中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

183 records (took 0.015 seconds)

    SYSTEMS AND METHODS FOR CONTROLLING AN AERIAL UNIT
    101.
    发明申请
    SYSTEMS AND METHODS FOR CONTROLLING AN AERIAL UNIT 审中-公开
    用于控制航空单元的系统和方法

    公开(公告)号：US20130206919A1

    公开(公告)日：2013-08-15

    申请号：US13759087

    申请日：2013-02-05

    Applicant: Gabriel Shachor ,  Shy Cohen ,  Ronen Keidar

    Inventor： Gabriel Shachor ,  Shy Cohen ,  Ronen Keidar

    IPC: B64C29/04

    CPC classification number: B64F1/12 ,  B64C27/04 ,  B64C27/08 ,  B64C29/04 ,  B64C39/022 ,  B64C39/024 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/122 ,  B64C2201/127 ,  B64C2201/148 ,  B64F1/007 ,  B64F1/125

    Abstract: An aerial unit that includes a first propeller; a second propeller that is spaced apart from the first propeller and is below the first propeller; a propelling module that is configured to rotate the first propeller and the second propeller about a first axis; an apertured duct that comprises a first duct portion and a second duct portion. The first duct portion surrounds the first propeller. The second duct portion surrounds the second propeller. The apertured duct defines at least one aperture at an intermediate area that is positioned below the first propeller and is above the second propeller. The aggregate size of the at least one aperture is at least fifty percent of a size of the intermediate area; a frame; and at least one steering element; an interfacing module arranged to be connected to a connecting element that couples the aerial unit to a ground unit. The propelling module and the duct are connected to the frame.

    Abstract translation: 包括第一螺旋桨的天线单元; 第二螺旋桨，其与第一螺旋桨间隔开并且在第一螺旋桨下方; 推进模块，其构造成围绕第一轴旋转所述第一螺旋桨和所述第二螺旋桨; 多孔管道，其包括第一管道部分和第二管道部分。 第一管道部分围绕第一螺旋桨。 第二管道部分围绕第二螺旋桨。 多孔管道在位于第一螺旋桨下方并在第二螺旋桨上方的中间区域处限定至少一个孔。 所述至少一个孔的聚集体尺寸为所述中间区域的尺寸的至少百分之五十; 一个框架; 和至少一个操纵元件; 连接模块被布置成连接到将天线单元耦合到接地单元的连接元件。 推进模块和管道连接到框架。

    DUAL-AIRCRAFT ATMOSPHERIC PLATFORM
    102.
    发明申请
    DUAL-AIRCRAFT ATMOSPHERIC PLATFORM 审中-公开
    双飞机大气平台

    公开(公告)号：US20120232721A1

    公开(公告)日：2012-09-13

    申请号：US13414451

    申请日：2012-03-07

    Applicant: William A. Engblom

    Inventor： William A. Engblom

    IPC: G05D1/00 ,  B64D41/00 ,  B64C37/02

    CPC classification number: G05D1/104 ,  B64C37/02 ,  B64C39/022 ,  B64C2201/104 ,  B64C2201/148 ,  G05D1/105 ,  Y10S244/90

    Abstract: A platform including two winged aircraft are tethered during flight by a single tether near their respective centers of gravity. The tether is windable about a reel, so that a distance between the aircraft can be changed during flight. The aircraft contain avionics configured to enable autonomous flight using natural wind gradients. One aircraft imposes aerodynamic forces on the other, through the tether, while flying at an altitude where wind speed is significantly different than wind speed at an altitude of the other aircraft. The two aircraft cruise back and forth within a maximum distance from a station on the ground. Cruise conditions are established using an iterative computer algorithm which utilizes flight measurements. The aircraft communicate information between each other, and the ground, and contain a payload which performs a useful function at high altitudes.

    Abstract translation: 包括两架有翼飞机在内的平台在飞行过程中由单个系绳在其各自的重心附近被束缚。 系绳可卷绕在卷轴上，使飞机之间的距离可以在飞行过程中改变。 该飞机包含配置成使用自然风向自动飞行的航空电子设备。 一架飞机通过系绳在另一架飞机的高度上与风速显着不同的高度飞行，同时在另一方面施加空气动力。 这两架飞机在距离地面车站最远的距离内来回巡航。 使用利用飞行测量的迭代计算机算法来建立巡航条件。 飞机在彼此之间和地面之间传递信息，并且包含一个在高海拔地区执行有用功能的载荷。

    AERIAL PAYLOAD DEPLOYMENT METHOD
    103.
    发明申请
    AERIAL PAYLOAD DEPLOYMENT METHOD 审中-公开
    AERIAL PAYLOAD DOPLOYMENT方法

    公开(公告)号：US20100185346A1

    公开(公告)日：2010-07-22

    申请号：US12690840

    申请日：2010-01-20

    Applicant: JOHN STEVEN SURMONT

    Inventor： JOHN STEVEN SURMONT

    IPC: B64B1/50 ,  G06F17/00 ,  H04B7/15 ,  G06F19/00

    CPC classification number: H04B7/18504 ,  B64B1/06 ,  B64B1/50 ,  B64B2201/00 ,  B64C2201/022 ,  B64C2201/101 ,  B64C2201/127 ,  B64C2201/148 ,  B64C2201/208

    Abstract: The present invention provides a method, comprising: providing an aerial platform having an outer shell; disposing a gas containment system within the outer shell; attaching the aerial platform to an object using a tether system; and inflating the aerial platform and lifting a payload; wherein the aerial platform is configured such that it may be completely collapsed when deployed.

    Abstract translation: 本发明提供一种方法，包括：提供具有外壳的空中平台; 在外壳内设置气体收容系统; 使用系绳系统将空中平台连接到物体上; 并对空中平台充气并提升有效载荷; 其中所述空中平台被构造成使得其在展开时可能完全折叠。

    Stabilizing control apparatus for robtic or remotely controlled flying platform
    104.
    发明授权
    Stabilizing control apparatus for robtic or remotely controlled flying platform 失效
    用于机器人或遥控飞行平台的稳定控制装置

    公开(公告)号：US06450445B1

    公开(公告)日：2002-09-17

    申请号：US09868008

    申请日：2001-10-12

    Applicant: Paul S. Moller

    Inventor： Paul S. Moller

    IPC: B64C2900

    CPC classification number: B64C39/024 ,  B64C29/02 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/162

    Abstract: A robotic or remotely controlled flying platform (10) with reduced drag stabilizing control apparatus constructed having an air duct (12) with an air intake (14) on the top and an exhaust (16) at the bottom, containing supported therein a clockwise rotating fan (22) and a counter-clockwise rotating fan (24). Directly below the perimeter of the air duct exhaust are mounted a plurality of trough shaped air deflection assemblies (32) each including a rotatably adjustable half trough (44) for selectively scooping a portion of the drive air, and a stationary adjacent half trough (36) for receiving the scooped drive air and redirecting it outward and upward from the air duct. A centrally positioned plate (112) has a plurality of rods (106), each pivotably connected between the plate (74) and a corresponding lever associated with each of the adjustable half troughs (44) so as to couple the adjustable half trough (44) in or out of the drive air steam according to the position of the plate (74), thereby providing control over the pitch and roll of the flying platform. The plate is driven by first and second motors responding to input control signals. The control signals also direct the yaw of the flying platform by selectively providing independent speed control to each of the clockwise and counter clockwise fan motors resulting in duct rotation in a clockwise or counter clockwise direction accordingly.

    Abstract translation: 一种机器人或远程控制的飞行平台（10），其具有减少的阻力稳定控制装置，其构造为具有在顶部具有进气口（14）的空气管道（12）和底部的排气（16），其包含支撑在其中的顺时针旋转 风扇（22）和逆时针旋转的风扇（24）。 安装有多个槽形的空气偏转组件（32），每个包括可旋转的可调节的半槽（44），用于选择性地舀取驱动空气的一部分，以及固定的相邻半槽（36） ），用于接收舀取的驱动空气并将其从空气管道向外和向上引导。 中心定位的板（112）具有多个杆（106），每个杆（106）可枢转地连接在板（74）和与可调节半槽（44）中的每一个相关联的相应杆，以便联接可调节半槽（44） ）根据板（74）的位置进入或离开驱动空气蒸汽，从而提供对飞行平台的俯仰和滚动的控制。 该板由响应于输入控制信号的第一和第二电动机驱动。 控制信号还通过选择性地为每个顺时针和逆时针风扇电动机提供独立的速度控制来引导飞行平台的偏转，从而导致管道沿顺时针或逆时针方向旋转。

    Payload delivery system
    105.
    发明申请
    Payload delivery system 审中-公开
    有效载送系统

    公开(公告)号：US20020066825A1

    公开(公告)日：2002-06-06

    申请号：US09884852

    申请日：2001-06-18

    Inventor： Carlos T. Miralles ,  Bart D. Hibbs

    IPC: B64C003/56

    CPC classification number: B64G1/222 ,  B64C1/30 ,  B64C3/56 ,  B64C39/024 ,  B64C2201/042 ,  B64C2201/082 ,  B64C2201/102 ,  B64C2201/126 ,  B64C2201/127 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/185 ,  B64C2201/203 ,  B64G1/105 ,  B64G1/62

    Abstract: Disclosed is a spacecraft carrying a number of pods, each containing an aircraft that has been folded to fit in the pod. Each aircraft has a vertical stabilizer and outboard wing-portions that fold around fore-and-aft axes. Each aircraft also has a fuselage that folds around a lateral axis. The spacecraft releases one or more of the pods into an atmosphere. Each of the pods is configured with an ablative heat shield and parachutes to protect its aircraft when the pod descends through the atmosphere. The pod releases its aircraft at a desired altitude or location, and the aircraft unfolds while free-falling. The aircraft then acquires and follows a flight path, and activates scientific experiments and instruments that it carries. The aircraft relays results and readings from the experiments and instruments to the spacecraft, which in turn relays the results and readings to a mission command center.

    Abstract translation: 公开了一种携带多个荚的飞船，每个荚都包含已折叠以适应荚的飞机。 每架飞机都有一个垂直的稳定器和外侧翼部分，它们围绕前后轴线折叠。 每架飞机还具有折叠横轴的机身。 航天器将一个或多个荚释放到气氛中。 每个荚配置有烧蚀式防护罩和降落伞，以在荚果通过大气层时保护其飞机。 吊舱将其飞机放置在所需的高度或位置，飞机在自由落体时展开。 飞机然后获得并遵循飞行路线，并激活它所携带的科学实验和仪器。 飞机将实验和仪器的结果和读数中继到航天器，然后将结果和读数中继到任务指挥中心。

Patent Agency Ranking