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1. 发明申请

US20220348313A1 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.

2. 发明申请

US20210253222A1 HYDRAULIC CONTROL SYSTEMS AND METHODS FOR COMPONENTS OF AN AIRCRAFT 有权
公开(公告)号：US20210253222A1
公开(公告)日：2021-08-19
申请号：US16789585
申请日：2020-02-13
申请人： THE BOEING COMPANY
发明人： Drew M. Thompson , Patrick M. Fahey , Paul Smith , Gen Matsui , John D. Farmer , Frank L. Wichman
IPC分类号： B64C13/40 , B64C13/36 , F15B20/00
摘要： A hydraulic system for a vehicle includes a hydraulic monitoring control unit configured to receive an operational signal from a sub-system of the vehicle and control flow of hydraulic fluid to actuators of components based on the operational signal. The hydraulic monitoring control unit is configured to bypass the flow of the hydraulic fluid in relation to a subset of the actuators in response to the operational signal indicating an altered operational state of the sub-system.

3. 发明授权

US10889369B2 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.

4. 发明授权

US10538310B2 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.

5. 发明授权

US10253838B2 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.

6. 发明申请

US20180274563A1 Aircraft Hydraulic Systems Having Shared Components 审中-公开
公开(公告)号：US20180274563A1
公开(公告)日：2018-09-27
申请号：US15466655
申请日：2017-03-22
申请人： Bell Helicopter Textron Inc.
发明人： Carl Theodore Elving , Robert Paul Reynolds , David Alan Hawthorne , Carlos Alexander Fenny
IPC分类号： F15B11/17 , F15B1/26 , B64D29/02 , B64C29/00 , B64C13/36
CPC分类号： F15B11/17 , B64C13/36 , B64C13/40 , B64C13/42 , B64C27/28 , B64C29/0033 , B64D29/02 , B64D41/00 , F15B1/26 , F15B18/00 , F15B2211/20507 , F15B2211/20523 , F15B2211/20576 , F15B2211/7142 , Y02T50/44
摘要： A hydraulic system for an aircraft having an engine and an auxiliary power unit includes a first hydraulic subsystem including a first hydraulic pump and a first set of hydraulic-powered components in fluid communication with the first hydraulic pump. The first hydraulic pump is powered by the engine to pump shared hydraulic fluid to the first set of hydraulic-powered components. The hydraulic system includes a second hydraulic subsystem including a second hydraulic pump and a second set of hydraulic-powered components in fluid communication with the second hydraulic pump. The second hydraulic pump is powered by the auxiliary power unit to pump the shared hydraulic fluid to the second set of hydraulic-powered components. A shared return line subsystem and reservoir is in fluid communication with the first and second hydraulic subsystems to return the shared hydraulic fluid to the first and second hydraulic pumps.

7. 发明授权

US09663221B2 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.

8. 发明授权

US09644648B2 Systems and methods for heat balance and transport for aircraft hydraulic systems 有权
公开(公告)号：US09644648B2
公开(公告)日：2017-05-09
申请号：US13937490
申请日：2013-07-09
申请人： The Boeing Company
发明人： Jianmin Liao
IPC分类号： F15B21/04 , B64C13/42 , B64C13/36 , B64C25/22 , F15B1/26
CPC分类号： F15B21/042 , B64C13/36 , B64C13/42 , B64C25/22 , F15B1/26 , F15B2211/20576 , F15B2211/611 , F15B2211/62
摘要： A thermal management system is provided. The thermal management system includes a first hydraulic system for circulating a first hydraulic fluid at a first temperature, a second hydraulic system for circulating a second hydraulic fluid at a second temperature that is higher than the first temperature, and a heat exchanger coupling the first hydraulic system to the second hydraulic system, wherein the heat exchanger is configured to exchange heat between the first hydraulic fluid and the second hydraulic fluid.

9. 发明授权

US08833695B2 Aircraft hydraulic air bleed valve system 有权
标题翻译：飞机液压排气阀系统
公开(公告)号：US08833695B2
公开(公告)日：2014-09-16
申请号：US13274384
申请日：2011-10-17
申请人： Sanjeev N. Dhuri , Rahul Bangar
发明人： Sanjeev N. Dhuri , Rahul Bangar
IPC分类号： B64C13/36 , F16K24/00 , F01D17/26 , F15B21/04
CPC分类号： F16K24/04 , F01D17/26 , F15B21/044 , F16K24/00 , Y10T137/0318 , Y10T137/0379 , Y10T137/3143 , Y10T137/7759
摘要： An aircraft hydraulic air bleed valve system having an air vent valve connected to an electronic controller where the opening of the air vent valve is permitted only when the aircraft is in a pre-determined flight mode where the aircraft flight mode is determined by a gyroscope connected to the controller.
摘要翻译：一种具有连接到电子控制器的排气阀的飞机液压排气阀系统，其中仅当飞行器处于预先确定的飞行模式时才允许排气阀的打开，其中飞行器飞行模式由连接的陀螺仪确定到控制器。

10. 发明申请

US20130020444A1 Trailing Edge Split Flap with Pneumatic Actuation 有权
标题翻译：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。

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