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    CIRCULAR VERTICAL TAKE-OFF AND LANDING AIRCRAFT
    212.
    发明公开
    CIRCULAR VERTICAL TAKE-OFF AND LANDING AIRCRAFT 审中-公开
    立式圆STARTER

    公开(公告)号：EP1370460A1

    公开(公告)日：2003-12-17

    申请号：EP02703709.2

    申请日：2002-02-26

    Applicant: Walmsley, Eric Ronald

    Inventor： Walmsley, Eric Ronald

    IPC: B64C39/00 ,  B64C39/06 ,  B64D27/26

    CPC classification number: B64C27/20 ,  B64C39/001 ,  B64C39/024 ,  B64C39/06 ,  B64C39/062 ,  B64C2201/027 ,  B64C2201/046 ,  B64C2201/048 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/162

    Abstract: A circular VTOL aircraft with a central vertically mounted turboprop engine (14), driving contra-rotating co-axial propellers (24), above a central jet engine, or engines (12), horizontally mounted on a turntable (11) and steerable through 360 degrees. The turboprop provides vertical thrust from propellers compressing air from an upper circular intake (5) downward through a circular funnel-shaped rotor-chamber (6), to a circular vent (10) at the base of the aircraft. The resulting column of compressed air gives lift for VTOL operations and a cushion of air in flight. The horizontally mounted turbine provides acceleration, retro-thrust and directional control for horizontal flight and vectored thrust for VTOL. An alternative engine configuration (Figure 9), replaces the turboprop and propellers with a vertical turbojet or rocket-engine system providing direct vertical thrust via four control vents (12/14), with an optional horizontal vectored thrust vent (15/37). he aircraft. Fuel-tanks are installed around the central engines. The flight-deck is at the top-centre of the craft above the engines, which are detachable for maintenance.

    Robotic or remotely controlled flying platform
    214.
    发明公开
    Robotic or remotely controlled flying platform 失效
    机动或遥控飞行平台

    公开(公告)号：EP0279391A3

    公开(公告)日：1989-04-26

    申请号：EP88102150.5

    申请日：1988-02-13

    Applicant: MOLLER INTERNATIONAL, INC.

    Inventor： Moller, Paul S.

    IPC: B64C39/02 ,  B64C27/00 ,  B64C27/20

    CPC classification number: B64C39/024 ,  B64C27/00 ,  B64C27/20 ,  B64C2201/027 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/127 ,  B64C2201/146 ,  B64C2201/148 ,  B64C2201/162

    Abstract: A flying platform (10), propelled by at least one ducted fan (11) causing a vertically downwardly directed airstream in and through a cylindrical duct (12). A vane system in the duct (12) has two mutually perpendicular pairs (31-34) of diametrically opposite first vanes, each extending in from the duct rim toward the center of the duct. Each pair of first vanes provides a pair of generally vertical walls parallel to a diametral line across the duct, and they define duct passages between the pairs of vanes and define quadrants between adjacent pairs. Each first vane has an upper, fixed, rigid portion and a variable camber flap (45, 46) depending therefrom. A first servomotor with linkages vary the camber of each pair of flaps (45, 46), so that the camber of the flaps (45, 46) of each pair is at all times the same amount but in opposite directions. Preferably, there are also four second vanes (41-44), one bisecting each quadrant, and a symmetric pair of spoilers (75-82) is mounted on each second vane (41-44). Each pair of spoilers (75-82) is independently movable, as a pair continuously between a position substantially blocking airflow through the outer portion of said quadrant and a position permitting substantially full airflow therethrough. A second servomotor with linkages symmetrically varies the position of its spoilers (75-82). There may be a radio receiver responsive to remote control signals for actuating each servo­motor and its linkages.

    APPARATUS FOR USE ON UNMANNED VEHICLES
    216.
    发明授权
    APPARATUS FOR USE ON UNMANNED VEHICLES 有权
    用于无人驾驶车辆的装置

    公开(公告)号：EP2723641B1

    公开(公告)日：2018-04-04

    申请号：EP12729189.6

    申请日：2012-06-20

    Applicant: BAE Systems PLC

    Inventor： FREEMAN, Isobel Louise ,  RIGBY, Keith Antony

    IPC: B64C39/02 ,  F41H7/00 ,  F42B12/36 ,  F41H13/00

    CPC classification number: B64C39/024 ,  B64C2201/00 ,  B64C2201/121 ,  B64C2201/123 ,  B64C2201/127 ,  F41H7/005 ,  F41H13/00 ,  F42B12/365

    Abstract: An apparatus, and a method performed by the apparatus, are disclosed wherein the apparatus can be mounted on an unmanned vehicle and arranged to act upon a payload. The payload can be mounted on the unmanned vehicle and, under an action of the apparatus, is able to be activated. The method can include receiving an activation instruction from an entity remote from the unmanned vehicle; determining whether or not the received activation instruction is valid by performing a validation process; and in response to determining that the received activation instruction is valid, activating the payload. In response to determining that the received activation instruction is not valid, activation of the payload may be prevented or opposed.

    SYSTEMS AND METHODS FOR COUNTERING AN UNMANNED AIR VEHICLE
    218.
    发明公开
    SYSTEMS AND METHODS FOR COUNTERING AN UNMANNED AIR VEHICLE 审中-公开
    圣彼得堡ZENG ENTGEGNEN EINEES UNBEMANNTEN LUFTFAHRZEUGS

    公开(公告)号：EP2979979A1

    公开(公告)日：2016-02-03

    申请号：EP15178375.0

    申请日：2015-07-24

    Applicant: Insitu, Inc.

    Inventor： GOODRICH, Wayne

    IPC: B64C39/02 ,  B64C11/48

    CPC classification number: B64C39/024 ,  B64C5/06 ,  B64C11/48 ,  B64C2201/042 ,  B64C2201/108 ,  B64C2201/121 ,  B64C2201/141 ,  B64C2201/162 ,  F41H11/02 ,  F41H13/0006 ,  G05D1/12

    Abstract: Systems and methods for countering an unmanned air vehicle are disclosed. Representative methods include directing an interceptor UAV (140) toward a target UAV (199), and directing the interceptor UAV back to ground along a controlled flight path, for example, in response to an instruction not to engage with the target UAV, and/or in response to an unsuccessful engagement. Another representative method includes disabling the target UAV by deploying a disabling element (e.g., a net) from the interceptor UAV to contact the target UAV. Representative systems include a target acquisition system, a launch control system, and an engagement system carried by the interceptor UAV. In particular embodiments, the interceptor UAV can have a generally cylindrical fuselage (112), one or more fins (114) carried by the fuselage, counter-rotating propellers (121a, 121b) carried by the fuselage, and a disabling system that is configured to disable the target UAV.

    Abstract translation: 公开了用于对抗无人驾驶飞行器的系统和方法。 代表性的方法包括将拦截器UAV（140）引导到目标无人机（199），并且将拦截器UAV沿着受控飞行路径引导回地面，例如响应于不与目标UAV接合的指令，和/ 或响应不成功的参与。 另一个代表性的方法包括通过从拦截器UAV部署禁用元件（例如网）来禁用目标UAV以接触目标UAV。 代表性系统包括目标采集系统，发射控制系统和拦截机无人机所携带的接合系统。 在特定实施例中，拦截器UAV可以具有大致圆柱形的机身（112），由机身承载的一个或多个翅片（114），由机身承载的反向旋转螺旋桨（121a，121b）和配置的禁用系统 禁用目标无人机。

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