CN211343531U - Pump and valve combined control electric hydrostatic actuator - Google Patents
Pump and valve combined control electric hydrostatic actuator Download PDFInfo
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- CN211343531U CN211343531U CN201922038993.2U CN201922038993U CN211343531U CN 211343531 U CN211343531 U CN 211343531U CN 201922038993 U CN201922038993 U CN 201922038993U CN 211343531 U CN211343531 U CN 211343531U
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Abstract
An electric hydrostatic actuator controlled by a pump valve in a combined mode comprises elements such as a rotary direct-drive type electro-hydraulic pressure servo valve, a controller, a power drive unit, a brushless direct-current motor, a hydraulic pump, a one-way valve, an energy accumulator, a filter, a bypass damping valve, a safety valve, a switch valve, a hydraulic control one-way valve, an actuating cylinder, a pressure sensor, a current sensor, a displacement sensor and a rotating speed sensor. The device integrates the advantages of pump control and valve control, gives consideration to efficiency and frequency response, and effectively solves the problem of inertia of a rotor when the motor of the electro-hydrostatic actuator commutates; meanwhile, the problem of leakage when the O-shaped middle position of the electric hydrostatic actuator in the prior art can lock the loop is effectively solved. The patent can improve the reliability of the system and ensure the rapidity of the response of the system.
Description
Technical Field
The invention relates to an actuator, and belongs to the technology of electro-hydraulic servo control of an aircraft.
Background
The airplane is controlled by a control surface when flying, and the airplane control surface is controlled by an actuator. The actuator is a key part for implementing active vibration control on the airplane, mainly plays a role in applying control force to the airplane according to a determined control rule, and is an important link of an active control system.
Conventional on-board actuation systems transmit Power from a Power source to the rams By means of Hydraulic transmission, so-called Power-By-Hydraulic (PBH). The power liquid transmission system has the advantages of quick response, high power and excellent self-lubricating property, but the aircraft performance is greatly influenced because the hydraulic oil is inflammable and explosive under high temperature and high pressure and has high quality.
The advent of new materials and new technologies in the late 70 s has prompted the development of Power-By-Wire (PBW) actuation systems. The electric power transmission refers to the transmission of power from the second energy source system of the airplane to each actuating mechanism of the actuating system through an electric lead. The power fly-by-wire type actuation system has the advantages of improving the maintainability of the airplane, having great flexibility of system layout, reducing the possibility of burning hydraulic oil, improving the survivability of the damaged airplane and the like.
Currently, Power By Wire (PBW) actuators are evolving towards electro-hydrostatic actuators (EHAs) and electro-mechanical actuators (EMA), and the present invention relates to electro-hydrostatic actuators (EHAs).
A typical EHA system is shown in fig. 1, and is of a variable speed and fixed displacement type, that is, the output flow and direction of a hydraulic pump are controlled by changing the speed and direction of a brushless dc motor, so as to generate load pressure to drive the control surface to deflect. The brushless dc motor plays a decisive role in the response speed of the actuator cylinder. However, the rotor of the brushless dc motor has a large moment of inertia, and therefore, commutation cannot be completed in time and accurately, so that the flight performance of the aircraft is affected.
At present, a two-stage servo valve structure is generally adopted in a common electro-hydraulic pressure servo valve, electro-hydraulic conversion and power amplification are realized in the first stage, and a slide valve power amplification part is adopted in the second stage. The first stage hydraulic amplifying part generally adopts a nozzle-baffle structure, and a few of the first stage hydraulic amplifying parts adopt a jet pipe type. Although the nozzle-baffle type pressure servo valve has excellent performance, the use condition is harsh, and the pollution resistance is weak; the jet pipe type pressure servo valve has strong anti-pollution capacity, but has large internal leakage, too many welding numbers of torque motors and poor anti-vibration zero drift capacity. The rotary direct-drive electro-hydraulic pressure servo valve adopted by the invention has samples in the market, such as original jiayang, Yao Bao, Luliang, Direction, Guo Sheng, which is published in a paper of 16 th mechanical engineering journal, 54 th volume, 2018, "mechanism and characteristic analysis of the rotary direct-drive electro-hydraulic pressure servo valve", and an original jiayang, Yao Bao, Luliang, Direction, Xiafaiyan, which is published in 46 nd volume, 2 nd university of Tongji (Nature science edition), "stability analysis of the rotary direct-drive electro-hydraulic pressure servo valve". The valve has the advantages of high reliability, high pollution resistance, high dynamic response and the like, and overcomes the defects of a common electro-hydraulic pressure servo valve.
At present, an O-shaped neutral position function is generally adopted by an electric hydrostatic actuator to lock a loop, and the tightness is poor. The O-shaped middle position can enable the oil inlet and the oil outlet of the actuating element to be in a closed state, so that the reversing valve can realize a locking function. However, most of the reversing valves are of slide valve structures, leakage inevitably exists, when the stopping time is long, looseness is possibly generated to enable a hydraulic cylinder piston to drift a small amount, the locking effect is poor, and the flight performance of the airplane is affected, so that the loop is mostly suitable for occasions with low locking precision requirements and short locking time.
Disclosure of Invention
The purpose of the patent is to solve the problem of inertia of a rotor when a motor of an electro-hydrostatic actuator in the prior art is reversed, and provide a pump control and valve control integrated machine which has the advantages of both pump control and valve control and has both efficiency and frequency response; meanwhile, the problem of leakage when the O-shaped neutral position of the electric hydrostatic actuator in the prior art can lock a loop is effectively solved, the system reliability is improved, and the system response rapidity is guaranteed.
To achieve the above object, the present patent discloses an electro-hydrostatic actuator system with combined pump and valve control, which has three operation modes:
master control mode of pump
The movement of the actuating cylinder of the electric hydrostatic actuator is controlled by combining a bidirectional hydraulic pump and a novel hydraulic lock no matter the rotary direct-driven electro-hydraulic pressure servo valve is positioned at an upper position or a lower position, and the oil inlet and oil return directions of the bidirectional hydraulic pump are controlled by the speed and the direction of a motor rotor so as to control the movement direction and the movement speed of the actuating cylinder; when the actuating cylinder moves in place, the switch valve is opened by a signal of the controller, the oil inlet and return paths of the actuating cylinder are short-circuited, the novel hydraulic lock control oil path is closed due to no pressure, and the hydraulic lock locks the loop at the moment;
② valve master control mode
Under the working condition, the movement of the actuating cylinder of the electric hydrostatic actuator is controlled by combining a rotary direct-drive electro-hydraulic pressure servo valve and a novel hydraulic lock. The size and the direction of the flow of hydraulic oil output by the hydraulic pump are unchanged in actual work no matter the direction of the oil liquid of an oil inlet and an oil outlet of the hydraulic pump, and the movement direction of the actuating cylinder can be controlled by reversing the rotary direct-drive type electro-hydraulic pressure servo valve; the displacement of the actuating cylinder is controlled by the opening degree of a valve port of the servo valve; when the actuating cylinder moves in place, the controller controls the switch valve to be opened, the oil inlet and return paths of the actuating cylinder are short-circuited, the novel hydraulic lock control oil path is closed due to no pressure, and the hydraulic lock locks the loop at the moment;
coordinate control mode of pump valve
The mode is the combination of the two modes, the movement of the actuating cylinder of the electric hydrostatic actuator is coordinately controlled by a hydraulic pump and a rotary direct-drive electro-hydraulic pressure servo valve, and the position of the actuating cylinder is locked by a novel hydraulic lock. The movement speed of the actuating cylinder is controlled by the output flow of the hydraulic pump, and the movement direction of the actuating cylinder is controlled by reversing a servo valve; when the actuating cylinder moves in place, the controller controls the switch valve to be opened, the oil inlet and return paths of the actuating cylinder are short-circuited, the novel hydraulic lock control oil path is closed due to no pressure, and at the moment, the hydraulic lock locks the loop.
The invention has the following beneficial effects:
the invention can jointly control the output flow of the system by the quantitative bidirectional hydraulic pump and the rotary direct-drive electro-hydraulic pressure servo valve, thereby controlling the movement speed of the actuating cylinder to meet different flight states of the airplane. The invention can greatly overcome the inertia when the brushless DC motor is adopted to commutate the actuator, reduce the loss of the DC motor and improve the action response speed of the system and the actuator.
The invention has 3 optional working modes and large control redundancy; the two-position four-way rotary direct drive type electro-hydraulic pressure servo valve is adopted to replace the original three-position four-way servo valve to control the actuator, so that the system complexity is reduced, the system cost is reduced, the looseness of the actuator cylinder caused by the leakage of hydraulic oil during positioning is reduced, and the positioning precision of the actuator cylinder is improved; the structure is simple, and the control is more convenient;
compared with the existing system, the integral control redundancy is increased, the positioning of the actuating cylinder is more accurate and stable, and the safety of the system is enhanced.
Drawings
FIG. 1 is a schematic diagram of a typical EHA;
FIG. 2 is a schematic diagram of an electro-hydrostatic actuation system with combined pump and valve control according to the present invention.
In the figure, the hydraulic control system comprises a direct current motor 1, a direct current motor 2, a hydraulic pump 3, a check valve 4, an accumulator 5, a filter 6, a safety valve 7, an electro-hydraulic pressure servo valve 8, a switch valve 9, a damping bypass valve 10, an actuator cylinder 11, a controller 12, a power driving unit 13, a current sensor 14, a valve core displacement sensor 15, a pressure sensor 16, an actuator cylinder displacement sensor 17, a rotating speed sensor 18, a hydraulic cylinder 19 and a hydraulic control check valve.
Detailed Description
As shown in fig. 2, the system of the pump-valve combined control electro-hydrostatic actuator comprises a direct current motor 1, a hydraulic pump 2, a check valve 3, an accumulator 4, a filter 5, a safety valve 6, an electro-hydraulic pressure servo valve 7, a switch valve 8, a damping bypass valve 9, an actuator cylinder 10, a controller 11, a power driving unit 12, a current sensor 13, a spool displacement sensor 14, a pressure sensor 15, an actuator cylinder displacement sensor 16, a rotating speed sensor 17, a hydraulic cylinder 18, a hydraulic control check valve 19 and the like; wherein: the electro-hydraulic pressure servo valve 7 is a two-position four-way valve, and the driving mode is a rotary direct driving type; the switch valve 8 is a normally open type high-speed switch valve and is a two-position two-way valve and is connected to two ends of an oil inlet and an oil outlet of the actuating cylinder 10; the high-speed switch valve 8 controls the pressure of the novel hydraulic lock control oil way through the controller 11, so that the opening and closing of the novel hydraulic lock are controlled, and the actuating cylinder 10 is controlled to be started and stopped. The novel hydraulic lock comprises two hydraulic control one-way valves 19 and two control oil paths K, and is matched with the high-speed switch valve 8. When the hydraulic cylinder 18 does not need to be locked, the high-speed switch 8 valve is in a disconnected state, the control oil path K of the hydraulic control one-way valve 19 has pressure, the hydraulic control one-way valve 19 is opened, and hydraulic oil can flow in two directions; when the hydraulic cylinder 18 needs to be locked, the high-speed switch valve 8 is closed, the oil inlet and the oil outlet at the two ends of the actuating cylinder 10 are in short circuit, at the moment, the control oil path K of the hydraulic control one-way valve 19 has no pressure, hydraulic oil cannot flow reversely, and the hydraulic cylinder 10 is locked.
In the working principle shown in fig. 2, the oil inlet and outlet of the EHA are connected to the actuator cylinder 10, so as to adjust the output position and speed of the actuator cylinder 10; the controller 11 receives a control instruction of a superior flight control computer, calculates an output signal through a control algorithm and transmits the output signal to the power driving unit 12; the power driving unit 12 outputs corresponding electric power to the direct current motor 1 according to the input signal, adjusts the rotating speed and the steering direction of the direct current motor 1, and the direct current motor 1 further drives the bidirectional hydraulic pump 2 to rotate; meanwhile, the power driving unit 12 inputs signals to the rotary direct-drive type electro-hydraulic pressure servo valve 7 to adjust the switching of the working position of the rotary direct-drive type electro-hydraulic pressure servo valve 7 and the size of the valve port throttling opening area so as to adjust the flow in the system; the oil enters the cavity of the actuator cylinder 10, and finally the output position and speed of the actuator cylinder 10 are adjusted. Because the EHA belongs to a closed hydraulic system, oil in the system needs to be kept balanced, and oil drainage and oil supplement of the system are controlled by arranging the check valve 5 and the energy accumulator 4, so that cavitation of the system is avoided; the damping bypass valve 9 is used for isolating the connection between the actuator cylinder 10 and the EHA so as to ensure that the channel EHA can be smoothly separated from the actuator cylinder 10 and the actuator cylinder 10 can enter a follow-up state; the safety valve 6 is used for overpressure protection to avoid damage caused by overhigh system pressure in an abnormal state; the novel hydraulic lock comprises two hydraulic control one-way valves 19 and two control oil paths K, is matched with the high-speed switch valve 8, and can lock the actuating cylinder 10 when the actuating cylinder 10 needs to be positioned. The rotation speed sensor 17 is used for feeding back the rotation speed and the direction of the direct current motor 1, and the controller 11 can perform real-time control and state monitoring; the current sensor 13 is used for feeding back the working current of the direct current motor 1 for the controller 11 to perform real-time control and state monitoring; the valve core displacement sensor 14 is used for feeding back the working displacement of the rotary direct-drive type electro-hydraulic pressure servo valve 7 for the controller 11 to carry out real-time control and state monitoring; the pressure sensor 15 is used for feeding back the working pressure in the corresponding cavity of the actuating cylinder 10, so that the controller 11 can perform real-time control and state monitoring; the ram displacement sensor 16 is used to feed back the working displacement of the ram 10 for real-time control and condition monitoring by the controller 11.
The following is described in connection with the actual operation of the aircraft in flight:
the airplane is divided into three stages when flying in the air: a normal flight phase, a high maneuvering flight phase, a take-off and landing phase; the three scenarios are now described one after the other:
1 phase of normal flight
When the airplane is in the sliding and general cruising stages, the requirement on the actuation response of a control surface is low, the controller 11 receives the instruction of a flight control computer, so that the rotary direct-drive type electro-hydraulic pressure servo valve 7 is in an upper position and is not reversed, and the EHA works in a pump control state. The displacement of the actuating cylinder, the rotating speed and the current of the brushless direct current motor and a double-cavity pressure signal which are detected by the sensor are transmitted to the controller 11, the controller 11 comprehensively generates a control signal according to the signals to adjust the rotating speed and the steering direction of the direct current motor 1, and the bidirectional hydraulic pump 2 outputs pressure oil under the driving of the direct current motor 1 and sends the pressure oil to the actuating cylinder 10, so that the displacement of the actuating cylinder 10 is controlled;
the rotary direct-drive type electro-hydraulic pressure servo valve 7 is in an upper position by receiving a control signal output by the controller 11 and is not reversed. When the piston rod of the hydraulic cylinder 18 needs to extend, the direct current motor 1 receives the control signal output by the controller 11 to rotate clockwise, the speed of the piston rod movement is determined by the rotation speed of the rotor of the direct current motor 1, when the rotor rotation speed is faster, the piston rod movement speed is faster, otherwise, the piston rod movement speed is slower. When the piston rod of the hydraulic cylinder 18 needs to be retracted, the direct current motor 1 rotates anticlockwise by receiving a control signal output by the controller 11, the moving speed of the piston rod is determined by the rotating speed of the rotor of the direct current motor 1, and the moving speed of the piston rod is faster when the rotating speed of the rotor is faster, and vice versa. When the piston rod of the hydraulic cylinder 18 needs to be positioned, the displacement signal of the actuating cylinder and the double-cavity pressure signal are fed back to the controller, the controller 11 sends a signal to the switch valve to close the high-speed switch valve 8, the oil circuit of the system is short-circuited, the hydraulic control one-way valve 19 is closed because the pressure of the control oil circuit K disappears immediately, the hydraulic cylinder 18 is locked bidirectionally because the oil circuits of the two cavities are closed, and the hydraulic lock plays a role in locking a loop at the moment.
2 high maneuver flight phase
When the aircraft is in the high maneuvering cruising and fighting stage, the flight control system frequently operates the control surface, the primary purpose is to complete the flight task, and the requirement on the actuation efficiency is low. At this time, the controller 11 receives an instruction to rotate the direct current motor 1 in a single direction at the highest rotation speed, and the bidirectional hydraulic pump 2 is equivalent to a hydraulic oil source; the flow and the flow direction of oil are controlled by moving a valve core of the rotary direct-drive type electro-hydraulic pressure servo valve 7, so that the EHA works in a valve control state, and the system has high response speed and low efficiency.
Specifically, the dc motor 1 rotates clockwise at the maximum speed in response to the control signal output from the controller 11. When a piston rod of the hydraulic cylinder 18 needs to extend out, the rotary direct-drive type electro-hydraulic pressure servo valve 7 receives a control signal output by the controller 11 and is in an upper position and is not reversed, the moving speed of the piston rod is determined by the displacement of the valve core, the larger the displacement of the valve core is, the larger the through-flow sectional area of the valve port is, the faster the moving speed of the piston rod is, and the slower the valve core is. When the piston rod of the hydraulic cylinder 18 needs to retract, the rotary direct-drive type electro-hydraulic pressure servo valve 7 receives a control signal output by the controller 11 and is in a lower position without reversing, the moving speed of the piston rod is determined by the displacement of the valve core, the larger the displacement of the valve core is, the larger the through-flow sectional area of the valve port is, the faster the moving speed of the piston rod is, and the slower the piston rod is. When the piston rod of the hydraulic cylinder 18 needs to be positioned, the displacement signal of the actuating cylinder and the double-cavity pressure signal are fed back to the controller 11, the controller 11 sends a signal to the high-speed switch valve 8, the high-speed switch valve 8 is closed, the oil circuit of the system is short-circuited, the hydraulic control one-way valve 19 is closed because the pressure of the control oil circuit disappears immediately, the hydraulic cylinder 18 is locked in two directions because the oil circuits of the two cavities are closed, and the hydraulic lock plays a role in locking a loop at the moment.
3 taking off and landing phases
When the aircraft is in the takeoff and landing stages, the actuation system is required to have higher stability and accuracy and certain response speed. The DSP controller 11 receives a command to enable the EHA to work in a pump-valve coordination control state. At the moment, the direct current motor 1 only adjusts the rotating speed to meet the requirement of load flow, and the flow direction of hydraulic oil is changed by controlling the positive and negative displacement of the rotary direct drive type electro-hydraulic pressure servo valve 7. Therefore, large inertia during the commutation of the brushless direct current motor 1 is avoided, too high throttling and leakage loss are avoided, and frequency response and efficiency are considered.
Specifically, when the piston rod of the hydraulic cylinder 18 needs to extend, the rotary direct-drive type electro-hydraulic pressure servo valve 7 receives a control signal output by the controller 11 and is in an upper position and is not reversed, the moving speed of the piston rod is determined by the rotating speed of the rotor of the direct-current motor 1, and the moving speed of the piston rod is higher when the rotating speed of the rotor is higher, and the moving speed of the piston rod is lower when the rotating speed of the rotor is lower. When the piston rod of the hydraulic cylinder 18 needs to retract, the rotary direct-drive type electro-hydraulic pressure servo valve 7 receives a control signal output by the controller 11 and is in a lower position and is not reversed, the moving speed of the piston rod is determined by the rotating speed of the rotor of the direct-current motor 1, and the faster the rotating speed of the rotor is, the faster the moving speed of the piston rod is, and the slower the piston rod is. When the piston rod of the hydraulic cylinder 18 needs to be positioned, the displacement signal of the actuating cylinder and the double-cavity pressure signal are fed back to the controller 11, the controller 11 sends a signal to the high-speed switch valve 8, the high-speed switch valve 8 is closed, the oil circuit of the system is short-circuited, the hydraulic control one-way valve 19 is closed because the pressure of the control oil circuit K disappears immediately, the hydraulic cylinder 18 is locked in two directions because the oil circuits of the two cavities are closed, and the hydraulic lock plays a role in locking a loop at the moment.
Claims (4)
1. The utility model provides a pump valve joint control's electronic hydrostatic actuator which characterized in that: the hydraulic control system comprises a rotary direct-drive type electro-hydraulic pressure servo valve, a controller, a power drive unit, a brushless direct-current motor, a hydraulic pump, a one-way valve, an energy accumulator, a filter, a bypass damping valve, a safety valve, a switch valve, a hydraulic control one-way valve, an actuating cylinder, a pressure sensor, a current sensor, a displacement sensor and a rotating speed sensor;
rotary direct drive electrohydraulic pressure servovalves: the device comprises an electronic controller, a limited angle torque motor, an eccentric driving mechanism, a power slide valve pair and a related sensor;
the valve converts the rotary motion of a torque motor into the linear motion of a power valve core through an eccentric driving mechanism, changes the ratio of the throttling areas of the oil inlet and the oil return, and further determines the output pressure of a servo valve;
a controller: the control instruction of a superior flight control computer can be received, and an output signal is calculated through a control algorithm and transmitted to the power driving unit;
a power driving unit: outputting corresponding electric power to the brushless DC motor according to the input signal, and adjusting the rotating speed and the rotating direction of the brushless DC motor;
brushless dc motor: according to the instruction of the power driving unit, different rotating speeds and steering directions are adjusted, and then the output flow of the bidirectional hydraulic pump and the flowing direction of hydraulic oil are controlled;
a hydraulic pump: the quantitative bidirectional plunger pump is driven by a brushless direct current motor, and the flow and the direction of output hydraulic oil are different according to different flight conditions;
a one-way valve: only allowing the hydraulic oil to flow in one direction;
an energy accumulator: the oil pump is matched with the one-way valve to supplement oil and drain oil for the whole control system, so that a cavity of the control system is prevented;
a filter: impurities in hydraulic oil of a control system are filtered, so that the oil of the system keeps certain cleanliness, and safe and reliable work of a hydraulic element and a hydraulic system is guaranteed;
a safety valve: the overflow of the valve port is utilized to maintain the pressure of the system to be constant, when the pressure of the system is overhigh, the pressure regulation, the pressure limitation and the pressure stabilization can be realized, and the system is provided with two safety valves because the motor can rotate positively and negatively;
a bypass damping valve: when the system is in fault, the hydraulic oil is returned to the oil suction port to play a role of short circuit;
switching on and off the valve: the hydraulic lock is matched with the two hydraulic control one-way valves to form a novel hydraulic lock;
novel hydraulic lock: the hydraulic lock comprises two hydraulic control one-way valves and two control oil paths, and is matched with a switch valve to form a novel hydraulic lock;
an actuating cylinder: the actuating cylinder is an actuating mechanism of the electric hydrostatic actuator;
the internal part of the balance cylinder is provided with a symmetrical hydraulic cylinder which is a balance cylinder, and the input flow and the output flow of the balance cylinder are equal;
a pressure sensor: the pressure of the actuating cylinder is detected and fed back to the controller in real time for the controller to detect and control;
a displacement sensor: the displacement of the actuating cylinder and the displacement of a valve core of the rotary direct-drive electro-hydraulic servo valve are detected and fed back to the controller in real time for the controller to detect and control;
a current sensor: detecting the working current of the brushless direct current motor, and feeding the working current back to the controller in real time for the controller to detect and control;
a rotation speed sensor: and detecting the working rotating speed of the brushless direct current motor, and feeding the working rotating speed back to the controller in real time for the controller to detect and control.
2. The electro-hydrostatic actuator with combined pump and valve control of claim 1, wherein: the system control modes include the following three types:
pump master control mode
The displacement of the actuating cylinder of the electric hydrostatic actuator is completely controlled by a hydraulic pump, the displacement speed of the actuating cylinder is regulated and controlled by the output flow of the hydraulic pump, and the displacement direction of the actuating cylinder is controlled by positive and negative rotation of the hydraulic pump;
② valve master control mode
The displacement of the actuating cylinder of the electric hydrostatic actuator is completely controlled by the rotary direct-drive type electro-hydraulic pressure servo valve, the speed of the displacement of the actuating cylinder is regulated and controlled by the valve port through-flow area of the rotary direct-drive type electro-hydraulic pressure servo valve, and the direction of the displacement of the actuating cylinder is controlled by the working position of the rotary direct-drive type electro-hydraulic pressure servo valve;
coordinate control mode of pump valve
The displacement of the actuating cylinder of the electric hydrostatic actuator is controlled by the coordination of a hydraulic pump and a rotary direct-drive type electro-hydraulic pressure servo valve, the speed of the displacement of the actuating cylinder is regulated by the output flow of the hydraulic pump, and the direction of the displacement of the actuating cylinder is controlled by two working positions of the rotary direct-drive type electro-hydraulic pressure servo valve.
3. The electro-hydrostatic actuator with combined pump and valve control of claim 1, wherein: the novel hydraulic lock consists of two hydraulic control one-way valves, two control oil ways and a switch valve;
the novel hydraulic lock in the pump-valve combined control electro-hydrostatic actuator has the following effects: when the actuating cylinder needs to be positioned, the hydraulic lock locks the oil way of the actuating cylinder and keeps the position of the piston rod unchanged;
the sealing performance is good, the leakage of hydraulic oil is less, and the control system is more accurate;
the control mode is as follows:
when the actuating cylinder does not need to be positioned, the switch valve is in a closed state, the hydraulic control one-way valve is opened by the pressure of the control oil path, hydraulic oil can flow in two directions, and the hydraulic lock does not play a role in locking a loop at the moment;
when the actuating cylinder needs to be positioned, the controller sends a signal to the switch valve to enable the working position of the switch valve to be reversed, the oil path of the system is short-circuited, the hydraulic control one-way valve is closed due to the disappearance of the pressure of the control oil path, the hydraulic cylinder is also locked in a two-way mode due to the fact that the two-cavity oil path is closed, and the hydraulic lock plays a role in locking the loop at the moment.
4. The electro-hydrostatic actuator with combined pump and valve control of claim 1, wherein: the rotary direct-drive type electro-hydraulic pressure servo valve is a two-position four-way valve, the rotary motion of a torque motor is converted into the linear motion of a power valve core through an eccentric driving mechanism, the ratio of the throttling areas of the oil inlet and the oil return is changed, and the output pressure of the servo valve is further determined;
the valve has the advantages of high reliability, high pollution resistance and high dynamic response, and overcomes the defects of large internal leakage, poor pollution resistance and poor vibration zero drift resistance of a common electro-hydraulic pressure servo valve.
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| CN201922038993.2U CN211343531U (en) | 2019-11-23 | 2019-11-23 | Pump and valve combined control electric hydrostatic actuator |
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| CN201922038993.2U CN211343531U (en) | 2019-11-23 | 2019-11-23 | Pump and valve combined control electric hydrostatic actuator |
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Cited By (5)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173165A (en) * | 2020-09-18 | 2021-01-05 | 凯迈（洛阳）测控有限公司 | Linear force loading system redundant force compensation control device and compensation control method |
| CN112460098A (en) * | 2020-11-13 | 2021-03-09 | 北京精密机电控制设备研究所 | High-reliability static pressure locking system |
| CN113021318A (en) * | 2021-03-22 | 2021-06-25 | 西安交通大学 | Digital-analog hybrid valve control hydraulic robot system |
| CN113417896A (en) * | 2021-06-04 | 2021-09-21 | 燕山大学 | Pump-controlled hydraulic system of press machine and control method thereof |
| CN116428230A (en) * | 2023-04-07 | 2023-07-14 | 浙江大学 | Global dynamic programming-based electro-hydrostatic operation system and compound control method |
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2019
- 2019-11-23 CN CN201922038993.2U patent/CN211343531U/en not_active Expired - Fee Related
Cited By (9)
| Publication number | Priority date | Publication date | Assignee | Title |
|---|---|---|---|---|
| CN112173165A (en) * | 2020-09-18 | 2021-01-05 | 凯迈（洛阳）测控有限公司 | Linear force loading system redundant force compensation control device and compensation control method |
| CN112173165B (en) * | 2020-09-18 | 2023-05-23 | 凯迈（洛阳）测控有限公司 | Device and method for compensating and controlling redundant force of linear force loading system |
| CN112460098A (en) * | 2020-11-13 | 2021-03-09 | 北京精密机电控制设备研究所 | High-reliability static pressure locking system |
| CN113021318A (en) * | 2021-03-22 | 2021-06-25 | 西安交通大学 | Digital-analog hybrid valve control hydraulic robot system |
| CN113021318B (en) * | 2021-03-22 | 2022-07-12 | 西安交通大学 | Digital-analog hybrid valve control hydraulic robot system |
| CN113417896A (en) * | 2021-06-04 | 2021-09-21 | 燕山大学 | Pump-controlled hydraulic system of press machine and control method thereof |
| CN113417896B (en) * | 2021-06-04 | 2022-05-10 | 燕山大学 | Pump-controlled hydraulic system of press machine and control method thereof |
| CN116428230A (en) * | 2023-04-07 | 2023-07-14 | 浙江大学 | Global dynamic programming-based electro-hydrostatic operation system and compound control method |
| CN116428230B (en) * | 2023-04-07 | 2024-03-08 | 浙江大学 | Global dynamic programming-based electro-hydrostatic operation system and compound control method |
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