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33 条记录 (耗时 0.011 秒)

    A REAR END SECTION FOR AN AIRCRAFT
    1.
    发明公开
    A REAR END SECTION FOR AN AIRCRAFT 审中-公开

    公开(公告)号：EP3904202A1

    公开(公告)日：2021-11-03

    申请号：EP20382351.3

    申请日：2020-04-29

    申请人： Airbus Operations, S.L.

    发明人： LLAMAS SANDIN, Raul Carlos

    IPC分类号： B64C1/06 ,  B64C1/00 ,  B64C9/38 ,  B64C21/06 ,  B64D27/14

    摘要： The invention refers to a rear end section (1) for an aircraft, having a fuselage (4), a v-tail (2), and a thruster assembly (3) comprising: at least one propulsion device (5) installed to ingest and consume air forming a fuselage boundary layer, a control surface (6) attached at the rearmost section of the rear end, and a casing (7) covering at least part of the propulsion device (5) such that an air inlet (8) and an air outlet (9) are defined between the casing (7) and the propulsion device (5), the air inlet (8) being designed for the passage of the fuselage boundary layer towards the propulsion device (5), and the air outlet (9) being designed for directing the airflow exhausted from the propulsion device (5) into the control surface (6), to divert said airflow and provide vectoring thrust for the aircraft.

    FLUIDIC CONTROL
    3.
    发明公开
    FLUIDIC CONTROL 审中-公开

    公开(公告)号：EP3812266A1

    公开(公告)日：2021-04-28

    申请号：EP19275104.8

    申请日：2019-10-22

    申请人： BAE SYSTEMS plc

    发明人： The designation of the inventor has not yet been filed

    IPC分类号： B64C15/02 ,  B64C9/38

    摘要： A vehicle control system for use with at least one fluidic control effector (102) for a vehicle, the vehicle control system comprising a controller (104), wherein the controller is configured to: receive a vehicle control input indicating a demanded vehicle manoeuvre, wherein the input is further configured to receive condition data; determine a fluid mass-flow for the at least one fluid control effector (102) based on the received vehicle control input and the condition data, wherein the relationship between the fluid mass-flow and the vehicle control input is substantially non-linear; and output data relating to the determined fluid mass-flow to effect the demanded vehicle manoeuvre, wherein the fluid mass-flow is determined to provide a substantially linear relationship between the vehicle control input and the effected demanded vehicle manoeuvre.

    AERODYNAMIC DEVICE
    7.
    发明公开
    AERODYNAMIC DEVICE 有权
    AERODYNAMISCHE VORRICHTUNG

    公开(公告)号：EP3077282A1

    公开(公告)日：2016-10-12

    申请号：EP15766257.8

    申请日：2015-07-09

    申请人： Akhmejanov, Alibi

    发明人： Akhmejanov, Alibi

    IPC分类号： B64C9/38 ,  B64C15/14 ,  B64C21/10 ,  B64C29/00

    CPC分类号： B64C3/10 ,  B64C3/44 ,  B64C3/54 ,  B64C9/00 ,  B64C9/38 ,  B64C15/14 ,  B64C21/10 ,  B64C29/0016 ,  B64C39/024 ,  Y02T50/166 ,  Y02T50/32

    摘要： The invention relates to aviation equipment. An object of this invention is to develop a new aerodynamic device which can extend the range of aerodynamic devices for aviation, increase the efficiency of the air flow power use, increase the efficiency of the lifting force and improve the efficiency of controlling the wing resultant forces. For this purpose, the aerodynamic device has an aerodynamic wing (2) with a blower (1) of gaseous working fluid (such as air) mounted above the wing (2), in accordance with the invention, the aerodynamic wing (2) has a specific shape it is designed in the form of a double-curved open surface made up by a system of longitudinal grooves (7,8) along the whole wing surface The wing (2) has a convergent segment (4) and a divergent segment (6); between the convergent and the divergent segments there is a smooth transitional segment (5). The wing outlines have end elements (11). In the convergent and the divergent segments of the wing lower surface which is not blown by air, there is a controlled drive system (10) for the wing surface cambering and area changing. The divergent segment tip on the wing trailing edge has a deflectable controlled element (9). The structural parts of the present invention meet special conditions.

    摘要翻译： 本发明涉及航空设备。 本发明的目的是开发一种新的空气动力装置，其可以扩展用于航空的空气动力装置的范围，提高空气流动功率利用的效率，提高提升力的效率并提高控制翼的合力的效率 。 为此，空气动力学装置具有气动翼（2），其具有安装在机翼（2）上方的气态工作流体（例如空气）的鼓风机（1），根据本发明，气动翼（2）具有 特定形状被设计成由沿着整个机翼表面的纵向槽（7,8）的系统组成的双曲面开口表面。翼（2）具有收敛段（4）和发散段 （6）; 在收敛和发散段之间有一个平滑的过渡段（5）。 机翼轮廓有端点元素（11）。 在未被空气吹送的翼下表面的收敛和发散段中，存在用于机翼表面弯曲和区域变化的受控驱动系统（10）。 机翼后缘上的发散段尖端具有可偏转控制元件（9）。 本发明的结构部分满足特殊条件。

    Autonomous active flow control system
    9.
    发明公开
    Autonomous active flow control system 审中-公开
    Autonomes aktives Flusssteuerungssystem

    公开(公告)号：EP2955105A1

    公开(公告)日：2015-12-16

    申请号：EP14460033.5

    申请日：2014-06-10

    申请人： Instytut Lotnictwa ,  Fraunhofer-Gesellschaft zur Förderung der angewandten Forschung e.V.

    发明人： Stalewski, Wienczyslaw ,  Krzysiak, Andrzej ,  Schüller, Martin

    IPC分类号： B64C9/38 ,  B64C21/00 ,  B64C21/02 ,  B64C21/04

    CPC分类号： B64C9/38 ,  B64C21/04 ,  B64C2230/04 ,  B64C2230/06 ,  Y02T50/166 ,  Y02T50/32

    摘要： The system comprises a main wing (3) with deflected flap (5), a blowing arrangement (1) with a number of nozzles located in front of the deflected flap (5) along the trailing edge of the main wing (3), static pressure sensors (4) fastened to the deflected flap (5), flight sensors (7) for measuring aircraft flight parameters, activating device for activating the blowing arrangement (1), and a control unit (6) connected to the sensors and activating device. The each nozzle is in the form of triple mini nozzle (2) with one inlet channel (10), streamlined collection chamber (9) and three outlet channels (11). wherein the outlet openings of the outlet channels (11) are located on the trailing edge of the main wing (3) above the axis of rotation of the flap (5) and the static pressure sensors (4) are located on the upper surface of the deflected flap (5), close to the flap trailing edge.

    摘要翻译： 该系统包括具有偏转翼片（5）的主翼（3），具有位于主翼（3）的后缘处的偏转翼片（5）前面的多个喷嘴的吹风装置（1），静止 紧固到偏转翼片（5）的压力传感器（4），用于测量飞行器飞行参数的飞行传感器（7），用于启动吹风装置（1）的启动装置;以及连接到传感器和启动装置的控制单元 。 每个喷嘴是具有一个入口通道（10），流线型收集室（9）和三个出口通道（11）的三重迷你喷嘴（2）的形式。 其中所述出口通道（11）的出口开口位于所述主翼（3）的位于所述挡板（5）的旋转轴线上方的后缘上，并且所述静压传感器（4）位于所述主翼 偏转翼片（5），靠近翼片后缘。

    FLOW CONTROL ACTUATORS
    10.
    发明公开
    FLOW CONTROL ACTUATORS 审中-公开
    执行器流量控制

    公开(公告)号：EP2059441A1

    公开(公告)日：2009-05-20

    申请号：EP07804107.6

    申请日：2007-08-31

    申请人： BAE Systems plc

    发明人： COOK, Michael, Victor ,  WARSOP, Clyde

    IPC分类号： B64C9/38 ,  B64C15/14 ,  B64C21/04

    CPC分类号： B64C9/38 ,  B64C15/14

    摘要： A flow control actuator (10) for a body exposed to fluid flow comprises first and second flow surfaces (14, 16) spaced to define an elongate gap (20) therebetween. An elongate control element is disposed in or adjacent the gap and has an externally facing arcuate surface and defines a first slot (24) between the control element and said first flow surface and a second slot between said control element and said second flow surface (26). The control element (22) is moveable to allow the width of said slots to be adjusted generally proportionally. The flow of pressurised flow control fluid passes from a plenum chamber (30) out through one or both slots (24, 26) to be deflected around the arcuate surface under the influence of the Coanda effect. The flow control actuator (10) may be provided in the trailing or leading edge of an aerofoil; alternatively it may be provided between two surfaces spaced to provide said gap but otherwise providing a generally continuous surface.