利索-全球专利检索

  1. Login
  2. Sign Up

Search Results

82 records (took 0.017 seconds)

    FLOW BODY FOR AN AIRCRAFT FOR PASSIVE BOUNDARY LAYER SUCTION
    3.
    发明公开
    FLOW BODY FOR AN AIRCRAFT FOR PASSIVE BOUNDARY LAYER SUCTION 审中-公开
    用于被动式边界层吸气式飞机的流体

    公开(公告)号：EP3199450A1

    公开(公告)日：2017-08-02

    申请号：EP16153298.1

    申请日：2016-01-29

    Applicant: Airbus Operations GmbH

    Inventor： Heller, Gerd

    IPC: B64C5/06 ,  B64C21/06

    CPC classification number: B64C21/06 ,  B64C5/02 ,  B64C5/06 ,  B64C2230/04 ,  Y02T50/166

    Abstract: A flow body (34) of an aircraft comprises a flow surface (46) exposed to an airstream during flight of the aircraft, at least one structural component (38) attached to an interior of the flow surface (46), at least one perforated area (12) comprising a plurality of openings extending through the flow surface (46), a manifold (36) positioned interior to the flow surface (46) in fluid communication with the openings and upstream of the at least one structural component (38), and at least one suction duct having a first end and a second end, the first end being in fluid communication with the manifold and the second end placed exterior to the flow surface (46) downstream of the at least one structural component (38). The at least one suction duct (42, 44) comprises a suction opening (56, 58) facing away from the first end. Further, the suction opening is adapted for inducing a suction force into the at least one suction duct (42, 44) when the flow surface (46) is exposed to an airstream during flight, thereby inducing a flow of air from through the openings to the suction opening (56, 58).

    Abstract translation: 飞行器的流体（34）包括在飞行器飞行期间暴露于气流的流动表面（46），至少一个连接到流动表面（46）内部的结构部件（38），至少一个穿孔的 包括延伸穿过流动表面（46）的多个开口的区域（12），位于流动表面（46）内部且与开口流体连通并且在至少一个结构部件（38）的上游的歧管（36） 以及至少一个具有第一端和第二端的吸气管，第一端与歧管流体连通并且第二端位于至少一个结构部件（38）下游的流动表面（46）外部， 。 所述至少一个吸气管道（42,44）包括背对第一端部的抽吸开口（56,58）。 此外，当流动表面（46）在飞行期间暴露于气流时，吸入开口适于引入吸入力到所述至少一个吸入管道（42,44）中，由此引导空气流从开口流到 吸入口（56,58）。

    METHODS AND APPARATUS TO CONTROL AIRCRAFT HORIZONTAL STABILIZERS
    4.
    发明公开
    METHODS AND APPARATUS TO CONTROL AIRCRAFT HORIZONTAL STABILIZERS 审中-公开
    VERFAHREN UND VORRICHTUNG ZUR STEUERUNG VONFLUGZEUGSHÖHENFLOSSEN

    公开(公告)号：EP3020630A1

    公开(公告)日：2016-05-18

    申请号：EP15192416.4

    申请日：2015-10-30

    Applicant: The Boeing Company

    Inventor： MOORE, Jonathan Kyle ,  BOCK, Brian Charles ,  COLEMAN, Edward E

    IPC: B64C13/16 ,  G05D1/06 ,  G05D1/08

    CPC classification number: B64C13/16 ,  B64C5/02 ,  B64C5/06 ,  B64C9/06 ,  G05D1/085

    Abstract: Methods and apparatus to control aircraft horizontal stabilizers are described herein. One described method includes calculating, using a processor (612), a desired movement of a horizontal stabilizer (104) of an aircraft to counteract a pitching moment of the aircraft, and controlling the horizontal stabilizer based on the desired movement.

    Abstract translation: 本文描述了控制飞机水平稳定器的方法和装置。 一种所描述的方法包括使用处理器（612）计算飞行器的水平稳定器（104）的期望运动以抵消飞行器的俯仰力矩，并且基于期望的运动来控制水平稳定器。

    Aerospace vehicle yaw generating tail section
    9.
    发明公开
    Aerospace vehicle yaw generating tail section 有权
    船尾部偏航在飞行器上运动生成

    公开(公告)号：EP2412628A2

    公开(公告)日：2012-02-01

    申请号：EP11172334.2

    申请日：2011-07-01

    Applicant: Rolls-Royce plc

    Inventor： Edwards, Huw Llewelyn ,  Husband, Stephen Mark ,  Fletcher, Paul

    IPC: B64C5/06 ,  B64C15/00

    CPC classification number: B64C5/06 ,  B64C15/00

    Abstract: A tail section (251) for an aerospace vehicle is provided. The tail section (251) comprises a rudder (253) which is movable about an axis to generate a yawing moment on the aerospace vehicle. The tail section (251) further comprises a thruster (257) having, in flow series, an air intake, an electrically powered device for accelerating the air received through the intake, and an air outlet which directs the accelerated air to increase the yawing moment generated by the rudder (253).

Patent Agency Ranking