovoltaic arrays (32), and produces its own lift independent of the other segments, to avoid loading them. Five two-sided photovoltaic arrays, in all, are mounted on the wing, and receive photovoltaic energy both incident on top of the wing, and which is incident also from below, through a bottom, transparent surface. The aircraft includes hinges and actuators capable of providing an adjustable dihedral for the wing. The actuators can be motors or control surfaces. Alternately, the actuators can be movable masses within the wing, which may be capable of deforming the wing to alter the aerodynamics of the wing, and thereby actuate the hinges. Because of wing dihedral, the aircraft includes motors both above and below the center of drag, and the aircraft uses differential thrust to control aircraft pitch. The aircraft has a wide variety of applications, which include serving as a long term high altitude platform that serves to link a ground station using radio wave signals and a satellite using optical signals.

    Abstract translation: 本公开提供了一种太阳能可再充电的飞机（10），其生产成本低，可操纵且可以几乎无限期地保持在空中。 首选的飞机是跨越式飞行机翼，没有机身或方向舵。 以相对较低的速度行驶，并且具有将光伏电池安装在大部分机翼（12）顶部表面（42）上的二百英尺翼展，飞机仅使用其推进器（16）的差动推力旋转。 机翼的每个部分都有一个或多个马达（14）和光伏阵列（32），并且独立于其他部分生成自己的升力，以避免加载它们。 总共五个双面光伏阵列安装在机翼上，并且接收入射在机翼顶部并且也从下面入射的光伏能量，通过底部透明表面。 该飞机包括能够为机翼提供可调整的二面角的铰链和致动器。 执行器可以是电机或控制面。 或者，致动器可以是机翼内的可移动质量块，其可以使机翼变形以改变机翼的空气动力学，并由此致动铰链。 由于机翼的二面角，该机包括在阻力中心上方和下方的电机，并且该机使用差速推力来控制飞机俯仰。 该飞机有多种应用，其中包括作为一个长期的高空平台，用于连接使用无线电波信号的地面站和使用光信号的卫星。

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