中科微点-全球专利检索

  1. Login
  2. Sign Up

Search Results

259 records (took 0.024 seconds)

    UNMANNED AIR VEHICULES AND METHOD OF LANDING SAME
    131.
    发明申请
    UNMANNED AIR VEHICULES AND METHOD OF LANDING SAME 审中-公开
    不限于空气的车辆和陆地的方法

    公开(公告)号：WO2006006151A1

    公开(公告)日：2006-01-19

    申请号：PCT/IL2005/000714

    申请日：2005-07-06

    Applicant: ELBIT SYSTEMS LTD. ,  SIRKIS, Omri

    Inventor： SIRKIS, Omri

    IPC: B64C39/02

    CPC classification number: B64C39/024 ,  B64C2201/021 ,  B64C2201/042 ,  B64C2201/044 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/167 ,  B64C2201/187

    Abstract: There is provided an Unmanned Air Vehicule (uav) (2) including an engine (4) and an airframe (6), including means for performing a deep stall maneouvre; at least one inflatable sleeve (12) connected or connectable to the airframe (6), and means for inflating the sleeve (12) during flight, wherein the inflated sleeve (12) extends along the lower side of the airframe (6) so as to protect same during deep stall landing. A method for operating an Unmanned Air Vehicle (UAV), including an engine and an airframe is also provided.

    Abstract translation: 提供了包括发动机（4）和机身（6）的无人驾驶飞机（uav）（2），其中包括用于执行深度失速行动的手段; 连接或连接到机身（6）的至少一个可充气套筒（12）以及用于在飞行期间使套筒（12）膨胀的装置，其中所述充气套筒（12）沿着所述机身（6）的下侧延伸，以便 在深层失速登陆期间保护相同。 还提供了一种用于操作无人机（UAV）的方法，包括发动机和机身。

    TAILBOOM-STABILIZED VTOL AIRCRAFT
    132.
    发明申请
    TAILBOOM-STABILIZED VTOL AIRCRAFT 审中-公开
    TAILBOOM稳定的垂直起降飞机

    公开(公告)号：WO2005039973A3

    公开(公告)日：2005-11-10

    申请号：PCT/US2004034581

    申请日：2004-10-19

    Applicant: BALDWIN DOUGLAS G

    Inventor： BALDWIN DOUGLAS G

    IPC: B64C29/00 ,  B64C39/02 ,  B64C27/28

    CPC classification number: B64C29/02 ,  B64C29/0033 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/024 ,  B64C2201/048 ,  B64C2201/104 ,  B64C2201/108 ,  B64C2201/128 ,  B64C2201/165

    Abstract: A disclosed flying craft (100) includes a suspension structure (110) having a first end and a second end, a lift unit (150), and a payload unit (190). The lift unit includes a nacelle (128) and a tailboom (140), and pivotally couples to the first end of the suspension structure, and a payload unit couples to the structure's second end. Thus the tailboom can pivotally couple with respect to the payload unit, which advantageously permits the tailboom to assume an orientation desirable for a particular mode of flight. During vertical flight or hover, the tailboom can hang from the lift unit in an orientation that is substantially parallel to the suspension structure and that minimizes resistance to downwash from the lift unit. During horizontal flight, the tailboom can be orthogonal to the suspension structure, extending rearward in an orientation where it can develop pitching and yawing moments to control and stabilize horizontal flight. Advantageous variations and methods are also disclosed.

    Abstract translation: 公开的飞行器（100）包括具有第一端和第二端的悬挂结构（110），升降单元（150）和有效载荷单元（190）。 提升单元包括机舱（128）和尾杆（140），并且枢转地联接到悬挂结构的第一端，并且有效载荷单元耦合到结构的第二端。 因此，尾巴可以相对于有效载荷单元枢转地联接，这有利地允许尾巴呈现对于特定飞行方式所需的取向。 在垂直飞行或悬停期间，尾巴可以以与悬挂结构基本平行的方向从提升单元悬挂，并且使得抵抗来自提升单元的降洗的阻力最小化。 在水平飞行期间，尾翼可以与悬架结构正交，向后延伸，在该方向上可以产生俯仰和偏转力矩以控制和稳定水平飞行。 还公开了有利的变型和方法。

    AUTOMATED CARGO TRANSPORTATION SYSTEM
    133.
    发明申请
    AUTOMATED CARGO TRANSPORTATION SYSTEM 审中-公开
    自动货物运输系统

    公开(公告)号：WO2004063008A3

    公开(公告)日：2004-09-23

    申请号：PCT/US2004000687

    申请日：2004-01-13

    Applicant: BOXAIR ENGINEERING LLC ,  STUPAKIS JOHN S

    Inventor： STUPAKIS JOHN S

    IPC: B64C39/02 ,  B64C1/00

    CPC classification number: B64C39/024 ,  B64C39/02 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2211/00 ,  B64D2011/0046 ,  Y10S244/903

    Abstract: A modular automated air transport system comprising an unmanned autonomous aircraft having a selectively detachable control systems portion and a structural air frame portion, wherein the structural air frame portion contains an interior cargo hold, aerodynamic members having control surfaces and at least one propulsion device attached to the structural air frame portion; and wherein the control system portion includes a control computer for autonomously controlling the flight of said air transport system from one known location to a second known location.

    Abstract translation: 一种模块化的自动航空运输系统，包括具有选择性地可拆卸的控制系统部分和结构空气框架部分的无人自主飞行器，其中所述结构空气框架部分包含内部货舱，具有控制表面的空气动力部件和附接到 结构空气框架部分; 并且其中所述控制系统部分包括用于自主地控制所述空中运输系统从一个已知位置到第二已知位置的飞行的控制计算机。

    AUTOMATED CARGO TRANSPORTATION SYSTEM
    134.
    发明申请
    AUTOMATED CARGO TRANSPORTATION SYSTEM 审中-公开
    自动货物运输系统

    公开(公告)号：WO2004063008A2

    公开(公告)日：2004-07-29

    申请号：PCT/US2004/000687

    申请日：2004-01-13

    Applicant: BOXAIR ENGINEERING, LLC ,  STUPAKIS, John, S.

    Inventor： STUPAKIS, John, S.

    IPC: B64C

    CPC classification number: B64C39/024 ,  B64C39/02 ,  B64C2201/048 ,  B64C2201/086 ,  B64C2201/104 ,  B64C2201/128 ,  B64C2201/141 ,  B64C2201/165 ,  B64C2201/187 ,  B64C2211/00 ,  B64D2011/0046 ,  Y10S244/903

    Abstract: A modular automated air transport system comprising an unmanned autonomous aircraft having a selectively detachable control systems portion and a structural air frame portion, wherein the structural air frame portion contains an interior cargo hold, aerodynamic members having control surfaces and at least one propulsion device attached to the structural air frame portion; and wherein the control system portion includes a control computer for autonomously controlling the flight of said air transport system from one known location to a second known location.

    Abstract translation: 一种模块化自动化空中运输系统，包括具有选择性可拆卸控制系统部分和结构空气框架部分的无人自主飞机，其中所述结构空气框架部分包含内部货舱，空气动力学构件具有控制表面 以及至少一个连接到结构空气框架部分的推进装置; 并且其中所述控制系统部分包括用于自主地控制所述空中交通系统从一个已知位置到第二已知位置的飞行的控制计算机。

    Modular aircraft system
    138.
    发明授权
    Modular aircraft system 有权
    模块化飞机系统

    公开(公告)号：US09505484B1

    公开(公告)日：2016-11-29

    申请号：US15096216

    申请日：2016-04-11

    Applicant: Nasser M. Al-Sabah

    Inventor： Nasser M. Al-Sabah

    IPC: B64C3/38 ,  B64C13/00 ,  B64C9/00 ,  B64C13/20 ,  B64C9/32 ,  B64D27/02 ,  B64C3/34 ,  B64D47/08 ,  B64D15/00 ,  B64C39/02 ,  B64D37/00 ,  B64D27/14 ,  B64D27/20

    CPC classification number: B64C3/38 ,  B64C1/26 ,  B64C3/34 ,  B64C5/06 ,  B64C9/00 ,  B64C9/326 ,  B64C13/00 ,  B64C13/20 ,  B64C39/024 ,  B64C2201/021 ,  B64C2201/048 ,  B64C2201/063 ,  B64C2201/104 ,  B64C2201/126 ,  B64C2201/141 ,  B64C2201/146 ,  B64C2201/16 ,  B64C2201/165 ,  B64C2211/00 ,  B64D15/00 ,  B64D27/02 ,  B64D27/14 ,  B64D27/20 ,  B64D37/00 ,  B64D39/00 ,  B64D47/08 ,  Y02T50/32

    Abstract: The modular aircraft system includes a single fuselage having a permanently installed empennage and plural sets of wing modules and engine modules, with each wing and engine module optimized for different flight conditions and missions. The fuselage and each of the modules are configured for rapid removal and installation of the modules to minimize downtime for the aircraft. Short wings having relatively low aspect ratio are provided for relatively high speed flight when great endurance and/or weight carrying capacity are not of great concern. Long wings having high aspect ratio are provided for longer range and endurance flights where speed is not absolutely vital. A medium span wing module is also provided. Turboprop, single turbojet, and dual turbojet engine modules are provided for installation depending upon mission requirements for any given flight. The aircraft is primarily adapted for use as an autonomously operated or remotely operated unmanned aerial vehicle.

    Abstract translation: 模块化飞机系统包括具有永久安装的尾翼和多组翼模块和发动机模块的单个机身，每个机翼和发动机模块针对不同的飞行条件和任务进行了优化。 机身和每个模块配置为快速拆卸和安装模块，以最大限度地减少飞机的停机时间。 在具有较高耐久性和/或重量承载能力的情况下，为相对高速飞行提供具有相对较低纵横比的短翼。 为长距离和耐力航班提供高长宽比的长翼，速度并不是绝对重要的。 还提供了中跨翼模块。 提供涡轮螺旋桨发动机，单涡轮喷气发动机和双涡轮喷气发动机模块用于安装，具体取决于任何给定航班的任务要求。 该飞机主要适用于自主操作或远程操作的无人驾驶飞行器。

    IN-FLIGHT BATTERY RECHARGING SYSTEM FOR AN UNMANNED AERIAL VEHICLE
    139.
    发明申请
    IN-FLIGHT BATTERY RECHARGING SYSTEM FOR AN UNMANNED AERIAL VEHICLE 审中-公开
    用于无人驾驶飞机的飞行式电池充电系统

    公开(公告)号：US20160325834A1

    公开(公告)日：2016-11-10

    申请号：US15149972

    申请日：2016-05-09

    Applicant: Curtis Asa Foster

    Inventor： Curtis Asa Foster

    IPC: B64C39/02 ,  B64D27/24 ,  B64C27/14

    CPC classification number: B64C39/024 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/042 ,  B64C2201/048 ,  B64C2201/066 ,  B64C2201/108 ,  B64C2201/162 ,  B64D27/24

    Abstract: An in-flight battery recharging system for Unmanned Aerial Vehicle (UAV). This invention converts byproducts of a multi-rotor unmanned aerial vehicle's conventional propulsion system operation and airframe movements to generate electricity that, in turn, is used to power the propulsion system's electric motors, power onboard electronic components, and recharge the battery that initially powers the propulsion system's electric motors. Having this ability of recharging the battery in-flight gives an unmanned aerial vehicle a much improved flight time and range, thereby greatly increasing its utility.

    Abstract translation: 无人机（UAV）的飞行中电池充电系统。 本发明转化了多转子无人驾驶飞行器的常规推进系统操作和机身运动的副产物，以产生电力，其又被用于为推进系统的电动机提供动力，并且对电子组件进行动力，以及对最初为 推进系统的电动机。 在飞行中为电池充电的能力给无人驾驶飞行器提供了大大改进的飞行时间和范围，从而大大提高了其效用。

Patent Agency Ranking