Hydraulic transmission system protection method and system

Abstract

The invention belongs to the field of hydraulic transmission system design, and discloses a hydraulic transmission system protection method and system.The protection method comprises the steps that onboard state signals, flight control system state signals and first hydraulic pressure and second hydraulic pressure of each hydraulic pipeline in a hydraulic transmission system are collected in real time; according to the onboard state signal, an electric pump closing instruction and a hydraulic pressure logic judgment instruction are output through an onboard state threshold value and first electric pump control logic, and an electric pump connected to a hydraulic pipeline is closed according to the electric pump closing instruction; and acquiring a flight control system state signal, first hydraulic pressure and second hydraulic pressure according to the hydraulic pressure logic judgment instruction, and automatically controlling the electric pump by adopting a second electric pump control mechanism and a hydraulic pipeline protection mechanism through a low-pressure threshold value and a pressure safety threshold value. According to the invention, the starting of each electric pump can be automatically controlled, a hydraulic passage can be protected through a plurality of mechanisms, and the flight safety can be improved.

Description

Technical Field

[0001] The invention belongs to the field of hydraulic transmission system design and relates to a hydraulic transmission system protection method and system. Background Art

[0002] The output of the electric pump in the aircraft system is usually connected to the input of the hydraulic transmission system. The hydraulic pressure or liquid power is controlled by the operation of the electric pump to drive the operation of the mechanism connected to the hydraulic transmission system. For example, in the hydraulic transmission system of the aircraft, the electric pump control system generally adopts dual redundancy or higher redundancy for control. The working scene and frequency of the electric pump are very high. At present, automatic control replaces manual control by the pilot. However, data source abnormalities or control logic abnormalities may occur during the control process, resulting in continuous erroneous opening or closing of the electric pump, providing incorrect hydraulic power and hydraulic pressure to the hydraulic transmission system, causing overpressure or underpressure in the hydraulic transmission system, affecting flight safety. Summary of the invention

[0003] In order to solve the technical problems that when the hydraulic transmission system is automatically controlled, the wrong hydraulic power and hydraulic pressure are provided to the hydraulic transmission system, resulting in overpressure or underpressure, which affects the normal operation and safety of the mechanism, the present invention discloses a method for protecting the hydraulic transmission system, which comprises the following steps:

[0004] S2, collecting in real time the onboard status signal, the flight control system status signal and the current hydraulic pressure of each hydraulic pipeline in the hydraulic transmission system, wherein the current hydraulic pressure includes a first hydraulic pressure and a second hydraulic pressure;

[0005] S3, according to the onboard status signal, outputting an electric pump shutdown instruction and a hydraulic pressure logic judgment instruction through an onboard status threshold and a first electric pump control logic, and shutting down the electric pump connected to the hydraulic pipeline according to the electric pump shutdown instruction;

[0006] S4. Acquire the flight control system status signal, the first hydraulic pressure and the second hydraulic pressure according to the hydraulic pressure logic judgment instruction, and automatically control the electric pump connected to each hydraulic pipeline by using the second electric pump control mechanism and the hydraulic pipeline protection mechanism through the low pressure threshold and the pressure safety threshold.

[0007] Furthermore, the method further comprises:

[0008] S11. Set the on-board status threshold. When the on-board status signal is less than the on-board status threshold, output the electric pump shutdown instruction. When the on-board status signal is greater than or equal to the on-board status threshold, output the hydraulic pressure logic judgment instruction to construct the first electric pump control logic.

[0009] Furthermore, the method further comprises:

[0010] S12, given the low pressure threshold and the pressure safety threshold, obtaining the first hydraulic pressure according to the hydraulic pressure logic judgment instruction, comparing the first hydraulic pressure and the low pressure threshold, outputting a hydraulic pipeline protection start instruction if the first hydraulic pressure is less than or equal to the low pressure threshold, and starting and controlling the electric pump connected to the hydraulic pipeline through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism according to the hydraulic pipeline protection start instruction; if the first hydraulic pressure is greater than the low pressure threshold, outputting a controlled mechanism logic judgment instruction on the machine;

[0011] The flight control system status signal is obtained according to the onboard controlled mechanism logic judgment instruction, and whether the controlled mechanism needs pressure is judged according to the flight control system status signal; if it is judged that there is a pressure demand, a hydraulic pipeline protection start instruction is output; according to the hydraulic pipeline protection start instruction, the electric pump connected to the hydraulic pipeline is started and controlled through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism; if it is judged that there is no pressure demand, an electric pump shutdown instruction is output to construct the second electric pump control logic.

[0012] Furthermore, the method further comprises:

[0013] S13. Acquire the second hydraulic pressure according to the hydraulic pipeline protection start instruction, compare the second hydraulic pressure with the pressure safety threshold, and if the second hydraulic pressure is greater than or equal to the pressure safety threshold, output the electric pump shutdown instruction, the electric pump prohibition start flag and the overpressure alarm signal to the second electric pump control logic; if the second hydraulic pressure is less than the pressure safety threshold, output the electric pump start flag to the second electric pump control logic to construct the hydraulic pipeline protection mechanism.

[0014] Preferably, the method further comprises:

[0015] S14. Start timing after outputting the hydraulic pipeline protection start instruction. When the second electric pump control logic does not receive the electric pump start prohibition flag or the electric pump start flag output by the hydraulic pipeline protection mechanism within a set time period, the timeout emergency mechanism is started. According to the timeout emergency mechanism, the electric pump start instruction output by the second electric pump control logic is used to control the start of the electric pump.

[0016] Furthermore, the flight control system status signal includes a landing gear signal and a control surface status signal, the onboard status signal includes a ground speed signal, and the controlled mechanism includes a landing gear and a control surface.

[0017] Furthermore, in step S12, judging whether the controlled mechanism needs pressure according to the flight control system state signal includes:

[0018] S121, judging whether the landing gear has a pressure requirement according to the landing gear signal, and if the landing gear signal is a retracting signal or a lowering signal, judging that the landing gear has a pressure requirement;

[0019] S122, judging whether the rudder surface has a pressure demand according to the rudder surface state signal, and if the rudder surface state signal is a rudder surface position change signal, judging that the rudder surface has a pressure demand;

[0020] S123: When any one or both of the control surface and the landing gear have pressure requirements, determine whether the controlled mechanism needs pressure.

[0021] The embodiment of the present invention further provides a hydraulic transmission system protection system, the protection system comprising a collection module, a data scheduling module, a monitoring module and a plurality of electric pump control modules, each of the electric pump control modules is respectively connected to an electric pump, and the output end of the collection module is connected to the input end of the data scheduling module and the monitoring module;

[0022] The data scheduling module and the monitoring module are both connected to each of the electric pump control modules. The electric pump control module uses the first electric pump control logic and the second electric pump control logic to output an electric pump control signal and a hydraulic pipeline protection start instruction based on the onboard status signal, the flight control system status signal and the first hydraulic pressure of the hydraulic pipeline extracted from the data scheduling module; the monitoring module extracts the second hydraulic pressure of the hydraulic pipeline based on the hydraulic pipeline protection start instruction, and outputs an electric pump start flag or an electric pump start prohibition flag to the electric pump control module through the second hydraulic pressure and the pressure safety threshold.

[0023] Furthermore, the protection system also includes a power supply module, the input end of the power supply module is connected to the onboard power supply, and the output end is connected to the acquisition module, the data scheduling module, the monitoring module and each of the electric pump control modules, and the power supply module supplies power to the acquisition module, the data scheduling module, the monitoring module and the electric pump control module.

[0024] Furthermore, there are at least two hydraulic pipelines in the hydraulic transmission system, and there are at least two electric pump control modules. Each electric pump control module is connected to one hydraulic pipeline in the hydraulic transmission system via an electric pump, and the collection module is connected to the hydraulic pipeline via two collection passages.

[0025] Compared with the prior art, the at least one technical solution adopted in the embodiments of this specification can achieve the following beneficial effects:

[0026] 1. By automating the electric pump on the hydraulic pipeline, the pilot does not need to spend a lot of energy on controlling the electric pump during the mission execution, which significantly reduces the pilot's workload;

[0027] 2. This system automatically controls the opening and closing of the electric pump according to different aircraft states, thus avoiding the need to keep the electric pump on all the time, significantly reducing aircraft energy consumption, improving energy efficiency, and avoiding overpressure in the hydraulic pipeline that may damage the hydraulic transmission system, thereby improving flight safety.

[0028] 3. Two-level protection is designed for the hydraulic transmission system. The monitoring module is designed to continuously and independently monitor the status of each hydraulic pipeline. When the safety risk of excessive pressure in the hydraulic pipeline occurs, the overpressure alarm information can be output to the electric pump control module. When the internal fault of the electric pump control module is caused by the data source or logic abnormality, the electric pump can be shut down in time. Otherwise, if a more serious situation occurs, such as a hardware failure of the control module drive, the monitoring module can directly shut down the corresponding electric pump as the second line of defense to enhance the protection effect;

[0029] 4. The safety design of configuring an electric pump control module for each hydraulic pipeline in the protection system avoids the problem of control failure and damage to the hydraulic transmission system caused by a single fault, thereby enhancing the safety of the aircraft;

[0030] 5. A timeout emergency mechanism is designed based on the hydraulic pipeline protection mechanism. In the extreme case that the electric pump control module fails to receive the indication signal from the monitoring module, the electric pump can be started normally to ensure the integrity and safety of the aircraft functions. BRIEF DESCRIPTION OF THE DRAWINGS

[0031] In order to more clearly illustrate the technical solutions of the embodiments of the present application, the drawings required for use in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of the present application. For ordinary technicians in this field, other drawings can be obtained based on these drawings without paying creative work.

[0032] Figure 1 A flow chart of a hydraulic transmission system protection method disclosed in an embodiment of the present invention;

[0033] Figure 2 The algorithm flow of the hydraulic pipeline protection mechanism disclosed in the embodiment of the present invention;

[0034] Figure 3The algorithm flow after the second electric pump control output starts the hydraulic pipeline protection instruction disclosed in the embodiment of the present invention;

[0035] Figure 4 It is an architecture diagram of the hydraulic transmission system protection system disclosed in an embodiment of the present invention;

[0036] Among them, 1. acquisition module; 2. data scheduling module; 3. monitoring module; 4. electric pump control module; 5. power supply module. DETAILED DESCRIPTION

[0037] The embodiments of the present application are described in detail below with reference to the accompanying drawings.

[0038] The following describes the implementation methods of the present application through specific specific examples, and those skilled in the art can easily understand other advantages and effects of the present application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of the present application, rather than all the embodiments. The present application can also be implemented or applied through other different specific implementation methods, and the details in this specification can also be modified or changed in various ways based on different viewpoints and applications without departing from the spirit of the present application. It should be noted that the following embodiments and the features of the embodiments can be combined with each other in the absence of conflict. Based on the embodiments in the present application, all other embodiments obtained by ordinary technicians in the field without making creative work belong to the scope of protection of the present application.

[0039] The embodiment of the present invention discloses a hydraulic transmission system protection method, see Figure 1 and Figure 2 As shown, the method comprises the following steps:

[0040] S2, collecting in real time the onboard status signal, the flight control system status signal and the current hydraulic pressure of each hydraulic pipeline in the hydraulic transmission system, wherein the current hydraulic pressure includes a first hydraulic pressure and a second hydraulic pressure;

[0041] S3, according to the onboard status signal, outputting an electric pump shutdown instruction and a hydraulic pressure logic judgment instruction through an onboard status threshold and a first electric pump control logic, and shutting down the electric pump connected to the hydraulic pipeline according to the electric pump shutdown instruction;

[0042] S4. Acquire the flight control system status signal, the first hydraulic pressure and the second hydraulic pressure according to the hydraulic pressure logic judgment instruction, and automatically control the electric pump connected to each hydraulic pipeline by using the second electric pump control mechanism and the hydraulic pipeline protection mechanism through the low pressure threshold and the pressure safety threshold.

[0043] Further, see Figure 1 and Figure 2As shown, the method also includes:

[0044] S11. Set the on-board status threshold. When the on-board status signal is less than the on-board status threshold, output the electric pump shutdown instruction. When the on-board status signal is greater than or equal to the on-board status threshold, output the hydraulic pressure logic judgment instruction to construct the first electric pump control logic.

[0045] Further, see Figure 1 and Figure 2 As shown, the method also includes:

[0046] S12, given the low pressure threshold and the pressure safety threshold, obtaining the first hydraulic pressure according to the hydraulic pressure logic judgment instruction, comparing the first hydraulic pressure and the low pressure threshold, outputting a hydraulic pipeline protection start instruction if the first hydraulic pressure is less than or equal to the low pressure threshold, and starting and controlling the electric pump connected to the hydraulic pipeline through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism according to the hydraulic pipeline protection start instruction; if the first hydraulic pressure is greater than the low pressure threshold, outputting a controlled mechanism logic judgment instruction on the machine;

[0047] The flight control system status signal is obtained according to the onboard controlled mechanism logic judgment instruction, and whether the controlled mechanism needs pressure is judged according to the flight control system status signal; if it is judged that there is a pressure demand, a hydraulic pipeline protection start instruction is output; according to the hydraulic pipeline protection start instruction, the electric pump connected to the hydraulic pipeline is started and controlled through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism; if it is judged that there is no pressure demand, an electric pump shutdown instruction is output to construct the second electric pump control logic.

[0048] Further, see Figure 1 and Figure 2 As shown, the method also includes:

[0049] S13. Acquire the second hydraulic pressure according to the hydraulic pipeline protection start instruction, compare the second hydraulic pressure with the pressure safety threshold, and if the second hydraulic pressure is greater than or equal to the pressure safety threshold, output the electric pump shutdown instruction, the electric pump prohibition start flag and the overpressure alarm signal to the second electric pump control logic; if the second hydraulic pressure is less than the pressure safety threshold, output the electric pump start flag to the second electric pump control logic to construct the hydraulic pipeline protection mechanism.

[0050] Preferably, see Figure 3 The method also includes:

[0051] S14. Start timing after outputting the hydraulic pipeline protection start instruction. When the second electric pump control logic does not receive the electric pump start prohibition flag or the electric pump start flag output by the hydraulic pipeline protection mechanism within a set time period, the timeout emergency mechanism is started. According to the timeout emergency mechanism, the electric pump start instruction output by the second electric pump control logic is used to control the start of the electric pump.

[0052] Furthermore, the flight control system status signal includes a landing gear signal and a control surface status signal, the onboard status signal includes a ground speed signal, and the controlled mechanism includes a landing gear and a control surface.

[0053] Further, see Figure 1 and Figure 2 As shown, in step S12, judging whether the controlled mechanism needs pressure according to the flight control system state signal includes:

[0054] S121, judging whether the landing gear has a pressure requirement according to the landing gear signal, and if the landing gear signal is a retracting signal or a lowering signal, judging that the landing gear has a pressure requirement;

[0055] S122, judging whether the rudder surface has a pressure demand according to the rudder surface state signal, and if the rudder surface state signal is a rudder surface position change signal, judging that the rudder surface has a pressure demand;

[0056] S123: When any one or both of the control surface and the landing gear have pressure requirements, determine whether the controlled mechanism needs pressure.

[0057] Based on the same inventive concept, a hydraulic transmission system protection system is also provided in an embodiment of the present invention, as described in the following embodiments. The hydraulic transmission system protection system is used to implement the above-mentioned hydraulic transmission system protection method. As used below, the term "unit" or "module" can be a combination of software and / or hardware that implements a predetermined function. Although the device described in the following embodiments is preferably implemented in software, the implementation of hardware, or a combination of software and hardware, is also possible and conceived.

[0058] See also Figure 4 As shown, the protection system includes an acquisition module 1, a data scheduling module 2, a monitoring module 3 and multiple electric pump control modules 4, each of the electric pump control modules 4 is connected to an electric pump, and the output end of the acquisition module 1 is connected to the input end of the data scheduling module 2 and the monitoring module 3.

[0059] The data scheduling module 2 and the monitoring module 3 are both connected to each of the electric pump control modules 4. The electric pump control module 4 uses the first electric pump control logic and the second electric pump control logic to output an electric pump control signal and a start hydraulic pipeline protection instruction based on the onboard status signal, the flight control system status signal and the first hydraulic pressure of the hydraulic pipeline extracted from the data scheduling module 2; the monitoring module 3 extracts the second hydraulic pressure of the hydraulic pipeline based on the start hydraulic pipeline protection instruction, and outputs an electric pump start flag or an electric pump prohibition start flag to the electric pump control module 4 through the second hydraulic pressure and the pressure safety threshold.

[0060] Furthermore, the protection system also includes a power supply module 5, the input end of the power supply module 5 is connected to the on-board power supply, and the output end is connected to the acquisition module 1, the data scheduling module 2, the monitoring module 3 and each of the electric pump control modules 4, and the power supply module 5 supplies power to the acquisition module 1, the data scheduling module 2, the monitoring module 3 and the electric pump control module 4.

[0061] Furthermore, there are at least two hydraulic pipelines in the hydraulic transmission system, and there are at least two electric pump control modules 4. Each electric pump control module 4 is connected to one hydraulic pipeline in the hydraulic transmission system via an electric pump, and the collection module is connected to the hydraulic pipeline via two collection passages.

[0062] 1. By automating the electric pump on the hydraulic pipeline, the pilot does not need to spend a lot of energy on controlling the electric pump during the mission execution, which significantly reduces the pilot's workload;

[0063] 2. This system automatically controls the opening and closing of the electric pump according to different aircraft states, thus avoiding the need to keep the electric pump on all the time, significantly reducing aircraft energy consumption, improving energy efficiency, and avoiding overpressure in the hydraulic pipeline that may damage the hydraulic transmission system, thereby improving flight safety.

[0064] 3. Two-level protection is designed for the hydraulic transmission system. The monitoring module is designed to continuously and independently monitor the status of each hydraulic pipeline. When the safety risk of excessive pressure in the hydraulic pipeline occurs, the overpressure alarm information can be output to the electric pump control module. When the internal fault of the electric pump control module is caused by the data source or logic abnormality, the electric pump can be shut down in time. Otherwise, if a more serious situation occurs, such as a hardware failure of the control module drive, the monitoring module can directly shut down the corresponding electric pump as the second line of defense to enhance the protection effect;

[0065] 4. The safety design of configuring an electric pump control module for each hydraulic pipeline in the protection system avoids the problem of control failure and damage to the hydraulic transmission system caused by a single fault, thereby enhancing the safety of the aircraft;

[0066] 5. A timeout emergency mechanism is designed based on the hydraulic pipeline protection mechanism. In the extreme case that the electric pump control module fails to receive the indication signal from the monitoring module, the electric pump can be started normally to ensure the integrity and safety of the aircraft functions.

[0067] Obviously, those skilled in the art should understand that the above description is only a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, the embodiments of the present invention may have various modifications and changes. Any modification, equivalent replacement, improvement, etc. made within the spirit and principle of the present invention shall be included in the protection scope of the present invention.

Claims

1. A method for protecting a hydraulic transmission system, characterized in that: The method comprises: Real-time collection of onboard status signals, flight control system status signals, and current hydraulic pressure of each hydraulic pipeline in the hydraulic transmission system, wherein the current hydraulic pressure includes a first hydraulic pressure and a second hydraulic pressure; According to the onboard status signal, an electric pump shut-down instruction and a hydraulic pressure logic judgment instruction are output through an onboard status threshold and a first electric pump control logic, and the electric pump connected to the hydraulic pipeline is shut down according to the electric pump shut-down instruction; The flight control system status signal, the first hydraulic pressure and the second hydraulic pressure are obtained according to the hydraulic pressure logic judgment instruction, and the electric pump connected to each hydraulic pipeline is automatically controlled by the second electric pump control mechanism and the hydraulic pipeline protection mechanism through the low pressure threshold and the pressure safety threshold.

2. The hydraulic transmission system protection method according to claim 1, characterized in that: The method further comprises: The on-board status threshold is set. When the on-board status signal is less than the on-board status threshold, an electric pump shutdown instruction is output. When the on-board status signal is greater than or equal to the on-board status threshold, a hydraulic pressure logic judgment instruction is output to construct the first electric pump control logic.

3. The hydraulic transmission system protection method according to claim 2, characterized in that: The method further comprises: Given the low pressure threshold and the pressure safety threshold, the first hydraulic pressure is obtained according to the hydraulic pressure logic judgment instruction, the first hydraulic pressure and the low pressure threshold are compared, if the first hydraulic pressure is less than or equal to the low pressure threshold, a hydraulic pipeline protection start instruction is output, and according to the hydraulic pipeline protection start instruction, the electric pump connected to the hydraulic pipeline is started and controlled through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism; if the first hydraulic pressure is greater than the low pressure threshold, a controlled mechanism logic judgment instruction is output; The flight control system status signal is obtained according to the onboard controlled mechanism logic judgment instruction, and whether the controlled mechanism needs pressure is judged according to the flight control system status signal; if it is judged that there is a pressure demand, a hydraulic pipeline protection start instruction is output; according to the hydraulic pipeline protection start instruction, the electric pump connected to the hydraulic pipeline is started and controlled through the second hydraulic pressure, the pressure safety threshold and the hydraulic pipeline protection mechanism; if it is judged that there is no pressure demand, an electric pump shutdown instruction is output to construct the second electric pump control logic.

4. The hydraulic transmission system protection method according to claim 3, characterized in that: The method further comprises: The second hydraulic pressure is obtained according to the hydraulic pipeline protection start instruction, and the second hydraulic pressure is compared with the pressure safety threshold. If the second hydraulic pressure is greater than or equal to the pressure safety threshold, the electric pump shutdown instruction, the electric pump prohibition start flag and the overpressure alarm signal are output to the second electric pump control logic; if the second hydraulic pressure is less than the pressure safety threshold, the electric pump start flag is output to the second electric pump control logic to construct the hydraulic pipeline protection mechanism.

5. The hydraulic transmission system protection method according to claim 4, characterized in that: The timing starts after the hydraulic pipeline protection start instruction is output. When the second electric pump control logic does not receive the electric pump start prohibition flag or the electric pump start flag output by the hydraulic pipeline protection mechanism within a set time period, the timeout emergency mechanism is started. According to the timeout emergency mechanism, the electric pump start instruction output by the second electric pump control logic is used to control the start of the electric pump.

6. The hydraulic transmission system protection method according to any one of claims 3 to 5, characterized in that: The flight control system status signal includes a landing gear signal and a control surface status signal, the onboard status signal includes a ground speed signal, and the controlled mechanism includes a landing gear and a control surface.

7. The hydraulic transmission system protection method according to claim 6, characterized in that: Judging whether the controlled mechanism needs pressure according to the flight control system state signal includes: Determining whether the landing gear has a pressure requirement according to the landing gear signal, and if the landing gear signal is a retracting signal or a lowering signal, determining that the landing gear has a pressure requirement; Determine whether the rudder surface has a pressure requirement according to the rudder surface state signal, and if the rudder surface state signal is a rudder surface position change signal, determine that the rudder surface has a pressure requirement; When any one or both of the control surface and the landing gear have pressure requirements, it is determined that the controlled mechanism needs pressure.

8. A hydraulic transmission system protection system, characterized in that: The protection system comprises an acquisition module, a data scheduling module, a monitoring module and a plurality of electric pump control modules, each of the electric pump control modules is respectively connected to an electric pump, and the output end of the acquisition module is connected to the input end of the data scheduling module and the monitoring module; The data scheduling module and the monitoring module are both connected to each of the electric pump control modules. The electric pump control module uses the first electric pump control logic and the second electric pump control logic to output an electric pump control signal and a hydraulic pipeline protection start instruction based on the onboard status signal, the flight control system status signal and the first hydraulic pressure of the hydraulic pipeline extracted from the data scheduling module; the monitoring module extracts the second hydraulic pressure of the hydraulic pipeline based on the hydraulic pipeline protection start instruction, and outputs an electric pump start flag or an electric pump start prohibition flag to the electric pump control module through the second hydraulic pressure and the pressure safety threshold.

9. The hydraulic transmission system protection system according to claim 8, characterized in that: The protection system also includes a power supply module, the input end of the power supply module is connected to the onboard power supply, and the output end is connected to the acquisition module, the data scheduling module, the monitoring module and each of the electric pump control modules, and the power supply module supplies power to the acquisition module, the data scheduling module, the monitoring module and the electric pump control module.

10. The hydraulic transmission system protection system according to claim 8, characterized in that: There are at least two hydraulic pipelines in the hydraulic transmission system, and at least two electric pump control modules. Each electric pump control module is connected to one hydraulic pipeline in the hydraulic transmission system via an electric pump, and the collection module is connected to the hydraulic pipeline via two collection passages.

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