中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

277 records (took 0.022 seconds)

    Aircraft
    201.
    发明申请
    Aircraft 有权
    飞机

    公开(公告)号：US20110031354A1

    公开(公告)日：2011-02-10

    申请号：US12847004

    申请日：2010-07-30

    Applicant: Christopher Charles Kelleher

    Inventor： Christopher Charles Kelleher

    IPC: B64C3/00

    CPC classification number: B64C39/024 ,  B64C23/069 ,  B64C23/076 ,  B64C2201/021 ,  B64C2201/126 ,  Y02T50/164

    Abstract: An aircraft, particularly a solar powered, high altitude, long endurance, unmanned aerial vehicle, is equipped with a combination of canted down, raked back wing tips and trailing “tip tails” carried on booms from the tip regions of the mainplane. Each tip tail is positioned to be subject to the upwash field of the respective wing tip vortex, at least in the cruise condition of the aircraft. The wing tip form can achieve a reduction in induced drag and help to relieve wing root bending moment while the tip tails can act through their connections to the mainplane to provide torsional relief to the latter, particularly under lower incidence/higher speed conditions. In the higher incidence/lower speed cruise condition, however, the presence of the tip tails in the upwash fields of the wing tip vortices means that they can generate lift with a component in the forward direction of flight and hence contribute to the thrust requirements of the aircraft.

    Abstract translation: 飞机，特别是太阳能，高空，长寿命，无人驾驶飞行器，配备有从主板的尖端区域承载在吊杆上的倾斜下倾斜后翼翼尖和尾部“尖端尾”的组合。 至少在飞行器的巡航条件下，每个末梢尾部定位成受到相应的翼尖涡流的上洗液场的影响。 翼尖形式可以实现诱导阻力的减小，并且有助于减轻翼根弯曲力矩，同时尖端尾部可以通过它们与主平面的连接而起作用，以向后者提供扭转释放，特别是在较低的入射/更高速度条件下。 然而，在较高的发生率/较低速度的巡航条件下，翼尖涡流的上冲流场中尖端尾部的存在意味着它们可以在飞行方向上产生具有部件的升力，因此有助于推力要求 飞机。

    Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV)
    204.
    发明授权
    Autonomous, back-packable computer-controlled breakaway unmanned aerial vehicle (UAV) 失效
    自主的，可回填计算机控制的无人机（UAV）

    公开(公告)号：US07237750B2

    公开(公告)日：2007-07-03

    申请号：US10976153

    申请日：2004-10-29

    Applicant: Tien Seng Chiu ,  Jay Willmott

    Inventor： Tien Seng Chiu ,  Jay Willmott

    IPC: B64C1/00

    CPC classification number: B64C1/00 ,  A45C5/00 ,  A45C13/02 ,  B64C1/30 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/084 ,  B64C2201/102 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2201/201 ,  B64C2201/203

    Abstract: A modular unmanned aerial vehicle (UAV) having a fuselage, a nose cone, a left wing piece, a right wing piece, and a tail section. The tail section and nose cone each join to the fuselage through mating bulkhead structures that provide quick connection capability while being readily separated so as to enable the UAV to break apart at these connection points and thereby absorb or dissipate impact upon landing. The UAV is capable of rapid assembly in the field for two-man launch and data retrieval, as well as quick disassembly into these five component parts for transport and storage in a highly compact transport case that can be carried as a backpack.

    Abstract translation: 具有机身，鼻锥，左翼片，右翼片和尾部的模块化无人驾驶飞行器（UAV）。 尾部和鼻锥每个通过配合的隔板结构连接到机身，提供快速的连接能力，同时易于分离，以便使UAV在这些连接点处分裂，从而吸收或消散着陆时的冲击。 无人机能够在现场快速组装两人发射和数据检索，以及快速拆卸到这五个部件中，用于运输和存储，可以作为背包携带的高度紧凑的运输箱。

    Dual wing-pair air vehicle
    205.
    发明申请
    Dual wing-pair air vehicle 失效
    双翼对机动车

    公开(公告)号：US20050178896A1

    公开(公告)日：2005-08-18

    申请号：US10774653

    申请日：2004-02-04

    Applicant: David Cylinder

    Inventor： David Cylinder

    IPC: B64C33/02 ,  B64C39/02 ,  B64C39/08

    CPC classification number: B64C39/08 ,  B64C33/02 ,  B64C39/024 ,  B64C2201/025 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/126 ,  B64C2201/141 ,  B64C2201/146

    Abstract: A vehicle for flying and having a forward portion and a rearward portion opposite the forward. The vehicle includes a first pair of wings arranged at the forward portion of the vehicle, a second pair of wings arranged at the rearward portion of the vehicle, and a support structure. The support structure is connected to the forward pair of wings and connected to the rearward pair of wings, the support structure being arranged to drive the forward pair of wings alternately toward each other and apart and drives the second pair of wings alternately toward each other and apart.

    Abstract translation: 用于飞行并具有向前部分和与向前相对的后部的车辆。 车辆包括布置在车辆前部的第一对翼，布置在车辆后部的第二对翼和支撑结构。 支撑结构连接到前一对翼部并且连接到后一对翼部，支撑结构被布置成相互交替地驱动前一对翼片并分开，并且将第二对翼片彼此交替地驱动， 分开

    AIRCRAFT CONTROL METHOD
    206.
    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。

    SPLIT TORQUE GEARBOX WITH PIVOTED ENGINE SUPPORT
    207.
    发明申请
    SPLIT TORQUE GEARBOX WITH PIVOTED ENGINE SUPPORT 有权
    带有发动机支撑的分体式扭矩齿轮箱

    公开(公告)号：US20050011990A1

    公开(公告)日：2005-01-20

    申请号：US10620793

    申请日：2003-07-16

    Applicant: Yuriy Gmirya

    Inventor： Yuriy Gmirya

    IPC: B64C29/00 ,  B64C39/02 ,  B64D35/04 ,  B64D27/00

    CPC classification number: F16H1/22 ,  B64C29/0025 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165 ,  B64D35/04

    Abstract: A powerplant system for a vehicle such as a hybrid UAV includes a miniature gas turbine engine and a gearbox assembly. The engine is mounted to the gearbox assembly through a support structure which provides for pivotal movement of the engine relative thereto. The input gear is engaged with two gears such that the pivoted engine arrangement permits the input gear to float until gear loads between the input gear and the first and second gear are balanced. Regardless of the gear teeth errors or gearbox shaft misalignments the input gear will float and split the torque between the two gears.

    Abstract translation: 用于诸如混合UAV的车辆的动力装置系统包括微型燃气涡轮发动机和齿轮箱组件。 发动机通过支撑结构安装到齿轮箱组件，该支撑结构提供发动机相对于其的枢转运动。 输入齿轮与两个齿轮接合，使得枢转的发动机装置允许输入齿轮浮动，直到输入齿轮与第一和第二齿轮之间的齿轮负载平衡。 齿轮齿轮误差或齿轮箱轴不对准，输入齿轮将浮动并分离两个齿轮之间的转矩。

    Transmission for a coaxial counter rotating rotor system
    208.
    发明授权
    Transmission for a coaxial counter rotating rotor system 有权
    同轴反转转子系统的传动

    公开(公告)号：US06672538B2

    公开(公告)日：2004-01-06

    申请号：US10153970

    申请日：2002-05-23

    Applicant: Vincent Francis Millea ,  Anthony George Chory ,  Michelle Consolini ,  Ralph D. Costanzo ,  Jules G. Kish

    Inventor： Vincent Francis Millea ,  Anthony George Chory ,  Michelle Consolini ,  Ralph D. Costanzo ,  Jules G. Kish

    IPC: B64C2730

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165 ,  B64D35/06

    Abstract: A transmission system for a hybrid aircraft is driven by a plurality of driveshafts and drives a translational propulsion system. Each driveshaft is mounted to a pinion gear which mesh with an upper and lower counter-rotating gear. The upper and lower counter-rotating gears drive a respective upper and lower rotor shaft which powers a counter-rotating rotor system. A first angle is defined between a first and a second driveshaft while a second angle is defined between the second and a third driveshaft. The angle between the driveshafts are a whole number multiple of the formula: &thgr;=(CP/R)*(180/&pgr;). By so angularly locating the driveshafts, proper meshing of the pinion gears and the upper and lower counter-rotating gears is assured and tolerances are less stringent as the support structure is effective designed around optimal location of the driveshafts for gear meshing rather than vice versa.

    Abstract translation: 用于混合飞机的传动系统由多个驱动轴驱动并驱动平移推进系统。 每个驱动轴安装在与上下反转齿轮啮合的小齿轮上。 上下反转齿轮驱动相应的上下转子轴，其对反向旋转的转子系统供电。 在第一和第二驱动轴之间限定第一角度，而在第二和第三驱动轴之间限定第二角度。 驱动轴之间的角度是以下公式的整数倍：θ=（CP / R）*（180 / pi）。 通过如此角度地定位传动轴，确保小齿轮和上下相对转动齿轮的适当啮合，并且由于支撑结构有效地围绕用于齿轮啮合的驱动轴的最佳位置设计而不是反之亦然，公差不太严格。

    TRANSMISSION FOR A COAXIAL COUNTER ROTATING ROTOR SYSTEM
    209.
    发明申请
    TRANSMISSION FOR A COAXIAL COUNTER ROTATING ROTOR SYSTEM 有权
    同轴旋转转子系统传动

    公开(公告)号：US20030218093A1

    公开(公告)日：2003-11-27

    申请号：US10153970

    申请日：2002-05-23

    Inventor： Vincent Francis Millea ,  Anthony George Chory ,  Michelle Consolini ,  Ralph D. Costanzo ,  Jules G. Kish

    IPC: B64D035/00

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/162 ,  B64C2201/165 ,  B64D35/06

    Abstract: A transmission system for a hybrid aircraft is driven by a plurality of driveshafts and drives a translational propulsion system. Each driveshaft is mounted to a pinion gear which mesh with an upper and lower counter-rotating gear. The upper and lower counter-rotating gears drive a respective upper and lower rotor shaft which powers a counter-rotating rotor system. A first angle is defined between a first and a second driveshaft while a second angle is defined between the second and a third driveshaft. The angle between the driveshafts are a whole number multiple of the formula: nullnull(CP/R)*(180/null). By so angularly locating the driveshafts, proper meshing of the pinion gears and the upper and lower counter-rotating gears is assured and tolerances are less stringent as the support structure is effective designed around optimal location of the driveshafts for gear meshing rather than vice versa.

    Abstract translation: 用于混合飞机的传动系统由多个驱动轴驱动并驱动平移推进系统。 每个驱动轴安装在与上下反转齿轮啮合的小齿轮上。 上下反转齿轮驱动相应的上下转子轴，其对反向旋转的转子系统供电。 在第一和第二驱动轴之间限定第一角度，而在第二和第三驱动轴之间限定第二角度。 驱动轴之间的角度是以下公式的整数倍：θ=（CP / R）*（180 / pi）。 通过如此角度地定位传动轴，确保小齿轮和上下相对转动齿轮的适当啮合，并且由于支撑结构有效地围绕用于齿轮啮合的驱动轴的最佳位置设计而不是反之亦然，公差不太严格。

Patent Agency Ranking