中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

277 records (took 0.024 seconds)

    Airship system
    271.
    发明授权
    Airship system 失效
    飞艇系统

    公开(公告)号：US06908061B2

    公开(公告)日：2005-06-21

    申请号：US10877082

    申请日：2004-06-25

    Applicant: Yutaka Akahori

    Inventor： Yutaka Akahori

    IPC: B64B1/06 ,  B64C39/02 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/02 ,  G08G5/00 ,  B64B1/00

    CPC classification number: G08G5/0052 ,  B64B1/06 ,  B64C39/024 ,  B64C2201/022 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/101 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/167 ,  B64F1/18 ,  G01S5/20 ,  G01S5/22 ,  G05D1/0202 ,  G08G5/00 ,  G08G5/0013

    Abstract: An airship system according to the invention has an airship (110), a base station (120), and at least three measurement points. The airship (110) emits ultrasonic waves upon receiving an instruction from the base station (120). Measurement point units (S1-S3) receive the ultrasonic waves, and thereby measure distances from the airship (110) to the respective measurement points. An MPU that is incorporated in the base station (120) calculates a position of the airship (110). The base station (120) controls a route of the airship (110) based on the calculated position by sending a flight instruction to the airship (110). In this manner, an airship system can be provided that makes it unnecessary for an operator to pilot the airship and that can reduce the load weight and the power consumption of the airship.

    Abstract translation: 根据本发明的飞艇系统具有飞艇（110），基站（120）和至少三个测量点。 飞艇（110）在接收到来自基站（120）的指令时发射超声波。 测量点单元（S 1 -S 3）接收超声波，从而测量从飞艇（110）到相应测量点的距离。 并入基站（120）的MPU计算飞艇（110）的位置。 基站（120）通过向飞艇（110）发送飞行指令，基于计算出的位置来控制飞艇（110）的路线。 以这种方式，可以提供一种飞艇系统，使得飞行员不需要飞行飞艇，并且可以减少飞艇的负载重量和功率消耗。

    AIRCRAFT CONTROL METHOD
    272.
    发明申请
    AIRCRAFT CONTROL METHOD 有权
    飞机控制方法

    公开(公告)号：US20050118952A1

    公开(公告)日：2005-06-02

    申请号：US09789450

    申请日：2001-02-20

    Applicant: Earl Cox ,  Kyle Swanson

    Inventor： Earl Cox ,  Kyle Swanson

    IPC: B64C39/00 ,  B64C3/42 ,  B64C3/52 ,  B64C15/02 ,  B64C39/02 ,  B64C39/10 ,  B64D27/24 ,  B64D31/06 ,  G05D1/00 ,  H04B7/185 ,  H04Q7/20

    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 ,  Y02T50/14 ,  Y02T50/44 ,  Y02T50/55 ,  Y02T50/62

    Abstract: This disclosure provides a solar rechargeable aircraft 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 top surface, the aircraft uses only differential thrust of its eight propellers to turn. Each of five segments of the wing has one or more motors and photovoltaic arrays, 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，其生产便宜，是可操纵的，并且几乎可以无限期地保持空中飞行。 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，并且拥有两百英尺的翼展，将光伏电池安装在大部分机翼的顶部表面上，飞机只使用其八个螺旋桨的差动推力来转动。 翼的五个部分中的每一个具有一个或多个电动机和光伏阵列，并且独立于其它部分产生其自身的升降机，以避免加载它们。 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。

    Micro-rotorcraft surveillance system
    273.
    发明申请
    Micro-rotorcraft surveillance system 审中-公开
    微旋翼航空器监控系统

    公开(公告)号：US20050051667A1

    公开(公告)日：2005-03-10

    申请号：US10499530

    申请日：2002-12-19

    Applicant: Paul Arlton ,  David Arlton

    Inventor： Paul Arlton ,  David Arlton

    IPC: B64C27/10 ,  B64C39/02 ,  B64C27/00

    CPC classification number: G08B13/19621 ,  B64C27/10 ,  B64C39/024 ,  B64C39/028 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/201 ,  B64C2201/203 ,  B64C2201/208 ,  G08B13/19619 ,  G08B13/1963

    Abstract: A flying micro-rotorcraft unit (18, 24, 310, 330, 370) is provided for remote tactical and operational missions. The unit (18, 24, 310, 330, 370) includes an elongated body (52) having an upper and a lower end. The body (52) defines a vertical axis (60). The unit (18, 24, 310, 330, 370) further includes a navigation module (54) including means for determining a global position of the elongated body (52) during flight of the unit (18, 24, 310, 330, 370). Rotor means of the unit (18, 24, 310, 330, 370) is coupled to the upper end of the elongated body (52) for generating a thrust force that acts in a direction parallel to the vertical axis (60) to lift the elongated body (52) into the air. The rotor means is located between the elongated body (52) and the navigation module (54).

    Abstract translation: 飞行的微型旋翼航空器（18,24,310,330,370）用于远程战术和作战任务。 单元（18,24,310,330,370）包括具有上端和下端的细长主体（52）。 主体（52）限定垂直轴线（60）。 该单元（18,24,310,330,370）还包括导航模块（54），该导航模块（54）包括用于在单元（18,24,310,330,370）的飞行期间确定细长主体（52）的全局位置的装置 ）。 单元（18,24,310,330,370）的转子装置联接到细长主体（52）的上端，用于产生沿平行于垂直轴线（60）的方向作用的推力，以提升 细长的主体（52）进入空气。 转子装置位于细长主体（52）和导航模块（54）之间。

    Liquid hydrogen aircraft
    275.
    发明申请
    Liquid hydrogen aircraft 审中-公开
    液氢飞机

    公开(公告)号：US20020070312A1

    公开(公告)日：2002-06-13

    申请号：US10073518

    申请日：2002-02-11

    Inventor： Paul B. MacCready ,  Bart D. Hibbs ,  Robert F. Curtin ,  Kyle D. Swanson ,  Paul Belik

    IPC: B64B001/20 ,  B64C001/00 ,  B64C017/00

    CPC classification number: B64D27/24 ,  B64C1/26 ,  B64C3/10 ,  B64C3/14 ,  B64C9/24 ,  B64C39/024 ,  B64C39/10 ,  B64C2201/021 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/165 ,  B64C2201/187 ,  B64D27/02 ,  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 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功率，同时以无阻碍的向下观看的方式支持通信平台。 飞机在翼的前缘包括可延伸的板条，以及反射的后缘。 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。 该飞机还包括被配置为经由燃料电池提供电力的功率模块。 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的燃料的沸腾率。 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。

    Nuclear powered drone
    276.
    发明授权
    Nuclear powered drone 失效
    核动力无人机

    公开(公告)号：US4786008A

    公开(公告)日：1988-11-22

    申请号：US855238

    申请日：1986-04-24

    Applicant: Marshall J. Corbett

    Inventor： Marshall J. Corbett

    IPC: B64C39/02 ,  B64D27/22 ,  B64D27/00

    CPC classification number: B64C39/024 ,  B64D27/22 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/165 ,  Y02T50/44

    Abstract: An unmanned aircraft is equipped with a helium-cooled Brayton cycle nuclear reactor. Heated helium gas drives turbines which in turn rotate propellers to maintain the aircraft aloft for a protracted period of time. After the helium gas expands in the turbines, it is passed through a closed loop including radiator tubes which radiate waste heat from the helium gas to space. The cooled helium gas is returned through the closed loop for repeat of the Brayton cycle.

    Abstract translation: 一架无人驾驶飞机配备有氦冷却的布雷顿循环核反应堆。 加热氦燃气驱动涡轮机，这些涡轮机又旋转螺旋桨，以维持飞机高空飞行的持续时间。 在氦气在涡轮机中膨胀之后，它通过包括散热器管的闭合回路，辐射管将废热从氦气辐射到空间。 冷却的氦气通过闭环返回，重复Brayton循环。

Patent Agency Ranking