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    METHODS AND SYSTEMS FOR CONTROLLING THE PITCH OF A PROPELLER
    151.
    发明申请
    METHODS AND SYSTEMS FOR CONTROLLING THE PITCH OF A PROPELLER 审中-公开
    用于控制螺旋桨的搅拌器的方法和系统

    公开(公告)号：WO2005084373A3

    公开(公告)日：2009-03-26

    申请号：PCT/US2005007035

    申请日：2005-03-03

    Applicant: INSITU GROUP INC ,  DENNIS BRIAN D ,  HILLEN KENNETH

    Inventor： DENNIS BRIAN D ,  HILLEN KENNETH

    IPC: B64C11/44 ,  F03D1/00

    CPC classification number: B64C11/44 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/165

    Abstract: Apparatuses and methods for controlling the motion of a propeller blade are disclosed. In one embodiment, the apparatus can include a first motor that rotates a propeller about a first axis with a first shaft. A first signal transmission portion, fixed relative to the first motor, can transmit signals to a second signal transmission portion that rotates with the first shaft. A second motor can be carried by the first shaft and can receive signals from the second signal transmission portion. The second motor can drive blades of the propeller about a second axis generally transverse to the first axis via a second shaft to vary the pitch of the blades.

    Abstract translation: 公开了用于控制螺旋桨叶片运动的装置和方法。 在一个实施例中，该装置可以包括第一马达，第一马达使螺旋桨围绕第一轴线与第一轴旋转。 相对于第一电动机固定的第一信号传输部分可以将信号发送到与第一轴一起旋转的第二信号传输部分。 第二电动机可以由第一轴承载并且可以从第二信号传输部分接收信号。 第二马达可以通过第二轴驱动螺旋桨的叶片大致横过第一轴线的第二轴线，以改变叶片的桨距。

    AIRCRAFT
    153.
    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。

    RING-WING AIRCRAFT
    155.
    发明申请
    RING-WING AIRCRAFT 审中-公开
    环宁飞机

    公开(公告)号：WO01096179A1

    公开(公告)日：2001-12-20

    申请号：PCT/GB2001/001769

    申请日：2001-04-20

    IPC: B64C39/02 ,  B64C39/06

    CPC classification number: B64C39/062 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/162

    Abstract: This invention relates to ring-wing aircraft and is suited particularly, although not exclusively, to use in micro-unmanned air vehicles (UAV's) with ring-wings. An aircraft (10) according to the invention comprises a ring-wing (11) defining a duct (16) with a longitudinally-extending central axis (31), propulsion means (15) located within the duct and moveable aerofoils (13, 18) for controlling the aircraft in flight, the ring-wing being truncated obliquely at one end, that end being the rear (11b) when in horizontal flight, to form a ring-wing with opposed sides of unequal length. This arrangement produces centre of mass offset from the central axis of the ring-wing, the pendulum effect will ensure that the aircraft will roll so that its centre of mass will always be at the lowest height possible when the aircraft is airborne. Therefore the aircraft has a preferred orientation, and the control surfaces can be oriented with respect to this preferred orientation. In addition, the oblique truncation at the rear keeps the centre of mass towards the front of the aircraft thereby giving improved stability in all three axes.

    Abstract translation: 本发明涉及环翼飞机，并且特别适用于具有环形翼的微型无人驾驶飞行器（UAV），尽管不是排他地。 根据本发明的飞机（10）包括限定具有纵向延伸的中心轴线（31）的管道（16）的环形翼（11），位于管道内的推进装置（15）和可移动的机翼（13,18） ）用于控制飞行中的飞行器，环形翼在一端倾斜地截取，当水平飞行时，该端部是后部（11b），以形成具有不相等长度的相对侧的环形翼。 这种布置产生的偏心距离环形翼的中心轴线，摆锤效应将确保飞机将滚动，使其质心总是在飞机空降时始终处于最低的高度。 因此，飞行器具有优选的定向，并且控制表面可以相对于该优选取向被定向。 此外，后方的倾斜截面使质心朝向飞机的前方，从而提高了所有三个轴线的稳定性。

    MICROWAVE-POWERED AIRCRAFT
    157.
    发明申请
    MICROWAVE-POWERED AIRCRAFT 审中-公开
    微型飞机

    公开(公告)号：WO1995011828A1

    公开(公告)日：1995-05-04

    申请号：PCT/US1994011775

    申请日：1994-10-17

    Applicant: SKYSAT COMMUNICATIONS NETWORK CORPORATION

    Inventor： SKYSAT COMMUNICATIONS NETWORK CORPORATION ,  FOOTE, Howard, A.

    IPC: B64C03/10

    CPC classification number: G05D1/0038 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/042 ,  B64C2201/122 ,  B64C2201/165 ,  B64D27/24 ,  H01Q1/248 ,  Y02T50/44 ,  Y02T50/64 ,  Y10S320/33

    Abstract: An unmanned, remotely controlled microwave-powered aircraft (26) for use as a stationary communications platform. The aircraft (26) is generally a flying wing with a large, flat inner wing (50) having a rectenna (58) on the underside. Rectennas may also be provided on the underside of the wings (52), the combined output from the rectenna being used to provide power to two eletric motors (74) housed within torpedo-shaped nacelles (28) which drive two rear propellers (30). The rectenna (58) converts a microwave signal at 35 GHz generated by a ground power station (20) utilizing dual gyrotrons and a 34-meter diameter antenna dish (22). The aircraft (26) has a preferred airfoil cross section throughout and is constructed of lightweight but strong materials in order to provide an enhanced flying time of several months. A power management and distribution system manages the DC power produced by the rectenna (58) to supply power to the flight controls, propulsion system and payload.

    Abstract translation: 一种无人遥控的微波动力飞机（26），用作固定通信平台。 飞机（26）通常是具有在下侧具有整流天线（58）的大的平坦内翼（50）的飞翼。 也可以在翼（52）的下侧设置整流器，来自整流天线的组合输出用于向容纳在鱼雷形发动机舱（28）内的两个驱动两个后部螺旋桨（30）的电动机（74）供电， 。 整流天线（58）利用双回旋加速器和直径34米的天线盘（22）转换由地面电站（20）产生的35GHz的微波信号。 飞机（26）在整个中具有优选的翼型横截面，并且由轻质但坚固的材料构成，以便提供几个月的增强的飞行时间。 电力管理和分配系统管理由天线（58）产生的直流电力，为飞行控制，推进系统和有效载荷提供动力。

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