| 序号 | 专利名 | 申请号 | 申请日 | 公开（公告）号 | 公开（公告）日 | 发明人 |
|---|---|---|---|---|---|---|
| 181 | Adjustment System for a Hydraulic Actuator | US15617481 | 2017-06-08 | US20180142711A1 | 2018-05-24 | Paul BREWER; Reg RAVAL; Andrew WALTON |
| The present disclosure relates to an adjustment system a method for compensating for temperature variations in a spool valve. The spool valve and adjustment system may be parts in a duplex hydraulic actuator. The adjustment device comprises a spring, a pivot point, and a shape memory alloy (SMA) device. The spring and SMA device are disposed on either side of the pivot point to hold the pivot point in a first position. The SMA device is configured to change size in response to a temperature change so as move the pivot point to a second location. This may eliminate force fight in the duplex hydraulic actuator by preventing asynchronous activation of the spool valves due to thermal expansion within the spool valves. | ||||||
| 182 | Hydraulic system | US13689549 | 2012-11-29 | US09897115B2 | 2018-02-20 | Simon Meier |
| The present disclosure relates to a hydraulic system with at least two main control valves and with a hydraulic pilot control system for actuating the main control valves, wherein the hydraulic pilot control system and/or the main control valves are constructed such that the at least two main control valves open one after the other. | ||||||
| 183 | DUPLICATED HYDRAULIC CIRCUIT WITH PRESSURE REGULATION | US15630332 | 2017-06-22 | US20180002007A1 | 2018-01-04 | Pascal LEGUAY; Jean-Yves AGRESTA; Arnaud GROLL |
| The present invention relates to A device for supplying hydraulic power, the device comprising two hydraulic circuits jointly feeding multi-cylinder hydraulic power transmission means in which each cylinder is connected to a single one of the hydraulic circuits independently of the others. Each hydraulic circuit includes a hydraulic pressure and flow rate generator and a pressure control module controlling said hydraulic pressure and flow rate generator so as to regulate the pressure of said fluid flowing in said hydraulic circuit as a function of said pressure of said fluid flowing in each hydraulic circuit and possibly as a function of one or more parameters external to said device. | ||||||
| 184 | Hydraulic Devices and Methods of Actuating Same | US15615239 | 2017-06-06 | US20170370384A1 | 2017-12-28 | John Matthew Dalton; Terry Dickson |
| This disclosure includes hydraulic apparatuses and methods for redundant actuation of a hydraulic device. Some apparatuses include a hydraulic device having a first hydraulic actuator and a second hydraulic actuator, wherein each of the first and second hydraulic actuators comprises at least a first hydraulic cavity, a second hydraulic cavity, and a piston. Some apparatuses also include a controller coupled to the hydraulic device. In some embodiments, the controller is configured to receive hydraulic fluid from a fluid source via at least two parallel hydraulic lines coupled to the controller, select a first hydraulic line of the at least two parallel hydraulic lines, and transfer the hydraulic fluid from the selected first hydraulic line to a first cavity of the first hydraulic actuator to apply pressure to a first piston to actuate the hydraulic device. | ||||||
| 185 | REDUNDANT VEHICLE CONTROL SYSTEMS | US15059494 | 2016-03-03 | US20170253318A1 | 2017-09-07 | Mark Williams; William Ernest Stone; Oscar R. Arguelles; Ori Dov Chen-Zion |
| A redundant control system for a vehicle includes: one or more actuator housings; a plurality of actuator pistons coupled to the actuator housings, each of the actuator pistons mechanically coupled to one another and a common output device; a plurality of primary stages coupled to the actuator housings, each of the primary stages operatively coupled to move a respective actuator piston relative to at least one of the actuator housings, and each of the primary stages functioning independent of any other primary stage when the control system is operating in a flight-operation mode; and an auxiliary stage operatively coupled to move a first of the plurality of actuator pistons relative to at least one of the actuator housings when the control system is operating in a ground-operation mode, with each of the plurality of primary stages being responsive to movement of the first actuator piston by the auxiliary stage. | ||||||
| 186 | Pressure-balance valve for balancing fluid feed to actuator cylinders of a servo-control for controlling rotor blades of a rotorcraft | US14682327 | 2015-04-09 | US09670940B2 | 2017-06-06 | Thibaut Marger; Arnaud Groll; Jean-Romain Bihel; Clement Coic |
| A pressure-balance valve for balancing the pressures of fluids admitted into the pressure-balance valve via respective second ducts. The pressure-balance valve has both a chamber for guiding movement in translation of a piston, and also fluid flow paths, each comprising a said second duct and a first duct for admitting a fluid coming from the same fluid source as the fluid flowing in its second duct. Each of the first ducts is provided with a shutter co-operating with a ramp arranged on the piston. Movement of the piston in translation as a result of a pressure difference between the fluids respectively admitted into the second ducts causes one of the shutters to slide along the corresponding ramp and consequently allows additional fluid to be delivered from a first duct to the second duct of the same fluid flow path. | ||||||
| 187 | DYNAMIC ACTIVATION OF PUMPS OF A FLUID POWER SYSTEM | US14626676 | 2015-02-19 | US20170057619A1 | 2017-03-02 | Thomas M. Wilson; Edmond C. Chin; Mark W. Lesyna; Thomas R. Hasenoehrl |
| A method includes receiving pump cycle location data associated with a fluid power system. The fluid power system includes a plurality of pumps (including at least a first pump, a second pump, and a third pump). Based on the pump cycle location data having a first value, the method includes activating the first pump as a primary pump. Based on the pump cycle having a second value, the method includes activating the second pump as the primary pump. The method also includes activating the third pump as a secondary pump when the fluid power system is in a multiple-pump operating mode. | ||||||
| 188 | Hydraulic Valve | US15229365 | 2016-08-05 | US20170037877A1 | 2017-02-09 | Paul BREWER; Reg RAVAL; Phillip A. ROWLES |
| A spool for a hydraulic spool valve, comprising: a pressure chamber for connecting a pressure line to a hydraulic cylinder; at least one return chamber for connecting the hydraulic cylinder to a reservoir; and an actuator slot for receiving a drive lever; wherein the spool further comprises a fluid path connecting said pressure chamber to said actuator slot and a pressure plate movably mounted in the slot such that in use it is disposed between the fluid path and the drive lever. | ||||||
| 189 | Flexible response secured mechanical balancing for multiple control actuators with a common output | US14463832 | 2014-08-20 | US09470248B2 | 2016-10-18 | Gregor Paulmann |
| A flexible response secured mechanical balancing device (D) for multiple hydraulic control actuators (1-2) with a common output member (5a-b). The balancing device (D) provides flexible/continuous fluid-pressure force fight compensation. Balance valves (17-20) are commanded to balance fluid-pressure from a first fluid-pressure network (52a) of a second actuator (2). Each fluid-pressure commanded balance valve (17-20) is arranged to allow relief of differential pressure, directly into a dedicated first (52a) or second fluid-pressure network (52b). A fluid-pressure controlled locking device (21-22) is allowing inhibiting the corresponding pairs of balance valves (17-20) e.g. in case of loss of fluid-pressure. The invention typically applies to vehicles (A) including: aircrafts, rotorcrafts, drones. | ||||||
| 190 | Torque limit control | US14146504 | 2014-01-02 | US09464580B2 | 2016-10-11 | James A. Aardema; Eric Engelmann |
| A prime mover transfers power to a separate hydraulic circuits via a power take off (PTO). In some situations, a peak torque demand in one of the hydraulic circuits may cause the total torque of all hydraulic circuits to exceed a rated torque at the PTO. An apparatus measures hydraulic fluid pressure in a first hydraulic circuit and adjusts the hydraulic fluid pressure in a second hydraulic circuit. Because pressure is directly correlated to torque at a pump, by adjusting the pressure in the second circuit based on the current pressure in the first hydraulic circuit, the total torque may be capped below the maximum torque rating at the PTO. The first hydraulic circuit may have a higher priority function, such as steering, compared to that of the second hydraulic circuit which may, for example, power a tool. | ||||||
| 191 | Hybrid Hydraulic and Electrically Actuated Mobile Robot | US15016729 | 2016-02-05 | US20160151911A1 | 2016-06-02 | John Aaron Saunders; Alex Khripin; Steven Potter; Michael Patrick Murphy; Christopher Everett Thorne |
| Example embodiments may relate to a robotic system that includes a hydraulic actuator and an electric actuator both coupled to a joint of the robotic system. Operation of the actuators may be based on various factors such as based on desired joint parameters. For instance, such desired joint parameters may include a desired output torque/force of the joint, a desired output velocity of the joint, a desired acceleration of the joint, and/or a desired joint angle, among other possibilities. Given a model of power consumption as well as a model of the actuators, the robotic system may determine operating parameters such as hydraulic and electric operating parameters as well as power system parameters, among others. The robotic system may then control operation of the actuators, using the determined operating parameters, to obtain the desired joint parameters such that power dissipation in the system is minimized (i.e., maximizing actuation efficiency). | ||||||
| 192 | Hybrid hydraulic and electrically actuated mobile robot | US14449471 | 2014-08-01 | US09283949B2 | 2016-03-15 | John Aaron Saunders; Alex Khripin; Steven Potter; Michael Patrick Murphy; Christopher Everett Thorne |
| Example embodiments may relate to a robotic system that includes a hydraulic actuator and an electric actuator both coupled to a joint of the robotic system. Operation of the actuators may be based on various factors such as based on desired joint parameters. For instance, such desired joint parameters may include a desired output torque/force of the joint, a desired output velocity of the joint, a desired acceleration of the joint, and/or a desired joint angle, among other possibilities. Given a model of power consumption as well as a model of the actuators, the robotic system may determine operating parameters such as hydraulic and electric operating parameters as well as power system parameters, among others. The robotic system may then control operation of the actuators, using the determined operating parameters, to obtain the desired joint parameters such that power dissipation in the system is minimized (i.e., maximizing actuation efficiency). | ||||||
| 193 | Hydraulic system for aircraft actuators | US13114849 | 2011-05-24 | US09103338B2 | 2015-08-11 | 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. | ||||||
| 194 | HYDRAULIC DEVICES AND METHODS OF ACTUATING SAME | US14506421 | 2014-10-03 | US20150096435A1 | 2015-04-09 | John Mathew Dalton; Terry Dickson |
| This disclosure includes hydraulic apparatuses and methods for redundant actuation of a hydraulic device. Some apparatuses include a hydraulic device having a first hydraulic actuator and a second hydraulic actuator, wherein each of the first and second hydraulic actuators comprises at least a first hydraulic cavity, a second hydraulic cavity, and a piston. Some apparatuses also include a controller coupled to the hydraulic device. In some embodiments, the controller is configured to receive hydraulic fluid from a fluid source via at least two parallel hydraulic lines coupled to the controller, select a first hydraulic line of the at least two parallel hydraulic lines, and transfer the hydraulic fluid from the selected first hydraulic line to a first cavity of the first hydraulic actuator to apply pressure to a first piston to actuate the hydraulic device. | ||||||
| 195 | FLEXIBLE RESPONSE SECURED MECHANICAL BALANCING FOR MULTIPLE CONTROL ACTUATORS WITH A COMMON OUTPUT | US14463832 | 2014-08-20 | US20150075149A1 | 2015-03-19 | Gregor PAULMANN |
| A flexible response secured mechanical balancing device (D) for multiple hydraulic control actuators (1-2) with a common output member (5a-b). The balancing device (D) provides flexible/continuous fluid-pressure force fight compensation. Balance valves (17-20) are commanded to balance fluid-pressure from a first fluid-pressure network (52a) of a second actuator (2). Each fluid-pressure commanded balance valve (17-20) is arranged to allow relief of differential pressure, directly into a dedicated first (52a) or second fluid-pressure network (52b). A fluid-pressure controlled locking device (21-22) is allowing inhibiting the corresponding pairs of balance valves (17-20) e.g. in case of loss of fluid-pressure. The invention typically applies to vehicles (A) including: aircrafts, rotorcrafts, drones. | ||||||
| 196 | Aircraft actuator hydraulic system | US13169644 | 2011-06-27 | US08418956B2 | 2013-04-16 | Atsushi Fukui |
| When a loss or degradation in the function of one of a first aircraft central hydraulic power source and a second aircraft central hydraulic power source occurs, a controller performs a control so as to operate the other backup hydraulic pump, out of a first backup hydraulic pump and a second backup hydraulic pump, which is connected downstream of the other hydraulic power source, which is the other of the first and second aircraft central hydraulic power sources. Oil flowing through the other backup hydraulic pump is cooled by an oil cooler of the other hydraulic power source by operation of the other backup hydraulic pump in a state where the other hydraulic power source is being operated. | ||||||
| 197 | Dual linear actuator | US12157934 | 2008-06-13 | US08356477B2 | 2013-01-22 | Bernhard Schlipf; Mark Heintjes |
| An actuator having two or more interconnected movement components, wherein the movement components are designed as linear actuators with substantially coaxial longitudinal axes or longitudinal axes that are parallel to each other and that are interconnected in longitudinal direction such that their linear movements are superimposed on one another, and such that at least one of the linear actuators can be stopped at one or several predetermined positions. | ||||||
| 198 | Double redundancy electro hydrostatic actuator system | US12285734 | 2008-10-14 | US08020379B2 | 2011-09-20 | Atsushi Kakino; Hiroshi Saito; Kenta Kawasaki; Takashi Oka |
| A double redundancy electro hydrostatic actuator system includes two hydraulic pumps; two fail safe valves connected with the two hydraulic pumps, respectively; one dual tandem hydraulic cylinder connected with the two fail safe valves and having a piston rod, wherein the piston rod is moved by switching supply and discharge of the fluid; two switching valves connected with the two fail safe valves; two accumulators connected with the two switching valves and the two hydraulic pumps, respectively; and two chambers connected with the two switching valves, respectively. Each of the two accumulators accumulates the fluid from a corresponding one of the two hydraulic pumps, and sends the fluid to a corresponding one of the two fail safe valves. The two chambers receive the fluid from the two fail safe valves, respectively. | ||||||
| 199 | Double redundancy electro hydrostatic actuator system | US12285734 | 2008-10-14 | US20090165457A1 | 2009-07-02 | Atsushi Kakino; Hiroshi Saito; Kenta Kawasaki; Takashi Oka |
| A double redundancy electro hydrostatic actuator system includes two hydraulic pumps; two fail safe valves connected with the two hydraulic pumps, respectively; one dual tandem hydraulic cylinder connected with the two fail safe valves and having a piston rod, wherein the piston rod is moved by switching supply and discharge of the fluid; two switching valves connected with the two fail safe valves; two accumulators connected with the two switching valves and the two hydraulic pumps, respectively; and two chambers connected with the two switching valves, respectively. Each of the two accumulators accumulates the fluid from a corresponding one of the two hydraulic pumps, and sends the fluid to a corresponding one of the two fail safe valves. The two chambers receive the fluid from the two fail safe valves, respectively. | ||||||
| 200 | HYDRAULIC DISTRIBUTOR PROVIDED WITH A DEVICE FOR DETECTING SEIZING | US12125078 | 2008-05-22 | US20080289487A1 | 2008-11-27 | Damien Sequera; Vincent Schwaller |
| The present invention relates to a hydraulic distributor (2) of a servo-control (1) of an aircraft, the hydraulic distributor comprising main distributor member (10) and emergency distributor member (20) that are coaxial, said emergency distributor member (20) being caused to move by said main distributor member (10) in the event of said main distributor member (10) seizing, said hydraulic distributor being provided with a detector device (60) for detecting said seizing. The detector device (60) is provided with a reed switch (66) and with amplification means (62, 69, 68) for amplifying said movement of the emergency distributor member, said amplification means comprising a lever (62) having a magnetized free end (621) that activates said reed switch (66) in the event of said emergency distributor member (20) moving. | ||||||
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