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115 条记录 (耗时 0.023 秒)

    CONTROL SYSTEM FOR AN AIRCRAFT
    1.
    发明申请
    CONTROL SYSTEM FOR AN AIRCRAFT 有权

    公开(公告)号：US20220348313A1

    公开(公告)日：2022-11-03

    申请号：US17731735

    申请日：2022-04-28

    申请人： Airbus Operations GmbH ,  Airbus Operations (S.A.S.)

    发明人： Alena Kaufmann ,  Jérôme Robillard

    IPC分类号： B64C13/36 ,  B64C9/08

    摘要： A control system for an aircraft includes a hydraulic pump, first hydraulic line, second hydraulic line, a first actuator coupled with a first control surface, a second actuator coupled with a second control surface, and a third actuator coupled with a third control surface. The first control surface and the second control surface are at a distance to each other and symmetrically relative to a symmetry axis. The third control surface is substantially on the symmetry axis, and the first hydraulic line and the second hydraulic line are connected to the hydraulic pump. The first actuator is connected to the first hydraulic line, and the second actuator is connected to the second hydraulic line. The third actuator is connected to the first hydraulic line downstream of the first actuator at a junction point, and the first hydraulic line at least partially includes a larger diameter than the second hydraulic line.

    Passive gust alleviation systems for aircraft devices
    3.
    发明授权
    Passive gust alleviation systems for aircraft devices 有权

    公开(公告)号：US10889369B2

    公开(公告)日：2021-01-12

    申请号：US16115919

    申请日：2018-08-29

    申请人： Bell Helicopter Textron Inc.

    发明人： George R. Decker

    IPC分类号： B64C13/16 ,  B64C13/36 ,  B64C3/56 ,  B64C29/00 ,  B64C3/38

    摘要： Described herein is an apparatus comprising an aircraft wing and a trailing edge aerodynamic surface connected to a trailing edge of the aircraft wing via a piston assembly in which the piston assembly holds the trailing edge aerodynamic surface in a neutral position relative to the aircraft wing at a constant supply pressure. The piston assembly may be implemented using a pneumatic piston or a hydraulic piston. A first end of the piston assembly may be connected to the aircraft wing and a second end of the piston assembly may be connected to the trailing edge aerodynamic surface. The piston assembly may include a pressure relief valve which may open or close, raising or lowering the aerodynamic surface, responsive to lift load on the aircraft wing.

    Near synchronous distributed hydraulic motor driven actuation system
    4.
    发明授权
    Near synchronous distributed hydraulic motor driven actuation system 有权

    公开(公告)号：US10538310B2

    公开(公告)日：2020-01-21

    申请号：US15613618

    申请日：2017-06-05

    申请人： Parker-Hannifin Corporation

    发明人： Eric Alexander Polcuch

    IPC分类号： B64C9/16 ,  B64C9/22 ,  B64C13/50 ,  B64C9/32 ,  B64C13/36

    摘要： A control system may be used to control actuators that actuate movement of flight control surfaces of an aircraft. Each actuator is couplable to a flight control surface and includes a motion control assembly having a hydraulic motor and a drive path from the hydraulic motor to the flight control surface. Each hydraulic motor includes an extend port and a retract port. The system includes a hydraulic control module fluidly connected to the extend port and the retract port of each hydraulic motor and a controller operable to output hydraulic power from the hydraulic control module to the motion control assembly to actuate movement of the flight control surfaces. The controller is configured to identify an actuator that positionally leads the other actuators and reduce hydraulic power to the motion control assembly assigned to such actuator.

    Linear hydraulic damping device
    5.
    发明授权
    Linear hydraulic damping device 有权

    公开(公告)号：US10253838B2

    公开(公告)日：2019-04-09

    申请号：US15088203

    申请日：2016-04-01

    申请人： Goodrich Actuation Systems SAS

    发明人： Jérôme Socheleau

    IPC分类号： F16F9/10 ,  B64C13/36 ,  F16F9/34 ,  F16F9/512 ,  F15B15/14 ,  F16F9/348

    摘要： A hydraulic circuit comprising an actuator having an extension chamber and a retraction chamber, a bypass passage provided in the hydraulic circuit between defined between the extension chamber and the retraction chamber, and a damping device. The damping device includes first and second chambers separated by a wall, a first movable element received within the first chamber and a second movable element received within the second chamber. The first moveable element is movable from its closed position against the force of the first spring by entry of fluid into the second chamber, and the second movable member being movable from its closed position against the force of the second spring by entry of fluid into the first chamber.

    Actuator device for flight control surface, flight control surface of aircraft, and aircraft
    7.
    发明授权
    Actuator device for flight control surface, flight control surface of aircraft, and aircraft 有权

    公开(公告)号：US09663221B2

    公开(公告)日：2017-05-30

    申请号：US14105763

    申请日：2013-12-13

    申请人： MITSUBISHI AIRCRAFT CORPORATION

    发明人： Kenya Ishihara

    IPC分类号： B64C13/36 ,  B64C9/02 ,  B64C9/00

    CPC分类号： B64C13/36 ,  B64C9/02 ,  B64C2009/005

    摘要： To provide an actuator device for a flight control surface which can reduce a stress applied to the flight control surface when one of two actuators is operated. The present invention relates to a hydraulically-operated actuator device 30 which drives a flight control surface of an aircraft 1, including a first actuator 31A that is provided with a first piston rod 39A, and drives an aileron body 11; a second actuator 31B that is provided with a second piston rod 39B, and drives the aileron body 11 when the function of the first actuator 31A is lost or reduced; and a single second connection fitting 41 to which the first piston rod 39A and the second piston rod 39B are both connected, wherein the first actuator 31A and the second actuator 31B are connected to the aileron body 11 via the second connection fitting 41.

    Trailing Edge Split Flap with Pneumatic Actuation
    10.
    发明申请
    Trailing Edge Split Flap with Pneumatic Actuation 有权
    带气动启动的后缘分流板

    公开(公告)号：US20130020444A1

    公开(公告)日：2013-01-24

    申请号：US13187634

    申请日：2011-07-21

    申请人： Michael A. Balzer ,  Gregory M. Santini ,  Michael K. Klein

    发明人： Michael A. Balzer ,  Gregory M. Santini ,  Michael K. Klein

    IPC分类号： B64C3/50 ,  B64C13/36

    CPC分类号： B64C9/16 ,  B64C3/46 ,  Y02T50/14 ,  Y02T50/32 ,  Y02T50/44

    摘要： A system for pneumatically actuating a split flap hingedly mounted near or at a trailing edge of an airfoil. The system includes a bladder system disposed between the split flap and the upper surface of the airfoil. The split flap is a small-chord (usually 1-3% of total wing chord) long-span lower panel which separates from the airfoil trailing edge by means of a hinge or a flexible lower skin. Deployment of the split flap is actuated pneumatically by the inflatable bladder system. The split flap may exist at a fixed wing trailing edge, a moving flap trailing edge, or an empennage trailing edge. The pneumatic bladder provides distributed force to extend and retract the split flap. This pneumatic approach eliminates extra drag, reduces cost and weight, and lessens flutter concerns.

    摘要翻译： 一种用于气动地致动分开的翼片的系统，其铰接地安装在翼型件的后缘附近或其后缘。 该系统包括设置在分裂翼片和翼型件的上表面之间的气囊系统。 襟翼是一个小和弦（通常是总翼弦的1-3％）长跨度下面板，通过铰链或柔性下皮肤与翼型后缘分离。 通过可充气膀胱系统气动地驱动分裂瓣的部署。 分裂瓣可以存在于固定的翼缘后缘，移动的翼片后缘或尾翼的后缘。 气动气囊提供分布的力以延伸和缩回分裂瓣。 这种气动方式消除了额外的阻力，降低了成本和重量，并减轻了颤抖的担忧。