CN114396401B

CN114396401B - Hydraulic actuating device and aircraft

Info

Publication number: CN114396401B
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: 2023-05-26
Anticipated expiration: 2042-01-17
Also published as: CN114396401A

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 of the servo valve 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 is arranged on one of the two liquid channels between the servo valve and the actuating mechanism, can switch working modes according to received control signals, allows liquid to flow unidirectionally in a first working mode, and allows liquid to flow bidirectionally 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 field of cabin door control systems of civil aircraft mostly adopts dual-mode servo actuators, and in general, the safety requirement on error recovery is higher when the cabin door is actuated, and in particular, the safety requirement on error recovery is more severe when the cabin door is in a stage of severe gesture change such as take-off.

The traditional dual-mode servo actuator realizes accurate retraction through an electrohydraulic servo valve, and when in a damping mode, the actuator can perform damping motion under the action of external force. However, the existing technical scheme is not specially designed for the fault of error recovery of the instruction, and when the instruction of a driver or a control circuit is wrong, the electro-hydraulic servo valve is reversely opened, so that the error recovery of the actuator is directly caused, and serious accidents are caused.

Therefore, the existing dual-mode servo actuator has potential safety hazards and is necessary for improving the safety of the dual-mode servo actuator.

Disclosure of Invention

The invention provides a hydraulic actuating device and an aircraft, which can effectively solve the problem that in the prior art, an electro-hydraulic servo valve is reversely opened to directly cause the error recovery of an actuator and cause serious accidents.

According to an aspect of the present invention there is provided a hydraulic actuation device comprising a servo valve and an actuation mechanism, one side of the servo valve being in fluid communication with a liquid inlet and outlet passageway of a liquid supply system, the other side of the servo valve being in fluid communication with the actuation mechanism via two liquid passageways, the servo valve controlling the flow and direction of its output liquid in dependence on a received servo electrical signal to drive the actuation mechanism to move in accordance with a predetermined command; the double-mode valve is arranged on one of the two liquid channels between the servo valve and the actuating mechanism, can switch working modes according to received control signals, allows liquid to flow unidirectionally in a first working mode, and allows liquid to flow bidirectionally 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 an energizing signal as the control signal and operates in the first operating mode after energizing, and takes a de-energizing signal as the control signal and operates in the second operating mode after de-energizing.

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

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

Further, the hydraulic actuating device further includes a selector valve having a first fluid passage and a second fluid passage respectively belonging to the two liquid passages on one side thereof, 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 indirectly in fluid communication with the servo valve via the double mode valve, the selector valve also having a third fluid passage and a fourth fluid passage respectively belonging to the two liquid passages on the other side thereof, both of the third fluid passage and the fourth fluid passage being in fluid communication with the actuating mechanism, wherein the selector valve is capable of operating in a non-damping normal operation mode when the control liquid is a high pressure liquid and in a damping operation mode when the control liquid is a non-high pressure liquid, according to a pressure switching operation mode of the control liquid inputted from the control passage.

Further, the hydraulic actuating device further comprises an electromagnetic control valve, wherein one side of the electromagnetic control valve is provided with a fifth fluid passage and a sixth fluid passage, the other side of the electromagnetic control valve is provided with the control passage, 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 selection 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 selection valve through the control passage.

Further, 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 respectively in fluid communication with a liquid outlet passage of the liquid supply system, and anti-cavitation valves and pressure sensors are arranged on the first bypass liquid channel and the second bypass liquid channel.

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

Further, the hydraulic actuation device further includes a compensator in fluid communication with the inlet of the back pressure valve via the first bypass liquid passage or the second bypass liquid passage.

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

Further, the selection valve is a two-position six-way electromagnetic 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 to divide the actuating cylinder into two closed first cavities and second cavities, and the first cavities and the second cavities are respectively in fluid communication with the two liquid channels; the connecting rod is fixedly connected with the piston, so that the connecting rod can move with the piston between the first cavity and the second cavity according to the direction of the liquid pressure in the actuating cylinder.

Further, 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.

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

The invention has the advantage that by means of the double-mode valve arranged on one of the two liquid channels between the servo valve and the actuating mechanism, the double-mode valve can be controlled to operate in the first operating mode when the aircraft is in a critical phase of flight, so as to allow only one-way circulation of liquid, thereby avoiding erroneous recovery of the actuating mechanism.

Drawings

The technical solution and other advantageous effects of the present invention will be made apparent by the following detailed description of the specific embodiments of the present invention with reference to the accompanying drawings.

Fig. 1 is a schematic structural diagram of a hydraulic actuating device according to a first 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 solutions 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 will be apparent that the described embodiments are only some, but not all, embodiments of the invention. All other embodiments, which can be made by those skilled in the art based on the embodiments of the invention without making any inventive effort, are intended to fall within the scope of the invention.

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

Illustratively, one side of the servo valve 400 is in fluid communication with the inlet 301 and outlet 302 fluid passages of the fluid supply system 300, the other side of the servo valve 400 is in fluid communication with the actuator 600 via two fluid passages, and the servo valve 400 controls the flow and direction of its output fluid according to the received servo electrical signal to drive the actuator 600 to move according to a predetermined command. For example, when the hydraulic actuation device acts on a door of an aircraft, the direction of movement required for the door to open and close is the commanded movement intended for the actuation mechanism 600.

Illustratively, a dual mode valve 500 is disposed in one of the two fluid passages between the servo valve 400 and the actuator 600, the dual mode valve 500 being capable of switching modes of operation in response to a received control signal, the dual mode valve 500 allowing one-way fluid communication in a first mode of operation and the dual mode valve 500 allowing two-way fluid communication in a second mode of operation.

Illustratively, as shown in FIG. 1, 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 this embodiment, the servo electrical signal and the control signal may be generated by the control circuit 100 or the independent control circuit 200, and the two signals 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 acts on the second solenoid valve 503 to control the dual mode valve 500 to operate in different modes.

Illustratively, the fluid supply system 300 is in communication with the servo valve 400 via the fluid inlet path 301 and the fluid outlet path 302, the servo valve 400 includes at least a first servo valve mode, a second servo valve mode, and a third servo valve mode, the servo valve 400 further includes a crossover line 401, a first damper valve 402, and a first connection line 403, wherein the crossover line 401, the first damper valve 402, and the first connection line 403 correspond to the first servo valve mode, the second servo valve mode, and the third servo valve mode of the servo valve 400, respectively.

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, the oil enters the crossover pipe 401 through the inlet passage 301, and flows directly to the actuator 600 after passing through the crossover pipe 401. It can be seen that in the first and third servo valve modes, the direction of movement of the actuator 600 is reversed.

Illustratively, the dual mode valve 500 is a two-position two-way solenoid valve incorporating a one-way valve, e.g., comprising a one-way valve 502 and a two-way valve 501, the one-way 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 one-way valve 502 is operative, i.e., only allowing one-way flow of liquid.

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

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

Illustratively, one side of the servo valve 400 is in fluid communication with the inlet 301 and outlet 302 fluid passages of the fluid supply system 300, the other side of the servo valve 400 is in fluid communication with the actuator 600 via two fluid passages, and the servo valve 400 controls the flow and direction of its output fluid according to the received servo electrical signal to drive the actuator 600 to move according to a predetermined command.

Further, the dual mode valve 500 is disposed on either the first fluid path 405 or the second fluid path 406 between the servo valve 400 and the selector valve 700. Specifically, when the dual mode valve 500 is disposed on the first fluid path 405, in the first mode of operation, the dual mode valve 500 allows fluid to flow to the servo valve 400, and when the dual mode valve 500 is disposed on the second fluid path 406, in the first mode of operation, the dual mode valve 500 allows fluid to flow to the selector valve 700. In other embodiments, the dual mode valve 500 may also be disposed on the third fluid passage 704 or the fourth fluid passage 705 between the selector valve 700 and the actuation 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 this embodiment, the servo electrical signal and the control signal may be generated by the control circuit 100 or the independent control circuit 200, and the two signals may be independent of each other. Wherein a 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 acts on the second solenoid valve 503 to control the 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, 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, the oil enters the crossover pipe 401 through the inlet passage 301, and flows directly to the actuator 600 after passing through the crossover pipe 401. It can be seen that in the first servo valve mode and the third servo valve mode, the direction of movement of the actuator 600 is opposite.

Illustratively, the dual mode valve 500 is a two-position two-way solenoid valve incorporating a one-way valve, e.g., comprising a one-way valve 502 and a two-way valve 501, the one-way 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 one-way valve 502 operates to allow only one-way flow of liquid, thereby avoiding erroneous recovery of the actuation mechanism. The flight critical phases include, but are not limited to, an aircraft climb phase and an aircraft attitude drastic change phase.

Illustratively, the selector valve 700 includes a first selection mode, a second connection line 701, and a third connection line 702, wherein the second connection line 701 and the third connection line 702 correspond to the first selection mode and the second selection mode, respectively. The actuator 600 is controlled by the servo valve 400 when the selector valve 700 is operating in the first selection mode, and the actuator 600 loses control of the servo valve 400 when the selector valve 700 is operating in the first selection mode. In other words, the second connecting line 701 may correspondingly communicate the first fluid passage 405 and the second fluid passage 406 to the third fluid passage 704 and the fourth fluid passage 705, such that the servo valve 400 controls the actuation mechanism 600. The third connecting line 702 disconnects the first and second

fluid passages

405, 406 and the corresponding third and fourth fluid passages 704, 705 and communicates the third and fourth fluid passages 704, 705 in a loop with a damping structure 706 to achieve an internal circulation structure independent of the servo valve 400, in a second selected mode the actuator 600 may receive an external force to move it in the direction of the external force, the damping structure 706 providing a resistance that facilitates control of the position of the actuator 600 movement. 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 liquid 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 liquid 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 includes 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-operated 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 actuator mechanism 600 includes an actuator cylinder 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 cavities 604 and second cavities 605, the first cavities 604 and the second cavities 605 are respectively in fluid communication with the two paths of liquid channels, and the connecting rod 601 is fixedly connected with the piston 602, so that the connecting rod 601 can move with the piston 602 between the first cavities 604 and the second cavities 605 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 outlet passageway 302 of the liquid supply system 300 for stabilizing the pressure of the liquid in the outlet passageway 302.

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

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

Fig. 3 is a hydraulic actuator according to a third embodiment of the present invention. The device comprises: a servo valve 400, an actuating mechanism 600, a double mode valve 500, a feed passage 301, a discharge passage 302, a selector valve 700, a solenoid 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, the control signal is generated by the independent control circuit 200, and in this embodiment, the servo electrical signal and the control signal may be generated by the control circuit 100 or the control circuit 200, respectively. 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 acts on the second solenoid valve 503 to control the 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 selection 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 then flows to the actuator 600. When the servo valve 400 is in the third servo valve mode, the oil enters the crossover pipe 401 through the inlet passage 301, and flows directly to the actuator 600 through the crossover pipe 401. It can be seen that in the first servo valve mode and the third servo valve mode, the direction of movement of the actuator 600 is opposite.

Illustratively, the dual mode valve 500 is a two-position two-way solenoid valve incorporating a one-way valve, e.g., comprising a one-way valve 502 and a two-way valve 501, the one-way 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 one-way valve 502 operates to allow only one-way flow of liquid. The flight critical phases include, but are not limited to, an aircraft climb phase and an aircraft attitude drastic change phase.

fluid passages

405, 406 and the corresponding third and fourth fluid passages 704, 705 and communicates the third and fourth fluid passages 704, 705 into a loop having a damping structure 706 to enable an internal circulation structure independent of the servo valve 400, in a second selection mode, the actuator 600 may receive an external force to move it in the direction of the external force, the damping structure 706 providing a resistance that facilitates control of the position of the actuator 600 movement. 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 liquid 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 liquid 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 includes a first control mode second control mode 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-operated valve 800 is a two-position three-way valve.

Illustratively, the actuating mechanism 600 includes an actuating cylinder 603, a piston 602, a connecting rod 601 and a displacement sensor 606, wherein the piston 602 is disposed in the actuating cylinder 603 to divide the actuating cylinder 603 into two sealed first cavities 604 and second cavities 605, the first cavities 604 and the second cavities 605 are respectively in fluid communication with the two liquid channels, and the connecting rod 601 is fixedly connected with the piston 602, so that the connecting rod 601 can move with the piston 602 between the first cavities 604 and the second cavities 605 according to the direction of the liquid pressure in the actuating cylinder 603. Further, a displacement sensor 606 is used to acquire displacement information of the actuator 600 in real time for achieving closed loop servo for the actuator 600.

Illustratively, one end of the first bypass liquid channel 903 and one end of the second bypass liquid channel 904 are in fluid communication with the two liquid channels, respectively, and 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 channel 302 of the liquid supply system 300, wherein anti-cavitation valves and pressure sensors are disposed on both 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 backpressure valve 303 via the first bypass liquid channel 903 or the second bypass liquid channel 904. The compensator 905 compensates the pressure inside the hydraulic actuator according to the pressure parameter acquired 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 embodiment, by providing a dual mode valve on one of the two liquid channels between the servo valve and the actuating mechanism, the dual mode valve can be triggered to operate in the first operating mode when the aircraft is in a critical flight phase, so as to only allow liquid to circulate unidirectionally, 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 in terms of the preferred embodiments, the preferred embodiments are not limited to the above embodiments, and various modifications and changes can be made by one skilled in the art without departing from the spirit and scope of the invention, and the scope of the invention is defined 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 of the servo valve 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 switch working modes according to received control signals, when the aircraft is in a flight critical stage, the double-mode valve allows liquid to flow unidirectionally in a first working mode, so that the actuating mechanism moves in one direction, and allows liquid to flow bidirectionally in a second working mode;

the control signal and the servo electrical signal are independent of each other, the hydraulic actuation device further comprises a selection valve, one side of the selection valve is provided with a first fluid passage and a second fluid passage which respectively belong to the two liquid channels, the first fluid passage is directly in fluid communication with the servo valve, the second fluid passage is in fluid communication with the dual-mode valve so as to indirectly be in fluid communication with the servo valve via the dual-mode valve, the other side of the selection valve is also provided with a third fluid passage and a fourth fluid passage which respectively belong to the two liquid channels, and both the third fluid passage and the fourth fluid passage are in fluid communication with the actuation mechanism, wherein the selection valve can switch the operation mode according to the pressure of the control liquid input from the control passage, when the control liquid is high-pressure liquid, the selection valve is operated in a damping normal operation mode, and when the control liquid is non-high-pressure liquid, the selection valve is operated in a damping operation mode.

2. The hydraulic actuation device of claim 1, wherein the dual mode valve operates in the first mode with an energizing signal as the control signal after energizing and in the second mode with a de-energizing signal as the control signal after de-energizing.

3. The hydraulic actuation device of claim 2, wherein the dual mode valve is a two-position, two-way solenoid valve with a built-in check valve.

4. A hydraulic actuation device according to claim 3, characterized in that a displacement sensor is provided in the actuation mechanism, which displacement sensor is used for acquiring displacement information of the actuation mechanism in real time for realizing a closed-loop servo for the actuation mechanism.

5. The hydraulic actuation device of claim 1, 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 the feed passage of the feed system to output high pressure liquid to the selector valve via the control passage after the solenoid control valve is energized and the sixth fluid passage being in fluid communication with the discharge passage of the feed system to output non-high pressure liquid to the selector valve via the control passage after the solenoid control valve is de-energized.

6. The hydraulic actuation device of claim 5, 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, and the other end of the first bypass fluid passage and the other end of the second bypass fluid passage being in fluid communication with the outlet passage of the fluid supply system, wherein anti-cavitation valves and pressure sensors are disposed on the first bypass fluid passage and the second bypass fluid passage, respectively.

7. The hydraulic actuation device of claim 6, further comprising a back pressure valve disposed between the servo valve and a tapping passage of the tapping system for stabilizing the pressure of the liquid in the tapping passage.

8. The hydraulic actuation device of claim 7, further comprising a compensator in fluid communication with the inlet of the backpressure valve via the first bypass fluid passage or the second bypass fluid passage.

9. The hydraulic actuation device of claim 8, further comprising two load relief valves disposed between and in fluid communication with the selector valve and the actuation mechanism.

10. The hydraulic actuation device of claim 9, wherein the actuation mechanism is a piston-cylinder actuator and the fluid is oil.

11. The hydraulic actuation device of claim 10, wherein the selector valve is a two-position six-way solenoid valve and the solenoid control valve is a two-position three-way valve.

12. The hydraulic actuation device of claim 11, wherein the piston-cylinder actuator comprises an actuator cylinder, a piston, and a connecting rod;

the piston is arranged in the actuating cylinder to divide the actuating cylinder into two closed first cavities and second cavities, and the first cavities and the second cavities are respectively in fluid communication with the two liquid channels;

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

13. The hydraulic actuation device of claim 12, wherein the two load relief valves are used to relieve pressure of the liquid in the first and/or second chambers during movement of the piston.

14. An aircraft comprising the hydraulic actuation device of any one of claims 1-13 and a controller, wherein the controller triggers the dual mode valve to operate in the first mode of operation when the aircraft is in a critical phase of flight and triggers the dual mode valve to operate in the second mode of operation when the aircraft is in a non-critical phase of flight.