Method and system for comprehensive control of electric pump operation

Abstract

The application belongs to the field of electromechanical control, and relates to electric pump working control technology, and discloses an electric pump working comprehensive control method and system.The working comprehensive control method comprises the following steps: collecting machine state signals, flight control system state signals and hydraulic pressure of each sub-hydraulic system in a hydraulic system in real time; controlling the opening and closing of the electric pump connected to the sub-hydraulic system according to the machine state signals through a first electric pump control logic and an error prevention working mechanism; and automatically controlling the electric pump connected to each sub-hydraulic system according to the flight control system state signals, the hydraulic pressure and the rest of the electric pump control instructions through a second electric pump control logic, the error prevention working mechanism and a staggered working mechanism.The application can ensure the accuracy of the electric pump working, avoid system damage caused by simultaneous starting of the electric pump, and improve system safety.

Description

Technical Field

[0001] This invention belongs to the field of electromechanical control, and relates to electric pump operation control technology, specifically to a comprehensive control method and system for electric pump operation. Background Technology

[0002] Electric pumps typically provide hydraulic or fluid power to hydraulic systems according to instructions. For complex equipment, redundant hydraulic systems are usually designed to ensure their normal operation. For example, in transport aircraft, depending on the transport capacity of the aircraft, complex hydraulic systems with dual redundancy, triple redundancy, or even quadruple redundancy are usually designed, and each redundant hydraulic system is equipped with an electric pump for control, so as to ensure the correct operation of the landing gear, control surface, and other mechanisms on the transport aircraft.

[0003] Due to the high complexity of hydraulic systems, the correct operation of the electric pumps that control them becomes crucial. If the data source controlling the electric pump is abnormal or the control logic malfunctions, incorrect control commands will be output, affecting the normal function of the hydraulic system. This makes it difficult to ensure the correct execution of mechanisms on transport aircraft, thereby impacting flight safety.

[0004] Furthermore, currently, all electric pumps are kept running continuously during flight preparation and flight, which increases aircraft energy consumption and operating costs. Simultaneous startup of all electric pumps also affects their lifespan. More seriously, without appropriate protective measures, simultaneous startup of multiple electric pumps can easily lead to excessive transient current, causing unstable power supply or pump damage, which also affects flight safety. Summary of the Invention

[0005] To improve the accuracy of electric pump operation control and avoid technical problems such as erroneous control affecting normal equipment operation and causing safety hazards, this invention discloses a comprehensive control method for electric pump operation, the method comprising the following steps:

[0006] S4. Real-time acquisition of onboard status signals, flight control system status signals, and hydraulic pressure of each sub-hydraulic system in the hydraulic system;

[0007] S5. Based on the machine status signal, output an electric pump shutdown command and a start error prevention operation command or output a hydraulic pressure logic judgment command through the machine status threshold and the first electric pump control logic. Obtain other electric pump control commands based on the start error prevention operation command. Shut down the electric pump connected to the sub-hydraulic system through the electric pump shutdown command and other electric pump control commands via the error prevention operation mechanism.

[0008] S6. Based on the hydraulic pressure logic judgment instruction, obtain the flight control system status signal and the hydraulic pressure, and automatically control the electric pump connected to each of the sub-hydraulic systems by using the second electric pump control logic, error prevention working mechanism and time-sharing working mechanism through the low pressure threshold.

[0009] Furthermore, the method also includes:

[0010] S11. Set the machine status threshold. When the machine status signal is less than the machine status threshold, output the electric pump shutdown command and the error prevention working command. Start the error prevention working mechanism to shut down the electric pump according to the error prevention working command.

[0011] S12. When the machine status signal is greater than or equal to the machine status threshold, output a hydraulic pressure logic judgment command to construct the first electric pump control logic.

[0012] Furthermore, the method also includes:

[0013] S21. Given a low-pressure threshold, obtain the hydraulic pressure according to the hydraulic pressure logic judgment instruction, compare the hydraulic pressure with the low-pressure threshold, and if the hydraulic pressure is less than or equal to the low-pressure threshold, output a start-up error prevention operation instruction and a start-up staggered operation instruction, and control the electric pump to start according to the start-up error prevention operation instruction and the start-up staggered operation instruction through the error prevention operation mechanism and the staggered operation mechanism; if the hydraulic pressure is greater than the low-pressure threshold, output a logic judgment instruction for the controlled mechanism on the machine.

[0014] S22. Obtain the flight control system status signal according to the logic judgment instruction of the onboard controlled mechanism, and determine whether the controlled mechanism needs pressure based on the flight control system status signal; if it is determined that there is a pressure requirement, output the start error prevention operation instruction and the start staggered operation instruction, and control the electric pump to start through the error prevention operation mechanism and the staggered operation mechanism according to the start error prevention operation instruction and the start staggered operation instruction; if it is determined that there is no pressure requirement, output the start error prevention operation instruction, obtain the remaining electric pump control instructions according to the start error prevention operation instruction, and shut down the electric pump connected to the sub-hydraulic system through the error prevention operation mechanism through the electric pump shutdown instruction and the remaining electric pump control instructions, thus constructing the second control logic.

[0015] Furthermore, the integrated protection mechanism includes an error-prevention mechanism and an electric pump start-up protection mechanism, and the method further includes:

[0016] S31. Establish an error prevention mechanism, specifically including:

[0017] S311. Number the electric pumps connected to all the sub-hydraulic systems in sequence and establish an association table for all the electric pumps;

[0018] S312. Based on the association table, obtain the current control information of the associated electric pump as the control instructions for the other electric pumps, and make a consistency judgment on the control instructions for the other electric pumps and the start / stop instructions for the electric pumps.

[0019] S313. If the judgment result is consistent, then control the electric pump according to the current control information; if the judgment result is inconsistent, then report the control information fault result and construct the error prevention mechanism.

[0020] S32. Construct a staggered work mechanism, specifically including:

[0021] S321. Define the priority order for starting the electric pumps connected to all the sub-hydraulic systems, give the data waiting time corresponding to each priority level in the priority order, and identify the priority level of the electric pumps connected to the sub-hydraulic system corresponding to the hydraulic pressure according to the priority order.

[0022] S322. Based on the start signal of the next higher priority level and the start counter of the priority level, start counting. When the count value reaches the data waiting time corresponding to the priority level and the start signal of the next higher priority level is received, output the electric pump start command to construct the electric pump start protection mechanism.

[0023] Furthermore, the onboard control signals include landing gear signals and control surface status signals, the onboard status signals include ground speed signals, and the controlled mechanisms include landing gear and control surfaces.

[0024] Furthermore, in step S22 above, determining whether the controlled mechanism requires pressure based on the flight control system status signal includes:

[0025] The landing gear signal is used to determine whether the landing gear has a pressure requirement. If the landing gear signal is a retraction signal or a lowering signal, it is determined that the landing gear has a pressure requirement.

[0026] The system determines whether the system has a pressure requirement based on the system status signal. If the system status signal is a signal to change the system position, it is determined that the system has a pressure requirement.

[0027] When any one or both of the control surfaces and the landing gear have a pressure requirement, it is determined that the controlled mechanism needs pressure.

[0028] This invention also provides an integrated control system for electric pump operation. The system includes a data acquisition module, a data scheduling module, an integrated protection module, and multiple electric pump control modules. The electric pump control module includes a first logic judgment module, a second logic judgment module, and an electric pump protection module.

[0029] All the electric pump control modules are connected in sequence to form a closed-loop control architecture. Each electric pump control module is connected to one electric pump. The output end of the acquisition module is connected to the input end of the data scheduling module and the integrated protection module. The data scheduling module and the integrated protection module are both connected to each electric pump control module. The integrated protection module includes an error prevention module and an off-time operation module.

[0030] Compared with the prior art, the beneficial effects that at least one technical solution adopted in the embodiments of this specification can achieve include at least:

[0031] 1. By automating the control of the electric pump, pilots are less likely to spend a lot of energy on controlling the electric pump during missions, significantly reducing their workload.

[0032] 2. By adopting error prevention and staggered operation mechanisms based on different aircraft conditions, the opening and closing of the electric pump is automatically controlled, avoiding the situation where the electric pump is running throughout the entire process, significantly reducing aircraft energy consumption and improving energy utilization efficiency.

[0033] 3. By designing a staggered working mechanism, the starting sequence of the electric pumps when they need to be used on the aircraft has been optimized, avoiding problems such as reduced aircraft power supply and damage to the electric pumps caused by starting the electric pumps at the same time, thus improving aircraft power supply safety and the service life of the electric pumps.

[0034] 4. The design of the control system through multiple electric pump control modules can avoid single point of failure. When the control system fails or fails in a single power supply, input information source, or control function, it will not completely lose the electric pump control function, which has high safety and increases the safety of the aircraft.

[0035] 5. The electric pump protection mechanism designed in this invention includes an overtime emergency mechanism, which can ensure the electric pump starts normally in extreme cases where the electric pump protection mechanism fails to complete its predetermined function, thus ensuring the integrity and safety of the aircraft's functions. Attached Figure Description

[0036] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0037] Figure 1 This is a flowchart of the integrated control method for electric pump operation disclosed in an embodiment of the present invention;

[0038] Figure 2 This is a flowchart illustrating the comprehensive control of the operation of the nth electric pump as disclosed in an embodiment of the present invention;

[0039] Figure 3 The execution flow of the error prevention mechanism disclosed in the embodiments of the present invention is as follows;

[0040] Figure 4 This describes the execution flow of time-lapse and error-prevention operations in the integrated control logic disclosed in this embodiment of the invention. Detailed Implementation

[0041] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0042] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features of the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0043] This invention discloses a comprehensive control method for the operation of an electric pump, see [link to relevant documentation]. Figure 1 and Figure 2 As shown, the method includes the following steps:

[0044] S4. Real-time acquisition of onboard status signals, flight control system status signals, and hydraulic pressure of each sub-hydraulic system in the hydraulic system;

[0045] S5. Based on the machine status signal, output an electric pump shutdown command and a start error prevention operation command or output a hydraulic pressure logic judgment command through the machine status threshold and the first electric pump control logic. Obtain other electric pump control commands based on the start error prevention operation command. Shut down the electric pump connected to the sub-hydraulic system through the electric pump shutdown command and other electric pump control commands via the error prevention operation mechanism.

[0046] S6. Based on the hydraulic pressure logic judgment instruction, obtain the flight control system status signal and the hydraulic pressure, and automatically control the electric pump connected to each of the sub-hydraulic systems by using the second electric pump control logic, error prevention working mechanism and time-sharing working mechanism through the low pressure threshold.

[0047] Further, see Figure 1 and Figure 2 As shown, the method further includes:

[0048] S11. Set the machine status threshold. When the machine status signal is less than the machine status threshold, output the electric pump shutdown command and the error prevention working command. Start the error prevention working mechanism to shut down the electric pump according to the error prevention working command.

[0049] S12. When the machine status signal is greater than or equal to the machine status threshold, output a hydraulic pressure logic judgment command to construct the first electric pump control logic.

[0050] Furthermore, see Figure 2 As shown, the method further includes:

[0051] S21. Given a low-pressure threshold, obtain the hydraulic pressure according to the hydraulic pressure logic judgment instruction, compare the hydraulic pressure with the low-pressure threshold, and if the hydraulic pressure is less than or equal to the low-pressure threshold, output a start-up error prevention operation instruction and a start-up staggered operation instruction, and control the electric pump to start according to the start-up error prevention operation instruction and the start-up staggered operation instruction through the error prevention operation mechanism and the staggered operation mechanism; if the hydraulic pressure is greater than the low-pressure threshold, output a logic judgment instruction for the controlled mechanism on the machine.

[0052] S22. Obtain the flight control system status signal according to the logic judgment instruction of the onboard controlled mechanism, and determine whether the controlled mechanism needs pressure based on the flight control system status signal; if it is determined that there is a pressure requirement, output the start error prevention operation instruction and the start staggered operation instruction, and control the electric pump to start through the error prevention operation mechanism and the staggered operation mechanism according to the start error prevention operation instruction and the start staggered operation instruction; if it is determined that there is no pressure requirement, output the start error prevention operation instruction, obtain the remaining electric pump control instructions according to the start error prevention operation instruction, and shut down the electric pump connected to the sub-hydraulic system through the error prevention operation mechanism through the electric pump shutdown instruction and the remaining electric pump control instructions, thus constructing the second control logic.

[0053] Furthermore, see Figure 3 and Figure 4 As shown, the integrated protection mechanism includes an error-prevention mechanism and an electric pump start-up protection mechanism, and the method further includes:

[0054] S31. Construct an error prevention mechanism (see below) Figure 3 and Figure 4 As shown, it specifically includes:

[0055] S311. Number the electric pumps connected to all the sub-hydraulic systems in sequence and establish an association table for all the electric pumps;

[0056] S312. Based on the association table, obtain the current control information of the associated electric pump as the control instructions for the remaining electric pumps, and make a consistency judgment on the control instructions for the remaining electric pumps and the start / stop instructions for the electric pumps.

[0057] S313. If the judgment result is consistent, then control the electric pump according to the current control information; if the judgment result is inconsistent, then report the control information fault result and construct the error prevention mechanism.

[0058] S32. Establish a staggered work mechanism, specifically including:

[0059] S321. Define the priority order for starting the electric pumps connected to all the sub-hydraulic systems, give the data waiting time corresponding to each priority level in the priority order, and identify the priority level of the electric pumps connected to the sub-hydraulic system corresponding to the hydraulic pressure according to the priority order.

[0060] S322. Based on the start signal of the next higher priority level and the start counter of the priority level, start counting. When the count value reaches the data waiting time corresponding to the priority level and the start signal of the next higher priority level is received, output the electric pump start command to construct the electric pump start protection mechanism.

[0061] Furthermore, see Figure 4 As shown, building a staggered work mechanism also includes:

[0062] S323. When no start signal of the higher priority level is received and the counter count value exceeds the data waiting time, the timeout emergency mechanism is activated and the synchronization failure information is reported. At the same time, the electric pump is turned on or off according to the electric pump control information output by the first electric pump control logic and the second electric pump control logic.

[0063] Specifically, the process for error-proof operation control of the electric pump can be found in [link to relevant documentation]. Figure 4 As shown, the process includes the following:

[0064] (1) Identify the predefined second logical unit object of the loop. Define the electric pumps in the following order: electric pump 1, electric pump 2, electric pump 3, ..., electric pump n. The corresponding electric pump control modules can be named control module 1, control module 2, control module 3, ..., control module n in sequence. If the control module is m (m is less than or equal to n-1), then the second logical unit object is electric pump m+1; if the control module is m (m equals n), then the second logical unit object is electric pump 1. The logic of the association table is shown in Table 1 below.

[0065] Table 1: Definition of Loop Control Logic Rules

[0066] Integrated control logic First control logic Second control logic Control object With logic Control Module 1 Control Module 2 Electric pump 1 With logic Control Module 2 Control Module 3 Electric pump 2 With logic ... ... ... With logic Control module n-1 Control module n Electric pump n-1 With logic Control module n Control Module 1 electric pump n

[0067] (2) According to the communication protocol agreed upon within the system, the second logic unit is activated to identify the control logic result, and the timing begins upon the first activation;

[0068] (3) Determine whether the control logic result determination signal of the second logic unit has been received, and based on... Figure 4 As shown, for dual-channel synchronous data, receiving data from either channel is considered a start signal.

[0069] (4) If the second logic unit control logic result determination signal is received, jump to (5); if the second logic unit control logic result determination signal is not received, jump to (8).

[0070] (5) Combine the judgment results of this control logic module to make a consistency judgment: if the judgment results are consistent, jump to (7); if the judgment results are inconsistent, jump to (6).

[0071] (6) Initiate logical fault status reporting and report inconsistent judgment conclusions;

[0072] (7) Determine whether the consistent control logic result is start: If the consistent control logic result is start, jump to start the electric pump; if the consistent control logic result is not start, jump to shut down the electric pump.

[0073] (8) Determine if the synchronization waiting time has been exceeded: If the synchronization waiting time has been exceeded, proceed to (9); if the synchronization waiting time has not been exceeded, proceed to (3).

[0074] (9) Determine whether the logic of this control module is to start: If the result of this control logic is to start, jump to start the electric pump; if the result of this control logic is not to start, jump to shut down the electric pump.

[0075] Furthermore, the onboard control signals include landing gear signals and control surface status signals, the onboard status signals include ground speed signals, and the controlled mechanisms include landing gear and control surfaces.

[0076] Furthermore, in step S22 above, see... Figure 2 As shown, determining whether the controlled mechanism requires pressure based on the flight control system status signal includes:

[0077] The landing gear signal is used to determine whether the landing gear has a pressure requirement. If the landing gear signal is a retraction signal or a lowering signal, it is determined that the landing gear has a pressure requirement.

[0078] The system determines whether the system has a pressure requirement based on the system status signal. If the system status signal is a signal to change the system position, it is determined that the system has a pressure requirement.

[0079] When any one or both of the control surfaces and the landing gear have a pressure requirement, it is determined that the controlled mechanism needs pressure.

[0080] This invention also provides an integrated control system for electric pump operation. The system includes a data acquisition module, a data scheduling module, an integrated protection module, and multiple electric pump control modules. The electric pump control module includes a first logic judgment module, a second logic judgment module, and an electric pump protection module.

[0081] All the electric pump control modules are connected in sequence to form a closed-loop control architecture. Each electric pump control module is connected to one electric pump. The output of the acquisition module is connected to the input of the data scheduling module and the integrated protection module. The data scheduling module and the integrated protection module are both connected to each electric pump control module. The integrated protection module includes an error prevention module and an off-time operation module.

[0082] Furthermore, the system also includes a power supply module, the input of which is connected to the onboard power supply, and the output of which is connected to the acquisition module, the data scheduling module, and each of the electric pump control modules. The power supply module provides power to the acquisition module, the data scheduling module, and the electric pump control modules.

[0083] 1. By automating the control of the electric pump, pilots are less likely to spend a lot of energy on controlling the electric pump during missions, significantly reducing their workload.

[0084] 2. By adopting error prevention and staggered operation mechanisms based on different aircraft conditions, the opening and closing of the electric pump is automatically controlled, avoiding the situation where the electric pump is running throughout the entire process, significantly reducing aircraft energy consumption and improving energy utilization efficiency.

[0085] 3. By designing an electric pump working protection mechanism, the starting sequence of the electric pump when it needs to be used on the aircraft has been optimized, avoiding problems such as reduced aircraft power supply and damage to the electric pump caused by starting the electric pump at the same time, thus improving aircraft power supply safety and the service life of the electric pump.

[0086] 4. The design of the control system through multiple electric pump control modules can avoid single point of failure. When the control system fails or fails in a single power supply, input information source, or control function, it will not completely lose the electric pump control function, which has high safety and increases the safety of the aircraft.

[0087] 5. The electric pump protection mechanism designed in this invention includes an overtime emergency mechanism, which can ensure the electric pump starts normally in extreme cases where the electric pump protection mechanism fails to complete its predetermined function, thus ensuring the integrity and safety of the aircraft's functions.

[0088] In this embodiment, a computer device is provided, including a memory, a processor, and a computer program stored in the memory and executable on the processor. When the processor executes the computer program, it implements any of the above-described integrated control methods for the operation of an electric pump.

[0089] Specifically, the computer device can be a computer terminal, a server, or a similar computing device.

[0090] In this embodiment, a computer-readable storage medium is provided, which stores a computer program that executes any of the above-described integrated control methods for electric pump operation.

[0091] Specifically, computer-readable storage media include both permanent and non-permanent, removable and non-removable media that can store information using any method or technology. Information can be computer-readable instructions, data structures, program modules, or other data. Examples of computer-readable storage media include, but are not limited to, phase-change memory (PRAM), static random access memory (SRAM), dynamic random access memory (DRAM), other types of random access memory (RAM), read-only memory (ROM), electrically erasable programmable read-only memory (EEPROM), flash memory or other memory technologies, CD-ROM, digital versatile optical disc (DVD) or other optical storage, magnetic tape, magnetic disk storage or other magnetic storage devices, or any other non-transfer medium that can be used to store information accessible by a computing device. As defined herein, computer-readable storage media do not include transient computer-readable media, such as modulated data signals and carrier waves.

[0092] Obviously, those skilled in the art should understand that the modules or steps of the above-described embodiments of the present invention can be implemented using general-purpose computing devices. They can be centralized on a single computing device or distributed across a network of multiple computing devices. Optionally, they can be implemented using computer-executable program code, thereby storing them in a storage device for execution by a computing device. In some cases, the steps shown or described can be performed in a different order than those presented here, or they can be fabricated as separate integrated circuit modules, or multiple modules or steps can be fabricated as a single integrated circuit module. Thus, the embodiments of the present invention are not limited to any particular hardware and software combination.

[0093] The above description is merely a preferred embodiment of the present invention and is not intended to limit the present invention. For those skilled in the art, various modifications and variations can be made to the embodiments of the present invention. Any modifications, equivalent substitutions, improvements, etc., made within the spirit and principles of the present invention should be included within the protection scope of the present invention.

Claims

1. A comprehensive control method for the operation of an electric pump, characterized in that, The method includes: Real-time acquisition of onboard status signals, flight control system status signals, and hydraulic pressure of each sub-hydraulic system in the hydraulic system; Based on the machine status signal, an electric pump shutdown command is output through the machine status threshold and the first electric pump control logic. At the same time, an error prevention operation command or a hydraulic pressure logic judgment command is output. Other electric pump control commands are obtained based on the error prevention operation command. The electric pump connected to the sub-hydraulic system is shut down through the error prevention operation mechanism using the electric pump shutdown command and the other electric pump control commands. The flight control system status signal and hydraulic pressure are obtained based on the hydraulic pressure logic judgment command. The electric pumps connected to each of the sub-hydraulic systems are automatically controlled by the second electric pump control logic, the error prevention working mechanism and the time-out working mechanism through the low pressure threshold.

2. The integrated control method for electric pump operation according to claim 1, characterized in that, The method further includes: Set the on-board status threshold. When the on-board status signal is less than the on-board status threshold, output an electric pump shutdown command and an error prevention working command. According to the error prevention working command, activate the error prevention working mechanism to shut down the electric pump. When the on-board status signal is greater than or equal to the on-board status threshold, a hydraulic pressure logic judgment command is output to construct the first electric pump control logic.

3. The integrated control method for electric pump operation according to claim 2, characterized in that, The method further includes: Given a low-pressure threshold, the hydraulic pressure is obtained according to the hydraulic pressure logic judgment instruction. The hydraulic pressure is compared with the low-pressure threshold. If the hydraulic pressure is less than or equal to the low-pressure threshold, a start-up error prevention operation instruction and a start-up staggered operation instruction are output. The electric pump is controlled to start according to the start-up error prevention operation instruction and the start-up staggered operation instruction through the error prevention operation mechanism and the staggered operation mechanism. If the hydraulic pressure is greater than the low-pressure threshold, a logic judgment instruction for the controlled mechanism on the machine is output. The flight control system status signal is obtained according to the logic judgment instruction of the onboard controlled mechanism. Based on the flight control system status signal, it is determined whether the controlled mechanism needs pressure. If it is determined that there is a pressure requirement, an error prevention operation instruction and an off-time operation instruction are output. The electric pump is controlled to start according to the error prevention operation instruction and the off-time operation instruction through the error prevention operation mechanism and the off-time operation mechanism. If it is determined that there is no pressure requirement, an error prevention operation instruction is output. The remaining electric pump control instructions are obtained according to the error prevention operation instruction. The electric pump connected to the sub-hydraulic system is shut down according to the error prevention operation mechanism through the electric pump shutdown instruction and the remaining electric pump control instructions, thus constructing the second electric pump control logic.

4. The integrated control method for electric pump operation according to claim 3, characterized in that, The method further includes: Number the electric pumps connected to all the sub-hydraulic systems sequentially and establish an association table for all the electric pumps; According to the association table, the current control information of the associated electric pump is obtained as the control command for the other electric pumps, and the consistency of the control command for the other electric pumps and the start / stop command for the electric pumps is judged. If the judgment result is consistent, the electric pump is controlled according to the current control information; if the judgment result is inconsistent, the control information fault result is reported, and the error prevention mechanism is constructed.

5. The integrated control method for electric pump operation according to claim 4, characterized in that, The method further includes: Define the priority order for starting the electric pumps connected to all the sub-hydraulic systems, give the data waiting time corresponding to each priority level in the priority order, and identify the priority level of the electric pumps connected to the sub-hydraulic system corresponding to the hydraulic pressure according to the priority order; The system starts counting based on the start signal of the next higher priority level and the start counter of the priority level. When the count value reaches the data waiting time corresponding to the priority level and the start signal of the next higher priority level is received, the system outputs an electric pump start command to construct the staggered working mechanism.

6. The integrated control method for the operation of an electric pump according to any one of claims 3 to 5, characterized in that, The flight control system status signals include landing gear signals and control surface status signals, the onboard status signals include ground speed signals, and the controlled mechanisms include landing gear and control surfaces.

7. The integrated control method for electric pump operation according to claim 6, characterized in that, Determining whether the controlled mechanism requires pressure based on the flight control system status signal includes: The landing gear signal is used to determine whether the landing gear has a pressure requirement. If the landing gear signal is a retraction signal or a lowering signal, it is determined that the landing gear has a pressure requirement. The system determines whether the system has a pressure requirement based on the system status signal. If the system status signal is a signal to change the system position, it is determined that the system has a pressure requirement. When any one or both of the control surfaces and the landing gear have a pressure requirement, it is determined that the controlled mechanism needs pressure.

8. A comprehensive control system for an electric pump, used to execute the comprehensive control method for an electric pump as described in any one of claims 1 to 7, characterized in that, The system includes an acquisition module, a data scheduling module, a comprehensive protection module, and multiple electric pump control modules. The electric pump control module includes a first logic judgment module, a second logic judgment module, and an electric pump protection module. All the electric pump control modules are connected in sequence to form a closed-loop control architecture. Each electric pump control module is connected to one electric pump. The output of the acquisition module is connected to the input of the data scheduling module and the integrated protection module. The data scheduling module and the integrated protection module are both connected to each electric pump control module. The integrated protection module includes an error prevention module and an off-time operation module.

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