| 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 | SPRING RETURN ACTUATOR | US13831851 | 2013-03-15 | US20140260953A1 | 2014-09-18 | Gaby Jaccoby; Ido Navon; Yoel Hadar; Efraim Maayan |
| Aspects of embodiments of the invention relate to a spring-return actuator comprising a first piston movable between a first and a second position by pressurized fluid to move a load; a safety system comprising a second piston movable by the pressurized fluid to arm the safety system and which returns the first piston from the second position to the first position when de-energizing the 3/2 pilot valve or when the pressure of the pressurized fluid drops below a safety pressure threshold; and a differential fluid channel for providing the pressurized fluid and configured so that the first piston while working to move the load remains substantially disengaged from the safety system being armed. | ||||||
| 122 | 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. | ||||||
| 123 | 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. | ||||||
| 124 | 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. | ||||||
| 125 | 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 | ||||||
| 126 | 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. | ||||||
| 127 | 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. | ||||||
| 128 | 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. | ||||||
| 129 | 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. | ||||||
| 130 | 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. | ||||||
| 131 | 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. | ||||||
| 132 | 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. | ||||||
| 133 | 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. | ||||||
| 134 | 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. | ||||||
| 135 | 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). | ||||||
| 136 | 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. | ||||||
| 137 | 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. | ||||||
| 138 | 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. | ||||||
| 139 | 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. | ||||||
| 140 | 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. | ||||||
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