序号 专利名 申请号 申请日 公开(公告)号 公开(公告)日 发明人
121 Single effect hydraulic cylinder US13074629 2011-03-29 US08826799B2 2014-09-09 Marc Anscieau; Alain Bignolais
The invention belongs to the field of single-effect hydraulic cylinders. It relates to a device that makes it possible to limit the pressure in the pressurization chamber of a single-effect cylinder when the rod thereof is in a particular range of longitudinal positions of safety, while respecting the operating safety of the device, that is, in the case that the power supply of the pilot valves of the distributors and of the hydraulic pump is cut, the rod of the cylinder remains in its position if this position does not lie within the safety position range.
122 PNEUMATIC ACTUATOR AIR FLOW CONTROL SYSTEM US13029472 2011-02-17 US20120211681A1 2012-08-23 James Wang
A pneumatic actuator air flow control system includes a pneumatic rotary actuator (PRA) and a solenoid air flow control valve (SAFCV). The PRA contains an air reservoir and two pistons on which a number of actuated racks are formed and engaged therewith, so the piston can drive the actuated rack and a pinion when the piston moves to achieve the goal of opening or closing the valve body. The SAFCV includes a flow control valve body (FCVB), a pilot solenoid valve (PSV) and a switch system, wherein the FCVB and the PRA can be connected to direct the pressurized air into the air reservoir, and the PSV is used to control the pressurized air in and out of the PRA to change the rotation direction of the pinion. Additionally, the switch system allows users to switch between a double-acting and fail-safe operation. When there is no pressurized air and/or electrical power and if an emergent need to open or close the valve, a manual override in the PSV can be used without further installation of a declutchable manual gear operator or external piping when there is no pressurized air and/or electrical power.
123 HYDRAULIC SYSTEM FOR AIRCRAFT ACTUATORS US13114849 2011-05-24 US20110290353A1 2011-12-01 Atsushi FUKUI; Yasuyuki SHIRAI
An electric motor drives a variable capacity backup hydraulic pump that can supply pressure oil to an actuator when a loss or reduction occurs in the function of an aircraft central hydraulic power source. A power source unit rectifies electric power supplied from a variable frequency supply. A driver supplies the electric power from the power source unit, and drives the electric motor so as to rotate the pump at a predetermined constant rotational speed. The constant rotational speed is set, based on the change in the efficiency of each of the pump, the electric motor, and the driver with respect to the rotational speed of the pump, such that the overall efficiency, obtained as a product of these efficiencies, has a maximum value.
124 SINGLE EFFECT HYDRAULIC CYLINDER US13074629 2011-03-29 US20110239855A1 2011-10-06 Marc Anscieau; Alain Bignolais
The invention belongs to the field of single-effect hydraulic cylinders. It relates to a device that makes it possible to limit the pressure in the pressurization chamber of a single-effect cylinder when the rod thereof is in a particular range of longitudinal positions of safety, while respecting the operating safety of the device, that is, in the case that the power supply of the pilot valves of the distributors and of the hydraulic pump is cut, the rod of the cylinder remains in its position if this position does not lie within the safety position range
125 Pneumatic Actuator Structure US12993504 2009-11-20 US20110226124A1 2011-09-22 James Wang; Yung-Chuan Chen
An actuator structure includes two half cylinders made respectively from the same mold and the two half cylinders engaged with each other to form an actuator. The actuator has an air reservoir chamber and a vane chamber dividing by a dividing unit, and the vane chamber has a vane inside. An O-shaped ring is formed around the vane and an elastic stopping edge is formed protrudingly from the O-shaped ring and linearly contacted an inner surface of the actuator. The volume ratio of the air reservoir chamber and the vane chamber is about three to one, and a channel groove is formed at an interface of the two half cylinders to connect an air inlet hole and a left side and a right side wall of the actuator. A fail-safe or dual-movement control structure is formed to control the direction of air supply to drive the shaft to rotate toward a predetermined direction, or utilizing the compressed air in the air reservoir chamber to force the vane to restore to its original position.
126 APPARARTUS TO INCREASE A FORCE OF AN ACTUATOR HAVING AN OVERRIDE APPARATUS US12648135 2009-12-28 US20110155937A1 2011-06-30 David Anthony Arnold
Apparatus to increase a force of an actuator having an override apparatus are described herein. An example fluid control system includes a first fluid control apparatus to fluidly couple a control fluid supply source to a control actuator via a first passageway. The control fluid supply source provides a control fluid to move a control actuator member of the control actuator in a first direction or a second direction opposite the first direction when the control actuator is in the operational state. A second fluid control apparatus is in fluid communication with the first fluid control apparatus and is configured to fluidly couple an override actuator to the control actuator via a second passageway when the control actuator is in a non-operational state. The override actuator is operatively coupled to the control actuator.
127 Local backup hydraulic actuator for aircraft control systems US12502958 2009-07-14 US07870726B2 2011-01-18 Gen Matsui
A backup system is provided that has a local electric motor and pump for some or all of hydraulic actuators. A local backup hydraulic actuator has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized fluid from a hydraulic system and the fluid flow to the chambers is controlled by a servo valve. If the hydraulic system fails, the electronic controller detects the failure by observing the signal indicative of the pressure from the pressure sensor, and the controller powers the local hydraulic pump to provide high pressure hydraulic fluid to the hydraulic actuator via the servo valve.
128 VALVE DEVICE AND METHOD FOR THE ACTIVATION OF AN ACTUATING DRIVE ACTED UPON WITH PRESSURE MEDIUM BY A POSITION CONTROLLER US12539123 2009-08-11 US20100037762A1 2010-02-18 Thomas KLEEGREWE; Dieter BINZ; Stefan TABELANDER
A valve device and method for the activation of an actuating drive, which can be acted upon with a pressure medium by a position controller. The position controller can be acted upon by a working connection of the actuating drive with a pressure medium which can be delivered to the position controller via a feed pressure connection. The valve device includes means for blocking the actuating drive in the event of a failure of the feed pressure. The blocking means includes a pilot-controlled shut-off valve which is arranged in the region of the working connection of the position controller, and a pilot control valve arrangement connected to the feed pressure connection of the position controller to control pressure of the feed pressure connection and cause the pilot-controlled shut-off valve to assume a shut-off position when the feed pressure falls below a defined first limit value.
129 HYDRAULIC SYSTEM FOR AIRCRAFT US12413818 2009-03-30 US20090242694A1 2009-10-01 Hiroki Oyama
A hydraulic system for aircraft operating devices provides a secondary pressure source for direction and deceleration control in case of loss of pressure from a primary pressure source. The system includes multiple pressure accumulators that include a primary accumulator, which supplies pressurized fluid to a first actuator, and first and second secondary accumulators, which supply pressurized fluid to second and third actuators, respectively. If the primary accumulator is disabled, the first secondary accumulator will supply pressurized fluid to the first actuator. If the first secondary accumulator is disabled, the second secondary accumulator will supply pressurized fluid to the second actuator. By providing multiple, substantially independent accumulators, direction and deceleration control is maintained even in the event of loss of the primary accumulator.
130 Hydraulic switching mechanism for longwall supports US11420317 2006-05-25 US07478884B2 2009-01-20 Willi Kussel
A hydraulic switching mechanism for longwall supports. The present invention provides a hydraulic system that is controlled by its own pressure and may be adaptable to those currently in use so that life-threatening and costly faults cannot occur. With the present invention, the retrofitting of existing systems may be made possible without significant expenditure in modification.
131 Trim Actuator Actuating System for a Hydraulically Actuatable Trimmable Horizontal Stabilizer Actuator US12065928 2006-09-06 US20080203234A1 2008-08-28 Gunnar Haase
The present invention relates to a trim actuator actuating system having two separate hydraulic power supply systems, through which it is possible for the first time to use a hydraulic linear actuator as a trimmable horizontal stabilizer actuator in an aircraft. The at least one hydraulic linear actuator is coupled to the first power supply system in such a way that it applies hydraulic power to the linear actuator during normal operation. In order to ensure the application of pressure to the hydraulic linear actuator in case of breakdown, in such a case, the pressure application to the hydraulic linear actuator is maintained with the aid of the second hydraulic power supply system.
132 HYDRAULIC SWITCHING MECHANISM FOR LONGWALL SUPPORTS US11420317 2006-05-25 US20070044647A1 2007-03-01 Willi Kussel
A hydraulic switching mechanism for longwall supports. The present invention provides a hydraulic system that is controlled by its own pressure and may be adaptable to those currently in use so that life-threatening and costly faults cannot occur. With the present invention, the retrofitting of existing systems may be made possible without significant expenditure in modification.
133 Local backup hydraulic actuator for aircraft control systems US11108036 2005-04-14 US20060226285A1 2006-10-12 Gen Matsui
A backup system is provided that has a local electric motor and pump for some or all of the hydraulic actuators on an aircraft. A local backup hydraulic actuator has two power sources, hydraulic as primary and electrical as backup. During normal operation, the hydraulic actuator receives pressurized fluid from a hydraulic system and the fluid flow to the chambers is controlled by a servo valve. If the hydraulic system fails, the electronic controller detects the failure by observing the signal indicative of the pressure from the pressure sensor, and the controller powers the local hydraulic pump to provide high pressure hydraulic fluid to the hydraulic actuator via the servo valve.
134 Assembly for a chassis stabilizing system US10924762 2004-08-24 US20050166750A1 2005-08-04 Dirk Kesselgruber
An assembly including a fluid pressure actuator (10), which has a guide part (22) and an active part (24) movable relative thereto, and a fluid pressure source (14) which is in communication with the fluid pressure actuator in order to supply the latter with fluid which is under pressure, is characterized in that a locking device (12) is provided which can interrupt the connection of the fluid pressure actuator (10) with the fluid pressure source (14), that a control unit (16) is provided which controls the locking device, and that the fluid pressure actuator (10) is provided with a sensor (30) by means of which the control unit (16) can determine the position of the active part (24) relative to the guide part (22).
135 Redundant flow control for hydraulic actuator systems US10746033 2003-12-23 US20050132877A1 2005-06-23 Kenneth Hart
Two or more flow control valves may be used to provide redundant flow control for a hydraulic actuator or servoactuator. The flow control valves include a sleeve, a bypass control spool, and a primary control spool. Under normal operating conditions, each bypass control spool is stationary relative to the sleeve and the flow control valve functions as a four-way hydraulic flow control valve. Each flow control valve is connected to a bypass-shutoff valve including a bypass spool that is moveable from a shut-off position to a bypass position. Upon supply pressure failure to one flow control valve, the bypass spool moves to the bypass position, reducing pressure in the corresponding actuator piston chambers. When a primary control spool becomes jammed, the corresponding bypass control spool moves within its sleeve allowing a bypass groove to port control pressure to the return line, thereby reducing pressure in the corresponding actuator piston chambers.
136 Electro-hydrostatic actuator with a failsafe system US10622949 2003-07-18 US06892534B2 2005-05-17 Gabriel Silva; David Faso
An electro-hydrostatic actuator unit that contains a sealed pressurized housing filled with a dielectric fluid. A bi-directional motor is immersed in the fluid and drives a gear pump for exchanging fluid via a control circuit between the chambers of a bi-directional hydraulic actuator in response to an input from a controller. The chambers are separated by a piston and a piston rod is connected to an external load such as a plunger type valve. A failsafe circuit is also provided which is arranged to override the control circuit in the event a failsafe condition is detected by the unit controller. The failsafe circuit contains a motor driven pump that provides high pressure fluid from the pressurized reservoir to an accumulator. Valves are arranged to shut down the control circuit and deliver fluid from the accumulator to one of the cylinder chambers to rapidly move the actuator to a desired failsafe position. Both motor drive pumps, the actuator, cylinder, and the controller are fully immersed in the fluid reservoir.
137 Actuator having both a hydraulic mode and a mechanical mode of operation US10917370 2004-08-13 US20050056146A1 2005-03-17 Marc Quenerch'Du
The invention relates to an actuator comprising a body with a cylindrical cavity, and a rod extending through one end of the cavity, being secured with a piston mounted to slide axially in the cavity so as to define therein two hydraulic chambers, the actuator including additional means for extending the rod, which comprise: means for preventing the rod from rotating relative to the body of the actuator; a nut rigidly secured to the rod; a screw extending axially inside the cavity and co-operating with the nut; a drive shaft extending axially inside the cavity and being free to turn, the screw being mounted to slide without rotation along the shaft; and rotary drive means for driving the drive shaft.
138 Transfer valve system US10405720 2003-04-02 US06823669B2 2004-11-30 Boris K. Kogan; William F. Lange
A hydraulic transfer valve system has a main valve selectively placing one of a primary and secondary hydraulic system in communication with a hydraulic load. A pilot valve provides a toggling action between the primary and secondary systems with respect to pressure changes in such systems.
139 Hydraulic valve system US10422209 2003-04-24 US06805161B2 2004-10-19 Siegfried Zenker; Thorkild Christensen
A hydraulic valve system (1) has a supply connection arrangement, having a high-pressure connection (P) and a low-pressure connection (T), a working connection arrangement, having two working connections (A, B), which can be connected with a hydraulic motor (2), and a directional valve (4) between the supply connection arrangement (P, T) and the working connection arrangement (A, B), which is connected with the working connection arrangement (A, B) via working lines (17, 18), in which are arranged check valves (21, 22), which can be opened by means of pressure.
140 Hydraulic circuit architecture US10483498 2004-01-12 US20040195909A1 2004-10-07 Walid Hamzeh; Jerome Libourel
The invention relates to an architecture for a hydraulic circuit associated with actuators (100), such as actuators for airplane brakes, the architecture comprising a main hydraulic circuit (C) having hydraulic components (4, 5 101, 6) and adapted to convey hydraulic fluid pressurized by at least one pressure generator (2) associated with a main supply (1) to the actuators (100). According to the invention, the architecture includes an emergency system comprising an auxiliary supply (8) permanently fed by a return circuit (R) collecting the returns from all of the hydraulic components (4, 5, 101, 6), the auxiliary supply (8) being connected to the main supply (1) via a relief valve (9), said emergency system further comprising an electrically driven pump unit (10) arranged to take fluid from the auxiliary supply (8) and to inject it into the main circuit (C) downstream from a general check valve (3).
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