CN114396401A

CN114396401A - Hydraulic actuating device and aircraft

Info

Publication number: CN114396401A
Application number: CN202210048065.8A
Authority: CN
Inventors: 朱晓博; 刘继; 段定杰; 张冲; 谷智超; 王佳奇; 曾含含; 吴昉晟
Original assignee: Comac Shanghai Aircraft Design & Research Institute; Commercial Aircraft Corp of China Ltd
Current assignee: Comac Shanghai Aircraft Design & Research Institute; Commercial Aircraft Corp of China Ltd
Priority date: 2022-01-17
Filing date: 2022-01-17
Publication date: 2022-04-26
Anticipated expiration: 2042-01-17
Also published as: CN114396401B

Abstract

The invention discloses a hydraulic actuating device and an aircraft, wherein the hydraulic actuating device comprises a servo valve and an actuating mechanism, one side of the servo valve is in fluid communication with a liquid inlet passage and a liquid outlet passage of a liquid supply system, the other side of the servo valve is in fluid communication with the actuating mechanism through two liquid passages, and the servo valve controls the flow and the direction of output liquid according to a received servo electric signal so as to drive the actuating mechanism to move according to a preset instruction; the double-mode valve can convert working modes according to received control signals, and allows liquid to flow in a one-way mode in a first working mode and in a two-way mode in a second working mode. The technical scheme provided by the invention can increase the safety of the aircraft.

Description

Hydraulic actuating device and aircraft

Technical Field

The invention relates to the technical field of aircrafts, in particular to a hydraulic actuating device and an aircraft.

Background

The door control system field of civil aircraft mostly adopts dual-mode servo actuator, generally speaking, has higher requirement on the safety of error recovery when the door actuates, and especially has more strict requirement on the safety of error recovery in the violent attitude change stages such as take-off and the like.

The traditional dual-mode servo actuator realizes accurate retraction and extension through an electro-hydraulic servo valve, and in a damping mode, the actuator can perform damping motion under the action of external force. However, the existing technical solutions are not specially designed for the fault of command error recovery, and when the command of the driver or the control circuit is incorrect, the electro-hydraulic servo valve is reversely opened, which directly causes the actuator to recover by error, resulting in serious accidents.

Therefore, the conventional dual-mode servo actuator has potential safety hazards, and the safety of the conventional dual-mode servo actuator needs to be improved.

Disclosure of Invention

The invention provides a hydraulic actuating device and an aircraft, which can effectively solve the problem that in the prior art, when an electro-hydraulic servo valve is reversely opened, the actuator is directly recovered by mistake, so that serious accidents are caused.

According to one aspect of the present invention, a hydraulic actuating device is provided, the device includes a servo valve and an actuating mechanism, one side of the servo valve is in fluid communication with a liquid inlet passage and a liquid outlet passage of a liquid supply system, the other side of the servo valve is in fluid communication with the actuating mechanism via two liquid passages, and the servo valve controls the flow rate and direction of output liquid thereof according to a received servo electrical signal so as to drive the actuating mechanism to move according to a predetermined command; the double-mode valve can convert working modes according to received control signals, and allows liquid to flow in a one-way mode in a first working mode and in a two-way mode in a second working mode.

Further, the control signal and the servo electrical signal are independent of each other.

Further, the dual-mode valve takes a power-on signal as the control signal and works in the first working mode after being powered on, and takes a power-off signal as the control signal and works in the second working mode after being powered off.

Further, the double-mode valve is a two-position two-way electromagnetic valve with a built-in one-way valve.

Furthermore, a displacement sensor is arranged in the actuating mechanism and used for acquiring displacement information of the actuating mechanism in real time so as to realize closed-loop servo for the actuating mechanism.

Further, the hydraulic actuating apparatus further includes a selector valve having a first fluid passage and a second fluid passage on one side thereof respectively belonging to the two-way fluid passage, the first fluid passage being in direct fluid communication with the servo valve, the second fluid passage being in fluid communication with the double mode valve so as to be in fluid communication with the servo valve indirectly via the double mode valve, and also having a third fluid passage and a fourth fluid passage on the other side thereof respectively belonging to the two-way fluid passage, the third fluid passage and the fourth fluid passage each being in fluid communication with the actuating mechanism, wherein the selector valve is capable of switching an operation mode according to a pressure of a control liquid input from the control passage, the selector valve operates in a normal operation mode without damping when the control liquid is a high pressure liquid, and operates in a non-high pressure liquid when the control liquid is a non-high pressure liquid, the selector valve operates in a damping mode of operation.

Furthermore, the hydraulic actuating device further comprises an electromagnetic control valve, a fifth fluid passage and a sixth fluid passage are arranged on one side of the electromagnetic control valve, the control passage is arranged on the other side of the electromagnetic control valve, after the electromagnetic control valve is electrified, the fifth fluid passage is in fluid communication with the liquid inlet passage of the liquid supply system so as to output high-pressure liquid to the selector valve through the control passage, and after the electromagnetic control valve is powered off, the sixth fluid passage is in fluid communication with the liquid outlet passage of the liquid supply system so as to output non-high-pressure liquid to the selector valve through the control passage.

Furthermore, the hydraulic actuating device further comprises a first bypass liquid channel and a second bypass liquid channel, one end of the first bypass liquid channel and one end of the second bypass liquid channel are respectively in liquid communication with the two liquid channels, the other end of the first bypass liquid channel and the other end of the second bypass liquid channel are both in fluid communication with the liquid outlet channel of the liquid supply system, and the first bypass liquid channel and the second bypass liquid channel are both provided with an anti-cavitation valve and a pressure sensor.

Furthermore, the hydraulic actuating device also comprises a back pressure valve, and the back pressure valve is arranged between the servo valve and a liquid outlet passage of the liquid supply system and used for stabilizing the pressure of liquid in the liquid outlet passage.

Further, the hydraulic actuation device also includes a compensator in fluid communication with an inlet of the backpressure valve via the first bypass fluid passage or the second bypass fluid passage.

Further, the actuating mechanism is a piston-cylinder actuator, and the liquid is oil.

Further, the selector valve is a two-position six-way solenoid valve, and the electromagnetic control valve is a two-position three-way valve.

Further, the piston-cylinder actuator comprises an actuator cylinder, a piston, and a connecting rod; the piston is arranged in the actuating cylinder so as to divide the actuating cylinder into a first closed cavity and a second closed cavity, and the first cavity and the second cavity are respectively communicated with the two liquid channels in a fluid mode; the connecting rod is fixedly connected with the piston, so that the connecting rod can do piston motion between the first cavity and the second cavity along with the piston according to the direction of the liquid pressure in the actuating cylinder.

Further, the two load relief valves are used to relieve pressure of liquid in the first and/or second chambers during movement of the piston.

According to another aspect of the invention, there is provided an aircraft comprising any of the hydraulic actuation devices described above and a controller, wherein the controller triggers the dual mode valve to operate in the first operating mode when the aircraft is in a critical phase of flight and triggers the dual mode valve to operate in the second operating mode when the aircraft is in a non-critical phase of flight.

The invention has the advantages that the double-mode valve arranged on one of the two liquid channels between the servo valve and the actuating mechanism can be controlled to work in the first working mode when the aircraft is in a flight critical stage so as to only allow the liquid to flow in a single direction, thereby avoiding the error recovery of the actuating mechanism.

Drawings

The technical solution and other advantages of the present invention will become apparent from the following detailed description of specific embodiments of the present invention, which is to be read in connection with the accompanying drawings.

Fig. 1 is a schematic structural diagram of a hydraulic actuating device according to an embodiment of the present invention.

Fig. 2 is a schematic structural diagram of a hydraulic actuating device according to a second embodiment of the present invention.

Fig. 3 is a schematic structural diagram of a hydraulic actuating device according to a third embodiment of the present invention.

Detailed Description

The technical solution in the embodiments of the present invention will be clearly and completely described below with reference to the accompanying drawings in the embodiments of the present invention. It is to be understood that the described embodiments are merely exemplary of the invention, and not restrictive of the full scope of the invention. All other embodiments, which can be derived by a person skilled in the art from the embodiments given herein without making any creative effort, shall fall within the protection scope of the present invention.

Referring now to fig. 1, fig. 1 is a hydraulic actuating device according to an embodiment of the present invention. As shown in fig. 1, a hydraulic actuator according to a first embodiment of the present invention includes: servo valve 400, actuating mechanism 600, dual mode valve 500, liquid inlet passage 301 and liquid outlet passage 302.

Illustratively, one side of the servo valve 400 is in fluid communication with an inlet liquid passage 301 and an outlet liquid passage 302 of the liquid supply system 300, the other side of the servo valve 400 is in fluid communication with the actuating mechanism 600 via two liquid channels, and the servo valve 400 controls the flow rate and the direction of the output liquid thereof according to the received servo electric signals so as to drive the actuating mechanism 600 to move according to a preset command. For example, when a hydraulic actuation device is applied to a door of an aircraft, the direction of movement required to open and close the door is the commanded movement predetermined by the actuation mechanism 600.

Illustratively, a dual-mode valve 500 is arranged on one of the two fluid passages between the servo valve 400 and the actuating mechanism 600, the dual-mode valve 500 can switch the working modes according to the received control signals, in the first working mode, the dual-mode valve 500 allows the fluid to flow in one direction, and in the second working mode, the dual-mode valve 500 allows the fluid to flow in two directions.

Illustratively, as shown in fig. 1, the servo electrical signal is generated by a control circuit 100, the control signal is generated by an independent control circuit 200, and the control signal and the servo electrical signal are independent of each other. In the present embodiment, the servo electrical signal and the control signal may be generated by the control circuit 100 or generated by the independent control circuit 200, and they may be independent of each other. The servo electrical signal is applied to the first solenoid valve 404 to control the servo valve 400 to operate in different modes. The control signal is applied to second solenoid 503 to control dual mode valve 500 to operate in different modes.

Illustratively, the liquid supply system 300 is communicated with the servo valve 400 through an inlet liquid passage 301 and an outlet liquid passage 302, the servo valve 400 comprises at least a first servo valve mode, a second servo valve mode and a third servo valve mode, the servo valve 400 further comprises a cross pipeline 401, a first damping valve 402 and a first connecting pipeline 403, wherein the cross pipeline 401, the first damping valve 402 and the first connecting pipeline 403 respectively correspond to the first servo valve mode, the second servo valve mode and the third servo valve mode of the servo valve 400.

Illustratively, when the servo valve 400 is in the first servo valve mode, oil enters the crossover line 401 through the inlet passage 301, flows through the crossover line 401 through the dual mode valve 500, and then flows to the actuator 600. When the servo valve 400 is in the third servo valve mode, oil enters the crossover line 401 through the inlet passage 301, and directly flows to the actuating mechanism 600 through the crossover line 401. It can be seen that the direction of movement of the actuator 600 is opposite in the first and third servo valve modes.

Illustratively, the dual mode valve 500 is a two-position two-way solenoid valve with a built-in check valve, e.g., it includes a check valve 502 and a two-way valve 501, the check valve 502 corresponding to a first mode of operation and the two-way valve 501 corresponding to a second mode of operation, e.g., when the aircraft is in a critical phase of flight, the check valve 502 operates, i.e., allows only one-way flow of liquid.

Illustratively, in the first embodiment, by providing the dual-mode valve 500 on one of the two fluid passages between the servo valve 400 and the actuating mechanism 600, the dual-mode valve 500 can be controlled to operate in the first operating mode when the aircraft is in a critical flight phase, so as to only allow one-way fluid circulation, thereby avoiding the erroneous recovery of the actuating mechanism 600.

Fig. 2 is a hydraulic actuating device according to a second embodiment of the present invention. The device comprises: the hydraulic control valve comprises a servo valve 400, an actuating mechanism 600, a double-mode valve 500, a liquid inlet passage 301, a liquid outlet passage 302, a selector valve 700, an electromagnetic control valve 800, two load unloading valves 900 and a back pressure valve 303.

Illustratively, one side of the servo valve 400 is in fluid communication with an inlet liquid passage 301 and an outlet liquid passage 302 of the liquid supply system 300, the other side of the servo valve 400 is in fluid communication with the actuating mechanism 600 via two liquid channels, and the servo valve 400 controls the flow rate and the direction of the output liquid thereof according to the received servo electric signals so as to drive the actuating mechanism 600 to move according to a preset command.

Further, the dual mode valve 500 is disposed on the first fluid passage 405 or the second fluid passage 406 between the servo valve 400 and the selector valve 700. Specifically, when dual mode valve 500 is disposed on first fluid passageway 405, in a first mode of operation, dual mode valve 500 allows fluid to flow to servo valve 400, and when dual mode valve 500 is disposed on second fluid passageway 406, in a first mode of operation, dual mode valve 500 allows fluid to flow to selector valve 700. In other embodiments, the dual mode valve 500 may be disposed in either the third fluid passage 704 or the fourth fluid passage 705 between the selector valve 700 and the actuator mechanism 600.

Illustratively, as shown in fig. 2, the servo electrical signal is generated by the control circuit 100, the control signal is generated by the independent control circuit 200, and the control signal and the servo electrical signal are independent of each other. In the present embodiment, the servo electrical signal and the control signal may be generated by the control circuit 100 or generated by the independent control circuit 200, and they may be independent of each other. Wherein the servo electrical signal is applied to the first solenoid valve 404 to control the servo valve 400 to operate in different modes. The control signal is applied to second solenoid 503 to control dual mode valve 500 to operate in different modes. The dual-mode valve 500 is controlled by an independent control channel, so that the influence of control instruction errors of the servo valve 400 and the selection valve 700 on the dual-mode valve 500 is avoided, and the logic complexity of a control loop is reduced.

Illustratively, the dual mode valve 500 is a two-position two-way solenoid valve with a built-in check valve, for example, it includes a check valve 502 and a two-way valve 501, the check valve 502 corresponds to the first operating mode, the two-way valve 501 corresponds to the second operating mode, for example, when the aircraft is in a critical phase of flight, the check valve 502 operates to allow only one-way fluid flow, thereby avoiding an actuator erroneous recovery. The flight key phases include, but are not limited to, an aircraft climb phase and an aircraft attitude sharp change phase.

Illustratively, the selector valve 700 includes a first selection mode, a second connecting line 701 and a third connecting line 702, wherein the second connecting line 701 and the third connecting line 702 correspond to the first selection mode and the second selection mode, respectively. When the selection valve 700 is operating in the first selection mode, the actuating mechanism 600 is controlled by the servo valve 400, and when the selection valve 700 is operating in the first selection mode, the actuating mechanism 600 loses control of the servo valve 400. In other words, the second connecting line 701 may communicate the first and second

fluid passages

405, 406 to the third and fourth fluid passages 704, 705, respectively, such that the servo valve 400 controls the actuation mechanism 600. The third connecting line 702 disconnects the first fluid passage 405 and the second fluid passage 406 and the corresponding third fluid passage 704 and fourth fluid passage 705, and connects the third fluid passage 704 and fourth fluid passage 705 to a loop with a damping structure 706, thereby realizing an internal circulation structure independent of the servo valve 400, and in the second selection mode, the actuating mechanism 600 can receive the action of an external force to move towards the direction of the external force, and the resistance provided by the damping structure 706 facilitates controlling the position of the movement of the actuating mechanism 600. Illustratively, the selector valve 700 is a two-position, six-way solenoid valve.

Illustratively, one side of the solenoid control valve 800 has a fifth fluid passage 804 and a sixth fluid passage 803, the other side of the solenoid control valve 800 has a control passage 805, the fifth fluid passage 804 is in fluid communication with the inlet passage 301 of the liquid supply system 300 to output high-pressure liquid to the selector valve 700 via the control passage 805 after the solenoid control valve 800 is energized, and the sixth fluid passage 803 is in fluid communication with the outlet passage 302 of the liquid supply system 300 to output non-high-pressure liquid to the selector valve 700 via the control passage 805 after the solenoid control valve 800 is de-energized. Further, the solenoid control valve 800 comprises a first control mode, a second control mode, a fourth connecting line 801 and a fifth connecting line 802, wherein the fourth connecting line 801 and the fifth connecting line 802 correspond to the first control mode and the second control mode, respectively. The fourth connecting line 801 communicates the control passage 805 to the liquid outlet passage 302, and the fifth connecting line 802 communicates the control passage 805 to the liquid inlet passage 301. Illustratively, the solenoid control valve 800 is a two-position, three-way valve. The control passage 805 of the solenoid control valve 800 communicates with the pressure valve 703 of the selector valve 700 to control the selector valve 700.

Illustratively, the actuating mechanism 600 includes a ram 603, a piston 602, and a connecting rod 601. The piston 602 is disposed in the actuator cylinder 603 to divide the actuator cylinder 603 into two sealed first and

second cavities

604 and 605, the first and

second cavities

604 and 605 are respectively in fluid communication with the two liquid passages, and the connecting rod 601 is fixedly connected to the piston 602, so that the connecting rod 601 can perform piston motion between the first and

second cavities

604 and 605 with the piston 602 according to the direction of the liquid pressure in the actuator cylinder 603.

Illustratively, a back pressure valve 303 is disposed between the servo valve 400 and the liquid outlet passage 302 of the liquid supply system 300 for stabilizing the pressure of the liquid in the liquid outlet passage 302.

Illustratively, the two load relief valves 900 are disposed between the selector valve 700 and the actuating mechanism 600 and are both in fluid communication with the selector valve 700 and the actuating mechanism 600. When the selector valve 700 is operated in the second selection mode, the load relief valves 900 are used to relieve the pressure of the conduits in the third fluid passage 704 and the fourth fluid passage 705, i.e. both load relief valves 900 are used to relieve the pressure of the liquid in the first cavity 604 and/or the second cavity 605 during the movement of the piston 602.

Embodiments are also possible to independently trigger the dual mode valve 500 to operate in the first operation mode when the aircraft is in a critical phase of flight by providing the dual mode valve 500 in one of the two fluid passages between the servo valve 400 and the actuator 600, thereby only allowing one-way fluid communication to avoid erroneous recovery of the actuator 600.

Fig. 3 is a hydraulic actuating device according to a third embodiment of the present invention. The device comprises: the hydraulic control system comprises a servo valve 400, an actuating mechanism 600, a double-mode valve 500, a liquid inlet passage 301, a liquid outlet passage 302, a selector valve 700, an electromagnetic control valve 800, two load unloading valves 900, a back pressure valve 303, a first bypass liquid passage 903, a second bypass liquid passage 904 and a compensator 905.

Illustratively, as shown in fig. 3, the servo electrical signal is generated by the control circuit 100, and the control signal is generated by the independent control circuit 200, in this embodiment, the servo electrical signal and the control signal may be generated by the control circuit 100 or the control circuit 200, and they may be independent of each other. The servo electrical signal is applied to the first solenoid valve 404 to control the servo valve 400 to operate in different modes. The control signal is applied to second solenoid 503 to control dual mode valve 500 to operate in different modes. The dual-mode valve 500 is controlled by the independent control channel 805, so that the influence of control instruction errors of the servo valve 400 and the selector valve 700 on the dual-mode valve 500 is avoided, and the logic complexity of a control loop is reduced.

Illustratively, when the servo valve 400 is in the first servo valve mode, oil enters the crossover line 401 through the inlet passage 301, flows through the crossover line 401 through the dual mode valve 500, and flows to the actuator 600. When the servo valve 400 is in the third servo valve mode, oil enters the crossover line 401 through the inlet passage 301, passes through the crossover line 401, and then flows to the actuator 600. It can be seen that the direction of movement of the actuator 600 is opposite in the first and third servo valve modes.

Illustratively, the dual mode valve 500 is a two-position two-way solenoid valve with a built-in check valve, e.g., including a check valve 502 and a two-way valve 501, the check valve 502 corresponding to a first mode of operation and the two-way valve 501 corresponding to a second mode of operation, e.g., when the aircraft is in a critical phase of flight, the check valve 502 operates to allow only one-way fluid flow. The flight key phases include, but are not limited to, an aircraft climb phase and an aircraft attitude sharp change phase.

fluid passages

405, 406 to the third and fourth fluid passages 704, 705, respectively, such that the servo valve 400 controls the actuation mechanism 600. The third connecting line 702 disconnects the first fluid passage 405 and the second fluid passage 406 and the corresponding third fluid passage 704 and fourth fluid passage 705, and connects the third fluid passage 704 and fourth fluid passage 705 to a loop with a damping structure 706, so as to realize an internal circulation structure independent of the servo valve 400, and in the second selection mode, the actuating mechanism 600 can receive the action of an external force to move towards the direction of the external force, and the resistance provided by the damping structure 706 facilitates the control of the position of the actuating mechanism 600. Illustratively, the selector valve 700 is a two-position, six-way solenoid valve.

Illustratively, one side of the solenoid control valve 800 has a fifth fluid passage 804 and a sixth fluid passage 803, the other side of the solenoid control valve 800 has a control passage 805, the fifth fluid passage 804 is in fluid communication with the inlet passage 301 of the liquid supply system 300 to output high-pressure liquid to the selector valve 700 via the control passage 805 after the solenoid control valve 800 is energized, and the sixth fluid passage 803 is in fluid communication with the outlet passage 302 of the liquid supply system 300 to output non-high-pressure liquid to the selector valve 700 via the control passage 805 after the solenoid control valve 800 is de-energized. The solenoid control valve 800 further comprises a first control mode, a second control mode, a fourth connecting line 801, a fifth connecting line 802, wherein the fourth connecting line 801 and the fifth connecting line 802 correspond to the first control mode and the second control mode, respectively. The fourth connecting line 801 communicates the control passage 805 to the liquid outlet passage 302, and the fifth connecting line 802 communicates the control passage 805 to the liquid inlet passage 301. Illustratively, the solenoid control valve 800 is a two-position, three-way valve.

Illustratively, the actuating mechanism 600 includes a cylinder 603, a piston 602, a connecting rod 601 and a displacement sensor 606, wherein the piston 602 is disposed in the cylinder 603 to divide the cylinder 603 into two closed first and

second cavities

604 and 605, the first and

second cavities

604 and 605 are respectively in fluid communication with the two liquid channels, and the connecting rod 601 is fixedly connected to the piston 602, so that the connecting rod 601 can move with the piston 602 as the piston 602 moves between the first and

second cavities

604 and 605 according to the direction of the liquid pressure in the cylinder 603. Further, the displacement sensor 606 is used for acquiring displacement information of the actuating mechanism 600 in real time so as to realize closed-loop servo for the actuating mechanism 600.

Illustratively, one end of the first bypass liquid channel 903 and one end of the second bypass liquid channel 904 are respectively in liquid communication with the two liquid channels, the other end of the first bypass liquid channel 903 and the other end of the second bypass liquid channel 904 are both in fluid communication with the liquid outlet passage 302 of the liquid supply system 300, wherein an anti-cavitation valve and a pressure sensor are respectively arranged on the first bypass liquid channel 903 and the second bypass liquid channel 904.

Illustratively, the compensator 905 is in fluid communication with the inlet of the back pressure valve 303 via the first bypass liquid passage 903 or the second bypass liquid passage 904. The compensator 905 compensates the pressure inside the hydraulic actuator according to the pressure parameter obtained by the pressure sensor, so that the pressure inside the hydraulic actuator is maintained in a stable range.

As can be seen from the above, in the third embodiment, by providing the dual-mode valve on one of the two liquid passages between the servo valve and the actuating mechanism, when the aircraft is in a critical flight stage, the dual-mode valve can be triggered to operate in the first operating mode, so as to only allow one-way circulation of liquid, thereby avoiding erroneous recovery of the actuating mechanism.

The invention also provides an aircraft comprising any of the hydraulic actuation devices described above.

In summary, although the present invention has been described with reference to the preferred embodiments, the above-described preferred embodiments are not intended to limit the present invention, and those skilled in the art can make various changes and modifications without departing from the spirit and scope of the present invention, therefore, the scope of the present invention shall be determined by the appended claims.

Claims

1. The hydraulic actuating device is characterized by comprising a servo valve and an actuating mechanism, wherein one side of the servo valve is in fluid communication with a liquid inlet passage and a liquid outlet passage of a liquid supply system, the other side of the servo valve is in fluid communication with the actuating mechanism through two liquid passages, and the servo valve controls the flow and the direction of output liquid according to received servo electric signals so as to drive the actuating mechanism to move according to a preset instruction;

the double-mode valve can convert working modes according to received control signals, and allows liquid to flow in a one-way mode in a first working mode and in a two-way mode in a second working mode.

2. A hydraulic actuating device according to claim 1, wherein the control signal and the servo electrical signal are independent of each other.

3. The hydraulic actuation device of claim 2, wherein the dual mode valve operates in the first mode of operation with an energized signal as the control signal after being energized, and operates in the second mode of operation with a de-energized signal as the control signal after being de-energized.

4. A hydraulic actuating device according to claim 3, wherein the dual mode valve is a two-position two-way solenoid valve with a built-in check valve.

5. The hydraulic actuating device of claim 4, wherein a displacement sensor is provided within the actuating mechanism for acquiring displacement information of the actuating mechanism in real time for implementing closed loop servo for the actuating mechanism.

6. The hydraulically actuated device of any one of claims 1 to 5, characterized in that it further comprises a selector valve having on one side a first fluid passage and a second fluid passage belonging to said two-way fluid passage, respectively, said first fluid passage being in direct fluid communication with said servo valve, said second fluid passage being in fluid communication with said double mode valve so as to be in fluid communication with said servo valve indirectly via said double mode valve, and also having on the other side a third fluid passage and a fourth fluid passage belonging to said two-way fluid passage, respectively, said third fluid passage and fourth fluid passage each being in fluid communication with said actuating mechanism, wherein said selector valve is capable of switching an operation mode according to a pressure of a control liquid input from the control passage, when said control liquid is a high-pressure liquid, the selector valve operates in a common undamped operating mode, and operates in a damped operating mode when the control fluid is a non-high pressure fluid.

7. The hydraulically actuated device of claim 6, further comprising a solenoid control valve having a fifth fluid passage and a sixth fluid passage on one side of the solenoid control valve and the control passage on the other side of the solenoid control valve, the fifth fluid passage being in fluid communication with an inlet passage of the liquid supply system to output high pressure liquid to the selector valve via the control passage upon energization of the solenoid control valve, the sixth fluid passage being in fluid communication with an outlet passage of the liquid supply system to output non-high pressure liquid to the selector valve via the control passage upon de-energization of the solenoid control valve.

8. The hydraulic actuating device of claim 7, further comprising a first bypass fluid passage and a second bypass fluid passage, one end of the first bypass fluid passage and one end of the second bypass fluid passage being in fluid communication with the two fluid passages, respectively, the other end of the first bypass fluid passage and the other end of the second bypass fluid passage being in fluid communication with a fluid outlet passage of the fluid supply system, wherein the first bypass fluid passage and the second bypass fluid passage are each provided with an anti-cavitation valve and a pressure sensor.

9. The hydraulic actuating device of claim 8, further comprising a back pressure valve disposed between the servo valve and a fluid outlet passage of the fluid supply system for stabilizing a pressure of fluid in the fluid outlet passage.

10. The hydraulic actuating device of claim 9, further comprising a compensator in fluid communication with an inlet of the backpressure valve via the first bypass fluid passage or the second bypass fluid passage.

11. The hydraulic actuating device of claim 10 further comprising two load relief valves disposed between and in fluid communication with the selector valve and the actuating mechanism.

12. A hydraulic actuating device according to claim 1, wherein the actuating mechanism is a piston-cylinder actuator and the liquid is oil.

13. Hydraulic actuating device according to claim 11, characterized in that the selector valve is a two-position six-way solenoid valve and the solenoid control valve is a two-position three-way valve.

14. The hydraulic actuating apparatus of claim 13 wherein the piston-cylinder actuator includes an actuator cylinder, a piston, and a connecting rod;

the piston is arranged in the actuating cylinder so as to divide the actuating cylinder into a first closed cavity and a second closed cavity, and the first cavity and the second cavity are respectively communicated with the two liquid channels in a fluid mode;

the connecting rod is fixedly connected with the piston, so that the connecting rod can do piston motion between the first cavity and the second cavity along with the piston according to the direction of the liquid pressure in the actuating cylinder.

15. A hydraulically actuated device according to claim 14, wherein the two load relief valves are used to relieve the pressure of the liquid in the first and/or second chambers during movement of the piston.

16. An aircraft comprising the hydraulic actuation device of any one of claims 1-15 and a controller, wherein the controller triggers the dual mode valve to operate in the first operating mode when the aircraft is in a critical phase of flight and triggers the dual mode valve to operate in the second operating mode when the aircraft is in a non-critical phase of flight.