中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

429 records (took 0.02 seconds)

    HYDROGEN POWERED AIRCRAFT
    241.
    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。

    METHODS AND SYSTEMS FOR CONTROLLING THE PITCH OF A PROPELLER
    242.
    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：WO2005084373A2

    公开(公告)日：2005-09-15

    申请号：PCT/US2005/007035

    申请日：2005-03-03

    Applicant: THE INSITU GROUP, INC. ,  DENNIS, Brian, D. ,  HILLEN, Kenneth

    Inventor： DENNIS, Brian, D. ,  HILLEN, Kenneth

    IPC: 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
    243.
    发明申请
    AIRCRAFT 审中-公开
    飞机

    公开(公告)号：WO01058756A2

    公开(公告)日：2001-08-16

    申请号：PCT/US2001/004378

    申请日：2001-02-07

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

    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。

    翼身融合飞机
    244.
    发明申请
    翼身融合飞机 审中-公开

    公开(公告)号：WO2018129768A1

    公开(公告)日：2018-07-19

    申请号：PCT/CN2017/072079

    申请日：2017-01-22

    Applicant: 顺丰科技有限公司

    Inventor： 李晓亮

    IPC: B64C3/14 ,  B64C39/10

    CPC classification number: B64C3/14 ,  B64C39/10 ,  B64C2201/028

    Abstract: 一种翼身融合飞机，包括翼身融合的机身（1）和机翼，机翼包括位于机身（1）左右两侧的机翼（2）；机身（1）具有中央对称面；机身（1）具有位于中央对称面上的中央截面、垂直于中央截面顶点处的重心截面；重心截面的上翼面呈中间高、两侧低的上凸流线形，重心截面的下翼面呈中间低、两侧高的下凹流线形，重心截面在中央对称面上的高度为H，重心截面的宽度为D，其中0.7≤H/D≤0.8。该翼身融合飞机采用新型的翼身融合布局，即从机身到机翼的外形平滑过渡，极大的减少了干扰阻力，同时增加了机体内部空间，提高承载能力；控制机身的最大厚度与机身的宽度比，使得机身具有高升阻比，提高飞机的气动性能。

    PROPELLER HAVING EXTENDING OUTER BLADES
    245.
    发明申请
    PROPELLER HAVING EXTENDING OUTER BLADES 审中-公开
    螺旋桨有扩展外刀片

    公开(公告)号：WO2017058329A2

    公开(公告)日：2017-04-06

    申请号：PCT/US2016/041167

    申请日：2016-07-06

    Applicant: NORTHROP GRUMMAN SYSTEMS CORPORATIONS

    Inventor： LINCH, Jonathon J. ,  RAHRIG, Kyle M.

    IPC: B64C11/00

    CPC classification number: B64C11/001 ,  B64C39/024 ,  B64C39/10 ,  B64C2039/105 ,  B64C2201/028 ,  B64C2201/104 ,  B64C2201/165

    Abstract: A propeller includes a hub coaxially surrounding a longitudinal axis. A ring shroud coaxially surrounds the longitudinal axis and is spaced radially from the hub. The ring shroud includes an inner ring surface and a radially spaced, oppositely facing outer ring surface. At least one propeller blade is fixedly attached to both the hub and the inner ring surface and extends radially therebetween for mutual rotation therewith. At least one extending blade has a first extending blade end radially spaced from a second extending blade end. The first extending blade end is fixedly attached to the outer ring surface. The second extending blade end is cantilevered from the first extending blade end and is radially spaced from the ring shroud.

    Abstract translation: 螺旋桨包括同轴地围绕纵向轴线的轮毂。 环形护罩同轴地围绕纵向轴线并与轮毂径向间隔开。 环形护罩包括内环表面和径向间隔开的相对的外环表面。 至少一个螺旋桨叶片固定地附接到轮毂和内环表面并且在其间径向延伸以与其相互旋转。 至少一个延伸叶片具有与第二延伸叶片端部径向间隔开的第一延伸叶片端部。 第一延伸叶片端固定地附接到外环表面。 第二延伸叶片端部从第一延伸叶片端部悬臂并且与环形护罩径向间隔开。

    UNIVERSAL VEHICLE WITH IMPROVED STABILITY FOR SAFE OPERATION IN AIR, WATER AND TERRAIN ENVIRONMENTS
    246.
    发明申请
    UNIVERSAL VEHICLE WITH IMPROVED STABILITY FOR SAFE OPERATION IN AIR, WATER AND TERRAIN ENVIRONMENTS 审中-公开
    具有改善航空，水和地球环境安全运行稳定性的通用车辆

    公开(公告)号：WO2017040493A1

    公开(公告)日：2017-03-09

    申请号：PCT/US2016/049429

    申请日：2016-08-30

    Applicant: UNIVERSITY OF MARYLAND, COLLEGE PARK

    Inventor： VALENTE, Evandro Gurgel do Amaral ,  WERELEY, Norman, M. ,  VALENTE, Eduardo Gurgel do, Amaral

    IPC: B64C3/14 ,  B64C29/00

    CPC classification number: B64C39/10 ,  B64C15/12 ,  B64C29/0033 ,  B64C37/00 ,  B64C39/024 ,  B64C2201/028 ,  B64C2201/088 ,  B64C2201/208 ,  B64C2211/00

    Abstract: The universal vehicle system is designed with a lifting body which is composed of a plurality of interconnected modules which are configured to form an aerodynamically viable contour of the lifting body which including a front central module, a rear module, and thrust vectoring modules displaceably connected to the front central module and operatively coupled to respective propulsive mechanisms. The thrust vectoring modules are controlled for dynamical displacement relative to the lifting body (in tilting and/or translating fashion) to direct and actuate the propulsive mechanism(s) as needed for safe and stable operation in various modes of operation and transitioning therebetween in air, water and terrain environments.

    Abstract translation: 通用车辆系统设计有提升体，其由多个相互连接的模块组成，所述多个互连模块被构造成形成提升体的空气动力学上可行的轮廓，其包括前部中央模块，后部模块和可移动地连接到 前中央模块并且可操作地耦合到相应的推进机构。 控制推力矢量模块以相对于提升体（以倾斜和/或平移方式）进行动态位移，以根据需要引导并致动推进机构，以便在空气中的各种运行模式和过渡之间进行安全和稳定的操作 ，水和地形环境。

    UNMANNED AIR VEHICLE (UAV), CONTROL SYSTEM AND METHOD
    249.
    发明申请
    UNMANNED AIR VEHICLE (UAV), CONTROL SYSTEM AND METHOD 审中-公开
    无人机（UAV），控制系统和方法

    公开(公告)号：WO2010100436A2

    公开(公告)日：2010-09-10

    申请号：PCT/GB2010/000399

    申请日：2010-03-05

    Applicant: CRANFIELD AEROSPACE LTD ,  THOMASSON, Peter, Geoffrey ,  JONES, Robert, Idris ,  POLL, David, Ian, Alistair

    Inventor： THOMASSON, Peter, Geoffrey ,  JONES, Robert, Idris ,  POLL, David, Ian, Alistair

    IPC: B64C13/16

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/141 ,  B64C2201/146 ,  G05D1/0094 ,  G05D1/0825

    Abstract: A gust-insensitive unmanned air vehicle (UAV) for imaging the ground, the UAV comprising: an airframe which is substantially neutrally stable and comprises a fuselage and at least three wings which include control surfaces, wherein the wings are arranged in symmetrical relation about the fuselage and confer the UAV with a roll stability about the longitudinal axis of the fuselage for any roll angle, thereby allowing the roll angle of the UAV to be set to any required angle independent of the heading and pitch angle of the UAV; a propulsion device for propelling the UAV in flight; an image sensor for imaging the ground, wherein the image sensor has a footprint, the position of which is determined by the roll angle of the UAV; and a flight control system for controlling the in-flight operation of the UAV, wherein the flight control system includes flight control sensors and is operative to render the UAV gust insensitive in response to inputs from the flight control sensors, whereby the UAV exhibits substantially only linear displacements in response to wind gusts, and control the roll angle of the UAV to determine the position of the sensor footprint.

    Abstract translation: 一种用于对地面进行成像的阵风不敏感的无人驾驶飞行器（UAV），所述无人机包括：基本中立稳定的机身，包括机身和至少三个包括控制表面的机翼，其中所述机翼围绕 机身并赋予无人机以任何滚动角度的关于机身的纵向轴线的滚动稳定性，从而允许无人机的侧倾角度被设定为独立于无人机的航向和俯仰角度的任何所需角度; 用于在飞行中推动无人机的推进装置; 用于对地面进行成像的图像传感器，其中图像传感器具有由UAV的滚动角确定的位置; 以及用于控制无人机的飞行操作的飞行控制系统，其中所述飞行控制系统包括飞行控制传感器并且可操作以响应于来自飞行控制传感器的输入而使UAV阵风不敏感，由此UAV仅显示出 响应于阵风的线性位移，并且控制无人机的侧倾角以确定传感器足迹的位置。

    VIBRATION ISOLATION DEVICES AND ASSOCIATED SYSTEMS AND METHODS
    250.
    发明申请
    VIBRATION ISOLATION DEVICES AND ASSOCIATED SYSTEMS AND METHODS 审中-公开
    振动隔离装置及相关系统及方法

    公开(公告)号：WO2009142790A1

    公开(公告)日：2009-11-26

    申请号：PCT/US2009/035320

    申请日：2009-02-26

    Applicant: INSITU, INC. ,  VON FLOTOW, Andreas, H. ,  HORTON, Tyler, Patrick

    Inventor： VON FLOTOW, Andreas, H. ,  HORTON, Tyler, Patrick

    IPC: B64C1/00

    CPC classification number: B64C39/024 ,  B64C2201/028 ,  B64C2201/127 ,  B64C2201/165

    Abstract: Vibration isolation devices and associated systems and methods are disclosed herein. In one embodiment, for example, an unmanned aircraft can include a fuselage having a first fuselage section and a second fuselage section adjacent to and at least approximately longitudinally aligned with the first fuselage section. The aircraft can also include at least one vibration isolation device coupling the first fuselage section to the second fuselage section. The vibration isolation device is translationally stiffer along a longitudinal axis than it is along a lateral and a vertical axis, and rotationally stiffer about a pitch and a yaw axis than it is about a roll axis.

    Abstract translation: 本文公开了隔振装置及相关系统和方法。 在一个实施例中，例如，无人飞行器可以包括具有第一机身部分的机身和与第一机身部分相邻并且至少大致纵向对齐的第二机身部分。 飞机还可以包括将第一机身部分连接到第二机身部分的至少一个隔振装置。 振动隔离装置沿着纵向轴线比沿着横向轴线和垂直轴线平移地更硬，并且围绕俯仰轴线和偏转轴线旋转地比围绕辊轴线旋转更硬。

Patent Agency Ranking